科研之友
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摘要
During axial thrusting of a spin-stabilized spacecraft undergoing orbital injections or control maneuvers, misalignments and center of mass offset create undesired body-fixed torques. The effects of the body-fixed torques, which in turn cause velocity pointing errors, can be reduced by ramping up (and then ramping down) the thruster. Closed-form solutions for the angular velocity, Euler angles, inertial velocity, and inertial displacement solutions with nonzero initial conditions are given. Using the closed-form solutions, the effect of variations in the spin axis moment of inertia and spin rate on the spacecraft velocity pointing error are shown. The analytical solutions closely match numerical simulations.
- 出版日期2014-8
