Patent US3591108A successfully refreshed from Google Patents.
US3591108A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Control system for spinning bodies
Assignee: RCA Corp
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Filing: 1967-01-27
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Granted: 1971-07-06
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Expires: 1987-01-27
Abstract
Abstract A control system for reducing undesirable motion in a spinning, orbiting satellite body is disclosed. A satellite having an angular momentum stabilizing system aboard is compensated in a manner to substantially reduce undesired motion about an axis, which may be the spin axis. A motion sensor is placed aboard the satellite to derive a signal proportional to the direction and magnitude of the undesired motion. This signal is used to rotate a flywheel, whose axis of rotation is perpendicular to the spin axis of the satellite. The flywheel is rotated either clockwise or counterclockwise depending on the signal from the motion sensor, causing the flywheel to produce an equal and opposite torque to the disturbing torque about the spacecraft''s spin axis. This action damps out the undesired motion by counteracting the undesired torque.
Inventors
- 👤 Harold Perkel
- 👤 William Herbert Comerford
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-24 22:59
CPC Classifications
B; B64; B64G; B64G1/00; B64G1/22; B64G1/24; B64G1/28; B64G1/285; B64G1/281; B64G1/36; B64G1/38; Y; Y10; Y10T; Y10T74/00; Y10T74/12; Y10T74/1229; Y10T74/1257
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
229 words
An active nutation damper for use on a spacecraft of the type having an angular momentum attitude stabilized wheel comprising in combination, a. a motion sensor having its momentum axis parallel to the axis of said attitude stabilized wheel, said sensor being mounted with said spacecraft to produce a signal related to the nutation motion of said spacecraft about an axis perpendicular to said attitude stabilized axis, b. a flywheel rotatably mounted within said spacecraft on an axis perpendicular to said attitude stabilized axis, c. first means responsive to said signal to provide a second signal related to the direction of said nutation motion, d. second means coupled to said first means and to said flywheel and responsive to said second signal for driving said flywheel in a direction dependent on the direction of said nutation motion to produce a torque about said stabilized axis to decrease said nutation motion whatever be the direction of said motion, wherein said first means is a first and second threshholding device, said first device being designed to trigger when said nutation motion is in the positive direction and said second device being designed to trigger when said nutation motion is in the negative directions, means for connecting said second means to said first and second devices to operate said flywheel in response to the triggering of said devices to produce said torque.
Claim 2
Dependent Claim
229 words
An active nutation damper for use on a spacecraft of the type having an angular momentum attitude stabilized wheel comprising in combination, a. a motion sensor having its momentum axis parallel to the axis of said attitude stabilized wheel, said sensor being mounted with said spacecraft to produce a signal related to the nutation motion of said spacecraft about an axis perpendicular to said attitude stabilized axis, b. a flywheel rotatably mounted within said spacecraft on an axis perpendicular to said attitude stabilized axis, c. first means responsive to said signal to provide a second signal related to the direction of said nutation motion, d. second means coupled to said first means and to said flywheel and responsive to said second signal for driving said flywheel in a direction dependent on the direction of said nutation motion to produce a torque about said stabilized axis to decrease said nutation motion whatever be the direction of said motion, wherein said first means is a first and second threshholding device, said first device being designed to trigger when said nutation motion is in the positive direction and said second device being designed to trigger when said nutation motion is in the negative directions, means for connecting said second means to said first and second devices to operate said flywheel in response to the triggering of said devices to produce said torque.
Claim 3
Dependent Claim
180 words
An active nutation damper for a spinning spacecraft, comprising, a. a motion sensor within said spacecraft and mounted to provide a signal related to the sense of nutation motion of said spacecraft in a plane perpendicular to said spin axis, b. a first threshold device coupled to said sensor to produce a first output when said signal indicates a positive sense of nutation, c. a second threshold device coupled to said sensor to produce a second output when said signal indicates a negative sense of nutation, d. first means coupled to said first and second threshold devices to provide a composite control signal derived from said first and second outputs, e. a flywheel rotatably mounted within said spacecraft and having its axis of rotation perpendicular to said spin axis and parallel to said plane, f. driving means, including a motor, coupled between said first means and said flywheel and responsive to said composite signal to drive said flywheel in either of two directions determined by said composite signal to produce a torque about said spin axis reducing said nutation motion.
Claim 4
Dependent Claim
180 words
An active nutation damper for a spinning spacecraft, comprising, a. a motion sensor within said spacecraft and mounted to provide a signal related to the sense of nutation motion of said spacecraft in a plane perpendicular to said spin axis, b. a first threshold device coupled to said sensor to produce a first output when said signal indicates a positive sense of nutation, c. a second threshold device coupled to said sensor to produce a second output when said signal indicates a negative sense of nutation, d. first means coupled to said first and second threshold devices to provide a composite control signal derived from said first and second outputs, e. a flywheel rotatably mounted within said spacecraft and having its axis of rotation perpendicular to said spin axis and parallel to said plane, f. driving means, including a motor, coupled between said first means and said flywheel and responsive to said composite signal to drive said flywheel in either of two directions determined by said composite signal to produce a torque about said spin axis reducing said nutation motion.
Claim 5
Dependent Claim
259 words
An active nutation damper for a spin stabilized spacecraft, comprising, a. a motion sensor within said spacecraft and mounted to provide a signal related to the sense of nutation motion of said spacecraft in a plane perpendicular to said spin axis, b. a first threshold device coupled to said sensor to produce a first output when said signal indicates one direction of nutation, c. a second threshold device coupled to said sensor to produce a second output when said signal indicates a different direction of nutation, d. first means coupled to said first and second threshold devices to provide a composite control signal derived from said first and second outputs, e. a flywheel rotatably mounted within said spacecraft and having iTs axis of rotation perpendicular to said spin axis and parallel to said plane, f. driving means coupled between said first means and said flywheel and responsive to said composite signal to drive said flywheel according to the magnitude of said composite signal, said driving means further disposed to be always responsive to said composite signal''s portion due to said first one threshold circuit to reduce said nutation motion in said one direction, g. direction reversal means coupled to said driving means and said second threshold device to cause said driving means to reverse the direction of said flywheel when said second threshold device produces its output enabling said driving means to be responsive to that portion of said composite signal due to said second threshold output devices to reduce said nutation motion in said negative sense of direction.
Claim 6
Dependent Claim
259 words
An active nutation damper for a spin stabilized spacecraft, comprising, a. a motion sensor within said spacecraft and mounted to provide a signal related to the sense of nutation motion of said spacecraft in a plane perpendicular to said spin axis, b. a first threshold device coupled to said sensor to produce a first output when said signal indicates one direction of nutation, c. a second threshold device coupled to said sensor to produce a second output when said signal indicates a different direction of nutation, d. first means coupled to said first and second threshold devices to provide a composite control signal derived from said first and second outputs, e. a flywheel rotatably mounted within said spacecraft and having iTs axis of rotation perpendicular to said spin axis and parallel to said plane, f. driving means coupled between said first means and said flywheel and responsive to said composite signal to drive said flywheel according to the magnitude of said composite signal, said driving means further disposed to be always responsive to said composite signal''s portion due to said first one threshold circuit to reduce said nutation motion in said one direction, g. direction reversal means coupled to said driving means and said second threshold device to cause said driving means to reverse the direction of said flywheel when said second threshold device produces its output enabling said driving means to be responsive to that portion of said composite signal due to said second threshold output devices to reduce said nutation motion in said negative sense of direction.
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) | 1974-07-05 | 1975-01-04 | 1975-07-06 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-07-05 | 1979-01-04 | 1979-07-06 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-07-05 | 1983-01-04 | 1983-07-06 | $7700.00 | Window Closed / Lapsed |