Patent ID: 6196502
Filing Date: 2001-03-06
Classification: B64G

Abstract:
An attitude control system for a spinning spacecraft comprising:a despun platform in rotational communication with said spacecraft;a momentum control system mounted on said despun platform, said momentum control system, including a gimbal adapted to be mounted on said despun platform, said gimbal having first and second portions respectively pivotable about first and second orthogonal axis;a spinning momentum wheel mounted on said gimbal;a first actuator connected between said first portion of said gimbal and said despun platform for applying a first control moment to said despun platform about said first axis; anda second actuator connected between said second portion of said gimbal and said despun platform for applying a second control moment to said spacecraft about said second axis, said first and second actuators being respectively secured to said first and second portions of said gimbal at locations along said first and second axes respectively to avoid the undesirable application to said spacecraft of unwanted secondary moments being operative to control the attitude of said spacecraft.