Patent US4054254A successfully refreshed from Google Patents.
US4054254A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Rolling airframe autopilot
Assignee: Hughes Missile Systems Co
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Filing: 1975-12-04
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Granted: 1977-10-18
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Expires: 1995-12-04
Abstract
Abstract The autopilot incorporates a single linear accelerometer transducer and a single pitch rate sensor. The outputs of the accelerometer and pitch rate sensor are summed with the command signal in the control circuit. A servo is controlled by the modified control signal to vary the incidence of a single plane control system, in an intentionally rolling airframe.
Inventors
- 👤 Donald E. Cole
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-04 10:46
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/10; G05D1/107; G05D1/108
Claims Analysis
Total Claims: 9
Claim 1
Independent Claim
163 words
An autopilot for an intentionally continuously axially rolling airframe having a pitch angle control system for producing pitch rotation of the airframe in a control plane in response to a rotation related guidance command signal to said control system by a control circuit comprising: an accelerometer means responsive to cyclically varying acceleration for mounting on the airframe and for detecting acceleration in the control plane and transverse to the longitudinal axis of the airframe during the continuous rolling of the airframe as a function of the rotation of said airframe and for producing acceleration signals corresponding to the detected acceleration, acceleration feed-back summer means in the control circuit for summing said acceleration signal and the guidance command signal to produce a control signal, said acceleration signal is summed as a negative feed-back to said guidance command signal, and control system drive means for driving said control system to produce a change in the pitch angle of attack in response to said control signal.
Claim 2
Dependent Claim
163 words
An autopilot for an intentionally continuously axially rolling airframe having a pitch angle control system for producing pitch rotation of the airframe in a control plane in response to a rotation related guidance command signal to said control system by a control circuit comprising: an accelerometer means responsive to cyclically varying acceleration for mounting on the airframe and for detecting acceleration in the control plane and transverse to the longitudinal axis of the airframe during the continuous rolling of the airframe as a function of the rotation of said airframe and for producing acceleration signals corresponding to the detected acceleration, acceleration feed-back summer means in the control circuit for summing said acceleration signal and the guidance command signal to produce a control signal, said acceleration signal is summed as a negative feed-back to said guidance command signal, and control system drive means for driving said control system to produce a change in the pitch angle of attack in response to said control signal.
Claim 3
Dependent Claim
76 words
The autopilot according to claim 1 further comprising: pitch rate sensor means mounted on said airframe for detecting the rate of change of said pitch angle of attack as a function of the rotational orientation of said airframe and for producing an pitch rate signal corresponding to the detected rate, pitch rate damping feed-back summer means in said control circuit for summing said control signal and said pitch rate signal to produce a damped control signal.
Claim 4
Dependent Claim
15 words
The autopilot according to claim 1 wherein: said accelerometer means comprises solid state acceleration sensors.
Claim 5
Dependent Claim
17 words
The autopilot according to claim 1 wherein: said accelerometer means comprises an acceleration sensor in wheatstone bridge.
Claim 6
Dependent Claim
21 words
The autopilot according to claim 1 wherein: said control system drive means comprises a servo motor and variable incidence control surfaces.
Claim 7
Dependent Claim
15 words
The autopilot according to claim 5 wherein: said control surfaces comprise delta planform canard surfaces.
Claim 8
Dependent Claim
22 words
The autopilot according to claim 2 wherein: said pitch rate sensor means comprises a sensor response to a cyclically varying pitch rate.
Claim 9
Dependent Claim
19 words
The autopilot according to claim 7 wherein: said pitch rate sensor means comprises a sensor stabilizer by airframe roll.
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) | 1980-10-17 | 1981-04-18 | 1981-10-18 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1984-10-17 | 1985-04-18 | 1985-10-18 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1988-10-17 | 1989-04-18 | 1989-10-18 | $7700.00 | Window Closed / Lapsed |