US3977633A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Orientation system for a spin stabilized spacecraft
Assignee: RCA Corp
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Filing: 1975-06-27
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Granted: 1976-08-31
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Expires: 1995-06-27
Abstract
Abstract A pair of reaction motors or thrusters connected to spin-stabilized spacecraft are used to reorient spacecraft attitude without affecting spacecraft velocity. The spacecraft reaction motors are arranged to produce a couple in response to an attitude reference signal without applying a spacecraft velocity changing force to the spin-stabilized spacecraft.
Inventors
- 👤 John Edward Keigler
- 👤 Ludwig Muhlfelder
- 👤 Robert Joseph Cenker
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-25 02:01
CPC Classifications
B; B64; B64G; B64G1/00; B64G1/22; B64G1/24; B64G1/28; B64G1/281; B64G1/26; B64G1/36; B64G1/363
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
155 words
A system for changing attitude of a spin-stabilized vehicle having a spin axis without affecting vehicle velocity comprising: inertial sensing means connected to said vehicle for detecting an inertial point of reference and generating a pulsed signal in response to said detected inertial point of reference; means coupled to said inertial sensing means for generating pulsed vehicle attitude control signals in response to said inertial sensor generated signal; and a pair of coplanar reaction means mounted on said vehicle in a plane parallel to said spin axis and operating in response to said vehicle attitude control signals for applying to said vehicle equal and opposite thrust forces perpendicular to the spin axis of said vehicle and for forming a couple producing a vehicle attitude changing torque perpendicular to the spin axis and being arranged to establish a net thrust force applied to said vehicle of substantially zero magnitude, whereby said vehicle velocity is substantially unaffected.
Claim 2
Independent Claim
155 words
A system for changing attitude of a spin-stabilized vehicle having a spin axis without affecting vehicle velocity comprising: inertial sensing means connected to said vehicle for detecting an inertial point of reference and generating a pulsed signal in response to said detected inertial point of reference; means coupled to said inertial sensing means for generating pulsed vehicle attitude control signals in response to said inertial sensor generated signal; and a pair of coplanar reaction means mounted on said vehicle in a plane parallel to said spin axis and operating in response to said vehicle attitude control signals for applying to said vehicle equal and opposite thrust forces perpendicular to the spin axis of said vehicle and for forming a couple producing a vehicle attitude changing torque perpendicular to the spin axis and being arranged to establish a net thrust force applied to said vehicle of substantially zero magnitude, whereby said vehicle velocity is substantially unaffected.
Claim 3
Dependent Claim
15 words
A system according to claim 1, wherein said inertial sensing means is a sun sensor.
Claim 4
Dependent Claim
40 words
A system according to claim 1, wherein said means for generating pulsed vehicle attitude control signals include logic circuit means coupled to said inertial sensing means, said logic circuit means having a delay circuit coupled to a fire command circuit.
Claim 5
Dependent Claim
37 words
A system according to claim 3, wherein said delay circuit is arranged to generate and transmit fire command signal to said fire command circuit after a predetermined time period in response to said inertial sensor generated signal.
Claim 6
Dependent Claim
25 words
A system according to claim 4, wherein said fire command circuit is arranged to generate a signal determining an operation period for said reaction devices.
References Cited (Backward Citations)
US2974594A
Cited
US3294344A
Cited
US3189299A
Cited
US3384323A
Cited
US3446023A
Cited
US3558078A
Cited
US3490719A
Cited
US3612442A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1979-08-31 | 1980-03-01 | 1980-08-31 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1983-08-31 | 1984-03-01 | 1984-08-31 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1987-08-31 | 1988-03-01 | 1988-08-31 | $7700.00 | Window Closed / Lapsed |