Title:
【発明の名称】宇宙機姿勢制御装置用遷移制御システム
Document Type and Number:
Japanese Patent JP2914998
Kind Code:
B2
Abstract:
A method for controlling transition from thruster control to momentum wheel control to minimize nutation angle and transition time in a three-axis stabilized spacecraft employing an internal body fixed-momentum wheel as an attitude stabilizer. The method employs direct, substantially real-time measurement of momentum components and angular rates and generates paired roll thrust impulses and paired yaw thrust impulses in synchronization with the nutation period of the spacecraft to drive the spacecraft to a state of substantially zero nutation. The controller employs a deadbeat principle in a closed-loop real-time feedback system. In a preferred embodiment, the impulsive thruster firing commands in roll and yaw are simultaneous, spaced one-half nutation period apart in time with the effect that the target momentum is achieved in one to three pairs of impulse firings. The invention provides, with minimum transient overshoot, automatic reduction of angular momentum relative to a desired on-orbit state to a level which can be managed by a low-authority momentum wheel controller.
Inventors:
SABUHATSUSHU SHII GAAGU
Application Number:
JP12800489A
Publication Date:
July 05, 1999
Filing Date:
May 23, 1989
Export Citation:
Assignee:
SUPEISU SHISUTEMUZU ROORARU INC
International Classes:
B64G1/24; B64G1/26; B64G1/28; B64G1/38; G05D1/08; G09B9/52; (IPC1-7): B64G1/38; B64G1/28
Domestic Patent References:
| JP51108500A | ||||
| JP5984700A |
Other References:
【文献】米国特許4728062(US,A)
Attorney, Agent or Firm:
Motohiro Kurauchi (1 outside)