Patent US4407469A successfully refreshed from Google Patents.
US4407469A
Expired / Lapsed
US
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Attitude control system for spacecraft utilizing the thruster plume
Assignee: Lockheed Martin Corp
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Filing: 1981-03-31
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Granted: 1983-10-04
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Expires: 2001-03-31
Abstract
Abstract An attitude control system for spacecraft having thrusters utilizes the exhaust plume of the thrusters for attitude control. At least one of the thrusters is canted so that its reaction line of thrust, when misaligned with one of the spacecraft's primary axes; causes a control torque to develop about said axis which aids the plume torque about said axis resulting from the plume of the one thruster impinging on a surface such as that of a solar panel on the spacecraft.
Inventors
- 👤 Stephen M. Fox
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-02 18:55
CPC Classifications
B; B64; B64G; B64G1/00; B64G1/22; B64G1/24; B64G1/26
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
232 words
An attitude control system for a spacecraft of the type having jet type thrusters for orbit adjustment and attitude control maneuvers, a structure having a surface disposed in the thruster exhaust plume of at least one of said thrusters so that said one thruster exhaust plume impinges on said structure to develop a plume torque in a given direction with respect to one of the spacecraft's three primary control axes, hereinafter termed said one axis, to rotate said spacecraft in said given direction about said one axis and so that said one thruster generates a reaction force to develop a control torque about said one axis and a control system for operating said thruster to control the attitude about said one axis or to change the orbit position of said spacecraft, comprising: said one thruster being spaced from the said structure and canted relative to a second of said spacecraft primary axes orthogonal to said one axis, hereinafter termed said second axis, to direct its reaction line of thrust to cross said second axis at said one axis or on the thruster side of said one axis to develop said control torque in only said given direction about said one axis, when said line of thrust does not pass through said one axis, such that the resultant torque about said one axis is caused by said control torque aiding said plume torque.
Claim 2
Dependent Claim
232 words
An attitude control system for a spacecraft of the type having jet type thrusters for orbit adjustment and attitude control maneuvers, a structure having a surface disposed in the thruster exhaust plume of at least one of said thrusters so that said one thruster exhaust plume impinges on said structure to develop a plume torque in a given direction with respect to one of the spacecraft's three primary control axes, hereinafter termed said one axis, to rotate said spacecraft in said given direction about said one axis and so that said one thruster generates a reaction force to develop a control torque about said one axis and a control system for operating said thruster to control the attitude about said one axis or to change the orbit position of said spacecraft, comprising: said one thruster being spaced from the said structure and canted relative to a second of said spacecraft primary axes orthogonal to said one axis, hereinafter termed said second axis, to direct its reaction line of thrust to cross said second axis at said one axis or on the thruster side of said one axis to develop said control torque in only said given direction about said one axis, when said line of thrust does not pass through said one axis, such that the resultant torque about said one axis is caused by said control torque aiding said plume torque.
Claim 3
Dependent Claim
64 words
A system according to claim 1 wherein said one thruster is canted relative to said second axis to generate a reaction line of thrust in a direction that crosses said second axis on the thruster side of said one axis such that said control torque produced by said one thruster has the same sense of rotation as the rotation caused by said plume torque.
Claim 4
Dependent Claim
41 words
A system according to claim 1 wherein said one thruster is canted to generate a reaction line of thrust which passes through the center of mass of said spacecraft, whereby the only torque resulting from said thruster is said plume torque.
Claim 5
Dependent Claim
92 words
A system according to claim 1 wherein said structure is mounted along a given axis parallel to but not coincident with said second axis, and wherein exhaust plumes of a given plurality of said thrusters including said one thruster impinge on the surface of said structure to generate a bias torque in said given direction about said one axis which is transverse to said given axis, and wherein each of said thrusters in said plurality is positioned on said spacecraft so that the respective reaction torques tend to offset said bias torque.
Claim 6
Dependent Claim
53 words
A system according to claim 1 wherein said one thruster is disposed to cause its reaction line of thrust to pass through said one axis of said spacecraft, whereby the control torque produced by said one thruster is zero magnitude so that the only torque resulting from said thruster is said plume torque.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1986-10-03 | 1987-04-04 | 1987-10-04 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1990-10-03 | 1991-04-04 | 1991-10-04 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1994-10-03 | 1995-04-04 | 1995-10-04 | $7700.00 | Window Closed / Lapsed |