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Patent US3984072A successfully refreshed from Google Patents.
US3984072A
Expired / Lapsed
US
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Attitude control system
Assignee: National Aeronautics and Space Administration
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Filing: 1974-10-02
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Granted: 1976-10-05
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Expires: 1994-10-02
Abstract
Abstract An attitude control system for a space vehicle in which angular rate signals are generated by rate gyros mounted closely adjacent to gimbaled engines at the rear of a vehicle, and wherein error signals representative of a commanded change in vehicle angle or attitude are obtained from a precision inertial platform located in the nose region of the vehicle. The rate gyro derived signals dominate at high frequencies where dynamic effects become significant, and platform signals dominate at low frequencies where precision signals are required for a steady vehicle attitude. The blended signals are applied in a conventional manner to control the gimbaling of vehicle engines about control axes.
Inventors
- 👤 George L. VON Pragenau
- 👤 Charles C. Rupp
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-23 21:37
CPC Classifications
B; B64; B64G; B64G1/00; B64G1/22; B64G1/24; B64G1/28; B64G1/244; B64G1/36; B64G1/369
Claims Analysis
Total Claims: 2
Claim 1
Independent Claim
259 words
In an attitude control system for a space vehicle including at least one aft mounted and gimbaled motor, a motor gimbal control, the guidance means positioned in the forward region of said vehicle having an inertial reference platform and computing means for computing and providing attitude error signals in terms of a fixed inertial set of axes, the improvement comprising: angular rate sensing means comprising at least one rate gyro fixedly mounted on said vehicle in the aft end region of said vehicle for providing at least one set of rate signals representative of the rate of rotation of said vehicle about at least one axis, said rate signals increasing in amplitude with increasing frequency and having a relatively low output at frequencies below the lowest resonance of said vehicle; summing means responsive to attitude error signals from said guidance means and rate signals from said angular rate sensing means for summing said rate signals and said error signals; low-pass filter means responsive to summed signals from said summing means for applying an integrating and attenuating effect to said summed signals above the lowest resonant frequency of said vehicle and providing the control signals to said motor gimbal control; and whereby for conditions of absence of vibrational frequencies higher than said lowest vehicle resonance, said control signals are dominated by attitude error filtered signals from said guidance means, and during the occurrence of vibrational frequencies of a freqency higher than said lowest vehicle resonant frequency, said control signals are dominated by filtered signals derived from said rate sensing means.
Claim 2
Dependent Claim
259 words
In an attitude control system for a space vehicle including at least one aft mounted and gimbaled motor, a motor gimbal control, the guidance means positioned in the forward region of said vehicle having an inertial reference platform and computing means for computing and providing attitude error signals in terms of a fixed inertial set of axes, the improvement comprising: angular rate sensing means comprising at least one rate gyro fixedly mounted on said vehicle in the aft end region of said vehicle for providing at least one set of rate signals representative of the rate of rotation of said vehicle about at least one axis, said rate signals increasing in amplitude with increasing frequency and having a relatively low output at frequencies below the lowest resonance of said vehicle; summing means responsive to attitude error signals from said guidance means and rate signals from said angular rate sensing means for summing said rate signals and said error signals; low-pass filter means responsive to summed signals from said summing means for applying an integrating and attenuating effect to said summed signals above the lowest resonant frequency of said vehicle and providing the control signals to said motor gimbal control; and whereby for conditions of absence of vibrational frequencies higher than said lowest vehicle resonance, said control signals are dominated by attitude error filtered signals from said guidance means, and during the occurrence of vibrational frequencies of a freqency higher than said lowest vehicle resonant frequency, said control signals are dominated by filtered signals derived from said rate sensing means.
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) | 1979-10-05 | 1980-04-05 | 1980-10-05 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1983-10-05 | 1984-04-05 | 1984-10-05 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1987-10-05 | 1988-04-05 | 1988-10-05 | $7700.00 | Window Closed / Lapsed |