A technique using a nonlinear helicopter model for determining trims and derivatives
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CALCULATION OF TRIMS AND STABILITY DERIVATIVES
HELICOPTER NONLINEAR MODEL
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aerodynamic angle of attack angular velocity APPENDIX E TABLE body axes Calculated data center of gravity cm-sec collective pitch control derivatives coordinate frame cyclic pitch deg/in deg/m DFUS2 drag coefficient equations eter Unit 40 flapping angle flight forces and moments front rotor front/rear rotor ft 1 ft ft ft ft ft/min FT/SEC helicopter center i/SEC i/SFC knots Figure Langley Research Center LDC/IXX linear model linear perturbation model LV/IXX NDC/IZZ nonlinear model NP/IZZ NR/IZZ 1/SEC OOOOO PHIN rad/sec rear rotor Referenced data rotor drag rotor forces rotor hub Rotor Inflow Ratios rotor wind axes rotor-shaft axes shown in figure side forces sideslip angle stability and control stability derivatives TABLE E2 tandem rotor thrust coefficients trim condition trims and derivatives U.S. Customary Units Vaiue of parameter variables vector vehicle y-axis z-axis