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

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APPENDIX - bsYMmLS The following symbols are used in this analysis: ratio of output amplitude at a given frequency to the output amplitude at zero frequency piston area, sq in. constant constant inertia index (transient response) inertia index (frequency response) low frequency band break frequency, cycles/sec high frequency band break frequency, cycles/sec cross-over frequency, cycle~/sec width of vane, rotary servomotor, in. polar moment of inertia, lb-in. sec2/rad inner radius, rotary servomotor vane, in. outer radius, rotary servomotor vane, in. lomi mass, lb sec2/in. upstream cylinder pressure, lb/sq in. abs downstream cylinder pressure, lb/sq in. abs drain pressure, lb/sq in. abs supply pressure, lb/sq in. abs ratio of valve travel to piston travel at fixed input ratio of valve travel to vane shaft rotation at fixed input, in./rd magnitude of step (measured at output), in. amplitude of output sine wave at zero frequency, in.
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CONTENTS 1, Centering Charauteristi
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CENTERING CHARACTERISTICS OF POWER
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Since pilqt effort and s*face force
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The centering characteristics excep
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-mtla= etlq 30 pwdo o q m ~APA opl
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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
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precisely. The fir at demonstration
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to hare thq coakpit controle comman
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conrtsnt speed). While this ryrtem
Page 35 and 36:
I I SURFACE I AIRCRAFT DYNAMICS LOA
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AUTOMATIC PUT DYNAMICS a LOAD DISTU
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FORCE ME- SERVO. \ - = AMPLIFIER =
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The configuration described above r
Page 43:
AN ANALYSIS OF FULLY-POWERED AIRCRA
Page 46 and 47:
"W@J@tI pendm ao poqtmeard euofenfo
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Ooeo red em;Co* ey tg areqm - a d m
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Variation of Valve Flcnr with Press
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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 99 and 100: The solution to equation (11) , is
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: CHART ILLUSTRATING EFFECT OF INERTI
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.
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