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

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Main Parachute Rotation. Rotation cf single parachute systems is ac::eptable as lon as it does not interfere with proper operation and discQ'inect of the main parachute dL.e to the orientction of the engagr:mEnt parachute load line which require that the aircraft approach from a discrete direcfon 172;'173 Gliding Parachute. In an attsmpt to stabilize the tandem parachute sy terl , tests have been rrade with gliding rr,ain paraerute systems, -his formd the engagement parachute to the rear 0"" the glide path and provided a stable system that could be approached fro 11 the rear (the so-called six 0 ' clock positi on) for engsgement. The problem INlth this aporoach is that gliding parachutp.s have a tendency -:0 turn, and it is difficult to limi: the turn rate to less than 1'V2 degrees per second, the acceptable level for helicopter irtercept. Approach from the rear of th gliding pa' achute system proved to be difficult. The ioad line between the engagement parachute and r1ain pa' achute becomc slack due to the geometry of the descending para:hute system with resultant contact between load line O!nd the helicopter. If the aircraft approached from the front. and the parachute system turned, the aircraft was not ab e to follow the flight path of a strongly tuning parachute systP.rl i: trle ceveloping curved purs'Jit, or engagement from the sij , a difficult maneuver. Minimum Weight and Volume, The weight of retrieval parachutes is inurea ecJ considerably due to the engageml'mt webbing system that is caught by the hook(s) of t")€ aircraft and the riser :1eLwork that guides the engagellent and tow forces into the payload. This is especially true with the tandem system that reClllirp.s a long load Ihe between engagener't paraer-ute and main ;Jcrachute. Parachute Collapse in Helicopter Tow. The large aerodynamit: drag end the flapping motions of collapsed or partially collapsed parachutes in helicopter tow make it impractical to tow parachutes of about more than 45 feet in diameter wit' the available HH-53 and HH- helicoPters. Certain paracnLite ,rpes used as main paracht;tes ha'/e a tendef'cy to partially reinflate ir tow, depending upon how ,me where the parachute was engaged by the aircraft h:Jok. ThE:se problems indicate the desirability of a systerr where the main descent pfJrachute is either completely collapsed or disccnnected after aircraft hook en. gagenent. Mid.air Retrieval Aircraft <strong>Systems</strong>, The Trapeze mid-air retrieval systen- Figure 1. , consists of a luad limiting pO'Nered-winch and associated load .ens. ing ard control equipment, the pickuP poles with mounting arrangement, the pickup cables with engagement hooks and fairings and guides for leading the winch cables. Retrieval gear also incl udes fixtures to assist in boarding nose c:Jnes , instrumented containers and similar equipmert. The model 80-H winch used in the HH- HH-3175 helicopters has a rated capacity of 4COO Ibs with a 50 percent overload capabili:y. The best helicopter engagement speed is approxima:ely 50 to 60 knots. The load control systp.m limi s pickup leads te between 1'h and 2 g s by oaying out the :lic up cable immediately after engagement and reeling the cable in as soo," as 8 steady pull condition is obtained. The JC- 130 ail craft arrangerren:, rigure 1.35, ' similar, but it uses the madel 90 winch with a capacity of 3000 Ibs. Erlg8YBment loads are limited to betweer 3 and 6 g s depending upon payload weigrt and load setting of the winch control system. The poles extenc 28 feet oUtside the airt:raft , are spreacl 20 feet at the end and extend downW8rc 43 degrees and outwad degrees. Tre cables are nylon ropes with six hocks attached, four at the pGles and two in the spcn bet"I'Jeen the poles. Pay-out of tile cables after engagement may extend to 230 feel depending llpon paylD3d weight, engagerr,ent speed and winch load setting. The Fulton mid-air retrieval system uses a yoke attached to the nose of the retrieval aircraft. .6.rms of the Y:JKe are approximately 10 feet long and spread 60 to 90 degrees apart. The pilat flies the yoke inca the cable between paracnute or balloon and p8',rload. A clamping device a t the connection between yoke and the nose of the aircraft snatches the ca:Jle The cable trails back , is hooked by the crew of the a rcraft and transferred :0 the arcraft winch for olJarding or tow. This sys:em hCiS been used suecessfuly for weights up o appro; imately 400 pounds. The bal" loon or parachJte is d"stroyed upon contact. This system s in operation today for the retrieval :!f personrel ard eqJipment with fixed-wing aircraft but it is not suitable for helicopter retrieval. Single Parachute System. This early system was developed in the late fifties and USi:d ill ALgust 1960 176 h the to recover the Diswversr satell ite capsule first successful mid-air retrievfJl. The single desc:mt and engagement paracnute is of a sta ,ciani st8ble ringslot parachute cesigr. The canopy is reinforced with laterO!I arid radial webbings and load lines. Load lines reolace sone of the suspension lines and extend w the connection wi:h the payoad. The retrieval airt engages the canopy witl, its hook-cable system
Figure 34 Trapaze/Helicopter (HH-53) Midair l1etrieva! System Figure 35 JC- 130 Midair Retrieval System
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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
Page 51 and 52: SeparB riot! Entrv Figure 1. T=O Fi
Page 53 and 54: TABLE 1.1 TECHNICAL DATA OF THE MER
Page 55 and 56: as lsed 0, the Mercury C:8psule. AI
Page 57 and 58: Three Main rachut:s Fxtracted by Mo
Page 59 and 60: Back-up Drogue Chute PIV Steel Cabl
Page 61 and 62: 95 Suspension Lines Number of parac
Page 63 and 64: Reference 32 suggests certain appli
Page 65 and 66: chute and slightly decreases the ve
Page 67 and 68: TABLE 1. S. NAVY PERSONNEL EMERGENC
Page 69 and 70: pilot chute extraction, independent
Page 71 and 72: Canopy Inflated Survival Kit Releas
Page 73 and 74: 58 Encapsulated Seat. The 8-58 airc
Page 75 and 76: 300 tOO 'l1j V- C- Stabilization Br
Page 77 and 78: TABLE 1.8 AIRCRAFT USED FOR AI'DROP
Page 79 and 80: These requirements have resulted in
Page 81 and 82: The advantages of the LAPES airdrop
Page 83 and 84: Con:ainer, Platform Piatform Weight
Page 85 and 86: defeated the low cost aspect. ::ffo
Page 87 and 88: , , Figure 26 10. Personnel Troop P
Page 89 and 90: Design TABLE 1 13 T. 10 PARACHUTE A
Page 91 and 92: In operation, the a rcraft pilot ma
Page 93 and 94: ment bag should closely contain the
Page 95 and 96: ' TABLE 1. PARACHUTE SYSTEMS FOR SP
Page 97 and 98: ORDNANCE The application of aerodyn
Page 99 and 100: Figure 33 Mark 82 AID Inflation 0 ;
Page 101: AERIAL PICKUP Aerial pickup is one
Page 105 and 106: Main Parachute as Suspension Lines
Page 107 and 108: Other Mid.air Retrieval Concepts. B
Page 109 and 110: apid turn rates. and minimal weight
Page 111 and 112: door of a cradle rrounted platf:rm
Page 114 and 115: CHAPTER 2 DEPLOYABLE AERODYNAMIC DE
Page 116 and 117: TABLE . 2. SOLID TEXTILE PARACHUTES
Page 118 and 119: Type Taja, TU Slots, etc. LeMoigne
Page 120 and 121: BIAS il BLOCK Figure 2. Flet Patter
Page 122 and 123: Specific; rdcrcncc data are listed
Page 124 and 125: .( Con ical. The ca'loPY is constru
Page 126 and 127: ! , Trj. Conical. The canopy is co,
Page 128 and 129: Full Extended Skirt. The canopy is
Page 130 and 131: Guide Surface, Ribbed. The canopy i
Page 132 and 133: Panels ROOF PATTRN X/I1, .70 Y/X 60
Page 134 and 135: - = Cross. The cross parachute, a F
Page 136 and 137: Slotted Canopy Parachutes Flat Circ
Page 138 and 139: Hemisflo. The constructed shape of
Page 140 and 141: --- Ringsail. This parachute design
Page 142 and 143: Rotating Parachutes Rotation Df par
Page 144 and 145: Low G!ide Parachutes gliding paracr
Page 146 and 147: '" Parawing, Single Keel. Tfe canep
Page 148 and 149: Parafoil. The canopy is cOlstructed
Page 150 and 151: 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
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TABLE 4. 23 (Continued) Dqta horn M
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(%) TABLE 4. RAYON TAPE AND WEBBING
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(%) TABLE 4 a from MI ranee 260 Cia
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Type III Weave: Finish: Use: TABLE
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TABLE 4. NYLON DUCK Data from MI L-
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yarns. In order to achieve low air
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!. Entrapped air in the cells contr
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method of joining textiles. Strong,
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However. if tile strength of the cl
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;: =::~~~~~~~~~ ::: ::.. "':;.. - -
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_._--_.- -------- ---- ------ -----
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--- -".. , ;;;" / . ----- ------- -
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width sec ion dimensions based on t
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and length depend on the type parac
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has become cOr/mon practice to x-ra
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TEST METHODS AND CAPABILITIES Selec
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cescent, drift terden::es, and ethe
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supported at other bases including
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stant of release, the free-flving p
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Figure 5.7 for the same type in wat
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Function and Performance Checks. Re
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Laboratorv apparatus has been assem
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The coeff icient of sl idin g frict
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White Sands Misslfe Range Texas Hol
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TABLE 5. DECELERATOR TESTING, PRINC
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allistics tEst tracks and special p
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atmospheric wind tunnel Tre test se
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i ng and launching models wh de the
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TEST VEHICLES In a free flght test
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Load-Searing Platform Paper Honeyco
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338 with an operation has been obta
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1, Central part of housing 2. Upper
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to the appl ied stifTl lus. In gene
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:ll€thod available is provided by
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The different deployrrent methoDs f
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a: 30 .. 60 t: 20 18 10 AV6r6ge New
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.q:.Q 1.0 002 -- ,. ,. '0. 1.. P (C
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2000 1000 Lbs Force Snatch Farce bp
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,\ )\' ""' Ij, !i!t: a) Opening of
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1.0 HORIZONiAL TRAJECTORY ft H. S.
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The Inflation 0 " clustered canopie
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"' area across the canopy s the gov
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j '" . =: qlide) and ringsail desig
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Canopy Type C-9 Canopy Con fig A Sn
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si'" 9 Configuration: 9 ConfiglJrti
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::. ::". :::. , " .:.' I I Ii 1! l4
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Figure 6, j; 5"O 540 u. :z 12 o 1.
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Fioure 27 Opening Force- Time Histo
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'" Axial Force Coefficient I t is c
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CAo 35 OM-O. a, Degrees Angle of At
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. /;. ;. - .'; , . .\. . ~~~ : ;:.
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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
Page 385 and 386:
D fDrii(! Coeffcient For Ul1iform M
Page 387 and 388:
:: . 0. .. Aluminum Canopies fDp 6.
Page 389 and 390:
axial and radial acceleration of th
Page 391 and 392:
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
Page 419 and 420:
A prima ry and obvious limitation o
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tive drag stabilizer because of ii:
Page 423 and 424:
tVa (min- (min. ) . '" M/M .4 . Mr!
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Angle of Atteck Deg S R8 &12 See In
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'" 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
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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
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t. 14 -- .: Jlten d ed SkI Ffar Cir
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Surface af Revolution: ; -1 Gore La
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TABLE 8.3 SYSTEM A OPENING FORCES (
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'" '" '" "" 156 '" 3 D,IDo 10 (reef
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TABLE 8. RECOMMENDED PARACHUTE DeSI
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adial distance a, ong the surf"ce f
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TABLE 8. STEERABLE PARACHUTE COMPAR
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Portion of canopy Sockiri up Fourth
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followed to create a sequence of ca
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ond /db =" 8. 3/5 7 D /CDt; Appra,s
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I'ne rraterfal required is 18 1583
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Unlock Action Riser Closure Flaps (
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'" "" "" = . where (see Page 344) p
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'), w m.rif 305 Mo' ar weight, m 18
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ecause the le1gth of riser branches
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( .,." ' 727J . ' LIST OF REFEi=ENC
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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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