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MUP 2006-751 PCV ReportIVUV-2tt—d3 0W.1b t'12UM-119;,L'th'1'tK VANCUUVEX ID E504 524'!Jltlb PAGE.. 2/16 • - ETL S EM KO REPORT OF A STANDARD FLAME SPREAD PROGRAM CONDUCTED ON PVC LAMINATED SCRIM CLIENT: PLASTATECH ENGINEERING, LTD. 725 E: MORLE'Y' DRIVE SAGINAW, MI 48601 i REPORT PREPARED B'Y: INTERTEK TESTING SERVICES NA LTD. i 211 SCHOOLHOUSE STREET COQUITLAM, B.C. V3K 4X9. REPORT NUMBER: 3051042 DATE: NOVEMBER 27, 2003 itvT. - t Ali services undertaken are subject to the following general policy: 1. This report is for the exclusive use of Intertek Testing Services NA Ltd.'s (Intertek 's) client and is provided pursuant to the agreement between Intertek and its client. Intertek's responsibility and liability are limited to, i the terms and conditions of.the agreement. Intertek assumes no liability to any party, other than to the client in accordance with the agreement, for any loss, expense or damage occasioned by the use of this report. 2. Only the client is authorized to copy or distribute this report and then.only in its entirety. Any use of the 4 4 Intertek name or one of its marls for the sale or advertisement of the tested material, product or service must fust be approved in writing by Intertek �. 3. The observations and test results in this report are relevant only to the sample tested. This report by itself does ��-not imply that the material, product or service is or has ever been under an Intertek certilication pros am � §1 lntertek Testing Services HA Ltd. C211 Schoolhouse Sc. CoquiUam, BC V3K aX9 Telephone: 60&6203321 Far- 604-524-9186 Web; ww lntenekatlsomko.com i NOV-28-03 06:15 FROM:INTER.TEK VANCOUVER ID=604 524 9186 PAGE.:: -3/16 PREFACE `I This report describes the tests, standards, and details for the sample of laminated polyester scrim with PVC and top coat (Lot Number 60329E), submitted by Plastatech Engineering, Ltd. This report does not automatically imply product certification. Products must bear O labels iri order to demonstrate Intertek/Wamock Hersey certification, Intertek/Warnock Hersey authorizes the named client to reproduce this report_ It must be copied in its entirety. d NOV-22-03 08-.16 FROM.INTERT9I VANCOUVER ID:664 524 9126 TABLE OF CONTENTS INTRODUCTION MATERIAL SPECIFICATIONS SAMPLE MOUNTING TEST PROCEDURE FLAME SPREAD CURVE SMOKE DEVELOPED CURVE TEST RESULTS CONCLUSION -PACE 416 . - ":-T'7'- - NOV=26-03 0B=16 FROM;INTERT$K+VANCOUVER ID:604'524 9186 P4AGE 53-16 Plastatech Engineering, Ltd_ November 27, 2003 Report No. 3051042 Page 1 of 8 INTRODUCTION tj. On November 27, 2003, Intertek Testing Services NA Ltd -[Warnock Hersey conducted a flame spread test program to determine the surface burning characteristics of alaminated polyester scrim, The material tested was selected and submitted by the client. Testing was conducted in accordance with ASTM E84 -03a, Standard Test Method for Surface i Burning Characteristics of Materials: Upon receipt of the samples at the Intertek/Wamock Hersey laboratory they were placed in a conditioning room where they remained in an atmosphere of 23.± 3°C (73.4 f 5°F) and 50 ± 5% j relative huTaidity_ One trial run was conducted on the sample material. i • i . i I 1 r MOV -28-03 0e:16 FROM:INTERTEK VANCOUVER Plastatech Engineering, Ltd. Report No. 3051042 ID:604 524 91136 PAGE. 6/16 November 27, 2003 Page 2 of 8 MATEMAL SPECMCA.TIONS -The material tested was selected and submitted by the client. The required specimen size was first cut from the supplied material roll. The cut sample was approximately 24 ft. long by 20-1/2 in. wide by approximately 0.024 in_ thick. It was described by the client as laminated polyester scrim with PVC and top coat (I.ot Number 60329E). SAMPLE MOUNTING The sample was placed on the upper ledge of the flame spread tunnel on 1/4 in. stainless steel rods, spaced at 24 in. on centre, and chicken wire to help support the material from sagging during the test. A layer of 6mm reinforced cement board was placed over top of the sample, the lid lowered into place, and then tested in accordance with ASTM E84 -03a. NOV-2B-03 09=16 FROM:INTERT-EK VANCOUVER ID:604 524 9196 PAGE 7/16:`' Plastatech.Engineering, Ltd. November 27, 2003 Report No_ 3051042 Page 3 of 8 TEST PROCEDURE f} The results of the tests are expressed by indexes, which compare the characteristics of the sample under tests relative to that of select grade red oak flooring and Haidi board - (A) FLAME SPREAD CLASSIFICATION: This index relates to the rate of progression of a flame along a sample in the 25 .foot tunnel. A natural gas flame is applied to the front of the sample at the start of the test and drawn along the sample by a draft kept constant for the duration of the test. An observer notes the progression of the flame front relative to time. This information is plotted on a graph (flame spread curve). The test apparatus is calibrated such that the flame spread classification for red oak flooring is 100, and 0 for asbestos -cement board 1 CALCULATIONS: ASTM E84 -03a According to the test standard, the flame spread classification is equal to. 4900 when (195_ - A0 At is the total area beneath the flame spread curve, if this area exceeds 97,5 minute feet. If the area beneath the curve is less than or equal to 97.5 minute feet the classification i becomes 0.515 x At. NOV-28-03 OB=17 FROM:INTERTEK VANCOUVER. ID:604 524 9186 PAGE 8/.16 Plastatech Enzineering, Ltd. November 27, 2003 Report No. 3051042 Page 4 of S TEST PROCEDURE (Continued) (B) SMOKE DEVELOPED: A photocell is used to measure the amount of light, which is obscuredby the smoke passing down the tunnel duct_ When the smoke from a burning sample obscures the light beam, the output from the- photocell hephotocell decreases. This decrease with time is recorded and compared to the results obtained for red oak, which is 100. CALCULATIONS: 10,000 - (smoke inWator readino x 100 = smoke developed 3356 NOV-2B-03 06z17 FROM-.INTERTEK VANCOUVER• lDzE04 524 9186 PAGE 1.6 Plastatech EnOneerinar, Ltd. November 27,2003 Repan No. 3051042 Page 5 of 8 FLANZ SPREAD DISTANCE IN FEET VS. TEVIE IN WNUTES RUN I Laminated Polyester Scrim with PVC and Top Coat (Lot Number 60329E) Flamespread=14, Smoke Developed=237 24.5' 22-5 20-5 18.5 14.5 I. .12.5 10.5 8.5 6.5 4.5 NOV-28-03 08;17 FROM:INTERTEX VANCOUVER ID:604 524 SIBS PAGE 10/16 Plasratech Engineeiing, Ltd. November 27, 2003 Report No. 3051042 Page 6 of 8 SMOKE DEVELOPED CURVE RUN 1 j;; i t., 101 FJT�kli! iitii;i th id: 1,;;j:ii qo;: A6 14.,!1i jJ li'1151 i it J; i I! i 1 1 ji j::;: 10 ilq it i; i;: i • i:idd I !Ihi it it IT. i;:. i la 80i!: !till i! p 1; j T T NOU-26-03 06=19 FROM=INTERTEK VANCOUVER `"`ID=604 524.9166 PAGE 11/16 CA Plastatech Engineering, Ltd. - November 27, 2003 Report No_ 3051042 . Page 7 of 8 TEST RESULTS FLAME SPREAD The resultant flame spread classifications are as follows: (classification rounded to nearest 5) Laminated Polyester Scrim with PVC and Top Coat (Lot Number 60329E) Flame Spread Flame Spread Classification Run t 14 15 SMOKE DEVELOPED The areas beneath the smoke developed curve and the related classifications are as follows - (For smoke developed indexes 200 or more, classification xs rounded to the nearest 50. For smoke developed indexes less than 200, classification is rounded to nearest 5) Laminated Polyester Scrim with PVC and Top Coat (Lot Number 60329E) Smoke Developed Smoked Developed Classification Run 1 237 250 NOV-26-03 08=18 FROM=INTERTEK VANCOUVER ID:604 524 9186 PAGE 12/16 Plastatech Ensineering, Ltd. November 27, 2003 Report No. 3051042 Page 8 of 8 CONCLUSION The sample of laminated polyester scrim with PVC and top coat (Lot Number 60329E) material, submitted by Plastatech Engineering, Ltd., exhibited the following flame spread characteristics when tested in accordance with ASTM E84 -03a, Standard Test Merhod- for Surface Burning Characteristics of Materials. Sample Material Flame Spread Smoke Developed CIassification Classification Laminated Polyester Scrim with PVC 15 250 and Top Coat (Lot Number 60329E) INTERTEK. TESTING SERVICES NA LTD. Warnock Kersey i Tested and Reported by: Greg Philp Technician — Construction Products Testing 0 Reviewed by: 1 Der- it d - Michael van Greyn, . c.T. Manager —Fire Testing & Technical Programs GP/bjm C:\Do=i— =4 Sadar,\8rcslalMy Docuu guU9SDATAN490-WPeM10o3 • -9i RP(&W6=M:D&=8.wy 03.dc NUV—zt+—tam 14W: 10- r1tUM= IN'Xl:lW1'l:�K 'VA[Vt:UUVI-;k IU-IiI04 b24'8186 ' PAGE 13/16 =..ETL SEM KO November 27, 2003 Plastatech Engineering, Ltd. 725 E. Morley Drive Saginaw, M( 48601 Attention: Mr. Wolfgang you Claparede Dear Sir_ Re: Proiect No. 3057.042--1 ' . On November 26, 2003, btertek Testing Services NA LtdJWarnock Heresy initiated a test program on behalf Plastatech Engineering,, Ltd. The purpose of the testing was to. determine whether the submitted samples of laminated polyester scrim with PVC and top coat (Lot Number 60329E) would meet the small flame and lar -e flame requirements of CANAMC S109, Standard for Flame Tests of Flume - Resistant Fabrics and Films, which also covers UBC 31-1. The test- samples were placed in a drying oven at 105°C for 30 minutes then allowed to cool in a. conditioning room at 20°C -and 50 % relative humidity, and then tested in accordance witb'the test . standard. The results of the tests are as follows. CAN/ULC S109 Small Flame Test Results: Sample No. Fabric Direction Aiter Sura . (see) Damaged Len (mm) 1 Warp 0 68 2 Wa2 0 64 3 Warp_0 64 ' 4 Warp 0 43' 5 Warp 0 40 6 Weft 0 65 7 Weft 0 65 8 Weft 0 52 9 Weft 0 58- 10 Weft 0 , 54 Average = - ___ 0 573 Allowable Limit - - --- 2' 165 All& -apices urqenakenare subjectto 6 --following general Pd -Y• Fa . 1. This report is for tra c h-lue use of Inttrrtdr Test'afg Serv(ees NA Ud.s OnWzlclfs) clam end Is provided Dutsuant to the agreement between trnettek and its dent. •,�-,;: ^. , tnteraeks tesponsibdityand r2buhyae Grtuledtotrs tcrtassnd eonokions of the agrewrcnL tntertek assumes no rabTlety to any patty. ower than to the Client M accord9nce wM tno agreement. for any loss. a=ettaa or daaage cocasloncd by the use of this report 2 orgy the c5a tt is autt+orced to copy or ohmibute aria report and then" to is � entirety. Any use a we,lrac tek name or one of its =rka for the ale or adVQnI6emom of Ilse lasted rrnseriaL product orservice mz= Oust be approwd In wrtting by Intermit. too3. The obaervatlons and test results In this report arc n3t.sm only to the mmpte %e=d. This repot bf ttsctt does not Impty dot the mater W, product of servlco L- or has l ever peon underan Irranck certification psogiarn. Intertek Testing Services NA Ltd. 211 Sehoelhousa St., Cogtdtlarn, BG V3K 4X9 Telephone: 604-520-3321 Fax: 604.624-9186 Wcb; wwwJrYrerwksJscTkO_cotn - NOV-29703 09: 19.FROM: INTERTEK VANCOUVER ID:604 524 9196 Plastatecb Engineering, ltd. Project No. 3051042-1 CA_N/ULC S109 Large Flame Test Results: PAGE 14/16 • 1 i November 27, 2003 Page 2 of 2 Sample No. Fabric Direction After Burn. (see) Damaged Length (x1m) 1 Warp 0 200 2 Waap 0 90 3 Warp 0 143 4 Warp 0 113 5 Warp 0 97 6 Weft 0 105 7 Weft 0 98 8 Weft 0 63 9 weft 0 100 10 Weft 0 77 Avera a =- — 0 108.6 Allowable Limit - ,,- = = N/A, 250 The submitted samples of laminated polyester scrim with PVC and top coat (Lot Number 60329E) therefore met the requirements of CAN/ULC S109, small flame test and large flame test. 'Y'ours truly, INTERTEK TESTING SERVICES NA. LTD_ � Tested and Reported by: / Y Greg Philp Technician — Construction Products Testing q1, 461-/ Reviewed by: Michae van Geyn, A" c"T. Manager — Fire Testing & Technical Programs GP/bjm C�Doantrncsor45ecdat:8 'MYDonvrcacltTS-DATA`�90.WPRPF2CU3-=93:PMIaysc7051O3Z-l�o�iae -NOV-26-03 09:19'FR0M-INTERTEK VANCOUVER: - tQW.ETL S EM KO November 27, 2003 PIastatech Engineering, Lid - 725 E- Morley Drive , Saginaw, MI 48601 Attention: Mr. Wolfgang von Claparede Dear Sir: ID=•604-•524,9196 S1 . PACE 15/16 Re: Proiect No. 3051042-2 On November 26 and 27, 2003, Intertek Testing Services NA Ltd -/Warnock Heresy initiated a test program on behalf Plastatech Engineering, Ltd. The purpose of the testing was to determine whether the submitted samples of laminated polyester scrim with PVC and top coat (Lot Number 60329E) would meet the small flame and large flame requirements of NFPA 701, Standard Methods of Fire Tests for Flame Resistant Textiles and Films_ The samples for the small flame .test were weighed before being placed in a drying oven at 105°C:, for not less than 30 minutes, and tested in accordance with the test standard- The samples.for the targe flame test were placed in a drying oven at 105°C, for not less than 1 hour nor no more than 3 hours, and tested in accordance with the test standard. The results of the tests are as follows. NFPA 701 Small Flame Test Results: t , Sample Na Fabric Direction After- Burn- (sec) - Damaged. .- Len (mm) -.Loss In Mass . - (%) 1 Vd 0 68 1.58- 2 Wam 0 64 2.12 3 Warp 0 64 1.14 4 Warp 0 - 43 1.23 5 Warp 0 40 1.33 6 Weft 0 65 1.98 7 Weft 0 65 2.45 8 9 Weft Weft 0 0 52 58 2.43 2.24 10 ' Weft 0 54, 2.22 Average - ::.; '' 0 57.3 1.37 Allowable Limit 2 N/A 40 6=) all ZCM086 ep unis to at are suolea a the fktcrt n9 ge ting policy: . A 1. Tnts report is far ttr¢ Qcltrsi4e t of lrtrctttk Testing Sers KA LttLk (IcrsMKa) Uient and is proKded prasvant to the agreement thin to a CIJQ SC and its Ukra. tntartswe respons3�Tity and-ttablity ace limited tomo ceras and conditions of the asttvne. Irdertak assumes tto itebatty to sr+Y party. of-b%nOt n to 11ra atertt to acmManCe .rids the a9nean=M to( any 1a66, exile tse or damage occasioned by the use of Lhte report- '-'on" Dogra 1s autho?2ed to copy or SmuiDutc tris report and Tran =If in its " V i annirmy. Any uae or tr= In ertek ram¢ or one of its martw,tor the este or ad+'ert"sement or M tcs'ted rnaurr" product or saMcs terror Rest be &epruvcd In writing by tntcnet. The Observations and test results in tnta report are Ietebert Doty to Lire sm+p!e Eesma. Tnls report by 18 art does not awry trot tt= rretecial. product or service 16 rX rus . werbeen unDar"'lnr"'Ek`otf0=i°rtptOg`atM lntertekTesting Services NALtd. 211 Schoolhouse St.; Coquitlam. BC V3K dX9 Telephone: 604-520-3321 Fax: 304.624-9136 Web: Wominterb*eu-semkamrn NOV-28-03 08-20 FROM:INTERTEK VANCOUVER ID -604 r 524 9386 PAGE 16/16 Plastatech Engineering, Ltd. Project No. 3051042-2 . NFPA 701 Large Flame Test Results: November 27, 2003 Page 2 of 2 Sample No. Fabric Direction After Burn (see) Damaged Length (mm) 1 Warp 0 200 2 Warp 0 180 3 Warp 0 200 4 Warp 0 173 5 Warp 0 181 6 Weft 0 100 7 Weft 0 230 8 Weft 0 140 9 Weft 0 105 10 Weft 0 0 - 90- Average —:;�;._ _ ,•:,,L..;s_ :. ; i ..::;:7 :....._. 0 Q 99 Allowable Limit -'' '_ � `° "` 2 435 The submitted samples of laminated polyester scrim with PVC and top coat (Lot Number 60329E) therefore met the requirements of NFPA 701, small flame test and large flame test. Yours truly, INTERTEK TESTING SERVICES NA LTD. l Tested and Reported by: (X-) Greg Philp Technician — Construction Products Testing Reviewed by: Manager — Fre Testing & Technical Programs GP/bjm C:47xvnem=aiScW2;SE4end.�My Do=i=.t0TS•DATM490-WFQtF 2003--9i Rpi\pL, x%h505100-1mv%3.d= j CAMPBELL WOODALL & ASSOCIATES CONSULTING ENGINEERS LTD. 250,1210 -8th STREET S.W., CALGARY, ALBERTA T2R 1L3- PHONE (403) 228-3178 FAX (403) 228-5130 WIND LOADS ON SPRUNG STRUCTURES INTRODUCTION Sprung Structures have been shaped to reduce wind effects on the structures. A sprung structure has rounded eaves with a roof slope of 260 . To take advantage of the structure's aerodynamic shape Sprung commissioned a wind tunnel experiment at the University of Calgary in 1981. The purpose of the wind tunnel experiment was to'ascertain the wind forces that occurred on the structure. A plan and cross section of a Sprung Structure is shown on drawing W- I. This report will discuss the wind tunnel experiment, if it 'can be applied to other sizes of Sprung Structures, how the pressure coefficients have been converted. for use in the United States and how the wind tunnel results can be used under UBC -97. WIND TUNNEL EXPERIMENT A wind tunnel experiment was completed for Sprung Instant Structures in 1981 at the University of Calgary. The experiment established wind pressure coefficients for a 50' Sprung Structure in a grassland exposure for winds at 0°, 300, 600, and 900 to the longitudinal axis of the structure. The wind tunnel experiments were conducted on a 1:196 scale model of the 50' structure. The report from the wind tunnel experiment is found in Appendix "A". The wind pressure coefficients found during the wind tunnel experiment were also checked against results of later research. This later research was used as the basis for wind forces in the 1980 ti to 1995 editions of the National Building Code of Canada (NBCC). The wind tunnel pressure coefficients were very similar to those used in the NBCC for buildings under 60'. It is comforting to have experimental results agreeing with other research. _ Partners Colin H. Campbell, B.Sc. P.Eng. F.E.I.C. M.C.S.C.E. David C. Woodall, Chief Engineer, M.Sc. P.Eng. M.E.I.C. M.C.&C.E. Verlin H. Koch, Senior Engineer, B.Sc. P.Eng. M.E.I.C. M.C.S.C.E. ' Associates - David P. Thompson, M.Sc. P.Eng. M.C.S.C.E. Philip J. Towers, B.Sc.-.P.Eng. M.C.S.C.E., E Member Firm CONSULTING ENGINEERS of ALBERTA.. _2- . OTHER SIZE STRUCTURES When considering, the validity of the wind pressure coefficients, from the 50' structure for use with the 30' to 130' structures we compared the shapes of the different structures. This was done by scaling drawings of the different structures, all have a base width of 50' (i.e. 30' up to 50', 130' down to 50'). ,The results of the scaled structures are shown on drawing W-2. , The structures all have very similar shapes and therefore" we concluded that pressure coefficients for the 50' structure can be used for the 30' to 130' Structures. PRESSURE COEFFICIENTS Canadian wind pressures are calculated on the average hourly wind pressure. This pressure is not the same as the fast mile wind pressure used in the United States. Therefore, the pressure coefficients derived from the wind tunnel experiment cannot be directly used in the United States. We have followed a similar procedure to what was done by ASCE-7 for Figure 2, "Average Loads on Main Wind -Force Resisting Systems". This procedure is outlined in, "Guide to the Use of the Wind Load Provisions of ASCE-7-88". The pressure coefficients from the wind tunnel multiplied by the Canadian Wind Gust Factor (2.0) were divided by 1.69, but the pressure coefficients were increased by 20% to account for concerns for peak pressures discussed on pages 86 and 89 of "Guide to the Use of the Wind Load Provisions of ASCE-7-88" by Mahta, Marshall and Perry, found in Appendix B. This expression becomes: Cp x 2.0 x 1.20/1.70 = 1.4 Cp. Please note that Cp used in ASCE-7 and the NBCC is the same as Cq in UBC -97. The pressure coefficients calculated using this procedures are shown on sheet W-3. As a secondary check we developed some wind pressure coefficients using ASCE-7. The ASCE-7 pressures were derived from Figure 2, "Average Loads on Main Wind -Force Resisting Systems The pressure coefficients are shown on sheet W-3. As can be seen the pressure distributions are very similar. As a final check we ran a two dimensional analysis using the ASCE-7 and wind tunnel test results. The results of the analysis is shown on the next page. Wind -US F 50' 1150'-0" STRUCTURE /30'-9" STRUCTURE w -z 50' STRUCTURE 88'-7' STRUCTURE \ / 1 50' 50'-0" STRUCTURE / 88'-7" STRUCTURE w -z �. -50' STRUCTURE i QUO' STRUCTURE i ♦ 3150'-0" STRUCTURE / 130'-0" STRUCTURE �/ • WIND TUNNEL STRUCTURE CAMPBELL WOODALL & ASSOCIATES CONSULTING ENGINEERS LTD. 250, 1210 -8TH STREET S.W., CALGARY, ALBERTA T2R 10 PHONE (403)228-3178 SPRUNG INSTANT STRUCTURES SHAPE OF STRUCTURES W-2 CROSS WIND PRESSURE COEFFICIENTS: -.42 -.7 FRAME 30' ROOF WIND FRAME 26' 'ROOF��' +.26 DIRECTION, -.42 FRAME 20' ROOF STRUCTURE WIND TUNNEL +.8 COMPARISON BETWEEN ASCE-7 AND WIND TUNNEL RESULTS -.58 WIND -.61 -.65 WIND DIRE-0-,�' .09 .17 -.71 DIRECTION -.15 .26 -.75 �p� 4%JjiT 51 ::;:::.. \ ¢yam ,(� 70 .60 <� 5 .59 �>` -.62 .59 -.62 -.50 WIND TUNNEL .80L: 3 FRAME 26' ROOF ASCE-7-93' LONGITUDINAL WIND PRESSURE COEFFICIENTS: -.54 _ 44 -.44-.38 -.38 -.37 -.37 ' \ -.38 -.70 -.70 -.35 -.32 -.32 -.32 -.32 FRAME 26' ROOF WIND TUNNEL ASCE-7-93 CAMPBELL WOODALL & ASSOCIATES CONSULTING ENONEERS LTD. 250, 1210 -8TH.; STREET S.W., CALGARY, ALBERTA T2R IL3 PHONE (403)228-3178 SPRUNG INSTANT STRUCTURES - Pressure Values (Cq) W-3 Comparison of Wind forces found from Wind Tunnel Experiments and Figure 2 of ASCE-7 Joints Moments in Members [kip ft.] Cross Wind Longitudinal Wind ASCE-7 Wind ASCE M max ASCE-7 Wind ASCE M max Mlong Tunnel WT Tunnel WT Mcross • 1 0.00 0.00 1.00 0.00 0.00 0.00 1.00 0.00 1.00 2 15.76 15.71 1.00 15.76 5.44 4.43 1.23 5.44 0.35 3- 36.88 38.74 0,95. 38.74 12.73 10.24 1.24 12.73 0.33 ' 4 44.40 50.95 0.87 50.95 9.71 9.25 1.05 9.71 0.19 5 39.58' 51.33 0.77 51.33 -2.97 1.82 -1.63 -2.97 0.06 6 21.29 36.18 0.59 36.18 •25.91 -12.83 2.02 -25.91 0.72 7 8.12 16.10 0.50 16.10 -24.89 "14.13 1.76 -24.89 1.55 ' 8 0.00 0.00 1,00 0.00 0.00 0.00 1.00 0.00 1.00 9 34.84 -32.01 1.09 -34.84 -24.89 •14.13 1.76 -24.89 0.71 10 •45.73 .44.94 1.02 -45.73 -25.91 -12.83 2.02., -25.91 0.57 11 ..-32.67 •37.01 0.88 -37.01 •2.97 1.82 -1.63 -2.97 0.08 12 -26.76 0.77 -26.76 ' 9.7,1 9.25 1.05 9.71 -0.36 13 .-20.51. -9.66 •15.57 0.62= . • 15.57 12.73 10.24 1.24 12.73 , 0.82 14 - - •2.79 -5.51 0.51' w -5.51 - r -5.54 4.28 1.30 5.54 1.01: 15 0.00 0.00 1.00 0.00 0.00 0.00 1.00 0.00 1.00 Mai Mom. -4533 51.33 " " 0.89 51.33 --25.91 44.13 1.83 -25'.91 .t 0.50 - Use of Wind Tunnel Cq values for Analysis of Sprung Structure _ 88' Structure 80 MPH Exposure C ' -3- Three conclusions can be reached reviewing these results: 1. The ASCE-7 maximum moment (Joint 6) is 1.83 times the maximum wind tunnel moment (Joint 7) for longitudinal wind. 2. Longitudinal wind pressures do not govern, the maximum moment for longitudinal wind pressures using ASCE-7 is only 50 % of the maximum moment for cross winds using the wind tunnel forces. 3. The ASCE-7 maximum moment (Joint 10) is 10% smaller than the wind tunnel moment (Joint 5), for cross wind. UNIFORM BUILDING CODE (UBC) AND WIND TUNNEL RESULTS If the wind tunnel experiments are to be of value, then they must be able to be used within the UBC code. This section explains how this can be done, and how the results are actually compatible with,the pressure coefficients used in Table 16-H of the UBC., A very important change between UBC-91 and UBC-97 is that Volume 1, Chapter, l6 'of the 1994 edition, recognizes "ASCE-7, Chapter 6" as a "recognized UBC Standard" (subsection 1604.1). As a recognized standard, ASCE-7 Chapter 6 (wind provisions), can be used by subsection 3504. Chapter 6 allows'a designer to use wind pressure coefficients found in wind tunnel tests or from pressure diagrams shown at the end of the chapter. The most appropriate pressure diagram for Sprung Structure shown'in Chapter 6 is Figure 2, "Average Loads on Main Wind-Force Resisting Systems". Wind-US -4 - We have compared the wind tunnel experiment results to Figure'2 in a previous section, but how does Figure 2 compare with Table 16-H of the UBC? Table 16-H has wind pressure coefficients (Cq) of 0.8 inward for the windward wall, 0.7 outward for the leeward roof, and 0.5•outward for the leeward wall. These values are all used in Figure 2. Table 16-H requires Cq values of 0.3 inward or 0.9 outward for the windward roof with a slope of 2:12 (9.50) to 9:12 (370). When you look at Figure 2, Cq values of 0.9 outward and 0.2 inward are required to be used for roof slopes of 10° to 15° and 0.3 inward for roof slope of 400. In other words Figure 2 from ASCE-7 and Table 16-H agree with each other. The only difference is that Figure 2 provides more detailed information for evaluating wind pressure coefficients for structures with different geometry, i:e. roof slopes and height to width ratios. CONCLUSIONS This report has discussed the basis for the wind pressure coefficients used in' the United States for Sprung Structures. The report has shown that the pressure coefficients can be used for all the sizes of Sprung Structures (30' to 130'.) The wind pressure coefficients from the wind tunnel experiment produced maximum moments in the frame 10% higher than Figure 2 of ASCE-7, and Figure 2 of ASCE-7 may be used under the 1994 edition of the UBC. Therefore, the modified results from the wind tunnel experiment can be used in the United States for municipalities using UBC -97. Wind -US -5- ®®� UNIVERSITY OF CALGARY y FACULTY OF ENGINEERING Department of Mechanical and. Manufacturing Engineering a '; ' __ _. _. . ••.: Telephone: (403) 220-5777 Fax: (403) 282-8406 _ February 17, 2000 Dr. Mahmoud Taha Campbell Woodall and Associates Consulting Engineers Ltd. 250, 1210 - 8`" Street S.W. Calgary, Alberta T2R 11_3 Dear Sir: Re: Wind Tunnel Test Report for Sprung Structures I have had forwarded to me your letter of 9/2/00 to Dr. M. Epstein regarding the above topic. As a former colleague of the late Dr. Joseph de Krasinski I can assure you that Dr. de Krasinski did carry out this test program, described by him in his report,using our departmental facilities. Although I was not, personally, a participant in the work I recall discussing the work with him briefly and also seeing a model Sprung building used for wind -tunnel testing. The top picture of plate 1, although not very clear in the copy of the report you sent to Dr. Epstein, shows the model Sprung building mounted in the working section of our departmental, open -jet, laminar flow wind -tunnel. Furthermore the top picture of plate. 2 shows our departmental data acquisition system in use at the time of Dr. de Krasinski's tests. This system was known as MEDAS (Mechanical Engineering Data Acquisition System). Additionally Figure A.1 shows the laminar boundary layer (no vortex generators) of the laminar wind -tunnel and also the conversion of this to a turbulent form as a result of adding vortex generators. It is clear, therefore, that the work reported by Dr. de Krasinski was, in fact, carried out in our department which was, at that time, known as the department of Mechanical Engineering. Yours sincerely, : J.A.C. Kentfield, Professor cc: Dr. M. Epstein JK/jo C:W.A.C. Kentfield\Taha.wpd 2500 University Drive N.W., Calgary, Alberta, Canada T2N 1N4 0 www.ucalgary.ca 1. INTRODUCTION Wind tunnel tests were required to obtain aerodynamic pressure distribution on a model of a "sprung structure" exposed to the wind. Drawings of the structures were provided and a special model for pressure distribution was built for this purpose out of acrylic 1/4" thick sheet. The. object of the tests was to obtain nondimensional pressure coefficients over the whole surface of the model tested in conditions of dynamical similarity as compared to the free atmosphere. Such pressure coeffi- cients are required. by the Canadian Building Code [1].. These results . have to.be modified depending on special local conditions like gustiness, site conditions, etc. as indicated by the Code. By integrating they pressure coefficients over the whole surface the aerodynamic loads on the structure can be estimated. More details about the tests can,be found in the Appendix. _ 2. PRESENTATION OF RESULTS 2.1 The Pressure Coefficient All the pressure measurements are calculated in a nondimensional form of pressure coefficients, obtained in conditions of dynamical similarity. The pressure coeff iciest at any point X on the structure is ' C = (Pressure at \) - (Pressure of ambient atmosphere) P Dynamic Pressure of. the Wind The dynamic' pressure of the wind 2 p V2 is taken at the position of the height of the building in free atmosphere as postul;rted by the Code [1], •, where V is the measured velocity of the wind and p is the air density.. In spite of the variations of the wind intensities.the cc2fficient C" Sprung Instant Structures Ltd. ' 2. remains substantially constant at a corresponding point and at any wind velocity.. This holds for the structure and the model. As the wind blows over a hollow• obstacle. it produces on the surface (and fre quently, inside) over -pressures and under -pressures, as compared to the. . atmosphere, thus originating aerodynamical loads. It is obvious from the definitions of the coefficient CP that under -pressures give negative values and vice versa. The pressures inside a hollow structure are approximately constant and can be estimated from [1]. These have also been measured as a matter of interest. Thus for example if at a point. X the external pressure coefficient CP = -1.2 and inside CP the measure of the pressure difference is -1.2 - (+0.8) _ -2.0. The net aerodynamical load upon an area A is from inside into outside F = (2) 2 p V2 where V is the wind velocity. at the height of the structure. With similar reasoning one can estimate the aerodynamic loads and,moments across the structure. 2.2 The Model and the Pressure Points Location The model.is scaled.1:96 (1'_ $"), manufactured from acrylic sheets 1/4" thick and all the pressure points are connected through a scanning valve to a high precision transducer, the recordings of which elaborated on a computer are printed automatically. Because of the discontinuity produced by the ribs which would result in a local distor- tion of the pressure coefficients, not representative of total distribu- tion, the rr-ssure holes are displaced on the model about 2 ..n in the If air density p is taken in slugs/ft3, velocity in fps, then the product 1/2 P V2 is in lb /ft2. If air density p is in kg/m3 and V in m/sec then 1/2 p V2 is in Newtons/m2. 1 3. Clockwise direction perpendicular to the rib. Only the central rib along the Y axis has the pressure.holes perforated on the discontinuity itself. Once the equilibrium of pressures is established at a certain point the transducer is made to record one "thousand pressure impulses the average of which is transformed into a pressure coefficient CP. Because of the symmetry of the model, the number of the pressure points is shown in the first quadrant only as in Figure 1.. The same number is also recorded in. the remaining quadrants 2, 3 and4 bearing again the same numeration. Thus, in the quadrant 2, the numbers of the pressure points are a mirror reflection across the Y axis of those in the quadrant 1. In the quadrant 3 the numbers are a mirror re— flection of those in the quadrant 2 across the X axis. In the quadrant- 4 uadrant4 the numbers are a mirror reflection across the X axis of those in quadrant 1. To be meaningful each pressure point, at a certain angle of the wind, must also be related to a quadrant like quadrant (1) point S, quadrant (3) point 17, etc. The internal pressures are uniform and are recorded as number 28. If Y and X axes divide .the plan of the model in 4 quadrants (see Figure 1), then the corresponding points across the Y axis are say (1) 9 and (2) 9, across the'X axis, say (1) 12 and (3) 12, etc. For. the stress analysis the exact position of the pressure prints will he required. For this purpose Figure 4 is a large scale. copy of the Figured giving more precise information about the position of the measured CP coefficients in full scale. 2.3 The Wind Directions If the plait of the model is 'attached to the X and Y axis as shown in Figure 2, with quadrants (1),.(2), (3) and (4) and the Y axis is pointing to the north, then a wind blowing from the northeast into the quadrant (1) at say azimuth angle 30% will produce four distinct Y 4, y pressure regions A, B, C, D. Marking with sub-index W "windward".and t with L "leeward" one observes AW, BL, CL and DW. 4Because of the symmetry ' of the model the rotation of the wind.to say a southwest direction.. (azimuth angle +210° _-150).will produce a rotation-of the regions A, B, C, D as shown in Figure 2, with the quadrants 1,2, 3, 4 unchanged.,- Because of the symmetry of the model the•same regions will have identical pressures as if the wind was blowing from the nor'theast,'only the position of the regions A, B, C, D will change with relation to the quadrants (see Figure 2). It follows that it is enough to give results for the wind blowing into the first quadrant only. The printed results on the tables will give for a set of CP 's the following information;. as an example: Azimuth Angle 30 (see Figure 2) Pressure Coefficients CP Quadrant. 1 4 .3 2 Observations•' Region AW DW . CL SBL Position Reference 30 " 150- 210 330 2 27 28 For principal directions: (Azimuth"0° + •90°) S. Azimuth Angle 0° .(see Figure 3) Pressure Coefficients CP Quadrant 1 & 2 3 & 4 Region (AW)Y = (BW)y (CL)Y (DL)Y Position Reference 0 180 1 . 2 27 28 Similarly for azimuth angle 90' the quadrants will be 1 & 4, regions X (�JX ) _ (BW)X, L ) and quadrants 2 & 3 with regions (C )` (DL)X , etc.. t ' The number following "Reference" -is required for testing procedure. For the stress analysis the exact position of'the_pressure points will be required. For this purpose Figure 4 is a large'scale copy of Figure I giving more precise information about the position of_,, the measured CP coefficients in full scale. "- The tests are done for the 4 azimuth'angl"es, i.e. 0% 30% 60°'and `90°. The 0° and 90° will be called "principal directions" and- it- may be noted that for these directions due 'to .symmetry for the azimuth angle 0° (AW),y = (BW)Y, (COY = (DL)Y. - Similarly for the azimuth. angle 900 (AW).X = (BW) X and (COX , (DI) X. This is shown in Figure 3. The same nomenclature will be given on the printed data of the CP coefficients. r 6 2.4 The Internal Pressure Coefficients During the.standard tests the internal pressure point (No. 28) was connected through the scannivalve to'the transducer., Because of -small leaks through the remaining pressure points and the floor it re corded a negative pressure coefficient reflecting the general rule that the pressure integral round a body in the stream is negative. These values are of no particular significance and were measured only as a routine procedure. In the last series of tests the side door (built on the azimuth angle 270°) was open and the model rotated in 'the wind stream from 270° (door facing windwards) to 90° (door facing leeward) every W., These . results are shown in Table 5. The size of the door was 6' x 7' full scale. Although the internal pressures in such a structure are foreseen in the Canadian Building Code they were measured as a matter of interest. 2.5 The .External- Pressure Coefficients All the external pressure coefficients collected during the tests are given in Tables 1 t 4. As explained in section 2-3 they give an. overall information required. for the load distribution. According to the location_of the structure, local gustiness, etc., the given values must be further multiplied by factors detailed in the Canadian Building Code (1]. 2.6 Final Observations The analysis of the data obtained in the wind tunnel reflects sell the type of pressure distribution one would expect to -occur or a building submerged in an atmospheric boundary layer. Thus all the pres- sure coefficients close to the ground are comparatively low (because of the surface roughness) while higher absolute values occur on more exposed parts of the structure at upper levels. _ 7. LIST OF REFERENCES 1. Canadian Building Code, (NBC), Sub-Section 4-1-8 and Commentary B, 1977: 2. Standen, N.M., "A Spire Array for Generating Thick Turbulent Shear G Layers for Natural Wind Simulation in Wind Tunnels", National Research Council of Canada, LTR-LA-94, Low Speed Aerodynamics Section,' May 1972. 3. Davenport, A.G., "Wind Effects on Building Structures", Symposium No. 16, Proceedings of N.P.L. Conference, Middlesex, Vol. I, H.M.S. Stationary Office 1965, June 1963. - •le ' APPENDIX 1. DETAILS OF THE TESTS 1.1 The Model and'Recording System ' The model was made of acrylic sheets 1/4" thick shaped to a high precision in the ratio 1;96. The sheets•,were glued together•'and the model was mounted on a rotating disc and sealed. A door (6' x 7' full scale) .was cut out on the azimuth angle of 270°'and afterwards sealed again. Only for the last set of tests required to measure pres- sures inside the structure, the door was open and the model rotated clockwise in the windstream every 30' from azimuth angle 270° to 90*. In the first case the position of the door was purely "windward" and • r at 90° "leeward ' -Besides -the 27 perforations on the structure to record pressures 8 additional points were also perforated -in the quadrants 2, 3 and 4 to cross check the results measured at all wind directions on the 27 points. These additional data gave about 150 control measurements of the CP coefficients which were in excellent agreement with the measurement's•' shown in Tables 1-4. The internaltubings were made of stainless steel of the same length to give equal time response. The tubes were connected to a•multi- position scanni valve. Each pressure point could be selected by rotating the valve and was connected to a Statham 283 -Tc high precision Transducer, which 'had a resolution of + 0.003" H2O. The data from the transducer were.record�' and Processed on a Data Acquisition System built in the Department of ,Mechanical Engineering, using Hewlett Packard Corp.; components. 9. 1.2 The Wind Tunnel Tests Initial tests indicated that after 5 seconds the pressures were in equilibrium after rotating the valve from one point to another. This time was approximately tripled during the tests for safety precautions. The sampling of the pressures was of 4 secs duration and 2000 samples were taken during this time, averaged and processed to obtain a pressure coefficient. The velocity of the wind tunnelwasabout 150 fps during the tests. As a control procedure, at each direction pressure from the wall of the jet was measured simultaneously with that of the room to give indication of any blockage of the stream during the tests. 1.3 Similarity Considerations The model was made with high exactitude and scaled 1:96 as compared to the prototype. Velocity profiles were measured at the position of the model without and with vortex generator's [2] to simulate artifi- cially the atmospheric boundary layer. The vortex generators were mounted at a distance of 46" from the center of the model. These profiles are shown in Figure A.1. The analysis of the second profile indicated a good logartlunic velocity distribution throughout. the range of, heights required for the model. The "roughness height" was Z0 = 0.0054". The model's height was h 2.95", the fundamental similarity condition o m o p where m model, p - prototype, gave for these tests (Zo)p = 0.48" _ 1.22 cm which corresponds to "open grassland [3). 10. Assuming that the logarithmic velocity profile holds for the atmosphere and the model and also that the velocity profile can be represented by a power law the velocity distribution could be roughly approximated to �U) _ �Z X0.16 g $ giving a power exponent adequate for open terrain. Because of the rela— tively reduced boundary layer height in the wind tunnel it is estimated that the pressure coefficients obtained during the tests are slightly, on the conservative side, i.e. the stresses obtained from these data would be a little higher than in steady wind in the atmosphere giving an additional margin of safety. Table 1 Azimuth Angle 0° Pressure Coefficient CP Quadrant 1 2 3 4 Region (Aw = BW)y (CL = DL)y Reference 0° 00 1800 1800 Position No. (CP) (CP) 1 .319 -.029 2 .383 -..027 3 .171 -.026 4 -.028 -.190 5 -.853 -.754 6 .023 -.053 7 .008 -.034 8 -.101 -.089 ' 9 -.318 -.333 10 -.619 -.040 11 -.591 -.149 12 -.525 -.355 13 -.591 -.587 14 -.388 -.296 15 -.488 -.405 16 -.423 -.395 17 -.528 -.506 18 -.104 -.118. 19 -.099 -.129 20 -.123 -.161 21 -.133 -.173 22 -.165 -.182 23 -.066 -.102 24 -.102 -.112 25 -.140- -.125 26 -.149 -.137 27 -.175 -.157 28 -.149 -.335 Table 2 Azi-nuth Angle 30° Pressure Coefficient Cp Quadrant 1 2 3 4 Region Ada BL , CL DW Reference 30° 150° 2100 3300 Position (CP) No. (CP) (CP) (CP) 1 -.139• -.133 -.145 -.021 2 -.017 -.164 -.193 -.148 3 -.138 -.145 -.178 -.271' 4 -:406 -.326 7,393 -.553 5 -.849 -.601 -.559 -.877 6 .380 -.130 -.130 -.752 7 .381 -.134 -.131 -.811• 8 .107 -,297 -.164 -.717 9 -.125 -.516 -.403 -,843 10 .162 -.250 -.145 -.813 11 .186 -.558 -.172 -.843 12 .051 -.664 -.331 -.843 13 -.220 =.725 -.312 -.838 14 -.040 -.322 .293 -.324 " 15 -.102 -.359 .337 -.519 16 -.167 -.410 .139 -.549 17 -.315 -.497 -.068 -.755 18 .060 -.012 .381 -.120 19 .057 -.055 .215 -.157 20 -.033 -.160 .002 -.321 21 -.166 -.228 -.084 -.415 22 -.746 -:746 -.658 -.809 23 .050 .036 .284 -.093 24 .030 .018 .285 -.112 25 -.073 -.099. -.235 -.232 26 -.163 -.196 -.317 -.314 27 -.736 -.757 -.735 -.777 28 -.118 -.676 -.449 -.232 Table 3 Azimuth Angle 60° Pressure Coefficients CP Quadrant 1 2 3 4 Region AW BL CL DW Reference 60° 1200 2400 3000 Position No. (CP) (CP) (CP), (CP)` 1 -.800 -.194 -.154 -.731 2 -.798 -.208 -.194 -.839 •3 -.775 -.321 -.311 -.837 4 -.800 -.481 -.440 -.839 5 -.800 -.427 -.424 -.839 6 .036 -.301 -.080 -.837 7 .041 -.490 -.158 -.797 8 -.176 -.595 -.270 -.797 9 -.428 -.614 -.482 -.797 10 .324 -.494 -.166 -.643 11 .352 -.519 -.209 -.786 12 .082 -.565 -.301 -.797 13 -.149 -.624 -.479 -.812 14 .333 -.043 -.351 -.381 15 .325 -.035 -.458 -.507 16 .094 -.190 -.405 -.728 17 -.123 -.300 -.487 -.812 18 .330 .226 -.259 -.277 19 .296 .215 -.583 -.467 20 .067 .002 -.604 -.694 21 -.074 -.084 -.552 -.756 22 -.731 -.658 -.646 -.756 23 .273 .284 -.244 =.252 24 .271 .285 -.547 -.565 25 .055 .044 -.684 -.747 -26 -.080 -.090 -.707 -.768 27 -.701 -.713 -.707 -.774 28 -.231 -.519 -.572 -.512 Table 4 Azimuth Angle 90° Pressure Coefficients CP Quadrant 1 4 2' 3 Region (AW = BW)X (CL DL)X Reference 900 270" Position No. (CP) (CP) 1 -.776. -.696 2 -.783 -.804 3- -.763 -.804 4 -.694 -.778 5 -.451 -.437 6 -.529 -.404 - 7 .. -.664 -.629 , 8 -.644 -.605 9 -.653 -.513 10 -.140 -.642 11 -.056 -.556 12 .-.243 -.534 13 -.312 -.466. 14 .293 -.507 15 .337 -.543 16 . .139. ` -:518 17 -.068 -.443 18 .381 -.399 19 .367 -.524 . 20 .158 --.484 21 .028 -.419 22 -.379 -.404 23 .375 -.288 24 .401 -.519 25 .198 _.460 26 .077 -.370 27 -.341 -:328 28 .259 -.515. Figure 1 The Distribution of the Pressure Points on the Model Figure 2 Notation for Non -Principal Azimuth Angles. Figure 3 .Notation for Azimuth Angles, Principal Directions Figure 4 Pressure Point Distribution and Arc Lengths (Inset) Plate 1 The Outlay of the Model in the Wind Tunnel Plate 2 The Recording System for Pressure Measurements A-1 The Velocity. Profiles Without and With Vortex Generators [2] r L1------- 7 1 63. 26' i IT c- P- 2'.%*- 7' 7 I 2t 18 r lo'-cr 1 1o':60" ........... . - ------------ Figure I The Distribution of the Pressure points on the Model .SCALE - '/8" - 1'- 0" L a = -300 4 3 4 (a) W — Windward (b.) L — Leeward ac — azimuth Y angle 2 CL CL DW I ac = -150° a! = 150' AW / BL BL �AW /3 4 3 4 \ (C•) (d.) Figure 2 &Notat ion for hon -Principal Azimuth Angles 3 I 4 3$ 4 (a) W - Windward t b.) L - Leeward Y a - azimuth Y angle 2 I 2 rM (Aw)X (DL) X rr, (XIfnw) X (BW)X (CL)X (DL)X (AW)X 3 4 3 I 4 .AW = BW and CL = DL ( Applies to X and Y') Figure 3 Notation for Azimuth Angles, Principal Directions t i T- T T t i T- or* ",-7 .. I Q� ,-, jwl�,� C) LL.3 —j C.D CE Of CD CD C.) cc el 1O L? 10C, O O Ir co Q - c �la� UH Lt t I Ol .. /f '0 ol 0.0 ol Vo- ol En In 777 06-3' ONU Hinwizu soOINOO aj , CD 0 L-1 I Z rrH N ZD O L-, Z O U Q U 3. Lo t-: in dl: �j C C: Q C5 'Z CC 2 E- N C!7 CD H Z O U 0 CU CD n I LLI CD :z m UI I C.) 4.7 Pressure and; Force Coefficients C Pressure and force coefficients C are designed to take into account the shape and size of a ' building: or structure and the location 'of a component on a- building or structure. The coefficients are developed through wind -tunnel tests in almost all cases; a few full-scale test results are used to check specific results of the wind -tunnel tests. Because the results of many different wind -tunnel tests were used , to assemble the , Standard, there are special characteristics for many of the coefficients. These characteristics and interpretations of the Standard are discussed below. ` 4.7.1 General Comments The Standard specifies three kinds of coefficients, namely external pressure coefficients, internal pressure coefficients, - and force coefficients. The external and internal pressure " coefficients are applicable to enclosed buildings while the ` force coefficients are used for roofs of open buildings and for other structures such as chimneys, towers, and signs. The applicability of pressure and force coefficients is specified in the Standard through design pressure equations. given in Table 4. 1 'The designer. should exercise judgment 'in applying. appropriate pressure coefficients. For example, wind -forces on ` a parapet wall of a building could be determined using force coefficients for signs, even though the parapet is part ..of an enclosed building. , Pressure coefficients given in the Standard have two signs: 1) a positive (+) sign indicates wind pressure acting toward the surface, and 2) a negative (-) sign indicates wind pressure acting away from the surface. This • sign convention is consistent with* the wind pressure sign convention of the Standard as specified in the design pressure equations of Table 4. Force coefficients have absolute values; the force is assumed to act in the direction of the wind unless otherwise specified. The Standard gives pressure and force coefficients for most of the common types of structures such as buildings, chimneys, signs, and others. The designer is- encouraged to.. use values - available in the literature when coefficients for a specific shape are not given in the Standard. The designer is cautioned that published values of pressure coefficients are not always consistent with the fastest -mile wind speed (basic, wind speed of the Standard) or have not been obtained using proper boundary layer wind simulation. _ Under these. conditions, use of prudent judgment is advised. For enclosed buildings, the pressure coefficients of ` the . Standard have the following characteristics: 1) Pressure coefficient values are associated with fastest -mile wind speed. Values available. in the literature may be related to wind speeds of different averaging time; hence they should- be modified appropriately. - 2) Pressure coefficient values for components and ' cladding are combined with the gust response factor (GCp); these should not be separated. Wind -tunnel ; testing procedures require that combined values of GC p be measured. 3) Pressure coefficient values for components and cladding depend on the tributary area of the member; pressure coefficient values become smaller (hence the wind pressure reduces) as the tributary areas become larger. This fact permits the professional designer to reduce wind loads on components with some -extra effort in the design process 4.7.2 Average Loads on Main Wind -Fore R sistin"ystems Figure 2 of the Standard These pressure coefficients are to -be used for, the determination of wind pressures on main wind -force resisting systems of all enclosed buildings. The -values are given for windward, leeward and side walls, and windward and leeward roofs. Since the resulting pressures are for the main wind - force resisting system, the wind pressures on side walls are . 84 ' generally not, critical. However, in cases of a single bay one- story rigid frame with a long span, the pressures associated . with the side wall may cause critical loading. conditions on the frame. The pressure coefficients for the windward wall are. , associated with velocity pressure qz,, evaluated at height z above ground, which in effect results in wind pressures varying with height. For the leeward wall, however, the coefficients are used with velocity pressure qh, evaluated at mean roof height h, thus resulting .in wind pressures that are uniform over the entire height. The eave height may be substituted for the mean roof height h if the roof slope from the horizontal for 'the . building is less than 10 degrees. The pressure coefficient values are provided for wind parallel to two major axes of the building. The main wind - force resisting system should be designed to resist winds from these directions. The pressure coefficient values do not provide for torsional or twisting forces. Torsional loading Js not generally a concern for inflexible buildings; however, -it can be a critical loading condition for flexible buildings. For wind direction normal to the roof ridge and a roof slope of 10-15 degrees, two pressure coefficient values of +0.2 and- -0.9 are specified for -the windward roof. It is the intent of the Standard that design of the main wind -force resisting system should be checked for two loading conditions associated with these pressure coefficients. For low height to length ratio and low roof slope, the windward roof can experience inward acting or outward acting pressures, at different times. The main wind -force resisting system should be able to resist either loading condition. 4.7.3 Components and Cladding for Buildings With Mean Roof = Height h. Less Than 60 Ft. Figure 3 of the Standard These pressure coefficients are related to the tributary area of the component as well as- to the location . of the` component on the building. Tributary area is .the area from which the component receives design wind load. If components are placed close together (e.g., roof joists) the tributary area becomes a narrow rectangular area. For a rectangular tributary area, the width of the area need, not be less . than one-third the length -of the area. Pressure coefficient values provided in the Standard are based, to a large extent, on the comprehensive wind -tunnel tests conducted at the University of Western Ontario (Davenport et al., 1977, 1978). The • wind -tunnel tests were conducted for a- variety of building lengths, widths, heights, roof slopes, roofs,,with parapets and overhangs, and two terrain ' roughnesses--Exposures B . and C categories. Pressure•, coefficients were measured for al•I exterior surfaces to give coverage to local loads : (for cladding and fasteners), distributed loads (for purlins, girts, and `other components), and, using d influence lines, the frame loads. Mean, root mean square, and peak load values 'were measured by an on-line computer for a full range of wind directions. 'The voluminous data were reduced ' using the following, steps: 1 Peak pressure coefficients .were scanned for each direction and the maximum and minimum values determined. 2) For design load format, concepts of zoned uniform loads and tributary area were adopted. Pressure coefficients for open country, smooth terrain (Exposure C) only were - recommended. Experimental data for suburban terrain (Exposure B) indicated that mean speed reduced -,but turbulence increased, resulting in wind pressures equal to or slightly less than those for open country, smooth terrain category. t 3) The wind tunnel measured peak values were divided by ' 1.69 to account for the change from mean hourly wind speed to fastest -mile wind speed. The concept of area averaging of wind pressures was applied to the wind -tunnel test data by combining measured values at .1 several pressure tapsof the model. This` combining and averaging of the measured pressures led to reductions in average pressures, hence reduction in - pressure coefficient values with increasing tributary area of a- component. Since the pressure taps being combined in '' the wind -tunnel tests 86 3, " often formed tributary areas approximating a circular area, the ' Standard allows that the width of a_' rectangular tributary area need not be less than one-third of the length of the rectangle. In recommending pressure coefficient values for the Standard, researchers at The University of Western Ontario' (Davenport and Surry, 1979) proposed a reduction .factor of 0.8 times maximum wind tunnel measured values. The subcommittee on wind loads did not accept this 0.8 reduction, factor for the Standard (ANSI, 1982). Arguments advanced in favor of the reduction factor were as follows: - 1) Although 20 percent of the experimental pressure coefficients measured may be slightly greater than those designated, this figure still implies that • 80 _ percent of the structures and/or roof areas in open country terrain see pressure 'coefficients which are less than those designated, sometimes appreciably so. Thus, in a limited sense, the risk of higher pressure coefficients is concentrated on. small areas of some buildings. 2) When considering the total population of buildings affected by these design pressures - (not pressure coefficients), the majority of buildings are not in open ' country areas but in urban terrain. In these areas, the general trend is for mean pressures to be appreciably less and peak pressures marginally less (about 10 percent on the average) than .those in open terrain. 3) The ranges of wind direction for which the maximum and minimum peak pressure coefficients apply are: - F generally narrow. (Even in individual zones they do not , necessarily occur for the same wind direction.) Thus, the effective pressure coefficient given by the ratio of the once -in -50 -years (say) pressure .to the velocity pressure based on the once -in -50 -years wind speed will always be less than the maximum peak pressure coefficient. Studies on the influence of wind direction' { (Davenport, 1977, Tryggvason, 1979) suggest that the so-called "effective pressure . coefficient" is approximately 70-80 percent of the maxim_ um (minimum) pressure coefficient. 87 F y 4) Most pressure coefficients have to be applied in, conjunction with internal pressure. The maximum difference between external and internal pressures is- somewhat s_somewhat less than . the difference of the maxima. The subcommittee on- wind loads did not accept the recommendation of the reduction factor of 0.8 (80 percent of maximum value). The subcommittee's arguments for not accepting the 0.8 reduction factor are as follows (Mehta, 1984): 1) Response characteristics of pressure measuring systems used in wind -tunnel tests are such that one - second peak 'pressures in full scale may- be _ underestimated in wind -tunnel results . by as much as -10 percent (Marshall and Reinhold, 198.1). ` 2) The_ directions investigated were in most cases limited to 45 -degree increments of wind azimuth;. thus, the data tend to underestimate the true peak . coefficients for critical wind directions. , 3) Tropical storms, such as hurricanes, subject buildings . to winds from many directions, thus creating critical wind loads ,for at least some of the cladding and components. Failure of one component or cladding leads to progressive failure of other members in' a' building.` These progressive failure effects are not well known, . as yet. , 4) In suburban areas, buildings are randomly 'oriented. High winds' from any direction are likely to cause maximum peak pressures on components of several buildings. If those components experiencing maximum peak pressures fail, they could cause windborne debris impact damage to surrounding buildings. Current state - of -knowledge is unable -to account for the uncertainty of windborne debris damage.. : r 5) The wind tunnel measured values were divided by a constant of 1.69 to make them consistent with fastest - mile wind speed. . This constant is not an exact value; there is a degree of uncertainty in the constant. 88 ' 6) Traditionally, pressure coefficient values are the envelope of the maximum values obtained in the experiments. There is no safety factor in the pressure coefficient values. For the sake of consistency in the Standard, pressure coefficient values should not be - adjusted upward or downward from the measured values. The preponderance of evidence based on these arguments suggests that it is not advisable to apply the reductio_ n factor of 0.8 to the pressure coefficient values. This controversy concerning the 0.8 reduction 'factor for pressure coefficient values is likely to continue for some time. The National Building ' Code of Canada (NRCC, 1990b) in its supplement, the Metal Building Manufacturers Association (MBMA, 1986) in its Design Guidelines, ' and the Standard „ Building Code (SBCCI, 1986) have adopted pressure coefficients that incorporate the 0.8 reduction factor. The Basic Building Code (BOCA, 1987) and the Uniform Building Code (ICBO, 1990)- have not adopted the 0.8 reduction factor for pressure coefficients. 4.7.4 Components and Cladding for Buildings with Mean Roof Height h Greater Than 60 Ft. Figure 4 of the Standard ' The .wind -tunnel test data obtained at Colorado State University (Peterka. and Cermak, 1974; Cermak, 1977; Akins and Cermak, 1976) provided the basis for pressure coefficient values in Figure 4 of the Standard. Pressure coefficient values depend on tributary area and location of- the component or cladding. One significant item to note is that the negative pressure coefficients are associated with' velocity pressure y determined at the roof height, thus making the outward acting pressures constant for the full height of the building. Wind - tunnel tests have shown that there are areas of high pressures located in the lower parts of a building. The pressure coefficients given reflect these high pressures noted in wind - tunnel tests.. ` 89 �f.` 1997 UNIFORM BUILDING CODE Volume 2 Chapters 1 through 15 are printed in Volume 1 of the Uniform Building Code. Chapter 16 STRUCTURAL DESIGN REQUIREMENTS NOTE: This chapter has been revised in its entirety. Division I—GENERAL DESIGN REQUIREMENTS SECTION 1601 —SCOPE This chapter prescribes general design requirements applicable to all structures regulated by this code. SECTION 1602 — DEFINITIONS The following terms are defined for use in this code: ALLOWABLE STRESS DESIGN is a method of proportion- ing structural elements such that computed stresses produced in the elements by the allowable stress load combinations do not exceed specified allowable stress (also called working stress design). BALCONY, EXTERIOR, is an exterior floor system project- ing from a structure and supported by that structure, with no addi- tional independent supports. DEAD LOADS consist of the weight of all materials and fixed equipment incorporated into the building or other structure. DECK is an exterior floor system supported on at least two opposing sides by an adjoining structure and/or posts, piers, or other independent supports. FACTORED LOAD is the product of a load specified in Sec- tions 1606 through 1611 and a load factor. See Section 1612.2 for combinations of factored loads. LIMIT STATE is a condition in which a structure or compo- nent is judged either to be no longer useful for its intended function (serviceability limit state) or to be unsafe (strength limit state). LIVE LOADS are those loads produced by the use and occu- pancy of the building or other structure and do not include dead load, construction load, or environmental loads such as wind load, snow load, rain load, earthquake load or flood load. LOAD AND RESISTANCE FACTOR DESIGN (LRFD) is a method of proportioning structural elements using load and resist- ance factors such that no applicable limit state is reached when the structure is subjected to all appropriate load combinations. The term "LRFD" is used in the design of steel and wood structures. STRENGTH DESIGN is a method of proportioning structural elements such that the computed forces produced in the elements by the factored load combinations do not exceed the factored ele- ment strength. The term "strength design" is used in the design of concrete and masonry structures. SECTION 1603 — NOTATIONS D = dead load. E = earthquake load set forth in Section 1630.1. E,,, = estimated maximum earthquake force that can be devel- oped in the structure as set forth in Section 1630.1.1. F = load due to fluids. H = load due to lateral pressure of soil and water in soil. CHAP. 16, DIV. 1 1601 1605.2.1 L = live load, except roof live load, including any permitted ' live load reduction. L,. = roof live load, including any permitted live load reduction. P = ponding load. S = snow load. 7' = self -straining force and effects arising from contraction or expansion resulting from temperature change, shrink- age, moisture change, creep in component materials, movemen! due to differential settlement, or combina- tions thereof. W = load due to wind pressure. SECTION 1604 — STANDARDS The standards listed below are recognized standards (see Section 3504). 1. Wind Design. 1.1 ASCE 7, Chapter 6, Minimum Design Loads for Buildings and Other Structures 1.2 ANSI EIA/TIA 222-E, Structural Standards for Steel Antenna Towers and Antenna Supporting Structures 1.3 ANSINAAMM FP1001, Guide Specifications for the Design Loads of Metal Flagpoles SECTION 1605 —DESIGN 1605.1 General. Buildings and other structures and all portions thereof shall be designed and constructed to sustain, within the limitations specified in this code, all loads set forth in Chapter 16 and elsewhere in this code, combined in accordance with Section 1612. Design shall be in accordance with Strength Design, Load and Resistance Factor Design or Allowable Stress Design meth- ods, as permitted by the applicable materials chapters. EXCEPTION: Unless otherwise required by the building official, buildings or portions thereof that are constructed in accordance with the conventional light -framing requirements specified in Chapter 23 of this code shall be deemed to meet the requirements of this section. 1605.2 Rationality. Any system or method of construction to be used shall be based on a rational analysis in accordance with well- established principles of mechanics. Such analysis shall result in a system that provides a.complete load path capable of transferring all loads and forces from their point of origin to the load -resisting elements. The analysis shall include, but not be limited to, the pro- visions of Sections 1605.2.1 through 1605.2.3. 1605.2.1 Distribution of horizontal shear. The total lateral force shall be distributed to the various vertical elements of the lateral -force -resisting system in proportion to their rigidities con- sidering the rigidity of the horizontal bracing system or dia- phragm. Rigid elements that are assumed not to be part of the lateral -force -resisting system may be incorporated into buildings, provided that their effect on the action of the system is considered and provided for in the design. 2-1 direction h1L 0 10-15 20 30 40' so 60 Leeward Normal <0.3 -0.7 0.2* 0.2 0.3 0.4 to ridge '0-5 0.010 -0.7 -0.9* 0.5 -0.7 -0.9 -0. 75 �0.2 0.3 -0.5 O.Ole 1.0 for all values -0.9 _03S -0.2 0.3 0.5 0.010 1.5 -0.7 -0.9 -0.9 -0.9 -0.35 0.2 of hIL 0.016 and 0 MINIMUM DESIGN LOADS to ridge < 2.5 -0.7 h1B or h1L 0.7 > 2.5 -0.8 �0.8 *Both values of CP shall be used in assessing load effects. NOTES: Wind (2) For flexible buildings and structures, use appropriate Gas determined by rational analysis. (3) Plus and minus signs signify pressures acting toward and away from the surfaces, respectively. (4) Linearinterpolation may be used for values of 0, h1L. and LIB ratios other than shown. (5) Notation: z: Height above ground, in feet h: Mean roof height, in feet, except that cave height may be used for a < 10 degrees qh.qz: Velocity pressure, in Pounds -force per square foot, evaluated at respective height G: CuSt response factor qzGhc 8 P of building, in feet, measured parallel to wind direction Roof slope from horizontal, in degrees qhGhCp JhGhCp F19. 2. External PressureI Coefficients, Cp, for Average Leads on Main Wind -Force Resisting Systems 16 Wall Pressure Coefficients, Cp q L Surface LIB Cp For use with PLAN qC hGhCP qhGhC hj, p Windward wall All values 0.8 qz qzGhCp Lee . ward wall 0-1 2 z4 -0.5 -0.3 . qh -0.2, Mpq Side walls All values -0.7 'qh Z h qhGhCp" L ELEVATION Roof Pressure Coefficients, CP' for Use with 41, Windward Angle, 6 Wind (degrees) direction h1L 0 10-15 20 30 40' so 60 Leeward Normal <0.3 -0.7 0.2* 0.2 0.3 0.4 to ridge '0-5 0.010 -0.7 -0.9* 0.5 -0.7 -0.9 -0. 75 �0.2 0.3 -0.5 O.Ole 1.0 for all values -0.9 _03S -0.2 0.3 0.5 0.010 1.5 -0.7 -0.9 -0.9 -0.9 -0.35 0.2 of hIL 0.016 and 0 Parallel h18 or QL to ridge < 2.5 -0.7 h1B or h1L 0.7 > 2.5 -0.8 �0.8 *Both values of CP shall be used in assessing load effects. NOTES: .0 ) Refer to Table 10 for arched roofs. (2) For flexible buildings and structures, use appropriate Gas determined by rational analysis. (3) Plus and minus signs signify pressures acting toward and away from the surfaces, respectively. (4) Linearinterpolation may be used for values of 0, h1L. and LIB ratios other than shown. (5) Notation: z: Height above ground, in feet h: Mean roof height, in feet, except that cave height may be used for a < 10 degrees qh.qz: Velocity pressure, in Pounds -force per square foot, evaluated at respective height G: CuSt response factor Horizontal dimension of building, in feet, measured normal to wind direction 0 L: Horizontal dimension of building, in feet, measured parallel to wind direction Roof slope from horizontal, in degrees F19. 2. External PressureI Coefficients, Cp, for Average Leads on Main Wind -Force Resisting Systems 16 1997 UNIFORM BUILDING CODE Chapter 35 UNIFORM BUILDING CODE STANDARDS Part I—General -` SECTION 3501 — UBC STANDARDS The Uniform Building Code standards referred to in various parts of this code, which are also listed in Part II of this chapter, are here- by declared to be part of this code and are referred to in this code as a "UBC standard." SECTION 3502 — ADOPTED STANDARDS The standards referred to in various parts of the code, which are listed in Part III of this chapter, are hereby declared to be part of this code. SECTION 3503 — STANDARD OF DUTY The standard of duty established for the recognized standards listed in Part IV of this chapter is that the design, construction and quality of materials of buildings and structures be reasonably safe for life, limb, health, property and public welfare. SECTION 3504— RECOGNIZED STANDARDS The standards listed in Part IV of this chapter are recognized standards. Compliance with these recognized standards shall be prima facie evidence of compliance with the standard of duty set forth in Section 3503. Part II—UBC Standards UBC STD. AND SEC. TITLE AND SOURCE CHAPTER 2-1; 201.2, 215 Noncombustible Material—Tests. Standard Method of Test E 136-79 of the ASTM.' CHAPTER 4 4-1; 303.8, 405.1.1, 405.3.4 Proscenium Firesafety Curtains. Installation Standard of the International Conference of Building Officials. CHAPTER 7 7-1; 405.1.1, 601.3, 703.2, 703.4, 706, 709.3.2.2, 709.5, 709.6, 710.2, Table 7-A, 2602.5.2 Fire Tests of Building Construction and Materials. Standard Methods E 119-83 of the ASTM. 7-2; 302.4, 703.4, 713.5, 713.9, 1004.3.4.3.2, 1005.3.3.5 Fire Tests of Door Assemblies. Standard IOB-1988 of Un- derwriters Laboratories Inc. and International Conference of Building Officials Test Standard for Smoke- and Draft - Control Door Assemblies. 7-3; 703.4, 713.5 Tinclad Fire Doors. Specification of the American National Standards Institute/Underwriters Laboratories Inc. IOA-1979 (R 1985). 3501 3504 7-4; 703.4, 713.5, 713.9 Fire Tests of Window Assemblies. Standard Methods E 163-76 of the ASTM. 7-5; 703.4, 714 Fire Tests of Through -penetration Fire Stops. Standard Method E 814-83 of the ASTM. 7-6; 703.4; 704.6; 1701.4; 1701.5, Item 10 Thickness and Density Determination for Spray -applied Fireproofing. Test Standard of the International Conference of Building Officials. 7-7; 703.3, 703.4 Methods for Calculating Fire Resistance of Steel, Concrete, Wood, Concrete Masonry and Clay Masonry Construction. Standard of the International Conference of Building Offi-' cials. 7-8; 308.2.2.1, 1001.2, 1003.3.1.2 Horizontal Sliding Fire Doors Used in an Exit. Test Stand- ard of the International Conference of Building Officials. CHAPTER 8 8-1; 201.2; 207; 215; 217; 405.1.1; 601.3; 707.2; 707.3; 801.2; 802.1, Item 1; 802.2; 2602.3; 2602.5.2; 2602.6 Test Method for Surface -burning Characteristics of Build- ing Materials. Standard Test Method E 84-84 of the ASTM. 8-2; 801.2, 805 Standard Test Method for Evaluating Room Fire Growth Contribution of Textile Wall Covering. Test Method of the International Conference of Building Officials. CHAPTER9 9-1; 307.11.3, 321.1, 403.2, 404.3.1, 405.1.1, 804.1, 902, 904.1.2, F F 904.1.3, 904.2.6.3, 904.2.7, 904.3.2, 2603.7.1, 2603.8.1 F Installation of Sprinkler Systems. Standard for the Installa- F lion of Sprinkler Systems, NFPA 13-1991, National Fire F Protection Association. F F 9-2; 902, 904.1.2, 904.5.1 F Standpipe Systems. The Standard for Installation of Stand- F pipe Systems and Hose Systems, NFPA 14-1993, National F Fire Protection Association. F F 9-3; 804.1, 805, 902, 904.1.2, 904.1.3, 2603.7.1, 2603.8.1 F Installation of Sprinkler Systems in Group R Occupancies F Four Stories or Less. Standard for the Installation of Sprin- F kler Systems in Residential Occupancies up to Four Stories F in Height, NFPA 1311-1989, National Fire Protection Asso- F ciation. F CHAPTER 10 10-1; 1001.2, 1003.3.1.2 Power -operated Exit Doors. Test Standard of the Interna- tional Conference of Building Officials. 10-2; 1001.2, 1003.3.3.13 F F Stairway Identification. Specification Standard of the Inter- F national Conference of Building Officials. F 10-3; Appendix 3407.1 Exit Ladder Device. Test Standard of the International Con- ference of Building Officials. 10-4; 1001.2, 1003.3.1:9 Panic Hardware. Standard 305, July 30, 1979, of Under- ' writers Laboratories Inc. 'ASTM refers to the American Society for Testing and Materials. 1-301' Reactions sum 0.00000 -10.43214 _ -7.71755 Moments fKip'ftl Forces [Kip] � f Node FX FY FZ Condition COM3=I.OSWT+I.IRFLD+.5HRFD+.5HRF2 0.00000 1 0.00000 0.98312 2.17218 15 -0.00001 -0.98312 2.17234 16 -0.00007 0.97882 2.17222 30 -0.00007 -0.97882 2.17232 31 0.00006 0.97881 2.17222 45 0.00006 -0.97881 2.17232 46 -0.00066 0.41830 1.56922 60 -0.00065 -0.41925 1.57529 61 0.00055 0.41776 1.56871 75 0.00054 -0.41871 1.57478 76 0.19846 0.20454 1.15186 83 -0.19932 0.20496 1.15358 90 0.26251 0.00001 1.13412 97 -0.26054 0.00001 1.13172 104 0.19761 -0.20360 1.15056 111 -0.19847 -0.20402 1.15227 sUM sum - ------------------- ----------------- 0.00000 0.00000 26.19571 Condition COME=0.9SWT+0.96LW 0.00000 0.00000 1 0.00000 0.05019 -0.32327 15 0.00000 -0.05019 -0.32327 16 0.00000 -0.07407 -0.69397 30 0.00000 0.07455 -0.69435 31 0.00000 -0.07530 -0.69398 45 0.00000 0.07578 -0.69435 46 0.00068 -0.01882 -1.43217 60 0.00067 0.04254 -1.43180 61 -0.00047 -0.15147 -1.14183 75 -0.00045 0.15108 -1.14142 76 0.04751 0.04367 -0.35469 83 0.00008 -0.00429 -0.08113 90 -0.13787 0.00002 0.57090 97 -0.10279 0.00001 0.20146 104 0.04604 -0.04215 -0.35686 111 0.00044 0.00467 -0.08168 sUM - ----------------------------------------------- -0.14618 0.02621 -8.67240 Condition COM7=0.9SWT+0.96CW 0.00000 0.00000 1 0.00000 -1.21827 -0.30375 15 0.00000 -0.78557 -0.40711 16 0.00010 -1.19640 -0.43956 30 0.00011 -0.79056 -0.53744 31 -0.00011 -1.19637 -0.43956 45 -0.00011 -0.79059 -0.53745 46 0.00151 -0.80312 -0.02623 60 -0.00071 -0.74524 -0.54958 61 -0.00144 -0.80034 -0.02326 75 0.00062 -0.74784 -0.54700 76 -0.23654 -0.25122 -0.79462 83 0.23832 -0.25444 -0.80498 90 0.17573 -0.00704 -0.99477 97 -0.17926 -0.00722 -0.98178 104 0.41413 -0.42057 -0.16114 111 -0.41237 -0.41735 -0.16931 sum 0.00000 -10.43214 _ -7.71755 0.00000 0.00000 0.00000 Moments fKip'ftl � f MY MZ 0.00000 0.00000 0.00000 Moments fKip'ftl MX MY MZ 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 ' 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 - 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000: 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 ---------------------------------------------- 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000. 0.00000 0.00000 0.00000 0.00000 _ 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 RAM International Page B -1 -SUMMARY File C:\Documents and Settings\Steven B. Brown\My Documents\Ramadvansedat Units syste: English Date ######## Aluminum Arch Analysis Results -4x4 Arch Maximum forces at members Reference page for IR equations IR= Interaction Ratio Condition: COM1=I.OSWT+I.IRFLD Axial Shear V2 Shear V3 Torsion M22 M33 IR IR (Kip] [Kip] [Kip] [Kip*ft] [Kip*ft] [Kip*ft] bending- bending - tension compression MEMBER 2 0 0 Max -0.53 0.14 0 0 0 • -0.66 0.073211 0.107342 Min -0.61 0.13 0 0 0 -1.08 0.116299 0.157558 MEMBER 13 0 0 Max -0.53 -0.13 0 0 0 -0.66 0.073211 0.107342 Min -0.61 -0.14 0 0 0 -1.08 0.116299 0.157558 Condition: COM2=I.OSWT+1.1RFLD+.5HRFD 0 0 Axial Shear V2 Shear V3 Torsion M22 M33 #VALUE! #VALUE! [Kip] [Kip] [Kip] [Kip*ft] [Kip*ft] [Kip*ft] #VALUE! #VALUE! MEMBER 2 0 0 Max 1 -1.66 0.31 0 0 0 -1.7 0.192585 0.314606 Min 1 -1.8 0.28 0 0 0 -2.62 0.28649 0.433017 MEMBER 12 0 0 Max I -1 -0.051 Oi 0 0 -3.05 0.318605 0.402008 Min 1 -1.07 -0.11 01 0 0 -3.281 0.342558 0.43389 Condition: COM3=I.OSWT+I.IRFLD+.5HRFD+.5HRF2 0 0 Axial Shear V2 Shear V3 Torsion M22 M33 #VALUE! #VALUE! [Kip] [Kip] [Kip] [Kip*ft] [Kip*ft] [Kip*ft] #VALUE! #VALUE! MEMBER 2 0 0 Max -2.11 0.6 0 0 0 -2.74 0.302707 0.477897 Min -2.24 0.58 0 0 0 -4.58 0.488476 0.711025 MEMBER 13 1 1 1 1 0 0 Max T -2.11 -0.58 0 0 0 -2.74 0.302707 0.477897 Min 1 -2.24 -0.611 01 0 0 -4.59 0.489476 0.712221 Condition: COM4=0.75SWT+0.IRFLD+0.71LW 0 0 Axial Shear V2 Shear V3 Torsion M22 M33 #VALUE! #VALUE! Ki [Kip] (Kip] [Kip*ft] [Ki *ft] [Kip*ft #VALUE! #VALUE! MEMBER 47 1 0 0 Max 0.91 0.34 0 0 0 -0.71 0.083381 0.142475 Min 0.9 0.03 0 0 0 -1.43 0.155245 0.218748 MEMBER 48 0 0 Max 0.921 0.021 01 0 0 -1.11 0.123517 0.186144 Min 0.91 -0.191 01 0 0 -1.44 0.156381 0.220669 Condition: COM5=0.75SWT+0.1RFLD+0.71CW 1 0 0 Axial Shear V2 Shear V3 Torsion M22 M33 #VALUE! #VALUE! [Kip] [Kip] [Kip] [Kip*ft] [Kip*ft] [Kip*ft] #VALUE! #VALUE! MEMBER 3 0 0 Max 0.5 -0.16 0 0 0 4.84 0.490803 0.53883 Min 0.48 -0.34 .0 0 0 4.06 0.412531 0.455778 MEMBER 4 0 0 Max 1 0.54 0.19i 01 01 4.841 0.491347 0.543276 Min 1 0.531 0.041 01 01 4.471 0.4542111 0.503675 RAM International Page B-1 File C:\Documents and Settings\Steven•B. Brown\My Documents\Ramadvansedata\Data\madisonclub-3 Units syste : English Date ######## Aluminum Arch Analysis Results -4x4 Arch Maximum forces at members Reference page for,IR equations IR= Interaction Ratio Condition: COM1=I.OSWT+I.IRFLD Axial Shear V2 Shear V3 Torsion M22 M33 IR IR [Kip] [Kip] [Kip] [Kip*ft] [Kip*ft] [Kip*ft] bending- bending - tension compression MEMBER 43 Max • -0.45 0.11 0 0 0 0 0.006122 0.032847 Min -0.53 0.11 0 0 0 -0.31 0.038211 0.070934 MEMBER 44 0 0 Max -0.38 0.04 0 0 0 -0.31 0.03617 0.059622 Min -0.46 0.02 0 0 0 -0.41 0.047259 0.076001 MEMBER 45 0 0 Max -0.29 -0.05 0 0 0 -0.17 0.020946 0.038536 Min -0.37 -0.1 0 0 0 -0.41 0.046034 0.069145 MEMBER 46 0 0 Max -0.24 -0.06 0 0 0 0.11 0.014265 0.028714 Min -0.28 -0.12 0 0 0 -0.17 0.02081 0.037793 MEMBER 47 0 0 Max -0.19 -0.03 0 0 0 0.35 0.037585 0.049361 Min -0.22 -0.1 0 0 0 0.11 0.013993 0.027238 MEMBER 48 0 0 Max -0.15 0.05 0 0 0 0.38 0.040041 0.04937 Min -0.18 -0.02 0 0 0 0.3 0.032449 0.043538 MEMBER 49 0 0 Max -0.12 0.11 0 0 '0 0.3 0.031633 0.039024 Min -0.15 0.05 0 0 0 0 0.002041 0.010949 MEMBER 50 0 0 Max -0.12 -0.05 0 0 0 0.3 0.031633 0.039024 Min -0.15 -0.11 0 0 0 0 0.002041 0.010949 MEMBER 51 p 0 Max -0.15 0.02 0 0 0 0.37 0.039041 0.048358 Min -0.18 -0.05_ 0 0 0 0.3 0.032449 0.043538 MEMBER 52 0 0 Max -0.19 0.1 0 0 0 0.35 0.037585 0.049361 Min -0.22 0.02 0 0 0 0.11 0.013993 0.027238 MEMBER 53 0 0 Max -0.24 0.12 0 0 0 0.11 0.014265 0.028714 Min -0.28 0.06 0 0 0 -0.17 0.02081 0.037793 MEMBER 54 0 0 Max -0.29 0.1 0 0 0 -0.17 0.020946 0.038536 Min -0.37 0.05 0 0 0 -0.41 0.046034 0.069145 MEMBER 55 0 0 Max -0.38 -0.02 0 0 0 -0.31 0.03617 0.059622 Min -0.46 -0.04 0 0 0 -0.41 0.047259 0.076001 MEMBER 56 0 0 Max -0.45 -0.11 0 0 0 0 0.006122 0.032847 Min -0.53 -0.11 0 0 0 -0.31 0.038211 0.070934 Page B-1 MEMBER 15 0.007891 0.042336 0 -0.66 Max 0.116733 -0.58 0.24 0 0 Min -0.66 -0.65 0.24 0 0 MEMBER 16 0 0 Max -0.94 -0.53 0.14 0 0 Min 0.151621 -0.61 0.13 0 0 MEMBER 17 0.05217 0.076078 0, 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Brown\My Docum Units syste: English Date Spreader Analysis Results Maximum forces at members Condition: COM1=1.OSWT+1.1RFLD Axial Shear V2 Shear V3 Torsion M22 M33 J[Kip] [Kip] Kip Ki *ft Kip*ft] [Ki *ft MEMBER 125 Max 0.12 0 0.01 0 0.01 0 Min 0.12 0 -0.01 0 0 0 MEMBER 137 Max -0.411 0 0.01 0 0 0 Min 1 -0.41 0 -0.01 0 -0.01 0 Condition: COM2=I.OSWT+1.1RFLD+.5HRFD Axial Shear V2 Shear V3 Torsion M22 M33 [Kip] [Kip] [Kip] [Kip*ft] [Kip*ft] . [Kip*ft] MEMBER 126 Max 0.29 0 0.01 0.01 0.01 0 Min 0.29 0 -0.01 0.01 0 0 MEMBER 137 Max -0.941 0 0.01 0.011 0 0 Min 1 -0.94 0 -0.011 0.01 -0.01 0 Condition: COM3=I.OSWT+1.1RFLD+.SHRFD+.5HRF2 Axial Shear V2 Shear V3 Torsion M22 M33 [Kip] [Kip] [Kip] [Kip*ft] [Kip*ft] [Kip*ft] MEMBER 118 Max 0.46 0 0.01 0 0 0 Min 0.46 0 -0.01 0 -0.01 0 MEMBER 137 Max 1 -1.48 01 0.011 0 0 0 Min 1 -1.48 0 -0.01 0 -0.01 0 Condition : COM4=0.75SWT+0.IRFLD+0.71LW Axial Shear V2 Shear V3 Torsion M22 M33 [Kip] [Kip] [Kip] [Kip*ft] [Kip*ft] [Kip*ft] MEMBER 126 Max 0.23 0 0 0 0.01 0 Min 0.23 0 0 0 0 0 MEMBER 137 Max 1 0.24 0 0 0 0 0 Min 1 -0.24 01 01 0 -0.01 0 Condition: COM5=0.75SWT+0.1RFLD+0.71CW Axial Shear V2 Shear V3 Torsion M22 M33 [Kip] [Kip] [Kip] [Kip*ft] [Kip*ft] [Kip*ft] MEMBER 137 Max 0.68 0 0 0.01 0 0 Min 0.68 0 0 0.01 -0.01 0 MEMBER 138 Max 0.68 0 0 0.01 0 0 Min 1 0.68 01 01 0.01 -0.01 0 Page C-1 RAM International Page C-1 File C:\Documents and Settings\Steven B. Brown\My,Docur Units syste : English Date Spreader Analysis Results. Maximum forces at members Condition: COM1=I.OSWT+I.1RFLD • Axial Shear V2 Shear V3 Torsion M22 M33 [Kip] [Kip] [Kip] [Kip'ft] [Kip'ft] [Kip'ft] MEMBER 133 Max 0 0 0.01 -0.02 0.01 0 Min 0 0 -0.01 -0.02 0 0 MEMBER 134 Max 0 0 0.01 0 0.01 0 Min 0 0 -0.01 0 0 0 MEMBER 135 Max 0 0 0.01 0 0.01 0 Min 0 0 -0.01 0 0 0 MEMBER 136 Max 0 0 0.01 0.02 0.01 0 Min 0 0 -0.01 0.02 0 0 MEMBER 129 Max 0 0 0.01 -0.02 0 0 Min 0 0 -0.01 -0.02 -0.01 0 MEMBER 130 Max 0 0 0.01 0 0 0 Min 0 0 -0.01 0 -0.01 0 MEMBER 131 Max 0 0 0.01 0 0 0 Min 0 0 -0.01 0 -0.01 0 MEMBER 132 Max 0 0 0.01 0.02 0 0 Min 0 0 -0.01 0.02 -0.01 0 MEMBER 124 Max 0.11 0 0.01 0 0.01 0 Min 0.11 0 -0.01 0 0 0 MEMBER 125 Max 0.12 0 0.01 0 0.01 0 Min 0.12 0 -0.01 0 0 0 MEMBER 126 Max 0.12 0 0.01 0 0.01 0 Min 0.12 0 -0.01 0 0 0 MEMBER 127 Max 0.12 0 0.01 0 0 0 Min 0.12 0 -0.01 0 -0.01 0 MEMBER 128 Max_ 0.12 0 0.01 0 0 0 Min 0.12 0 -0.01 0 -0.01 0 MEMBER 113 Max 0.11 0 0.01 0 0 0 Min 0.11 0 -0.01 0 -0.01 0 Page C-1 MEMBER 114 Max 0.11 0 0 0 0 0.01 Min 0.11 0 0 0 -0.01 0 MEMBER 115 Max 0.11 0 0.01. 0 0 0 ' . Min 0.11 0 -0.01' 0 -0.01 0 MEMBER 116 ' Max 0.11 0 0.01 0 0 0 - Min 0.11 0 -0.01 0 -0.01 0 MEMBER 117 - '. Max 0.12 0 0.01. 0 0 0 Min 0.12 0 -0.01 0 -0.01 0 MEMBER 118 ' Max 0.12 0 0.01 0 0 0 Min 0.12 0 -0.01 0 -0:01 ' 0 MEMBER 119 z Max 0.12 0 0.01 0 0.01 0 Min 0.12 0 -0.01 0 - 0 0 - MEMBER 120 Max 0.12 0 0.01 0 0.01 0 Min 0.12 0 -0.01 0 0 0 " MEMBER 121 Max 0.11 0 0.01 0 0.01 0 Min 0.11 0. -0.01 0 0 0 MEMBER 122 - Max 0.11 0 0.01 0 0.01 0 Min 0.11 0 -0.01 0 0 0. _ MEMBER 123 Max 0.11 0 0.01 0 0.01 0 Min 0.11 0 -0.01 0 0 0 MEMBER 137 - Max -0.41 0 0.01 0 0 0 Min -0.41 0 -0.01 0 -0.01 0 MEMBER 138 , Max -0.41 0 0.01 0, 0 0 Min -0.41 0 -0.01 0' -0.01 0 ' MEMBER 139 Max .-0.41 0 0.01 0 0 0 Min -0.41 0 " -0.01 0 -0.01 -0 ' MEMBER 140 Max -0.41 0 0.01 0 0 0 Min -0.41 0 -0.01 0 -0.01 0 Condition: COM2=1.OSWT+1.1RFLD+.5HRFD Axial Shear V2 Shear V3 Torsion M22 M33 [Kip] [Kip] [Kip] [Kip*ft] [Kip*ft] [Kip*ft] - MEMBER 133 Max 0 0 0.01 -0.04 0.01 0 , Min 0 0. -0.01 -0.04 0 0 MEMBER 134 ` Max 0 0 0.01 0 0.01 0 ,. Min 0 0 -0.01 0 0 4 0 -' MEMBER 135 Max 0 0 0.01 0 0.01 0 - Min 0 0 -0.01 0 0 0 Page C-2 t MEMBER 136 Max 0 0 0.01 0.04 0.01 -0. Min 0 0 -0.01 0.04 0 0 MEMBER 129 Max 0 0 0.01 -0.04 0 0 Min 0 0 -0.01 -0.04 -0.01 0 MEMBER 130 Max 0 0 0.01 0 0 0 Min 0 0 -0.01 0 -0.01 0 MEMBER 131 Max' 0 0 0.01 0 0 0 Min 0 0 -0.01 0 • -0.01 0 MEMBER 132 Max 0 0 0.01 0.04 0 0 Min 0 0 -0.01 0.04 -0.01 0 MEMBER 124 Max 0.26 0 0.01 0 0.01 0 Min 0.26 0 -0.01 0 0 0 MEMBER 125 Max 0.28 0 0.01 0.01 0.01 0 . Min 0.28 0 -0.01 0.01 0 0 MEMBER 126 Max 0.29 0 0.01 0.01 0.01 0 Min 0.29 0 -0.01 0.01 0 0 MEMBER 127 Max 0.28 0 0.01 0 0 0 ; Min 0.28 0 -0.01 0 -0.01 0 MEMBER 128 Max 0.28 0 0.01 0 0 0 Min 0.28 0 -0.01 0 -0.01 0 MEMBER 113 Max 0.26 0 0.01 -0.01 0 0 Min 0.26 0 -0.01 -0.01 -0.01 0 MEMBER 114 Max 0.26 0 0 0 0 0.01 Min 0.26 0 0 0 -0.01 0 MEMBER 115 Max 0.26 0 0.01 0 0 0 Min 0.26 0 -0.01 0 -0.01 0 MEMBER 116 Max 0.26 0 0.01 0.01 0 0 Min 0.26 0 -0.01 0.01 -0.01 0 MEMBER 117 Max 0.28 0 0.01 0 0 0 Min 0.28 0 -0.01 0 -0.01 0 MEMBER 118 Max 0.29 0 0.01 0 0 0 Min 0.29 0 -0.01 0 -0.01 0 MEMBER 119 Max 0.29 0 0.01 0 0.01 0 Min 0.29 0 -0.01 0 0 0 MEMBER 120 Max 0.28 0 0.01 0 0.01 0 Min 0.28 0 -0.01 0 0 0 MEMBER 121 Max 0.26 0 0.01 0 0.01 0 Min 0.26 0 -0.01 0 0 0 Page C-3 MEMBER 122 Max 0.26 0 0.01 0 0.01 0 Min 0.26 0 -0.01 0 0 0 MEMBER 123 Max 0.26 0 0.01- 0 0.01 0 Min 0.26 0 -0.01 0 0 0 MEMBER 137 Max -0.94 0 0.01 0.01 0 0 Min -0.94 0 -0.01 0.01 -0.01 0 MEMBER 138 Max -0.94 0 0.01 0.01 0 0 Min -0.94 0 -0.01 0.01 -0.01 0 MEMBER 139 Max -0.94 0 0.01 0.01 0 0 Min -0.94 0 -0.01 0.01 -0.01 0 MEMBER 140 Max -0.94 0 0.01 0.01 0 0 Min -0.94 0 -0.01 0.01 -0.01 0 Condition: COM3=I.OSWT+1.1RFLD+.5HRFD+.5HRF2 Axial Shear V2 Shear V3 Torsion M22 M33 [Kip] [Kip] [Kip] [Kip'ft] [Kip"ft] [Kip"ft] MEMBER 133 Max 0 0 0.01 -0.07 0.01 0 Min 0 0 -0.01 -0.07 0 0 MEMBER 134 Max 0 0 0.01 0 0.01 0 Min 0 0 -0.01 0 0 0 MEMBER 135 Max 0 0 0.01 0 0.01 0 Min 0 0 -0.01 0 0 0 MEMBER 136 Max 0 0 0.01 0.07 0.01 0 Min 0 0 -0.01 0.07 0 0 MEMBER 129 Max 0 0 0.01 -0.07 0 0 Min 0 0 -0.01 -0.07 -0.01 0 MEMBER 130 Max 0 0 0.01 0 0 0 Min 0 0 -0.01 0 -0.01 0 MEMBER 131 Max 0 0 0.01 0 0 0 Min 0 0 -0.01 0 -0.01 0 MEMBER 132 Max 0 0 0.01 0.07 0 0 Min 0 0 -0.01 0.07 -0.01 0 MEMBER 124 Max 0.41 0 0.01 0 0.01 0 Min 0.41 0 -0.01 0 0 0 MEMBER 125 Max 0.45 0 0.01 0.01 0.01 0 Min 0.45 0 -0.01 0.01 0 0 MEMBER 126 Max 0.45 0 0.01 0 0.01 0 Min 0.45 0 -0.01 0 0 0 Page C-4 MEMBER 127 Max 0.45 0 0.01 0 0 0 Min 0.45 0 -0.01 0 -0.01 0 MEMBER 128 Max 0.45 0 0.01 -0.01 0 0 . Min 0.45 0 -0.01 -0.01 -0.01 0 MEMBER 113 " Max 0.41 0 0.01 0 0 0 " Min 0.41 0 -0.01 0 -0.01 0 MEMBER 114 Max 0.41 0 0 0 0 0.01 Min 0.41 0 0 0 -0.01 0 MEMBER 115 Max 0.41 0 0.01 0 0 0 Min 0.41 0 -0.01 0 -0.01 0 MEMBER 116 Max 0.41 0 0.01 0 0 0 Min 0.41 0 -0.01 0 -0.01 0 MEMBER 117 Max 0.45 0 0.01 0.01 0 0 Min 0.45 0 -0.01 0.01 -0.01 0 MEMBER 118 Max 0.46 0 0.01 0 0 0 Min 0.46 0 -0.01 0 -0.01'' 0 _ MEMBER 119 Max 0.46 0 0.01 0 0.01 0 Min 0.46 0 -0.01 0 0 0 MEMBER 120 Max 0.45 0 0.01 -0.01 0.01 0 Min 0.45 0 -0.01 -0.01 0 0 MEMBER 121 Max 0.41 0 0.01 0 0.01 0 Min 0.41 0 -0.01 0 0 0 MEMBER 122 Max " 0.41 0 0.01 0 0.01 0 Min 0.41 0 -0.01 0 0 0 MEMBER 123 Max 0.41 0 0.01 0 0.01 0' Min 0.41 0 -0.01 0 0 0 MEMBER 137 Max -1.48 0 0.01 0 0 0 Min -1.48 0 -0.01 0 -0.01 0 MEMBER 138 Max -1.48 0 0.01 0 0 0 Min -1.48 0 -0.01 0 -0.01 0 MEMBER 139 Max -1.48 0 0.01 0 0 0 Min -1.48 0 -0.01 0 -0.01 0 MEMBER 140 Max -1.48 0 0.01 0 0 0 Min -1.48 0 -0.01 0 -0.01 0 Condition: COM4=0.75SWT+0.1 RFLD+0.71 LW Axial Shear V2 Shear V3 Torsion M22 M33 [Kip] [Kip] [Kip] [KiP*n] [KiP*ft] [KiP'ft] Page C-5 MEMBER 133 Max 0 0 0 -0.01 0.01 0 Min 0 0 0 -0.01 0 0. MEMBER 134 Max 0 0 0 -0.01 0.01 0 Min 0 0 0 -0.01 0 0 MEMBER 135 Max 0 0 0 0.01 0.01 0 , Min 0 0 0 0.01 0 0 MEMBER 136 Max 0 0 0 -0.01 0.01 0 Min 0 0 0 -0.01 0 0 MEMBER 129 Max 0 0 0 0.01 0 0 Min 0 0 0 0.01 -0.01 0 MEMBER 130 Max 0 0 0 -0.01 0 0 Min 0 0 0 -0.01 -0.01 0 MEMBER 131 Max 0 0 0 0.01 0 0 Min 0 0 0 0.01 -0.01 0 MEMBER 132 Max 0 0 0 0.01 0 0 Min 0 0 0 0.01 -0.01 0 MEMBER 124 Max 0.17 0 0 0.01 0.01 0 Min 0.17 0 0 0.01 0 -0 MEMBER 125 Max 0.18 0 0 -0.01 0.01 0 Min 0.18 0 0 -0.01 0 0 MEMBER 126 Max 0.23 0 0 0 0.01 0 Min 0.23 0 0 0 0 0 MEMBER 127 Max 0.23 0 0 0 0 0 Min 0.23 0 0 0 -0.01 0 MEMBER 128 Max 0.18 0 0 0.01 0 0 Min 0.18 0 0 0.01 -0.01 0 . MEMBER 113 Max 0.17 0 0 -0.01 0 0 Min 0.17 0 0 -0.01 -0.01 0 MEMBER 114 Max 0.17 0 0 0 0 0.01 Min 0.17 0 0 0 -0.01 0 MEMBER 115 Max 0.17 0 0, 0 0 0 Min 0.17 0 0 0 -0.01 0 MEMBER 116 Max 0.17 0 0 0 0 0 Min 0.17 0 0 0 -0.01 0 MEMBER 117 Max 0.18 0 0 0 0 0 Min 0.18 0 0 0 -0.01 0 MEMBER 118 Max 0.23 0 0 0 0 0 Min 0.23 0 0 0 -0.01 0 Page C-6 MEMBER 119 Max 0.23 0 0 0 0.01 0 Min 0.23 0 0 0 0 0 MEMBER 120 Max 0.18 0 0 0 0.01 0 Min 0.18 0 0 0 0 0 . MEMBER 121 Max 0.17 0 0 0 0.01 0 ' Min 0.17 0 0 0 0 0 MEMBER 122 Max 0.17 0 0 0 0.01 0 Min 0.17 0 0 0 0 0 MEMBER 123 Max 0.17 0 0 0 0.01 0 Min 0.17 0 0 0 0 0 MEMBER 137 Max -0.24 0 0 0 0 0 Min -0.24 0 0 0 -0.01 0 MEMBER 138 Max -0.24 0 0 0 0 0 Min -0.24 0 0 0 -0.01 0 MEMBER 139 Max -0.24 0 0 0 0 0 Min -0.24 0 0 0 -0.01 0 MEMBER 140 Max -0.24 0 0 0 0 0 Min -0.24 0 0 0 -0.01 0 Condition: COM5=0.75SWT+0.1RFLD+0.71CW Axial Shear V2 Shear V3 Torsion M22 M33 [Kip] [Kip] [Kip] [Klp*ft] [Klp`ft] [Kip'ft] MEMBER 133 Max 0 0 0 0 0.01 0" Min 0 0 0 0 0 0 MEMBER 134 Max 0.01 0 0 0 0.01 0 Min 0.01 0 0 0 0 0 MEMBER 135 Max 0.01 0 0 0 0.01 0 Min 0.01 0 0 0 0 0 MEMBER 136 Max 0 0 0 0 0.01 0 Min 0 0 0 0 0 0 MEMBER 129 Max 0 0 0 0.02 0 0 Min 0 0 0 0.02 -0.01 0 MEMBER 130 Max 0 0 0 0 0 0 Min 0 0 0 0 -0.01 0 MEMBER 131 Max 0 0 0 0 0 0 Min 0 0 0 0 -0.01 0 MEMBER 132 Max 0 0 0 -0.02 0 0 Min 0 0 0 -0.02 -0.01 0 = Page C-7 MEMBER 124 Max 0.35 Min 0.35 MEMBER 125 Max 0.38 Min 0.38 MEMBER 126 Max 0.48 Min 0.48 MEMBER 127 Max 0.47 Min 0.47 MEMBER 128 Max 0.4 Min 0.4 MEMBER 113 Max 0.37 Min 0.37 MEMBER 114 Max 0.36 Min 0.36 MEMBER 115 Max 0.36 Min 0.36 MEMBER 116 Max 0.37 Min 0.37 MEMBER 117 Max 0.4 Min 0.4 MEMBER 118 Max 0.49 Min 0.49 MEMBER 119 Max 0.5 Min 0.5 MEMBER 120 Max 0.38 Min 0.38 MEMBER 121 Max 0.35 Min 0.35 MEMBER 122 Max 0.35 Min 0.35 MEMBER 123 Max 0.35 Min 0.35 MEMBER 137 Max 0.68 Min 0.68 MEMBER 138 Max 0.68 Min 0.68 MEMBER 139 Max 0.68 Min 0.68 0 0 -0.02 0.01 0 0 0 -0.02 0 0 0 0 0.01 0.01 0 0 0 0.01 0 0 0 0 0.03 0.01 0 0 0 0.03 0 0 0 0 0.03 0 '0 0 0 0.03 -0.01 0 0 0 0.02 0 0 0 0 0.02 -0.01 0 0 0 -0.02 0 0 0 0 -0.02 -0.01 0 0 0 0 0 0.01 0 0 0 -0.01 0- 0 0 0 0 0 0 0 0 -0.01 0 0 0 0.02 0 0 0 0, 0.02 -0.01 0 0 0 -0.01 0 0 0 0 -0.01 -0.01 0 0 0 -0.03 0 0 0 0 -0.03 -0.01 0 0 0 -0.03 0.01 0 0 0 -0.03 0 0 0 0 -0.01 0.01 .0 0 0 -0.01 0 0 0 0 0.02 0.01 0 0 0 0.02 0 0 0 0 0 0.01 0 0 0 0 0 0 0 0 0 0.01 0 0 0 0 0 0 0 0 0.01 0 0 0 0 0.01 -0.01 0 0 0 0.01 0 0 0 0 0.01 -0.01 0 0 0 0.01 0 0 0 0 0.01 -0.01 0 Page C-8 D-1 D. RAM RAM International File C:\Documents and Settings\Steven B. Brown\My Documents\Ramadvansedata\Data\madisonclub-30-classic-1.AVW Units system English Date 2/3/2006 2:26:34 PM Geometry data GLOSSARY Cb22, Cb33 : Moment gradient coefficients Cm22, Cm33 : Coefficients applied to bending term in interaction formula d0 : Tapered member section depth at J end of member DJX : Rigid end offset distance measured from J node in axis X DJY : Rigid end offset distance measured from J node in axis Y DJZ : Rigid end offset distance measured from J node in axis Z DKX : Rigid end offset distance measured from K node in axis X DKY :,Rigid end offset distance measured from K node in axis Y DKZ : Rigid end offset distance measured from K node in axis Z dl : Tapered member section depth at K end of member Ig factor : Inertia reduction factor (Effective Inertia/Gross Inertia) for reinforced concrete members K22 : Effective length factor about axis 2 K33 : Effective length factor about axis 3 L22 : Member length for calculation of axial capacity L33 : Member length for calculation of axial capacity LB pos : Lateral unbraced length of the compression flange in the positive side of local axis 2 LB neg : Lateral unbraced length of the compression flange in the negative side of local axis 2 RX : Rotation about X RY : Rotation about Y RZ : Rotation about Z TO : 1 = Tension only member 0 = Normal member TX : Translation in X TY : Translation in Y TZ : Translation in•Z Nodes Node, X Y Z Floor Ift] Ift] [ft] 1 ------------------------------------------------------------------- 0.00 -15.208 0.00 0-, 2 0.00 -15.205 2.79 0 3 0.00 -14.628 5.861 0 4 0.00 12.969 8.522 0 5 0.00 10.458 10.392 0 6 0.00 -6.972 - 12.05 0 7 0.00 -3.486 13.78 0 8 0.00 0.00 15.493 0 9 0.00 3.486 13.79 0 10 0.00 6.972 12.09 0 11 0.00 10.458 10.392 0 12 0.00 12.969 8.522 0 13 0.00 -14.628 5.867 0 14 0.00 15.205 2.79 0 15 0.00 15.208 0.00 0 16 -10.00 -15.208 0.00 0 17 -10.00 -15.205 2.79 0 18 -10.00 -14.628 5.867 0 19 -10.00 -12.969 8.522 0 20 -10.00 -10.458 10.392 0 21 -10.00 -6.972 12.05 0 22 -10.00 -3.486 13.78 0 23 -10.00 0.00 15.493 0 24 -10.00 3.486 13.79 0 25 -10.00 6.972 12.09 0 D-1 Nodes Node X Y Z Floor [ft] {ft] [ft] 26 ----------------------------------------------------------------- -10.00 10.458 10.392 0 27 10.00 12.969 8.522 0 28 -10.00 14.628 5.867 0 29 -10.00 15.205 2.79 0 30 -10.00 15.208 0.00 0 31 10.00 -15.208 0.00 0 • • 32 10.00 -15.205 2.79 0 33 10.00 -14.628 5.867 0 34 10.00 -12.969 8.522 0 35 10.00 -10.458 10.392 0 36 10.00 -6.972 12.05 0 37 10.00 -3.486 13.78 0 38 10.00 0.00 15.493 0 39 10.00 3.486 13.79 0 40 10.00 6.972 12.09 0 41 10.00 10.458 10.392 0 42 10.00 12.969 8.522 0 43 10.00 14.628 5.867 0 44 10.00 15.205 2.79 0 45 10.00 15.208 0.00 0 46 -20.00 -15.208 0.00 0 47 -20.00 -15.205 2.79 0. 48 -20.00 -14.628 5.867 0 49 -20.00 -12.969 8.522 0 50 -20.00 -10.458 10.392 0 51 -20.00 -6.972 12.05 0 52 -20.00 3.486 13.78 0 53 -20.00 0.00 15.493 0 54 -20.00 3.486 13.79 0 55 -20.00 6.972 12.09 0 56 -20.00 10.458 10.392 0 , 57 -20.00 12.969 8.522 0 58 -20.00 14.628 5.867 0 59 -20.00 15.205 2.79 0 60 -20.00 15.208 0.00 0 61 20.00 -15.208 0.00 0 62 20.00 -15.205 2.79 0 63 20.00 -14.628 5.867 0 64 20.00 -12.969 8.522 0 65 20.00 -10.458 10.392 0 66 20.00 -6.972 12.05 0 67 20.00 -3.486 13.78 0 68 20.00 0.00 15.493 0 69 20.00 3.486 13.79 0 70 20.00 6.972 12.09 0 71 20.00 10.458 10.392 0 " 72 20.00 12.969 8.522 0 73 20.00 14.628 5.867 0 74 20.00 15.205 2.79 0 " 75 20.00 '15.208 0.00 0 76 -30.438 -10.816 0.00 0 77 -30.438 -10.816 2.79 0: 78 -30.028 -10.344 5.867 0 79 -28.855 -9.17 8.522 0 80 -27.079 -7.395 10.392 0 81 -24.614 4.93 12.09 0 82 -22.149 -2.465 13.78 0 83 30.438 -10.816 0.00 0 84 30.438 -10.816 2.79 0 85 30.028 -10.344 5.867 0 86 28.855 -9.17 8.522 0 87 27.079 -7.395 10.392 0 88 24.614 -4.93 12.09 0 89 22.149 -2.465 13.78 0 90 -34.892 0.00 0.00 0 91 -34.892 0.00 2.79 0 D-2 Nodes Node X Y Z - Floor . [ft] [ft] [ft] 92 -34.312 --------------------------------------------- 0.00 5.867 0 93 -32.653 0.00 8.522 0 94_ -30.142 0.00 10.392. p 95 -26.656 0.00 12.09 0 96 -23.17 0.00 13.78 0 97 34.892 0.00 0.00 0 98 34.892 0.00 2.79 0 99 34.312 0.00 5.867 0 100 32.653 0.00 8.522 0 r 101 30.142 0.00 10.392 0. : 102 26.656 0.00 12.09 0 103 23.17 0.00 13.78 0 104 -30.438 10.816 0.00 0 105 -30.438 10.816 2.79 0 , 106 -30.028 10.344 5.867 0 ' 107 -28.855 9.171 8.522 0 108 -27.079 7.395 10.392 0 109 -24.614 4.93 12.09 0 110 -22.149 2.465 13.78 0 111 30.438 10.816 0.00 0 ' 112 30.438 10.816 .2.79 0 113 30.028 10.344 5.867 0 114 28.855 9.171 8.522 0 115 27.079 7.395 10.392. 0 - 116 24.614 4.93 12.09 0 117 22.149 2.465 13.78 0 Restraints - Node TX TY TZ RX RY RZ 1 1 --------- -- -- - 1 - - - O - - - O - O 15 1 1 1 0 0 p 16 1 1 1 0 0 0 30 1 1 1 0 0 0 31 1 1 1 0 0 0 45 1 1 1 0 0 0 46 1 1 1 0 0 0 - 60 1 1 1 0 0 0 61 1 1 1 0 0 0 .. 75 1 1 1 0 0 0 ` 76 1 1 1 0 0 0 83 1 1 1 0 0 0 90 1 1 1 0 0 0 97 1 1 1 0 0 0 104 1 1 1 0 0 0 111 1 1 1 0 0 0 f Members Member NJ NK Description Section Material d0 dL Ig factor ------------- ------------------ ---------------- - _ - [in] [in] 1 1 2 - -- - - - ---------------- W SPRUNG4X4 ----- --------- - Aluminum ------ ------ ----------��-- 0.00 0.00 • •0.00 2 2 3 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 3 3 4 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 4 4 5 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 5 5 6 W SPRUNG4X4 Aluminum 0.00' 0.00, 0.00 6 6 7 - W SPRUNG4X4 Aluminum 0.00 0.00 0.00 D-3 Members Member NJ NK Description Section Material d0 dL Ig factor [in] [in] 7 7 8 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 8 8 9 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 9 9 10 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 10 10 -11 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 11 11 12 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 12 12 13 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 13 13 14 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 14 14 15 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 15 16 17 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 16 17 18 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 17 18 19 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 18 19 20 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 19 20 21 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 20 21 22 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 21 22 23 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 22 23 24 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 23 24 25 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 24 25 26 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 25 26 27 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 26 27 28 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 27 28 29 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 28 29 30 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 29 31 32 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 30 32 33 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 31 33 34 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 32 34 35 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 33 35 36 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 34 36 37 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 35 37 38 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 36 38 39 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 37 39 40 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 38 40 41 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 39 41 42 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 40 42 43 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 41 43 44 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 42 44 45 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 43 46 47 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 ' 44 47 48 W SPRUNG4X4 Aluminum 0.00 0.00. 0.00 45 48 49 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 46 49 50 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 47 50 51 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 48 51 52 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 49 52 53 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 50 53 54 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 51 54 55 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 52 55 56 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 53 56 57 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 54 57 58 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 55 58 59 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 56 59 60 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 57 61 62 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 58 62 63 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 59 63 64 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 60 64 65 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 61 65 66 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 62 66 67 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 63 67 68 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 64 68 69 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 65 69 70 W SPRUNG4X4 Aluminum 0.00 0:00 0.00 66 70 71 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 67 71 72 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 68 72 73 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 69 73 74 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 70 74 75 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 71 76 77 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 72 77 78 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 D-4, Members Member NJ NK Description Section Material d0 dL Ig factor [in] [in], 73 78 -- ------------------------------------------------------------------------------------- 79 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 74 79 80 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 75 80 81 W SPRUNG4X4 Aluminum 0.00 0.00. 0.00 76 81 82 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 77 53 82 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 78 83 84 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 79 84 85 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 80 85 86 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 81 86 87 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 82 87 88 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 83 88 89 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 84 68 •89 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 85 90 91 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 86 91 92 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 87 92 93 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 88 93 - 94 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 89 94 95 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 90 95 96 W SPRUNG4X4: Aluminum 0.00 0.00 0.00 91 53 96 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 92 97 98 W SPRUNG4X4 Aluminum 0.00 0.00, 0.00 93 98 99 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 94 99 100 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 95 100 101 W SPRUNG4X4 Aluminum 0.00 0.00. 0.00 96 101 102 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 97 102 103 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 98 68 103 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 99 104 105 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 100 105 106 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 101 106 107 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 102 107 108 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 103 108 109 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 104 109 110 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 105 53 110 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 106 111 112 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 107 112 113 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 108 113 114 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 109 114 115 W SPRUNG4X4 Aluminum 0.00 . " 0.00 0.00 110 115 116 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 • 111 116 117 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 112 68 117 W SPRUNG4X4 Aluminum 0.00 0.00 0.00 113 49 19 T 2.2X2.4 Aluminum 0.00 0.00 0.00 114 19 4 T 2.2X2.4 Aluminum 0.00 0.00 0.00 115 4 34 T 2.2X2.4 Aluminum 0.00 0.00 0.00 116 34 64 T 2.2X2.4 Aluminum 0.00 0.00 0.00 117 64 86 T 2.2X2.4 Aluminum 0.00 0.00 0.00 118 86 100 T 2.2X2.4 Aluminum 0.00 0.00 0.00 119 100 114 T 2.2X2.4 Aluminum 0.00 0.00 0.00 120 114 72 T 2.2X2.4 Aluminum 0.00 0.00 0.00 121 72 42 T 2.2X2.4 Aluminum 0.00 0.00 0.00 122 42 12 T 2.2X2.4 Aluminum 0.00 0.00 0.00 123 12 27 T 2.2X2.4 Aluminum 0.00 0.00 0.00 124 27 57 T 2.2X2.4 Aluminum 0.00 0.00 0.00 125 57 107 T 2:2X2.4 Aluminum 0.00 0.00 0.00 126 107 93 T 2.2X2.4 Aluminum 0.00 0.00 0.00 127 93 79 T 2.2X2.4 Aluminum 0.00 0.00 0.00 128 79 49 T 2.2X2.4 Aluminum 0.00 0.00 0.00 129 51 21 T 2.2X2.4 Aluminum 0.00 0.00 0.00 130 21 6 T 2.2X2.4 Aluminum 0.00 0.00 0.00 131 6 36 T 2.2X2.4 Aluminum 0.00 0.00 0.00 132 36 66 T 2.2X2.4 Aluminum 0.00 0.00 0.00 133 70 40 T 2.2X2.4 Aluminum 0.00 0.00 0.00 134 40 10 T 2.2X2.4 Aluminum 0.00 0.00 0.00 135 10 25 T 2.2X2.4 Aluminum 0.00 0.00 0.00 136 25 55 T 2.2X2.4 Aluminum 0.00 0.00 0.00 137 53 23, T 2.2X2.4 Aluminum 0.00 0.00 0.00 138 23 8 T 2.2X2.4 Aluminum 0.00 0.00 0.00 D-5 Members Member NJ - NK Description Section Material dD dL Ig factor ------------------ [in] [in] 139 8 38 ------------------- T 2.2X2.4 - - - ----------- Aluminum - ---- - 0.00 --- -- 0.00 - - - -- . 0.00 140 38 68 T 2.2X2.4 Aluminum 0.00• 0.00 ' 0.00 Orientation of local axes Member Rotation Axes23 NX NY' NZ " [Deg] 1 - -- -- 180.00 - - - ---------------------------- 0 0.00 0.00 ------ - - - 0.00 - - 2 180.00 0 0.00 0.00 0.00 3 180.00 0 0.00 0.00 0.00 ' 4 180.00 0 0.00 0.00 0.00 5 180.00 0 0.00 0.00 0.00 6 180.00 0 0.00 0.00 0.00 7 180.00 0 0.00 0.00 0.00 15 180.00 0 0.00 0.00 0.00 16 180.00 0. 0.00 0.00 0.00 17 180.00 0 0.00 0.00 0.00 18 180.00 0 0.00 0.00 0.00 19 180.00 0 0.00 0.00 0.00 20 .180.00 0 0.00 0.00 0.00 21 180.00 0 0.00 0.00 0.00 29 180.00 0 0.00 0.00 0.00 ; 30 180.00 0 = 0.00 0.00 0.00 31 180.00 0 0.00 0.00 0.00 32 180.00 0 0.00 0.00 0.00 33 180.00 0 0.00 0.00 0.00 34 180.00 • 0 0.00 0.00 0.00 ' 35 180.00 0 0.00 0.00 0.00 - 43 180.00 0 0.00 0.00 0:00 44 180.00 0 0.00 0.00 0.00 45 180.00 0 0.00 0.00 0.00 46 180.00 0 0.00 0.00 0.00 47 180.00 0 0.00 0.00 0.00 48 180.00 0 0.00 0.00 0.00 ' 49 180.00 0 0.00 0.00 0.00 57 180.00 0 0.00 0.00 0.00 58 180.00 0 0.00 0.00 0.00 59 180.00 0 0.00 0.00 0.00 60 180.00 0 0.00 0.00 0.00 61 180.00 0 0.00 0.00 0.00 62 180.00 0 0.00 0.00 0.00 63 180.00 0 0.00 0.00 0.00 71 135.00 0 0.00 0.00 0.00 •_ , 72 135.00 0 0.00 0.00 0.00 73 - 135.00 0 0.00 0.00 0.00 74 135.00 0 0.00 0.00 0.00 75, 135.00 0 0.00 0.00 0.00 76 135.00 0 0.00 0.00 0.00 77 225.00 0 0.00 0.00 0.00 78 -135.00 0 0.00 0.00 0.00 79 -135.00 0 0.00 0.00 0.00 80 -135.00 0 0.00 0.00 0.00 81 -135.00 0 0.00 0.00 0.00 r 82 -135.00 0 0.00 0.00 0.00 83 -135.00 0• 0.00 0.00 0.00 - 84 135.00 0 0.00 0.00 0.00 85 90.00 0 0.00 0.00 0.00 86 90.00 0 0.00 0.00 0.00 87 90.00 0 0.00 0.00 0.00 88 90.00 0 0.00 0.00 0.00 89 90.00 0 0.00 0.00 0.00 90 90.00 0 ,: 0.00 0.00 0.00 ' D-6 Orientation of local axes Member Rotation Axes23 NX NY NZ [Deg] 91 270.00 --- 0 - 0.00 -- ----------------------------- 0.00 0.00 92 -90.00 0 0.00 0.00 0.00 93 90.00 0 0.00 0.00 0.00 94 -90.00 0 0.00 0.00 0.00 95 -90.00 0 0.00 0.00 0.00 96 -90.00 0 0.00 0.00 _ 0.00 ... ' • 97 -90.00 0 0.00 0.00 0.00 98 90.00 • 0 0.00 0.00 0.00 99 45.00 0 0.00 0.00 0.00 100 45.00 0 0,00 0.00 0.00 101 45.00 0 0.00 0.00 0.00 " 102 45.00 0 0.00 0.00 0.00 ' 103 45.00 0 0.00 0.00 0.00 104 45.00 0 0.00 0.00 0.00 105 315.00 0 0.00 0.00 0.00 106 -45.00 0 0.00 0.00 0.00 107 -45.00 0 0.00 0.00 0.00 108 -45.00 0 0.00 0.00 0.00 y 109 -45.00 0 0.00- 0.00 0.00 ^ 110 -45.00 0 0.00 0.00 0.00 " 111 -45.00 0 0.00 0.00 0.00 112 45.00 0 0.00 0.00 0.00 114 845.00 0 0.00 0.00 0.00 Hinges Node -J Node -K Member TO . M33 M22 V3 V2 M33 M22 V3 V2 4 ,TOR AXL 7 0 0 0 0 0 '' 1. 1 10, 0 0 0 8 0 1 1• 0 0 0 0 0 0 0 0 21 0 0 0 0 0 1 1 0 0 0 0 22 0 1 1 0 0 0 0 0 0 0 0 35 0 0 0 0 0 1 1 0 ,0 0 0 36 0 1 1 0 0 0 0 0 0 0 0, 49 0 0 0 0 0 1- 1 0 0 0 0 r. 50 0 1 1 0 0 0 0 0 0 '" 0 0 63 0 0 0 0, 0 1 1 0 0 0' 0 64 0 1 1 0 0 0 0 0 0 0 "0 84 0 1 1 0 0 0 0 0 0 0 0 91 0 1 1 0 0 0 0 0 0 0 0 112 0 1 1 0 0 0 0 0 0 0 0 113 0 1 1 0 0 1 1 0 0 0 0 114 0 1 1 0 0 1 1 0 0 0 0 115 0 1 1 0 0 1 1 •, 0"^ 0 0 0 116 0 1 1 0 0 1 1 0 0 0 0 ' 117 0 1 1. 0 0 '1 1 0• 0 0 0 118 0 1 1 0 0 1 1 0 0 0 0 119 0 1 1 0 0 1 1 0 0 0 0 120 0 1 F, 1 00 1 1 0' 0 0 0 121 0 1 1 0, .. 0' 1 1 0 0 0 0 122 0 1 1 0 0 1 1 0 0 0 0 123 0 1 1 0 0 1 1 0 0 0 0 124 0 1 1• 0 0 1 1 0 0 0 0 125 0 1 1 0 0 1 1 0 0 0 0 126 0 1 1 0 0 .1 1 0 0 0 0 127 0 1 1 0 0 1 1 0 0 0 0 128 0 - 1 1 0 0 1" 1 0 0 0 0 129 0 1 1 0 0 1 1 0 0 0 0 130 0 1 1 0 0 1 1 .. 0 0 0 0 131 0 1' 1 0, 0 1 1 0 0 0 0 - 132 -0 1 1 0 0. 1 1 0 0 0 0 D-7 Hinges x Node -J Node -K Member TO M33 M22 V3 V2 M33 M22 V3 V2 TOR AXL 133 0 1 1 0 0 1 1 ------------------------------- 0 0 0 0 134 0 1 1 0 0 1 1 0 0 0 0 135 0 1 1 0 0 1 1 .0 0` 0 0 136 0 1 1 0 0 1 1. ;, 0 0 0 0 137 0 1 1 0 0 1 1 0 0 0 0. 138 0 1 1 0 0 1 1 0 0 0 0 139 0 1 1 0 0 1 1 0 0 0 0 140 0 1 1 0 0 1 1 r 0 0 0 0 r • " n D-8 i Fil E-1 E. RAM. RAM International File C:\Documents and Settings\Steven B. Brown\My Documents\Ramadvansedata\Data\madisonclub-30-classic-1.AVW Units system English Date 4/27/2006 4:52:22 PM Analysis Results Translations Translations finl Rotations [Radl Node TX TY TZ RX RY RZ ------------------ ----------------------------------- Condition COM1=I.OSWT+I.1RFLD --- ----------------------- - ------- --- - - - 1 0.00000 0.00000 0.00000 0.00672 -0.00001 0.00000 2 -0.00024 -0.21280 -0.00036 0.00556 -0.00001 0.00000 3 -0.00049 -0.36090 0.02684 0.00217 -0.00001 0.00000 4 -0.00063 -0.36595 0.02934 -0.00178 -0.00001 -0.00001 ' 5 -0.00063 -0.29167 -0.07115 -0.00454 -0.00001 -0.00001 6 -0.00044 -0.18848 -0.28912 -0.00540. -0.00001 -0.00001 7 -0.00021 -0.08392 -0.50066 -0.00458 -0.00001 -0.00001 8 0.00006 0.00137 -0.67495 0.00000 -0.00002 0.00001 9 -0.00026 0.08687 -0.49919 0.00461 -0.00002 0.00002 10 -0.00053 0.18995 -0.28695 0.00540 -0.00002 0.00001 11 -0.00072 0.29527 -0.06972 0.00451 -0.00002 0.00001 12 -0.00068 0.36898 0.02998 0.00176 -0.00001 0.00001 13 -0.00049 0.36320 0.02702 -0.00219 -0.00001 0.00000 , 14 0.00024 0.21382 -0.00036 -0.00559 -0.00001 0.00000 15 0.00000 0.00000 0.00000 -0.00675 -0.00001 0.00000 16 0.00000 0.00000 0.00000 0.00667 ' -0.00001 0.00002 17 -0.00049 -0.21119 -0.00036 0.00552 -0.00001 0.00002 18 -0.00120 -0.35804 0.02655 0.00213 -0.00002 0.00001 19 =0.00203 -0.36234 0.02858 -0.00179 -0.00005 -0.00003 20 -0.00215 -0.28827 -0.07162 -0.00451 -0.00013 -0.00009 21 -0.00042 -0.18610 -0.28745- -0.00533 -. -0.00009 -0.00010 22 0.00214 -0.08298 -0.49609 -0.00452 -0.00009 -0.00011 23 0.00528 0.00105 -0.66781 0.00000 -0.00017 0.00004 24 0.00211 0.08530 -0.49464 0.00455 -0.00012 0.00013 25 -0.00051 0.18695 -0.28533 0.00532 -0.00013 0.00012 26 -0.00224 0.29124 -0.07022 0.00448 -0.00014 0.00010 27 -0.00208 0.36475 0.02922 0.00176 -0.00005 0.00003 28 -0.00118 0.35969 0.02671 -0.00216 -0.00002 -0.00002 29 -0.00046 0.21197 -0.00036 -0.00554 -0.00001 . -0.00003 30 0.00000 0.00000 0.00000 -0.00669 -0.00001 -0.00003 31 0.00000 0.00000 0.00000 0.00667 0.00000 -0.00003 32 0.00000 -0.21118 0.00036 0.00552: 0.00000 -0.00003 33 0.00023 -0.35803 0.02655 0.00213 0.00000 -0.00002 34 0.00076 -0.36234 0.02858' -0.00179 0.00003 0.00002 35 0.00089 -0.28826 -0.07162 -0.00451 0.00010 0.00007 36 -0.00045 -0.18609 -0.28745 -0.00533 0.00007 0.00007 37 -0.00255 -0.08298 -0.49608 -0.00452 0.00007 0.00009 38 -0.00516 0.00105 -0.66780 0.00000 0.00012 -0.00003 39 -0.00262 0.08530 -0.49464 0.00455 0.00009 -0.00010 40 -0.00054 0.18695 -0.28533 0.00532 0.00010 -0.00009 41 0.00081 0.29123 -0.07022 0.00448 0.00010 -0.00008 42 0.00071 0.36475 0.02922 0.00176 0.00003 -0.00002 43 0.00019 0.35969 0.02671 -0.00216 0.00000 0.00002 44 -0.00002 0.21197 -0.00036 -0.00554 0.00000 0.00003 45 0.00000 0.00000 0.00000 -0.00669 0.00000 0.00003 46 0.00000 0.00000 0.00000 0.00141 0.00005 0.00034 47 0.00172 -0.04165 -0.00043: 0.00088 0.00005 0.00034 48 0.00108 -0.04986 0.00065 -0.00051 0.00003 0.00026 49 -0.00342 -0.01361 -0.02242 -0.00161 -0.00022 -0.00011 50 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