US3582019A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Rotor for satellite stabilization
Assignee: Individual
•
Filing: 1969-03-24
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Granted: 1971-06-01
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Expires: 1989-03-24
Abstract
Abstract The subject invention relates to a rotor for three-axis stabilization of a passively damped gravity-gradient spacecraft, and more particularly to a rotor for yaw stabilization, yaw-roll decoupling, and libration damping, when used in combination with an energy dissipator, for example, a ball-in-ball damper. The angular momentum vector of the rotor is oriented along the preferred pitch axis of the spacecraft. The motor is utilized to spin the rotor and produce a yaw-controlling reaction torque of the spacecraft and, thereby, to overcome disturbing torques occasioned by thermal bending forces in gravity-gradient stabilizing booms, radiation pressure, residual magnetization and aerodynamic forces.
Inventors
- 👤 Vincent L Pisacane
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-25 15:54
CPC Classifications
B; B64; B64G; B64G1/00; B64G1/22; B64G1/24; B64G1/34; B64G1/28; Y; Y10; Y10T; Y10T74/00; Y10T74/12; Y10T74/1229; Y10T74/1257
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
81 words
In a spacecraft, apparatus for yaw stabilization and libration damping of said spacecraft, comprising rotatable means in the spacecraft which will on rotation produce an angular momentum vector that will be oriented along the preferred pitch axis of the spacecraft, energy dissipative means provided between and joined to said rotatable means and the body of the spacecraft for providing libration damping of said spacecraft, and, means for rotating said first-mentioned means in order to produce yaw-controlling reaction torques on the spacecraft.
Claim 2
Dependent Claim
81 words
In a spacecraft, apparatus for yaw stabilization and libration damping of said spacecraft, comprising rotatable means in the spacecraft which will on rotation produce an angular momentum vector that will be oriented along the preferred pitch axis of the spacecraft, energy dissipative means provided between and joined to said rotatable means and the body of the spacecraft for providing libration damping of said spacecraft, and, means for rotating said first-mentioned means in order to produce yaw-controlling reaction torques on the spacecraft.
Claim 3
Dependent Claim
35 words
The spacecraft stabilization apparatus of claim 1, wherein said rotatable means comprise a rotor of circular dimensions, said rotor having a rim in which is concentrated a large proportion of the weight of said rotor.
Claim 4
Dependent Claim
15 words
The spacecraft stabilization apparatus of claim 1, wherein said energy dissipative means comprise spring means.
Claim 5
Dependent Claim
109 words
Apparatus for three-axis, gravity-gradient stabilization of a passively damped spacecraft comprising a housing fixedly attached to the spacecraft and having opposed walls, a rotor within the housing, the rotor having a rim in which is concentrated a large proportion of the weight of said rotor and further having a central hub, bearing means journaling said central hub for rotatably supporting said rotor, said bearing means being disposed in said opposed walls, energy dissipative means provided between and connected to said rotatable means for providing libration damping of the spacecraft, and a motor operatively connected to the rotor for rotating said rotor to produce yaw-controlling reaction torques on the spacecraft.
Claim 6
Dependent Claim
109 words
Apparatus for three-axis, gravity-gradient stabilization of a passively damped spacecraft comprising a housing fixedly attached to the spacecraft and having opposed walls, a rotor within the housing, the rotor having a rim in which is concentrated a large proportion of the weight of said rotor and further having a central hub, bearing means journaling said central hub for rotatably supporting said rotor, said bearing means being disposed in said opposed walls, energy dissipative means provided between and connected to said rotatable means for providing libration damping of the spacecraft, and a motor operatively connected to the rotor for rotating said rotor to produce yaw-controlling reaction torques on the spacecraft.
References Cited (Backward Citations)
No citation records indexed.
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1974-05-31 | 1974-11-30 | 1975-06-01 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-05-31 | 1978-11-30 | 1979-06-01 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-05-31 | 1982-11-30 | 1983-06-01 | $7700.00 | Window Closed / Lapsed |