A Mathematical Model of a Single Main Rotor Helicopter for ... - Read

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8 . c 2- APPENDIX J CONFIGURATION DESCRIPTION REQUIREMENTS Table J-1 lists the parameters required to describe a helicopter configuration for use in the computer simulation. Listed are the parameter name, algebraic symbol, computer mnemonic, and units for each parameter. In addition, an example value based on an AH-1G is provided for each parameter. AH-1G parameters are based on values in reference 8. 41
TABLE J-1.- CONFIGURATION DESCRIPTION REQUIREMENTS Name Main rotor (MR) group MR rotor radius MR chord MR rotational speed Number of blades MR Lock number MR hinge offset MR flapping spring constant MR pitch-flap coupling tangent of 63 MR blade twist MR precone angle (required for teetering rotor) MR solidity MR lift curve slope MR maximum thrust MR longitudinal shaft tilt (positive forward) MR hub stationline MR hub waterline Tail rotor (TR) group TR radius TR rotational speed TR Lock number TR solidity TR pitch-flap coupling tangent of 63 TR precone TR blade twist TR lift curve slope TR hub stationline TR hub waterline Algebraic CmPuter symbol mnemonic RMR QMR nb YMR E: KB Kl ‘~MR a OMR UMR aMR ‘Tmax iS STAH WLH RTR QTR YTR OTR K 1 ~ ~ a OTR ‘~TR a~~ STAm WLTR 42 ROTOR CHORD OMEGA BLADES GAMMA EPSLN AKBETA AKONE ft ft Units rad/sec N-D N-D percent/100 lb-f t/rad N-D THETT rad AOP rad SIGMA N-D ASLOPE rad’’ CTM N-D CIS rad S TAH in. WLH in. RTR ft OMTR rad 1 sec GAMATR N-D STR N-D FKITR N-D AOTR rad THETR rad ATR rad’’ STATR in. WLTR in. Example value 22 2.25 32.88 2 m 5.216 0 0 0 -0.17453 0.048 0.0651 6.28 0.165 0 200 152.76 4.25 168.44 2.2337 0.105 0.5773 0.02618 0 6.28 520.7 118.27 - -9
Page 1 and 2: 1 \ 1 i I ! t ... NASA Technical Me
Page 3 and 4: I . I CONTENTS SuMMAEtY ...........
Page 5 and 6: 1 2 3 4 B- 1 B-2 D- 1 FIGURES Block
Page 7 and 8: 0 Q p 0 16 9 2 w a, U & 3 4 t4 0 U
Page 9 and 10: summing the contributions, to each
Page 11 and 12: sideslip that will be encountered a
Page 13 and 14: gust levels. For this representatio
Page 15 and 16: damping matrix in flapping differen
Page 17 and 18: 0 Euler pitch angle, rad 00 et A bl
Page 19 and 20: HU B-BODY AIRCRAFT REFERENCE SYSTEM
Page 21 and 22: 1w II 8 2 + - + w 0 N Nlm I n "w (N
Page 23 and 24: 18 c
Page 25 and 26: (-& Q = nb pacR2 (RR) [l + (1 - - (
Page 27 and 28: (B, is defined as zero if VH = UH =
Page 29 and 30: 1 + jJ KlTRblTR - a blm +-- 4 'TR T
Page 31 and 32: This implicit relationship is solve
Page 33 and 34: APPENDIX E EMPENNAGE FORCES AND MOM
Page 35 and 36: The angle iHs is the incidence of t
Page 37 and 38: APPENDIX F CALCULATION OF FUSELAGE
Page 39 and 40: The forces and moments in the body-
Page 41 and 42: It is important to note that the cu
Page 43 and 44: c, = ‘C, (s) The terms CK1 and CK
Page 45: a 8 a m a ma a 0 a m 0. a 3" a m a
Page 49 and 50: Fus pitch moment, a = B = 0 TABLE J
Page 51 and 52: REFERENCES l . 1 . Sinacori, J. B.;

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