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c AGARD-R-800 ADVISORYGROUPFORAEROSPACE RESEARCH &DEVELOPMENT 7 RUE ANCELLE, 92200 NEUILLY-SUR-SEINE, FRANCE AGARD REPORT 800 The Design, Qualification and Maintenance of Vibration-Free Landing Gear (la Conception, la qualification et la maintenance des trains d’atterrissage sans vibration) Papers presented at the 81st Meeting of the AGARD Structures and Materials Panel, held in Banff, Canada 4-5 October 1995. I - North Atlantic Treaty Organization Organisation du Traite de I’Atlantique Nord
Page 1: 336853 AQARD-U-800 A\ T ADVISORY GR
Page 5 and 6: The Design, Qualification and Maint
Page 7 and 8: Contents Executive Summary iii Synt
Page 9 and 10: - - Structures and Materials Panel
Page 11 and 12: It became evident bat the classical
Page 13 and 14: T-4 PAPERS PRESENTED AT "HE WORKSHO
Page 15 and 16: 1-2 were defined by a 2.0g requirem
Page 17 and 18: 1-4 antiskid vibrations from transm
Page 19 and 20: 1-6 Many nonstructural components m
Page 21 and 22: Deck Obstruction Loads High Catapul
Page 23 and 24: 1-10 Front View (a) Main Gear Front
Page 25 and 26: 20 7, 7 X 4 15 w $ f? 10 2 f n 5 10
Page 27 and 28: 1-14 40 -I I 350 k 350 400 k 4 I: w
Page 30 and 31: SUMMARY A review of two different l
Page 32 and 33: 8. y = (IN)*[dy/dt + Wdt - R*da/dt
Page 34 and 35: FIGURE S 3. SENSITIVITY ANALYSIS OF
Page 36 and 37: . . landing gear when the values li
Page 38 and 39: - - - - - In comparing these graphs
Page 40 and 41: - - CD -TIRE LATERAL DAMPING 0 2 4
Page 42 and 43: - - .- SUMMARY Present paper is tre
Page 44 and 45: - . - - 2nd (5 1 .d Hz) vertical be
Page 46 and 47: - -. . - - Ref. 3-2 treats this sub
Page 48 and 49: 3.4 RECOMMENDATIONS AND CONCLUSIONS
Page 50 and 51: . . With APPENDIX Consider a wheel
Page 52 and 53:
. A ....; ...............; ........
Page 54 and 55:
I second BRAKE PRESS& BRAKE TORQUE
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Fig. A-1 AKE RISE TlME BRAKING DRAG
Page 59 and 60:
0-2 0 IO TIME (s) 20 Fig. 2-1 An ex
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4-4 itself able to predict it; 3) b
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4-6 In Fig. 5.1-3 qualitative respo
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4-8 0 0.2 0.4 0.6 0.8 1 vc (dS) 0.2
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4-10 Mod' ieems to L give satis :to
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4-12 model and the brush model (see
Page 72 and 73:
- Summary: Fuselage Vibration Contr
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tems usually require a heavy and co
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control law parameters or some para
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._ The following existing runway Nr
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with J CLRMS = j(iz-Xm) dt (4.6) r,
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Power Spectral Density of Cockpit A
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Dynamic Behaviour of Motorbikes F.
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Figure 1: Ezomples of wheel suspens
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for c: # 0 but kL = 0, we obtain th
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The linear theory, however, does in
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n ~ ~~ Figure 9 Model for ihe mofio
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- - of the wheel together with the
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possible to accomplish a local extr
Page 98 and 99:
- - - - ia 1 LMPUTUDE (lldegree) U.
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etillness factor CR [Nm/deg] U 2 2s
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0.02 0.01 As result there can be co
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_ 2x Example: Contact with plane in
Page 106 and 107:
[Nastg 1) [NYb731 [Pac66] [ Ruf831
Page 108 and 109:
- - LANDING GEAR SHIMMY - DE HAVILL
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the purpose for presenting the abov
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. . Establish standardized terminol
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exception - the tire time constantr
Page 116 and 117:
7-9
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. . . ::-I : : : : i ; : t i ; - :
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Unsteady Tire Dynamics and the Appl
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- : - - o = z0 wi,, (2 - d, q,, + r
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- 8-5 cn W z 0 W r k n w I cn i m 3
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V T- zt 20 zrn bottom dew wheel cen
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I . ‘ V I)R (nose to the right) F
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9-2 Solutions of (3) correspond to
Page 133 and 134:
9-4 3.2 Numerical simulation of fri
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9-6 A second test campaign was perf
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9-8 Fnqwncy mxponurfor Bflsmnt8Xddr
Page 139 and 140:
9-10 10 8 6 4 2 0 -2 40 50 60 70 80
Page 142 and 143:
- - - - SUMMARY A Nonlinear Model f
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UPPER PISTON BEAR LOWER PISTON BEAR
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the lower strut) is ~ c = p { ~pcol
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3. MORELAND POINT-CONTACT TIRE MODE
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UTAW 3.4. Tire Oynamies Summing for
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- .- . ’ modular in design and be
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REPORT DOCUMENTATION PAGE 1. Recipi
Page 158:
NATO -@- OTAN 7 WE AMCELLE S2ZW NEU
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