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General Equation 13 Motion of the Earths
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acceleration angular momentum apoapsis apogee applied assumed attitude control attraction bias momentum calculated center of mass circular orbit components Consider constant control mass control system coordinate corresponding damping defined depicted in Figure despin determined devices direction disturbance torque eccentricity ellipse ellipsoid energy dissipation equations of motion error expression flight force gimbal gravity gyro heliocentric hyperbolic illustrated in Figure impulse initial integration Kepler's equation km/s limit linear lunar magnitude major axis maneuver method moments of inertia momentum wheel nutation nutation angle obtained orbit normal osculating orbit parameters path periapsis permits perturbing pitch plane poles polhode position and velocity precession principal axes rad/s Referring to Figure reorientation result rigid body roll roll/yaw root locus rotor satellite semimajor axis separatrix shown in Figure sin2 situation solution spacecraft spin axis stability technique thrusters torque transfer function transformation true anomaly two-body vector vehicle zero