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

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A,. Area of bydraullc jack giston. c, ceJ cn# &S % Parameters In electrical system nrrrlngcrus to bydmullc aystsp! vith compensation. Damping coefficient of mechanical linkages. f~ fn ~~mping coefficient of bydrau~c agrstcm canpamator. c Damping factor in hydraulic systsla loed. pa Bob weight acceleration force. 8 Aoceleratiata of gravity. H(8) Overall system finetion h(s) Denanbator polynomial for H.(B) J(s) *stem function from stick to control 8uriaee. K Gain constant. k Spr3.ng constant of prsh rod from stiok to qydrrulla qpd& kc A-c force spring rate. k e OF1 oompressibility spripg rate. KQ Qnirau3.i~ elyatan control valve gain. k, Spring constent of wraallc qgstam wmpn88tioa nstworlr. =, Velocity constant. 1 Born we-t mss. Msc@anicsl linkage mass. Wp n, Cantrdl column mass. Hc EXfectiw mass of elwator. n, kes of 4pdraul.i~ system ampmeation nstmrk. n &ad factor. P Pressure across hydraulic jack. PI, p2,. . Negative of poles of trandar hnctions. ~[s) Nunrrtrator po- far ~(s). s 6) ~emdnator polyr~~ndal fool opgl loop trandor hmcticm. fa Net rate of flow through bdraulic qpstm aatrol valm. 8 Isplace transform variable t Timb Time Lag from stick to cc4rtirol surface. Tlag U Average f OM airplene velocity. 5 Inpllt to hydsaulic Iaystmn =c Output displacement of maulic qstm. % Valve displaament Control coluaP diaplauenmt ]b Mechanical linkage displaaaernnt.
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-3-a'uo#Su!qs~~ MVN 3Hl 4 0 lN3WlIJ
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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
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Returning to the discussion of the
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loaded by-pass valve closes, and fr
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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
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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
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AN ANALYSIS OF FULLY-POWERED AIRCRA
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"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
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where %, , %+ , fi , and A r' are p
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The error equation (l), with XI * i
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C C U P m ZERO - (Bulk Modulus infi
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Canparing equation (32) vith eqatio
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EFFECT OF ADDRIG A SPEUNC IllbD AT
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The outtmt 4 is then -tion (a) may
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71 It is of interest to anmine the
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It w ill now be shrnm that the quad
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tp = 4 1' ( 4 include. aU flaxibill
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Frequancy Response of Another prore
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or, ii the pinton s p w A, in f ~ t
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$ - BZ~W~ pfY88WC)* - presstam on e
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INTRODUCTION PARAMETERS FOR THE DES
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to the piston. When the spool membe
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Figure 2 shows an oscillographlc re
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lication of equations. - The method
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The solution to equation (11) , is
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I RATIO OF PEAK TRANSIENT CYLINDER
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Equations (21) and (22) are written
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variation of this rise time with T
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CHART ILLUSTRATING EFFECT OF INERTI
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pa lo=$ $8 uoy$eyQd moy pamwam $ndq
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IMPROVEMENT OF POWER SURFACE CONTRO
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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-,
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