"lfk f; \"A Lt. - Airborne Systems

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TABLE 5.4 SUBSONIC WIND TUNNELS Facilty Name Tvpe of Facility Test Section Mach Reynolds Tota' Dynamic Organ lzatio Type of Throat Size Range Number . Temp Pressure Location (ft) (10 /ftJ (psf) AFFDL Vertical Wind Tunnel Wright-Patterson AFB, Ohio Annular return, continuous flow, open throat 12 dia. x 12 Ambient NASA Langley Spin Tunnel Annular return, continuous flow, 25 x 20 Ambiem Hamptofl, Virginia cI osed. th roat NASA Ames Closed circuit Ambient 40. foot by aD. foot Subsonic Wind Tunnel single retu rn cor,tinuous flaw 40 x 80 600 138 Moffett Field, Calif. closed throat NASA Langley Closed circuit, Full Scale Tunnel Hampton , Virginia double return continuous flow, open th roat 30 x 60 x 56 Ambient NASA Langley Closed circuit V/STOL Transition single return, 14.5 x 21.5 x 50 Ambienl Research Wind Tunnel continuous flow, 135 Hampton, Virginia closed th roat NASA Ames Closed circuit, ?-oot by to.foot single return, 7x10x15 Ambient Subsonic Wind Tunnel continuous flow 210 Moffett Field, Calif. closed throat NASA Langley Closed circuit 490 200 High Speed Hoot single return 6 x 9. 6 x 10 by 1 Q.foot Tunnel continuous flow 3.2 620 750 Hamptor , Virginia closed tio.oat NASA Ames Closed circuit, 5CO 12.foot Pressure Tunnel single return 11.3 die. x 1 8 Moffett Field, Calif. variable density, 625 600 closed throat 219
atmospheric wind tunnel Tre test sec:ion is 40 by 80 feet. The tunnel has a contraction ratio of 8 to The air is driven by six 40-fQot-diameter fans, each pQwered bv a 60GO- sepower electric mOlOr. The speed of the Ciirflow though the te5: sectior is can. tinuously variable from zero to the maximum. The tunnel is used primarily for testing the 1:)\1 speed characti'H- istics of hi!;h-performance aircraft and spececraft. and for :esting V/STOL aircraft and rotorcraft. This facility has been found to be particularly useful for researcr-, and ceveloplTent testing of large scale gliding parachutF.s. A conventional upportstrut system and a set of val-iable- height struts are available for stud)lng the effects of ground proximiw. Data a:-e recoded on: Tunrel scale system (digital) 10 channels. Auxil iary data (digital) 480 channels, AnalQg tape 14 channels and redu:ed site with cards read into COTlputer. NASA Langlev Full-Scale Tunnel. This facility, located at Hampton Virginia , i5 continuous flov" dou;)le ret..fn, open throa: t'lpe tunnel. The test section is 30 feet by 60 feet uy 56 feet. Airspeed ral1ge is tram 25 to 110 rnph in 24 step - . A. separlJte speed control is avaih,ble ;)erl1ltting a continuous airspeed variation from C to approxiln1tely 40 mpl1, This facility' is pO\'\ered by an 8000 hp main drive. The tunnel is equipped for free-flight dynamic model studies, and shielded struts are available for model 5..ppon. A reflec(on plane floor 42 feEt wide and 32 feet long can be ins1alled fOI- full scale semi span wi,'lg investigations. Date are recorded with ac chonnels on a data acquisition system and redL.ced off site. This tacilitV can accornodate models up to 40 fOOL win!) span 2nd weighing 15,000 pounds NASA Langley V/STOL Transition Research Wind Tunnel. This is a closeu circuit, single relurn cuntinuous flow atmosphere type V/STOL tLnnel T18 test section is 14. 5 feet high by 21.75 fee: wide by 50 feet long, which can be operated as a closed tU'1nel with slotted walls or a one or more opt!n configurations bV removing the side walls and ceil in9. The speed is variable from 0 to 200 :(110;:5. This tunnel has a con1raction ratio of 9 to 1. The facility is puwered by an 8000 ho main drivE!- This tunnel is capable of force. moment and pressure SLdics of full span and semispan poweced and unpowered 'J/S70L, parawing and grOJnd transport models. A moving be:t ground board wiLh boundary laver suction and variable speed capabil ities fer operation at test section flow velocities can be installed for ground ef1ects t8S:5. A universal model support sysiem uliliL8S a three Joint rotary sling Wilh f:45 pitch of yaw and a pont of vertical traverse. Trlis systern is Ir,oun1ed on hOI'izontal turntable with 220 f:165 of rotation. D3ta are recorded with 60 channels and reduced off site NASA Ames 7- Foot by 10- Foot Subsonic Wind Tunnel. This tunnel is a clo ed circuit, single return atmospheric facL ity powered by. a variable speed 1800 ilP motor wl'dch drives 8 fixed piech fan. The tunnel has a rectangular test sectiof1 7 feet high , 10 feet wide and 15 feet long end a cO'ltraction ratio of 14. 14 to 1 The tunllel is capable of most aerodynamic type test.: , 2-D airfeils . . et flap models and V/STOL models with scaled propt,,sion units. This tunnel can accommodate two-dimensional models spanning the tunnel height with supports at both floor alid ce ling anr:! tf'ree-dillf!nsiOIli!1 illonel, which can be supported by one v'ertical strL t. Continuous angle of attack variation jrorr 0 to :! 180 is avai able. Data am recoeded on t"pes , mechanical y prir ted (6 channels), and the cards are then read into a corn pLrter at the cOllputing e8:1ter. NASA Langley High Speed 7- Foot by 10-FQot Tunnel Th is IS a dosed circuit , si 19le rEturn , continuous fiow, atmospheric type tunnel. The test section is 6. 6 feot wide by 9.6 feet higl1 by 10 feet long. The tunnel is cooled by an air exchange system which introduces filtered atlTosp1eric air into the diffLlser short distance downst'eall from the test section. A series of four turbulence darlping screens of 16-mesh wire is installed in the settlingcharnber. This facility is powered bv a 14 000 hp mai., drive. The facility is Lsed for static and dynamic studies of the aerodynamic characteristics of aircraft and spacecraft. Mod,,1 mounting consists of sling support system, forced oscil.aticn apparatus. and sidewcll rntable Only a limited amount of Dynamic da:a instrumentation is available. Closed circuit television is available for rnc1iitodng tests. NASA Ames 12-Foot Pressure Tunnel. This is a closec' circuit. Gcn:inuous flow, single return , variable density, low turbule1ce tunnel that operates at subsen ie speeds up to sli ghtly less than Mach The w nel tunnel is powered by a two-state , aXial- flow fan driven by electric motors totaling 12,000 horsepower. Arspeed in the test section is contro:l-ed by variation of the rotational speed of tile fan. The test section is 11. 3 feet in diameter and is 18-feet long. Eightfinemesh screens in the settling Cllombcr together with tile large contraction ratio of 25 to 1 provide an air. stream of exceptionally low turbu:ence. The facility is dsed for testing force and moment. pressure , and dvnamic stabilit'. This tunnel is well suited for research on rnissile grounc'-wind loads. An exlerl al bclance and imemal str"j:n-gage balances are
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AFFDL- TR-78-151 IRVIN INDUSTRIES I
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UNCLASSIFIED SECURITY CLASSIFICATIO
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. . . . . . . . . . . . CHAPTE R IN
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. . . . . . . . . . . . . CHAPTER 4
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CHAPTE R 6 (Cont) RELIABILITY Typic
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GURE 1.2 1.4 1.5 1 10 1-1 1 12 1 13
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FIGURE 3.40 3.41 3.42 3.43 3.44 3.4
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FIGURE 6AD 10A 10B . . . . . . . .
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LIST OF ILLUSTRATIONS (Continued) U
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FIGURE 7.45 7.4 7 7.48 7.49 LIST OF
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i'Jz dl.'lI/b"W"O","'"' J! L E 101
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GDA LIST Of SYM BO LS - Area (cross
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ob Mass of Body I ncluded Mass Any
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X-r r/c SYMBOLS (Continued) - Numbe
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Inertial Elasticity Canopy ventilat
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INTRODUCTION Recovery is a term pop
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deceleration stages were possible b
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TABLE B WEIGHTS AND MEASURES Length
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Z, (- y% T AS LE C PROPERTIES OF EA
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TABLE D TYPICAL GROUND WIND VELOCIT
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VEHICLE RECOVERY Vehicle!; that hav
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. . Recovery was initiated with pne
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vehicle enters the continuum flow a
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They "re scheduled to arrive in Dec
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SeparB riot! Entrv Figure 1. T=O Fi
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TABLE 1.1 TECHNICAL DATA OF THE MER
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as lsed 0, the Mercury C:8psule. AI
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Three Main rachut:s Fxtracted by Mo
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Back-up Drogue Chute PIV Steel Cabl
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95 Suspension Lines Number of parac
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Reference 32 suggests certain appli
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chute and slightly decreases the ve
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TABLE 1. S. NAVY PERSONNEL EMERGENC
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pilot chute extraction, independent
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Canopy Inflated Survival Kit Releas
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58 Encapsulated Seat. The 8-58 airc
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300 tOO 'l1j V- C- Stabilization Br
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TABLE 1.8 AIRCRAFT USED FOR AI'DROP
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These requirements have resulted in
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The advantages of the LAPES airdrop
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Con:ainer, Platform Piatform Weight
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defeated the low cost aspect. ::ffo
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, , Figure 26 10. Personnel Troop P
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Design TABLE 1 13 T. 10 PARACHUTE A
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In operation, the a rcraft pilot ma
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ment bag should closely contain the
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' TABLE 1. PARACHUTE SYSTEMS FOR SP
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ORDNANCE The application of aerodyn
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Figure 33 Mark 82 AID Inflation 0 ;
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AERIAL PICKUP Aerial pickup is one
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Figure 34 Trapaze/Helicopter (HH-53
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Main Parachute as Suspension Lines
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Other Mid.air Retrieval Concepts. B
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apid turn rates. and minimal weight
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door of a cradle rrounted platf:rm
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CHAPTER 2 DEPLOYABLE AERODYNAMIC DE
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TABLE . 2. SOLID TEXTILE PARACHUTES
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Type Taja, TU Slots, etc. LeMoigne
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BIAS il BLOCK Figure 2. Flet Patter
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Specific; rdcrcncc data are listed
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.( Con ical. The ca'loPY is constru
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! , Trj. Conical. The canopy is co,
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Full Extended Skirt. The canopy is
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Guide Surface, Ribbed. The canopy i
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Panels ROOF PATTRN X/I1, .70 Y/X 60
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- = Cross. The cross parachute, a F
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Slotted Canopy Parachutes Flat Circ
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Hemisflo. The constructed shape of
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--- Ringsail. This parachute design
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Rotating Parachutes Rotation Df par
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Low G!ide Parachutes gliding paracr
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'" Parawing, Single Keel. Tfe canep
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Parafoil. The canopy is cOlstructed
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DECELERATORS OTHER THAN PARACHUTES
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CHAPTER 3 COMPONENTS AN SU BSYSTEMS
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drogue and starts the timer which o
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alloth r is the pyrotechnic delay t
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that an'! Ai r- Iaunched from a car
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Catapult/Telescoping Thruster. Tele
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Inflation Phase Actuators. Pym/mech
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\()\ \, '.. , i. ,, / " .. $) -' .,
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Figure 18 Cargo Parachute Release 5
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Figure 21 AlP 28S-2 Personnel Harne
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wiDensi on Linlis 'I, Gre;ur.d t_C
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Bridles. A bridle IS :J connectirg
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Sus,GfinsiQn Line Sigh -Sleeve Mout
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Figure 38 Representative Cargo Harn
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, ':"' -." (, ::. :: - , :..' ' , .
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sharp edged corner knifes into the
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compartments or in ex ernal fairing
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from the air , and hydrogen from wa
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ather tran measuring its cross-sect
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tion potential. The first !;::lunll
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(%) TABLE 4. (cont'd) MECHANICAL PR
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'R 1000 800 600 400 200 1000 800 60
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For a hypothetical fabric composed
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TABLE 4. NYLON SEWING THREADS Data
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TABLE 4. THREAD , NYLON , NON MELTI
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Type Iia Iii I'la -1!L VII VIII XII
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Narrow Woven Fabrics. The strength
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111 Yarn: Color: Ident Use: Min. Br
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TABLE 4. 19 POLYESTER WEBBING, IMPR
Page 209 and 210: TABLE 4. 23 (Continued) Dqta horn M
Page 211 and 212: (%) TABLE 4. RAYON TAPE AND WEBBING
Page 213 and 214: (%) TABLE 4 a from MI ranee 260 Cia
Page 215 and 216: Type III Weave: Finish: Use: TABLE
Page 217 and 218: TABLE 4. NYLON DUCK Data from MI L-
Page 219 and 220: yarns. In order to achieve low air
Page 221 and 222: !. Entrapped air in the cells contr
Page 223 and 224: method of joining textiles. Strong,
Page 225 and 226: However. if tile strength of the cl
Page 227 and 228: ;: =::~~~~~~~~~ ::: ::.. "':;.. - -
Page 229 and 230: _._--_.- -------- ---- ------ -----
Page 231 and 232: --- -".. , ;;;" / . ----- ------- -
Page 233 and 234: width sec ion dimensions based on t
Page 235 and 236: and length depend on the type parac
Page 237 and 238: has become cOr/mon practice to x-ra
Page 239 and 240: TEST METHODS AND CAPABILITIES Selec
Page 241 and 242: cescent, drift terden::es, and ethe
Page 243 and 244: supported at other bases including
Page 245 and 246: stant of release, the free-flving p
Page 247 and 248: Figure 5.7 for the same type in wat
Page 249 and 250: Function and Performance Checks. Re
Page 251 and 252: Laboratorv apparatus has been assem
Page 253 and 254: The coeff icient of sl idin g frict
Page 255 and 256: White Sands Misslfe Range Texas Hol
Page 257 and 258: TABLE 5. DECELERATOR TESTING, PRINC
Page 259: allistics tEst tracks and special p
Page 263 and 264: i ng and launching models wh de the
Page 265 and 266: TEST VEHICLES In a free flght test
Page 267 and 268: Load-Searing Platform Paper Honeyco
Page 269 and 270: 338 with an operation has been obta
Page 271 and 272: 1, Central part of housing 2. Upper
Page 273 and 274: to the appl ied stifTl lus. In gene
Page 275 and 276: :ll€thod available is provided by
Page 277 and 278: The different deployrrent methoDs f
Page 279 and 280: a: 30 .. 60 t: 20 18 10 AV6r6ge New
Page 281 and 282: .q:.Q 1.0 002 -- ,. ,. '0. 1.. P (C
Page 283 and 284: 2000 1000 Lbs Force Snatch Farce bp
Page 285 and 286: ,\ )\' ""' Ij, !i!t: a) Opening of
Page 287 and 288: 1.0 HORIZONiAL TRAJECTORY ft H. S.
Page 289 and 290: The Inflation 0 " clustered canopie
Page 291 and 292: "' area across the canopy s the gov
Page 293 and 294: j '" . =: qlide) and ringsail desig
Page 295 and 296: Canopy Type C-9 Canopy Con fig A Sn
Page 297 and 298: si'" 9 Configuration: 9 ConfiglJrti
Page 299 and 300: ::. ::". :::. , " .:.' I I Ii 1! l4
Page 301 and 302: Figure 6, j; 5"O 540 u. :z 12 o 1.
Page 303 and 304: Fioure 27 Opening Force- Time Histo
Page 305 and 306: '" Axial Force Coefficient I t is c
Page 307 and 308: CAo 35 OM-O. a, Degrees Angle of At
Page 309 and 310: . /;. ;. - .'; , . .\. . ~~~ : ;:.
Page 311 and 312:
LID .. .. Hlen Gliding: W"'W FC08(J
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Proiect System Descent Parachute We
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;J = I .. !-- 1// 10. i- ,\;y q.. C
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-.rQ W/. '" 300 '" 2.35 PSF TURN RA
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db == p' Mgr ,, ". .. al Velocity D
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;. ti c: 1). 0.4 C-' -.- --- .. - '
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TABLE 6.9 MID-AIR RETRIEVAL SYSTEM
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three dimensional body ha'Je been s
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;'1 Fig. 6. 55. For a given Mach nU
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CDo 0.4 'siD LJ 0,. 0 1. Ipd 4.70 0
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-- I- l- -2 /:INCR c)-200 lo/in Nyl
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(J f. :' ' - ... . -- ' ;,' ; .; '-
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p. 'e- - - - - - - - - - - - - ven)
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2 0. 0.4 0. REEFING RATIO D,ID Figu
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lengths during deplovment and openi
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(CoSJ o varies with in the same way
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Flar Circular Conical 10'1 Extended
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-2.4 1.6 1.2 -0.4 0.4 0.4 a! Model
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flralleJ and the (-- to X Axis Cent
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a) Tap View of MARS Axis SV5tems OI
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- ----- --- Figure 6. 48 Ft Ribbon
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""' . it -; 1. " _._,.- 0.4 measure
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:9 0. 20. 0.40 Q; O. 10 -0_05 0. -0
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ing points of poIY'TIers , their sp
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2500 (A) Ascent 2000 1500 100 500 I
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Water Impact (Spla$hdown) In a wate
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where is the instantaneous r:eight
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Bag 'Material.NvllJn Cloth! Narsyn
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.. , , ; . '(. ., ' .. . ! '.: \ '
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Human error is more difficult to de
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TABLE 14 8-YEAR SUPPL Y/EQUIPMENT D
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Scale Camp ressibillty Factor Fluid
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"' been unlocked. :he bag offers ve
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() = Drogue Parachute Angle of Atta
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270 180 o - 120 Pe rcent Per See 6
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€ = PI .. velocity of mass added
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e f312JK PICoSJ1I2 (C (CDS! n((CD S
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D fDrii(! Coeffcient For Ul1iform M
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:: . 0. .. Aluminum Canopies fDp 6.
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axial and radial acceleration of th
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Iy in Figs. 7. 14b and c. Inflating
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p, '" '" inflowin9 air is subjected
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Gore Dimensions Warp or Fil Inflate
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The posi tive internal differential
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d) View of Plane A- el View of Plan
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area '" (R/ /2Jf2(J-sin := g., The
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COMPUTE ,,, ASSUME TRIAL CONVERGENC
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Note: ABterisk denote, inPt/f bvana
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at a) Canopy Tension Approach Tsnoe
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_-- "" - .. -.. (fnviscid) Wake Qf
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easonable to use Reynolds and Nusse
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Figure 7. ReD x 10 t: 3. 'V 4.42 .
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= 10. iFf: = 1. 86 x 10 Deg. Deg ,!
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If/db Figure 34 Wake Coefficients v
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A prima ry and obvious limitation o
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tive drag stabilizer because of ii:
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tVa (min- (min. ) . '" M/M .4 . Mr!
Page 425 and 426:
Angle of Atteck Deg S R8 &12 See In
Page 427 and 428:
'" 0.4 Ex"eriment iSSinger Nt) Adju
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Jt (See XI0) e IGz J (3) (4) FPS (6
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point the discharge or tices open.
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FPS K. 10. f( 60 80 100 - Lb Sec/Lb
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they are analogm.. s to the inacleq
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"" usr=d in th 8 computations. The
Page 439 and 440:
desc-ibed in References 285 and 552
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pre-seleCting the final confidence-
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g., system is to be identified. Thi
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'/, too heavy., too bulky or too lo
Page 447 and 448:
t. 14 -- .: Jlten d ed SkI Ffar Cir
Page 449 and 450:
Surface af Revolution: ; -1 Gore La
Page 451 and 452:
TABLE 8.3 SYSTEM A OPENING FORCES (
Page 453 and 454:
'" '" '" "" 156 '" 3 D,IDo 10 (reef
Page 455 and 456:
TABLE 8. RECOMMENDED PARACHUTE DeSI
Page 457 and 458:
adial distance a, ong the surf"ce f
Page 459 and 460:
TABLE 8. STEERABLE PARACHUTE COMPAR
Page 461 and 462:
Portion of canopy Sockiri up Fourth
Page 463 and 464:
followed to create a sequence of ca
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ond /db =" 8. 3/5 7 D /CDt; Appra,s
Page 467 and 468:
I'ne rraterfal required is 18 1583
Page 469 and 470:
Unlock Action Riser Closure Flaps (
Page 471 and 472:
'" "" "" = . where (see Page 344) p
Page 473 and 474:
'), w m.rif 305 Mo' ar weight, m 18
Page 475 and 476:
ecause the le1gth of riser branches
Page 478 and 479:
( .,." ' 727J . ' LIST OF REFEi=ENC
Page 480 and 481:
104 LIST OF REFERENCES (Continued!
Page 482 and 483:
138 141 144 146 147 148 149 150 151
Page 484 and 485:
206 207 208 209 210 Z), 212 213 214
Page 486 and 487:
290 291' 293 294 295 296 297 298 29
Page 488 and 489:
353 354 355 356 357 358 359 364 365
Page 490 and 491:
411 412 413 414 415 416 417 418 419
Page 492 and 493:
463 464 465 466 467 468 469 470 471
Page 494 and 495:
..'- 524 525 526 527 533 534 535 53
Page 496 and 497:
Acceleration Measurement, 232 Actua
Page 498 and 499:
Pressure Distribution , 227 Strain,
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"lfk f; \"A Lt. - Airborne Systems

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