Compensated transition for spacecraft attitude control

Details Compensated transition for spacecraft attitude control Compensated transition for spacecraft attitude control

1991-04-02

1993-06-22

Lall, Parshotam S.

Boots, shoes, and leggings

364459, 244170, B64G 138

Patent

active

052220230

ABSTRACT:
An improved method for transitioning a spacecraft from a thruster (5) controlled, station keeping mode to an operational, on-orbit mode, in which attitude control is maintained using internal momentum wheels (3). The method first utilizes a thruster compensation technique to supplement the conventional transition mode control system. This compensation uses empirical thruster data to derate thruster (5) efficiency for extremely short pulse durations necessarily used in transition mode operation. Secondly, a three step deadbeat thruster (5) sequence is employed in which a first pulse linearizes spacecraft (1) motion prior to orienting and stopping nutation. This linearization provides improved accuracy in computing and shortens the waiting time for subsequent thruster (5) firings.

REFERENCES:
patent: 3624367 (1971-11-01), Hamilton
patent: 3643897 (1972-02-01), Johnson, Jr.
patent: 3866025 (1975-02-01), Cavanagh
patent: 3937423 (1976-02-01), Johansen
patent: 3944172 (1976-03-01), Becker
patent: 3984071 (1976-10-01), Fleming
patent: 3997137 (1976-12-01), Phillips
patent: 4023752 (1977-05-01), Pistiner
patent: 4174819 (1979-11-01), Bruderle
patent: 4288051 (1981-09-01), Goschel
patent: 4370716 (1983-01-01), Amieux
patent: 4386750 (1983-06-01), Hoffman
patent: 4504032 (1985-03-01), Phillips et al.
patent: 4521855 (1985-06-01), Lehner
patent: 4537375 (1985-08-01), Chan
patent: 4725024 (1988-02-01), Vorlicek
patent: 4758957 (1988-07-01), Hubert
patent: 4927101 (1990-05-01), Blancke
patent: 4931942 (1990-06-01), Garg
patent: 5098041 (1992-03-01), Uetrecht
Fidelis O. Eke and Estelle M. Eke, "Backup Nutation Damping Strategy For The Galileo Spacecraft", Jun. 21-23, 1989, Proceedings of the 1989 American Control Conference, vol. 3, pp. 2263-2268.
J.S.-C. Yuan, "Deadbeat Nutation Controller for Momentum Bias Stabilized Spacecraft", Jul.-Aug. 1980, Journal Guidance and Control, vol. 3, No. 4, pp. 361-368.

Affiliated with

Also associated with

Rating

Compensated transition for spacecraft attitude control does not yet have a rating. At this time, there are no reviews or comments for this patent.

If you have personal experience with Compensated transition for spacecraft attitude control, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Compensated transition for spacecraft attitude control will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFUS-PAI-O-1444563