Modern Spacecraft Dynamics and Control |
Contents
INTRODUCTION | 1 |
General Equation 13 Motion of the Earths | 17 |
Central Force Motion 29 Keplers Time Equa | 37 |
Copyright | |
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acceleration angular momentum apoapsis apogee applied assumed attitude control attraction bias momentum c₁ center of mass circular orbit components Consider constant control mass control system coordinates corresponding cos² damper damping defined depicted in Figure determine device direction earth eccentricity ellipse energy dissipation equations of motion error expression force gimbal gravity gyro heliocentric hyperbolic I₁ illustrated in Figure impulse inertia initial integration K₁ Kepler's equation kinetic energy km/s linear m₁ M₂ magnitude maneuver method moments of inertia momentum wheel nutation nutation angle obtained orbit normal osculating orbit parameters path periapsis perturbing pitch plane poles polhode position and velocity precession principal axes r₁ rad/s result rigid body roll roll/yaw root locus rotation rotor satellite semimajor axis shown in Figure sin² situation solution spacecraft spin axis stability thrusters torque true anomaly vector vehicle w₁ w₂ zero