US3834653A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Closed loop roll and yaw control for satellites
Assignee: RCA Corp
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Filing: 1972-03-27
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Granted: 1974-09-10
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Expires: 1992-03-27
Abstract
Abstract A magnetic torquing control system for the attitude control of pitch momentum biased satellites utilizing a closed loop for roll-axis control by interacting the satellite''s magnetic dipole with the earth''s magnetic field. The closed-loop system includes a pair of attitude sensors whose output error signals are processed in the satellite-mounted logic circuits to control correcting torques. At a predetermined clock-controlled time or, in response to control or sensing signals from a magnetometer, a torquer such as a magnetic dipole is energized at the position of its satellite''s orbit relative to the magnetic equator to develop a magnetic field which interacts with the magnetic field of the earth to torque, primarily, the roll axis to correct thereby the errors in attitude of the pitch axis.
Inventors
- 👤 H Perkel
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-26 05:39
CPC Classifications
B; B64; B64G; B64G1/00; B64G1/22; B64G1/24; B64G1/36; B64G1/365; B64G1/28; B64G1/281; B64G1/285; B64G1/32; B64G1/366
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
142 words
A magnetic torquing system in a closed-loop system in an orbiting pitch momentum biased satellite for automatically controlling the roll error and yaw error of the satellite, to thereby orient the pitch axis to a desired attitude, said pitch axis being colinear with the momentum vector of the satellite, comprising: a closed loop consisting essentially of: a. roll error sensing means for generating a signal representing a deviation of the roll axis from said desired attitude relative to the pitch axis, b. magnetic torquing means comprising a single magnetic dipole for developing a magnetic torque only along a selected axis of the satellite, and c. means responsive to said roll error signal to energize said magnetic torquing means to correct the deviation of said roll axis to change the orientation of said momentum vector without changing the magnitude of said momentum vector.
Claim 2
Dependent Claim
142 words
A magnetic torquing system in a closed-loop system in an orbiting pitch momentum biased satellite for automatically controlling the roll error and yaw error of the satellite, to thereby orient the pitch axis to a desired attitude, said pitch axis being colinear with the momentum vector of the satellite, comprising: a closed loop consisting essentially of: a. roll error sensing means for generating a signal representing a deviation of the roll axis from said desired attitude relative to the pitch axis, b. magnetic torquing means comprising a single magnetic dipole for developing a magnetic torque only along a selected axis of the satellite, and c. means responsive to said roll error signal to energize said magnetic torquing means to correct the deviation of said roll axis to change the orientation of said momentum vector without changing the magnitude of said momentum vector.
Claim 3
Dependent Claim
37 words
A system according to claim 1 wherein said energizing means includes a clock programmed to generate a signal when said satellite is in a portion of its orbit having significant Magnetic field strength of the earth''s field.
Claim 4
Dependent Claim
43 words
A system according to claim 1 wherein said energizing means includes a magnetometer for sensing the magnetic field of the earth, and means for generating a signal from said magnetometer for energizing said magnetic torquing means to correct deviations in said roll axis.
Claim 5
Dependent Claim
35 words
A system according to claim 1 wherein said energizing means includes means to determine the sense of the magnetic field generated by said torquing means to correspond to the sense of the earth''s magnetic field.
Claim 6
Dependent Claim
42 words
A system according to claim 1 wherein said satellite is of the dual-spin type having a momentum wheel, and said error sensing means comprise a pair of horizon sensors oriented to scan the earth''s surface on opposite sides of the local vertical.
Claim 7
Dependent Claim
29 words
A system according to claim 5 wherein said magnetic torquing means has a major axis which is oriented to be parallel with the spin axis of the momentum wheel.
Claim 8
Dependent Claim
56 words
A system according to claim 5 wherein said satellite is in a geo-synchronous orbit whereby the satellite remains in substantially a fixed position above the earth''s surface on the equatorial plane of the earth, and wherein said magnetic torquing means is oriented in said satellite to be substantially parallel to the roll axis of the satellite.
References Cited (Backward Citations)
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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) | 1977-09-09 | 1978-03-11 | 1978-09-10 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1981-09-09 | 1982-03-11 | 1982-09-10 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1985-09-09 | 1986-03-11 | 1986-09-10 | $7700.00 | Window Closed / Lapsed |