|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/169 ; 244/321 ; 244/171|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 12 인용 특허 : 0|
An attitude control system for a space vehicle in which angular rate signals are generated by rate gyros mounted closely adjacent to gimbaled engines at the rear of a vehicle, and wherein error signals representative of a commanded change in vehicle angle or attitude are obtained from a precision inertial platform located in the nose region of the vehicle. The rate gyro derived signals dominate at high frequencies where dynamic effects become significant, and platform signals dominate at low frequencies where precision signals are required for a steady v...
In an attitude control system for a space vehicle including at least one aft mounted and gimbaled motor, a motor gimbal control, the guidance means positioned in the forward region of said vehicle having an inertial reference platform and computing means for computing and providing attitude error signals in terms of a fixed inertial set of axes, the improvement comprising: angular rate sensing means comprising at least one rate gyro fixedly mounted on said vehicle in the aft end region of said vehicle for providing at least one set of rate signals repres...