US5413293A
Expired / Lapsed
US
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Magnetic torque attitude control systems
Assignee: The AT&T MVPD Group LLC
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Filing: 1992-12-22
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Granted: 1995-05-09
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Expires: 2012-12-22
Abstract
Abstract A magnetic torquing system for a spacecraft using conducting coils is disclosed. In one embodiment, the conductors (44, 46) on a spacecraft's (10) solar wing (28, 30) which connect the solar cell strings (38) to the voltage controller (48) are wired to produce a magnetic torque which can be regulated by shunting individual strings to ground (52) or by opening a string circuit. This embodiment does not require the extra weight of a coil because the panel's solar string produces the torque normally produced by an additional coil. In another embodiment, a coil (44, 46)is wired between a shunting switch (54) in the spacecraft voltage controller (48) and a ground (32) so that shunting a string to ground (52) supplies current first to the coil to generate a magnetic torque in the desired direction.
Inventors
- 👤 Louis Gomberg
- 👤 Shibu Basuthakur
- 👤 Joseph H. Hayden
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-07 18:55
CPC Classifications
B; B64; B64G; B64G1/00; B64G1/22; B64G1/42; B64G1/428; B64G1/24; B64G1/32; B64G1/44; B64G1/443
Claims Analysis
Total Claims: 27
Claim 1
Independent Claim
125 words
An attitude control system for a spacecraft having a main body and a solar panel extending from the main body, the solar panel having a plurality of solar cells grouped into strings, each cell being electrically connected to the other cells in its respective string, for generating electric current for use by the spacecraft comprising: an electrically conducting coil having a plurality of conductors coupled to the solar cells for conducting the current generated by the solar cell to the spacecraft main body for use by the spacecraft, each conductor being electrically connected to a different one of the strings, the coil being positioned so as to generate a magnetic field to interact with an external magnetic field for adjusting the attitude of the spacecraft.
Claim 2
Dependent Claim
125 words
An attitude control system for a spacecraft having a main body and a solar panel extending from the main body, the solar panel having a plurality of solar cells grouped into strings, each cell being electrically connected to the other cells in its respective string, for generating electric current for use by the spacecraft comprising: an electrically conducting coil having a plurality of conductors coupled to the solar cells for conducting the current generated by the solar cell to the spacecraft main body for use by the spacecraft, each conductor being electrically connected to a different one of the strings, the coil being positioned so as to generate a magnetic field to interact with an external magnetic field for adjusting the attitude of the spacecraft.
Claim 3
Dependent Claim
26 words
The system of claim 1 further comprising a voltage controller for alternately coupling or decoupling current from the coil to current consuming portions of the spacecraft.
Claim 4
Dependent Claim
38 words
The system of claim 1 wherein the spacecraft center of solar pressure is displaced from the spacecraft center of mass and wherein the coil is adapted to at least partially compensate for attitude disturbances caused by solar pressure.
Claim 5
Dependent Claim
27 words
The system of claim 1 wherein each string has a positive end and a negative end, the conductors being connected across the positive and negative string ends.
Claim 6
Dependent Claim
33 words
The system of claim 4 wherein the conductors are connected and disposed so that at least some of the conductors generate a magnetic field substantially equal and opposite to others of the conductors.
Claim 7
Dependent Claim
31 words
The system of claim 1 further comprising a switch for alternately connecting the solar cell through the coil to a current consuming device on the spacecraft or to a voltage ground.
Claim 8
Dependent Claim
19 words
The system of claim 1 further comprising a switch for alternately breaking the flow of current through the coil.
Claim 9
Dependent Claim
112 words
A spacecraft comprising: a main body; a solar panel extending from the main body, the panel having a plurality of solar cells grouped into strings each cell being electrically connected to the other cells in its respective string for generating electric current an electrically conducting coil having a plurality of conductors coupled to the solar cells for conducting the current generated by the solar cells to the spacecraft main body for use by the spacecraft, each conductor being electrically connected to a different one of the strings, the coil being positioned so as to generate a magnetic field to interact with an external magnetic field for adjusting the attitude of the spacecraft.
Claim 10
Dependent Claim
112 words
A spacecraft comprising: a main body; a solar panel extending from the main body, the panel having a plurality of solar cells grouped into strings each cell being electrically connected to the other cells in its respective string for generating electric current an electrically conducting coil having a plurality of conductors coupled to the solar cells for conducting the current generated by the solar cells to the spacecraft main body for use by the spacecraft, each conductor being electrically connected to a different one of the strings, the coil being positioned so as to generate a magnetic field to interact with an external magnetic field for adjusting the attitude of the spacecraft.
Claim 11
Dependent Claim
21 words
The spacecraft of claim 8 wherein the conductors comprise a loop which extends substantially along the perimeter of the solar panel.
Claim 12
Dependent Claim
16 words
The spacecraft of claim 9 wherein the loop extends substantially along the entire solar panel perimeter.
Claim 13
Dependent Claim
35 words
The spacecraft of claim 9 wherein the solar panel is substantially in the shape of a flat, rectangular surface and wherein the loop is substantially rectangular and proximate the substantially rectangular edge of the panel.
Claim 14
Dependent Claim
33 words
The spacecraft of claim 8 wherein the conductors are connected and disposed so that at least some of the conductors generate a magnetic field substantially equal and opposite to others of the conductors.
Claim 15
Dependent Claim
27 words
The spacecraft of claim 8 further comprising a switch for alternately connecting a conductor to a current consuming device on the spacecraft or to a voltage ground.
Claim 16
Dependent Claim
19 words
The spacecraft of claim 8 further comprising a switch for alternately breaking the flow of current through a conductor.
Claim 17
Dependent Claim
30 words
The spacecraft of claim 8 wherein the spacecraft is adapted to orbit a celestial body and the external magnetic field comprises the magnetic field generated by the orbited celestial body.
Claim 18
Dependent Claim
12 words
The spacecraft of claim 15 wherein the celestial body comprises the earth.
Claim 19
Dependent Claim
26 words
The spacecraft of claim 8 further comprising a voltage controller for alternately coupling or decoupling current from the coil to current consuming portions of the spacecraft.
Claim 20
Dependent Claim
38 words
The spacecraft of claim 8 wherein the spacecraft center of solar pressure is displaced from the spacecraft center of mass and wherein the coil is adapted to at least partially compensate for attitude disturbances caused by solar pressure.
Claim 21
Dependent Claim
27 words
The spacecraft of claim 8 wherein each string has a positive end and a negative end, the conductors being connected across the positive and negative string ends.
Claim 22
Dependent Claim
11 words
The spacecraft of claim 8 wherein the payload comprises communications transponders.
Claim 23
Dependent Claim
134 words
An attitude control system for a spacecraft having a main body and a solar panel extending from the main body, the solar panel having a plurality of solar cell strings independently coupled to the spacecraft power bus for generating electric current for use by the spacecraft, the system comprising: an electrically conducting coil on the solar panel adapted to carry current for generating a magnetic field for interacting with an external magnetic field to adjust the attitude of the spacecraft, the coil being electrically connected to a voltage ground; a power bus controller having a plurality of coil switches for independently shunting current received from each solar cell string to the coil and thereby to the voltage ground for regulating the voltage on the power bus and for controlling the attitude of the spacecraft.
Claim 24
Dependent Claim
134 words
An attitude control system for a spacecraft having a main body and a solar panel extending from the main body, the solar panel having a plurality of solar cell strings independently coupled to the spacecraft power bus for generating electric current for use by the spacecraft, the system comprising: an electrically conducting coil on the solar panel adapted to carry current for generating a magnetic field for interacting with an external magnetic field to adjust the attitude of the spacecraft, the coil being electrically connected to a voltage ground; a power bus controller having a plurality of coil switches for independently shunting current received from each solar cell string to the coil and thereby to the voltage ground for regulating the voltage on the power bus and for controlling the attitude of the spacecraft.
Claim 25
Dependent Claim
33 words
The system of claim 21 further comprising a polarity switch for controlling the direction of current flow through the coil and thereby controlling the orientation of the magnetic field generated by the coil.
Claim 26
Dependent Claim
30 words
The system of claim 21 wherein the power bus controller further comprises a plurality of shunting switches each shunting switch directly coupling a solar cell string to the voltage ground.
Claim 27
Dependent Claim
45 words
The system of claim 23 wherein the coil switches are electrically connected between the solar cell strings and the shunting switches and wherein the coil has a first end electrically connected to the coil switches and a second end electrically connected to the voltage ground.
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) | 1998-05-08 | 1998-11-07 | 1999-05-09 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2002-05-08 | 2002-11-07 | 2003-05-09 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2006-05-08 | 2006-11-07 | 2007-05-09 | $7700.00 | Window Closed / Lapsed |