US4023752A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Elimination of residual spacecraft nutation due to propulsive torques
Assignee: RCA Corp
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Filing: 1975-03-13
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Granted: 1977-05-17
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Expires: 1995-03-13
Abstract
Abstract Spacecraft nutation caused by applying propulsive forces to a spacecraft along an axis which does not pass through the spacecraft's center of gravity is eliminated by a signal responsive control system which operates the propulsive forces for a predetermined time period which corresponds to an integral number of nutation periods.
Inventors
- 👤 Josef Siegfried Pistiner
- 👤 Ludwig Muhlfelder
- 👤 John Edward Keigler
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-26 09:28
CPC Classifications
B; B64; B64G; B64G1/00; B64G1/22; B64G1/24; B64G1/38; B64G1/28; B64G1/281; B64G1/283; B64G1/285
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
125 words
A control system for a spacecraft of the dual-spin type having a spin axis and a characteristic nutation frequency, and further having a platform despun from a spinning member, for eliminating nutation caused by a thrust force not passing through the center of gravity of said spacecraft comprising: receiver means included in said spacecraft for receiving signals transmitted to said spacecraft, and generating in response thereto a receiver means output signal; and force generating means mounted on said platform and coupled to said receiver means and, in response to said receiver output signal, activating said force generating means for an operating time, τ, wherein said force generating means operating time, τ, is: ##EQU6## where n is an integer and ω n is said nutation frequency.
Claim 2
Dependent Claim
125 words
A control system for a spacecraft of the dual-spin type having a spin axis and a characteristic nutation frequency, and further having a platform despun from a spinning member, for eliminating nutation caused by a thrust force not passing through the center of gravity of said spacecraft comprising: receiver means included in said spacecraft for receiving signals transmitted to said spacecraft, and generating in response thereto a receiver means output signal; and force generating means mounted on said platform and coupled to said receiver means and, in response to said receiver output signal, activating said force generating means for an operating time, τ, wherein said force generating means operating time, τ, is: ##EQU6## where n is an integer and ω n is said nutation frequency.
Claim 3
Dependent Claim
24 words
A control system according to claim 1 wherein said force generating means include a signal responsive throttle means for controlling said thrust force magnitude.
Claim 4
Dependent Claim
17 words
A control system according to claim 1 wherein said force generating means includes at least one thruster.
Claim 5
Dependent Claim
148 words
A control system for a spacecraft of the dual-spin type having a spin axis and a characteristic nutation frequency, and further having a platform despun from a spinning member, for eliminating nutation caused by a thrust force not passing through the center of gravity of said spacecraft, comprising: detector means included in said spacecraft for detecting a deviation from a desired spacecraft attitude, and generating in response thereto a detector means output signal; logic means coupled to said detector means and in response to said detector output signal generating a logic output signal; and force generating means mounted on said platform and coupled to said logic means and, in response to said logic control output signal activating said force generating means for an operating period, τ, wherein said force generating means operating period, τ, is: ##EQU7## where n is an integer and ω n is said nutation frequency.
Claim 6
Dependent Claim
148 words
A control system for a spacecraft of the dual-spin type having a spin axis and a characteristic nutation frequency, and further having a platform despun from a spinning member, for eliminating nutation caused by a thrust force not passing through the center of gravity of said spacecraft, comprising: detector means included in said spacecraft for detecting a deviation from a desired spacecraft attitude, and generating in response thereto a detector means output signal; logic means coupled to said detector means and in response to said detector output signal generating a logic output signal; and force generating means mounted on said platform and coupled to said logic means and, in response to said logic control output signal activating said force generating means for an operating period, τ, wherein said force generating means operating period, τ, is: ##EQU7## where n is an integer and ω n is said nutation frequency.
Claim 7
Dependent Claim
24 words
A control system according to claim 4 wherein said force generating means includes a signal responsive throttle means for controlling said thrust force magnitude.
Claim 8
Dependent Claim
17 words
A control system according to claim 4 wherein said force generating means includes at least one thruster.
Claim 9
Independent Claim
120 words
A method for eliminating spacecraft nutation caused by a thrust force not passing through the center of gravity of said spacecraft, in a spacecraft of the dual-spin type having a spin axis and a characteristic nutation period and further having a platform despun from a spinning member, comprising the steps of: transmitting signals to a spacecraft receiver means causing a receiver means output signal; activating a force generating means mounted on said spacecraft in response to said receiver output signal for an operating period, τ; deactivating said force generating means at the end of said operating period, τ, wherein said force generating means operating period, τ, is: ##EQU8## where n is an integer and ω n is said nutation frequency.
Claim 10
Independent Claim
120 words
A method for eliminating spacecraft nutation caused by a thrust force not passing through the center of gravity of said spacecraft, in a spacecraft of the dual-spin type having a spin axis and a characteristic nutation period and further having a platform despun from a spinning member, comprising the steps of: transmitting signals to a spacecraft receiver means causing a receiver means output signal; activating a force generating means mounted on said spacecraft in response to said receiver output signal for an operating period, τ; deactivating said force generating means at the end of said operating period, τ, wherein said force generating means operating period, τ, is: ##EQU8## where n is an integer and ω n is said nutation frequency.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1980-05-16 | 1980-11-15 | 1981-05-17 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1984-05-16 | 1984-11-15 | 1985-05-17 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1988-05-16 | 1988-11-15 | 1989-05-17 | $7700.00 | Window Closed / Lapsed |