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

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deceleration stages were possible by depl:ying the parachutes in a temporarily reefed state. The 1960' s and 19-/0' saw the successful <strong>Lt</strong>ilization of aerodY'lamic accelerators to meet the continued challenges of higher velocities, higher altitudes and more complex orerational parameters. This was the result of the broadening of knowledge in engineering and scientific approac' lEs to analyze and Grsoict the performance of oarachutes and other aerodvnamic decelerators. The use of this knowledge manifested itself in the success of soph isticated recovery programs such as the Apollo spacecraft. when the world watched the return ot men tron the Moon. Significant advances in higr-glide , guidable decelerators were made by the introduction of ram-air , airfoil types of "pari;chutes Pilots and aircrew mellbers enjoyed the increased safe:v of reliable, though more complicated emergency escape systems. -he introduction of Kevlar threads, fabrics . and webbings as an alternate for Nylol has opened up new possibilities in the production of stronger ane lighter aerodynaMic decelerators for use wrere exceedingly stringent volume constraints exist. Parachute Data Bank The sources of information used in this Handbook may be found in the List of References. Most Rderanees are available to the public through normal cl-annels from originating aQencies :Jr on request from the Defense Documantation Center (DOC). There were numerous reports rl'Vif;!Vved in the process of composing the Handboo,., which including the references, constitute fI Bibliographv of Iite'8tu' e consid- ered useful on the sub!ect of parachute and recovery. The bibliography is maintained in an up-to-date list. ing as the basic source of information employed in a computerized data storage and retrieval system known as the Parachute Data Bank. The Data Bank currently stores only design details and performance inform at' on extracted from the var:ous bibliographic scurces. A FORTRAN extended program provides ighly flexible anc very selective retrieval of stored cata. Procedures for L. tilization of the D8ta Bank are outlined in Reference 192. The Data Bank will be found most useful on those problems which have can. fr::mted the recovery system designer /investiga tor who needS performance data. The involvement in laborious, haphazard data searches may be greatly reduced. Coordinati on between the Data Bank and various organizations throughout the technical field st"iuld focus attention on more preci e terminologv 8S well as more meaningful data reporting and eventual accession whether of a narrative , numerical, logio:el or tabular nature. xxxv p, Units of Measure Throughout the Handbook, the English units of measure (feet, pounds, seconds) predominate. However, the most commonly used units from botll the English system and from the me:ric system (centimeters, grams, seconds) a 8 listed in Table A with their abbreviations as used throughout the Handbook and the conversion factors for translat: ng values illto units of either system are given in Table B. Earth and Planetary Environments Aerodynamic deceleration devices may be employed over a wide range of altitudes alld Mach nL:m. bers. For greatest effectiveness , they should o:Jerate in a reg' on where the density of the atmosohere is sufficient to produce a positive and continuous resist. ance force. In Earth' s atmosphere, the de1sitY even above 600,000 feet altitLJce will decelerate a relatively large ae'odynamic drag device and alter the traiector,/ of its payload. The atmospheres of Venus and Mars , although different froll Earth's atmosphere have been penetrated with instrunented vehicles using parachutes, and the gravitational forces and the atmospheric properties of these and o:her planets are of interest for recovery purposes. in space "light applications, the effect 07 exposure to long duration ambient vacuum and temperature gradients on a stowed recovery system may be partiol strength loss due to out.gas or aging of some polymeric materials and finishes. PropertiCls of Earth's Atmosphere. The atmosphere as a fluid blanket surroundin;J Earth varies in dellsity. temperature, viscosity and to a small degree, in corn. position according to distance above the surface. The best current estimates of the variation of ztmospheric properties with altitude are given by the 1976 US Standard Atmosptlere Table C sUlllmar izes mean pressure, density, temperature and :he speed of sound as a function of geometric alti1ude, Z. Geometric altitude is tre phY,$:cal distance along the line of force due to gravity which is i: straight radius line at the poles and "t the equa:or, but bends polewsrds as latitude is increased . influenced by the combined effects of gravity and centrifugal force on the atmosphere. Geopotential altitude H, differs in numerical value ta:..ing into account the variation of acceleration due. to gravity. Atmospheric density is expressed in slugs per cubic foct , when a slug is a gravitational udt of mass in the fps system , and a pound force can impart an acceleration of one foot per second per second. At sea level, :he symbol for density equals 0.00237689 Ibs sec , or slugs 1 ft Values in Table C represent an average of the overall relevant data without spatial or temporalvariati ons. Measurements were obtained 568
y a variety of techniques and the accuracy of the data summarized jf' Tab!e C is estimated to be :110 percent. Although inaccruacy incc eases with altitude mean dersi tics have aean generally confirmed by observations. Temporal variatiars of the atmospheric density and density variations with latitude deserve considerations. The variation of ambient temperature with altitude is a significant factor , as is true of all atmospheric paramete,s . the temperature at any specific location and tir'€ may be somewhat different from that given in the table. due, for example , to seasonal and latitudinal variations. The dominating influence upon the temperature is the sun: the in"'ensity and angle of incidence of the sun s raV3 an the su rfacB , and the duration of exposure. Typical ground wind velocities for vanous cit:es the United States are given in Table D as these are Liquid Measure US gallons (gal) liters (I) Mass (Weight, Avoirdupoisl ounces (oz) paunds lib) or (Ibm) grains (gr) tons (t) grams (gm) klograms (kg) Force pounds ;Ib) or (Ibf) Newtons (N) Velocity feet per second (ft/sec) or (fpsJ miles r:er hour (mi/hr) or (mp'") knots (kt) meters per second (m/sec) kilometers per hour (km/hr) TABLE A important factors influencing tre terminal portion of € decelerator operation. Physical Relationships of Planets. Gaseous atmospheres surround the major outer planets, and some of thei r large satell ites. Except for Venus and Mars, densities of Jlanetary atmospheres are un nown although some knowlege exists of gaseous composition through occulation. Table E gives physical relationships of Venus, Mars and Jupiter in terms of Earth data. Applications of recovery incorporation for the purpose of aiding atmospheric penetraton and descent should consider envirO \TTlents in transit as well as the properties of the gaseous media oerformance, Interplanetary vacuum varies from 10- 3 Tor at lunar distance to 10- 23 Tor absolute pressu reo UNITS OF MEASURE Length Measure mil inches (In! feet (ft) yards (yd) miles (mil nautical miles ' nml micron centimeters (em) millimeters (m11) Illeters (m) k ilameters (km) Density pou1ds per cujic inch (lb/in pounds per cubic foot (lb/ft grams per cubic centimeter (gm/cm Cubic Measure cubic inches (cun) or In cubic feet (eu H) or (ft cubic centimeters (cu em) or lem cubic meters (eu rnJ or 11 xxxvi Temperature degrees Fahrenheit ("' F I degrees Kelvin ( degrees Cemigrade ( Pressure pounds per square , neh (lb/in ) or (ICsi) pounds per square foot nb/ft ) or (psfl Acceleration feet per second PI:' second (1t/5e:: meters per second per second (rn/sec Square Measure square inc es (sq in) or On sq uare feet ;sq ft) or (ft square yards (sq yd) or (yd square miles (sq mil or (mi square centi11eters (sq em) or (cm square meters isq 17) or 1m square kilometers (sq km) or (km
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 and 22: i'Jz dl.'lI/b"W"O","'"' J! L E 101
Page 23 and 24: GDA LIST Of SYM BO LS - Area (cross
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 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
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 and 102:
AERIAL PICKUP Aerial pickup is one
Page 103 and 104:
Figure 34 Trapaze/Helicopter (HH-53
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
Page 152 and 153:
CHAPTER 3 COMPONENTS AN SU BSYSTEMS
Page 154 and 155:
drogue and starts the timer which o
Page 156 and 157:
alloth r is the pyrotechnic delay t
Page 158 and 159:
that an'! Ai r- Iaunched from a car
Page 160 and 161:
Catapult/Telescoping Thruster. Tele
Page 162 and 163:
Inflation Phase Actuators. Pym/mech
Page 164 and 165:
\()\ \, '.. , i. ,, / " .. $) -' .,
Page 166 and 167:
Figure 18 Cargo Parachute Release 5
Page 168 and 169:
Figure 21 AlP 28S-2 Personnel Harne
Page 170 and 171:
wiDensi on Linlis 'I, Gre;ur.d t_C
Page 172 and 173:
Bridles. A bridle IS :J connectirg
Page 174 and 175:
Sus,GfinsiQn Line Sigh -Sleeve Mout
Page 176 and 177:
Figure 38 Representative Cargo Harn
Page 178 and 179:
, ':"' -." (, ::. :: - , :..' ' , .
Page 180 and 181:
sharp edged corner knifes into the
Page 182:
compartments or in ex ernal fairing
Page 185 and 186:
from the air , and hydrogen from wa
Page 187 and 188:
ather tran measuring its cross-sect
Page 189 and 190:
tion potential. The first !;::lunll
Page 191 and 192:
(%) TABLE 4. (cont'd) MECHANICAL PR
Page 193 and 194:
'R 1000 800 600 400 200 1000 800 60
Page 195 and 196:
For a hypothetical fabric composed
Page 197 and 198:
TABLE 4. NYLON SEWING THREADS Data
Page 199 and 200:
TABLE 4. THREAD , NYLON , NON MELTI
Page 201 and 202:
Type Iia Iii I'la -1!L VII VIII XII
Page 203 and 204:
Narrow Woven Fabrics. The strength
Page 205 and 206:
111 Yarn: Color: Ident Use: Min. Br
Page 207 and 208:
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 and 260:
allistics tEst tracks and special p
Page 261 and 262:
atmospheric wind tunnel Tre test se
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
Page 313 and 314:
Proiect System Descent Parachute We
Page 315 and 316:
;J = I .. !-- 1// 10. i- ,\;y q.. C
Page 317 and 318:
-.rQ W/. '" 300 '" 2.35 PSF TURN RA
Page 319 and 320:
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
Page 343 and 344:
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
Page 357 and 358:
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
Page 373 and 374:
Scale Camp ressibillty Factor Fluid
Page 375 and 376:
"' been unlocked. :he bag offers ve
Page 377 and 378:
() = Drogue Parachute Angle of Atta
Page 379 and 380:
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
Page 409 and 410:
_-- "" - .. -.. (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 .
Page 415 and 416:
= 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:
Page 423 and 424:
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
Page 429 and 430:
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
Page 435 and 436:
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
Page 441 and 442:
pre-seleCting the final confidence-
Page 443 and 444:
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
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
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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