Aeronautics and astronautics – Spacecraft – Attitude control
Patent
1974-11-27
1976-02-24
Blix, Trygve M.
Aeronautics and astronautics
Spacecraft
Attitude control
B64G 110
Patent
active
039400964
ABSTRACT:
The orientation maneuver of a bias momentum stabilized spacecraft is achieved without the need of attitude determination by sensors and gyros and the like and without the conventional spin-down and spin-up procedures. The spacecraft is provided with a momentum wheel mounted in perpendicular relation to the axis of maximum moment of inertia. The wheel is initially de-energized during the time the spacecraft is initially launched from the ground launching platform until it is desired to orient the spacecraft in the final orbit. The momentum wheel, when energized from zero rotation to increasing rotation speeds, causes the rotation of the spacecraft from spinning about the maximum moment of inertia axis to an axis parallel to the momentum wheel axis with the final convergence of the wheel axis to the momentum vector being effected by energy dissipation in a nutation damper.
REFERENCES:
patent: 2963243 (1960-12-01), Rothe
patent: 3171612 (1965-03-01), Hildebrant
patent: 3294344 (1966-12-01), Rosen et al.
patent: 3591108 (1971-07-01), Perkel
patent: 3695554 (1972-10-01), Phillips
patent: 3767139 (1973-10-01), Fischell
Keigler John Edward
Muhlfelder Ludwig
Barefoot Galen L.
Blix Trygve M.
Lazar Joseph D.
Norton Edward J.
RCA Corporation
LandOfFree
Re-orientation of a spacecraft relative to its angular momentum does not yet have a rating. At this time, there are no reviews or comments for this patent.
If you have personal experience with Re-orientation of a spacecraft relative to its angular momentum , we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Re-orientation of a spacecraft relative to its angular momentum will most certainly appreciate the feedback.
Profile ID: LFUS-PAI-O-2077073