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

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TABLE 611 8.4 R8A . . ..... . . . . . . - - ....... . . -... . ..... ... . . . . . . . . . ,." . . . . . . . . ............ . .. . .. . .. . . . . . .. . .. , . .. . . ..........., . . , . .. . . , . . ..... . - . . . . . . . . . . .... . . . - . . . .. . . . . LIST OF TABLES (Continued) Parafoil Opening Force Coefficient Dimensional Characteristics. . . . . . Summary of Impact Bag Dynamic Performance Data Year Malfunction Statistics Personnel Drop Record. . . . . Year Supply/Equipment Drop Record. . . Added Air Mass Coefficient of Hollow Shells. . . . . . . . . . - . . . . . . . . . . . . . . . . . . . . . . . .. Sample Calculations for Sizing Main Parachute. . . Effect of Shortened Vent Lines (D o = 0. 101 " System A Opening Forces (Non.Reefed) Permanent Reefing Shape as a Function of No. of Gores. Lead Canopy Worst Case Opening Loads Recommended Parachute Design Factors Requirements. Steerable Parachute Comparison for System D . . - Ribbon Parachute Material Strength .. Material Strength Requirements for Other Than Ribbon Parachutes Pilot Parachute Relative Drag Area Pilot Parachute Performance Constants and for Various Canopy Titles and Canopy Materia Is. Decelerator Pack Densities. . xxii PAGE 299 303 325 329 330 344 404 407 410 411 . 413 415 418 425 425 429 429 1134 . . . . . . . . . . 435
GDA LIST Of SYM BO LS - Area (cross section or frontal) Dimensionless apparent moment of inertia Allowable Strength Factor Aspect Ratio Acceleration Number of blades (autorotor); Volumetric rate of discharge; Added mass coefficient Span or spanwise dimension; Adiabatic recovery factor Coefficient, constant or factor (general) 2 + Aerodynamic Force Coefficient CL Drag Coefficient Cluster Drag Coefficient Drag Coefficient (canopy area Drag Coefficient (projected area Discharge Coefficient Coefficient of friction Lift Coefficient Aerodynamic Moment Coefficient Normal or Side Force Coefficient Pressure Coefficient Radial Force Coefficient Axial Force Coefficient Opening Load Factor Chord or chord-wise dimension; Effective porosity, factor related to suspension line convergence Characteristic Velocity Specific Heat Velocity of Sound Drag Area of Forebody or Vehicle Effective Drag Area Diameter; Drag Design Factor Nominal Diameter of Canopy Projected Inflated Diameter of Canopy '" Diameter of reefing line circle Vent Diameter Nozzle Throat Diameter Young s Modulus of Elasticity Kinetic Energy Euler Number (Plpv (f/f) (4S /1T) Strength 10$s factor (abrasion); Gore width dimension , Material stiffness Width of Gore at Skirt Width of Gore at Vent Length of Gore Chord in Inflated Canopy Force; Structural Load Constant Force; Steady-Stage Drag Limit Load xxv (4S
Page 1 and 2: AFFDL- TR-78-151 IRVIN INDUSTRIES I
Page 3 and 4: UNCLASSIFIED SECURITY CLASSIFICATIO
Page 5 and 6: . . . . . . . . . . . . CHAPTE R IN
Page 7 and 8: . . . . . . . . . . . . . CHAPTER 4
Page 9 and 10: CHAPTE R 6 (Cont) RELIABILITY Typic
Page 11 and 12: GURE 1.2 1.4 1.5 1 10 1-1 1 12 1 13
Page 13 and 14: FIGURE 3.40 3.41 3.42 3.43 3.44 3.4
Page 15 and 16: FIGURE 6AD 10A 10B . . . . . . . .
Page 17 and 18: LIST OF ILLUSTRATIONS (Continued) U
Page 19 and 20: FIGURE 7.45 7.4 7 7.48 7.49 LIST OF
Page 21: i'Jz dl.'lI/b"W"O","'"' J! L E 101
Page 25 and 26: ob Mass of Body I ncluded Mass Any
Page 27 and 28: X-r r/c SYMBOLS (Continued) - Numbe
Page 29 and 30: Inertial Elasticity Canopy ventilat
Page 32 and 33: INTRODUCTION Recovery is a term pop
Page 34 and 35: deceleration stages were possible b
Page 36 and 37: TABLE B WEIGHTS AND MEASURES Length
Page 38 and 39: Z, (- y% T AS LE C PROPERTIES OF EA
Page 40: TABLE D TYPICAL GROUND WIND VELOCIT
Page 43 and 44: VEHICLE RECOVERY Vehicle!; that hav
Page 45 and 46: . . Recovery was initiated with pne
Page 47 and 48: vehicle enters the continuum flow a
Page 49 and 50: 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
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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
Page 89 and 90:
Design TABLE 1 13 T. 10 PARACHUTE A
Page 91 and 92:
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
Page 116 and 117:
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
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
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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
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
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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
Page 162 and 163:
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
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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
Page 217 and 218:
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
Page 227 and 228:
;: =::~~~~~~~~~ ::: ::.. "':;.. - -
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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
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
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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 and 260:
allistics tEst tracks and special p
Page 261 and 262:
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
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
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.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
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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
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
Page 313 and 314:
Proiect System Descent Parachute We
Page 315 and 316:
;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
Page 321 and 322:
;. ti c: 1). 0.4 C-' -.- --- .. - '
Page 323 and 324:
TABLE 6.9 MID-AIR RETRIEVAL SYSTEM
Page 325 and 326:
three dimensional body ha'Je been s
Page 327 and 328:
;'1 Fig. 6. 55. For a given Mach nU
Page 329 and 330:
CDo 0.4 'siD LJ 0,. 0 1. Ipd 4.70 0
Page 331 and 332:
-- I- l- -2 /:INCR c)-200 lo/in Nyl
Page 333 and 334:
(J f. :' ' - ... . -- ' ;,' ; .; '-
Page 335 and 336:
p. 'e- - - - - - - - - - - - - ven)
Page 337 and 338:
2 0. 0.4 0. REEFING RATIO D,ID Figu
Page 339 and 340:
lengths during deplovment and openi
Page 341 and 342:
(CoSJ o varies with in the same way
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Flar Circular Conical 10'1 Extended
Page 345 and 346:
-2.4 1.6 1.2 -0.4 0.4 0.4 a! Model
Page 347 and 348:
flralleJ and the (-- to X Axis Cent
Page 349 and 350:
a) Tap View of MARS Axis SV5tems OI
Page 351 and 352:
- ----- --- Figure 6. 48 Ft Ribbon
Page 353 and 354:
""' . it -; 1. " _._,.- 0.4 measure
Page 355 and 356:
:9 0. 20. 0.40 Q; O. 10 -0_05 0. -0
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ing points of poIY'TIers , their sp
Page 359 and 360:
2500 (A) Ascent 2000 1500 100 500 I
Page 361 and 362:
Water Impact (Spla$hdown) In a wate
Page 363 and 364:
where is the instantaneous r:eight
Page 365 and 366:
Bag 'Material.NvllJn Cloth! Narsyn
Page 367 and 368:
.. , , ; . '(. ., ' .. . ! '.: \ '
Page 369 and 370:
Human error is more difficult to de
Page 371 and 372:
TABLE 14 8-YEAR SUPPL Y/EQUIPMENT D
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Scale Camp ressibillty Factor Fluid
Page 375 and 376:
"' been unlocked. :he bag offers ve
Page 377 and 378:
() = Drogue Parachute Angle of Atta
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270 180 o - 120 Pe rcent Per See 6
Page 381 and 382:
€ = PI .. velocity of mass added
Page 383 and 384:
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
Page 393 and 394:
p, '" '" inflowin9 air is subjected
Page 395 and 396:
Gore Dimensions Warp or Fil Inflate
Page 397 and 398:
The posi tive internal differential
Page 399 and 400:
d) View of Plane A- el View of Plan
Page 401 and 402:
area '" (R/ /2Jf2(J-sin := g., The
Page 403 and 404:
COMPUTE ,,, ASSUME TRIAL CONVERGENC
Page 405 and 406:
Note: ABterisk denote, inPt/f bvana
Page 407 and 408:
at a) Canopy Tension Approach Tsnoe
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_-- "" - .. -.. (fnviscid) Wake Qf
Page 411 and 412:
easonable to use Reynolds and Nusse
Page 413 and 414:
Figure 7. ReD x 10 t: 3. 'V 4.42 .
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= 10. iFf: = 1. 86 x 10 Deg. Deg ,!
Page 417 and 418:
If/db Figure 34 Wake Coefficients v
Page 419 and 420:
A prima ry and obvious limitation o
Page 421 and 422:
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
Page 431 and 432:
point the discharge or tices open.
Page 433 and 434:
FPS K. 10. f( 60 80 100 - Lb Sec/Lb
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they are analogm.. s to the inacleq
Page 437 and 438:
"" 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
Page 445 and 446:
'/, 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
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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
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followed to create a sequence of ca
Page 465 and 466:
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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