Report of the Second Piloted Aircraft Flight Control System - Acgsc.org

More documents

Recommendations

Info

CHART FOR DETERMINATION OF TlME TO REACH 90 PERCENT OF FINAL VALUE. HYDRAULIC SERVOMOTOR WITH MECHANICAL FEED BACK .NO LOAD TlME CONSTANT (TI SEC FIGURE 4 MEASURED AND CALCULATED TRANSIENT RESPONSES OF A HYDRAULIC SERVOMOTOR I 65 - 0 EFFECT OF LWD INERTIA ,-GALCUTLATE! RESTONSE FIGURE 5
The solution to equation (11) , is iB The term Ae is a vector quantity having an' amplitude A and a phase angle fd. From equation (12) High frequency amgUtude attenuation. - At no-load the piston velocity is at all times proportional to the valve opening; therefore in the response to a sinusoidal input at no-load the pilot valve area is zero at the ends of the output travel (the velocity 'being zero). Under an inertia load the piston velocity is not linearly proportional to the pilot valve opening and hence in the response to a sinusoidal input the valve area is not necessarily zero at the ends of the output travel. If at high frequencies, the response of the servomotor is assumed to be essentially sinuaoidal, the maximum acceleration can be considered to occur at the Limits of the output travel and hence when the piston velocity ie zero. Under the condition of negligible mass of the hydraulic fluid, the pressure difference across the piston at any instant when the piston velocity is zero and the pilot valve area is greater than zero, is the pressure difference acrose the servomotor. Above some frequency the system may then be approximated by a Unear system wherein the preseure difference across the piston varies sinurroidally with an amplitude of (P,-P~) and with the frequency of the input. On the baeie of this app~oximetion the acceleration of the piston is Integrating equation (15) and introducing the condition that x varies about zero and neglecting changes in sign
Page 1 and 2:
-3-a'uo#Su!qs~~ MVN 3Hl 4 0 lN3WlIJ
Page 3 and 4:
CONTENTS 1, Centering Charauteristi
Page 5 and 6:
CENTERING CHARACTERISTICS OF POWER
Page 8:
Since pilqt effort and s*face force
Page 14:
The centering characteristics excep
Page 18:
-mtla= etlq 30 pwdo o q m ~APA opl
Page 21 and 22:
HELICOPTER POWERED CONTROL SYSTEM P
Page 23 and 24:
Returning to the discussion of the
Page 25 and 26:
loaded by-pass valve closes, and fr
Page 27 and 28:
FUGET RESEARCH ON FORCE WHEEL CONTR
Page 29 and 30:
precisely. The fir at demonstration
Page 31 and 32:
to hare thq coakpit controle comman
Page 33 and 34:
conrtsnt speed). While this ryrtem
Page 35 and 36:
I I SURFACE I AIRCRAFT DYNAMICS LOA
Page 37 and 38:
AUTOMATIC PUT DYNAMICS a LOAD DISTU
Page 39 and 40:
FORCE ME- SERVO. \ - = AMPLIFIER =
Page 41 and 42:
The configuration described above r
Page 43:
AN ANALYSIS OF FULLY-POWERED AIRCRA
Page 46 and 47: "W@J@tI pendm ao poqtmeard euofenfo
Page 48 and 49: Ooeo red em;Co* ey tg areqm - a d m
Page 50 and 51: Variation of Valve Flcnr with Press
Page 52 and 53: p - instantaneons density (mare per
Page 54 and 55: where %, , %+ , fi , and A r' are p
Page 57 and 58: The error equation (l), with XI * i
Page 61 and 62: C C U P m ZERO - (Bulk Modulus infi
Page 63 and 64: Canparing equation (32) vith eqatio
Page 66 and 67: EFFECT OF ADDRIG A SPEUNC IllbD AT
Page 70: The outtmt 4 is then -tion (a) may
Page 74 and 75: 71 It is of interest to anmine the
Page 77 and 78: It w ill now be shrnm that the quad
Page 79: tp = 4 1' ( 4 include. aU flaxibill
Page 83 and 84: Frequancy Response of Another prore
Page 85 and 86: or, ii the pinton s p w A, in f ~ t
Page 88 and 89: $ - BZ~W~ pfY88WC)* - presstam on e
Page 90 and 91: INTRODUCTION PARAMETERS FOR THE DES
Page 92 and 93: to the piston. When the spool membe
Page 94 and 95: Figure 2 shows an oscillographlc re
Page 96: lication of equations. - The method
Page 101 and 102: I RATIO OF PEAK TRANSIENT CYLINDER
Page 103 and 104: Equations (21) and (22) are written
Page 105 and 106: variation of this rise time with T
Page 107 and 108: CHART ILLUSTRATING EFFECT OF INERTI
Page 109 and 110: pa lo=$ $8 uoy$eyQd moy pamwam $ndq
Page 111 and 112: IMPROVEMENT OF POWER SURFACE CONTRO
Page 113 and 114: FIG. 2 INSTALLATION - POWER OPERATE
Page 115 and 116: AMPLITUDE RATIO- DB I 0 I 0 I cn 0
Page 117 and 118: The overall reaotien rpring rate ir
Page 119 and 120: FIG.5 - SCHEMATIC -- BASIC TYPE POW
Page 122 and 123: With theae substitutions into equat
Page 124: Although only one type of power oon
Page 127 and 128: 0 AMPLITUDE RATIO- D8 I I I I rU rU
Page 129: In the range ai airplane natural fr
Page 132 and 133: Figure 1. anticipation of the targe
Page 134 and 135: The constant k helped to improve th
Page 137 and 138: to determine if there was behaviora
Page 139 and 140: SYNTHESIS OF FLIGHT CONTROL SYSTEMS
Page 145 and 146: The hydraulic system itself is a hi
Page 147:
P :: 7 OT- a- ' 06- 09- . I
Page 150 and 151:
Zeros introduced by resonance of th
Page 152 and 153:
explicit set of specifications-or a
Page 155:
her@ is to lnake the push-rod as st
Page 160:
particular problem. We then choose
Page 164 and 165:
changing flight corditions. Idea-,
Page 166 and 167:
A,. Area of bydraullc jack giston.
show all

Report of the Second Piloted Aircraft Flight Control System - Acgsc.org

You also want an ePaper? Increase the reach of your titles

Delete template?

Save as template?