Patent US4396878A successfully refreshed from Google Patents.
US4396878A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Body referenced gimballed sensor system
Assignee: Hughes Missile Systems Co
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Filing: 1981-07-13
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Granted: 1983-08-02
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Expires: 2001-07-13
Abstract
Abstract A system for proportionally navigating an airframe to a target wherein the airframe is maneuvered by an onboard flight control system including body rate gyros for detecting the movement of the airframe relative to a fixed reference. A target sensor is mounted for pivotal movement in the pitch and yaw planes on a gimbal assembly rigidly connected to the airframe body. Mechanisms, such as motor/tachometer/potentiometer assemblies, pivot the sensor in the pitch and yaw planes and provide signals representative of the angular rate of motion and angular position of the sensor. These signals, along with the sensor output, are utilized in a gimbal track loop for pivoting the sensor so that it tracks the target. The outputs of the body rate gyros are utilized to remove or decouple the airframe body motion from the gimbal track loop signal. The system eliminates the need for a costly and complex space stabilized gimballed sensor while offering improved performance over a system utilizing a pure body fixed sensor.
Inventors
- 👤 Donald E. Cole
- 👤 John M. Speicher
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 09:33
CPC Classifications
F; F41; F41G; F41G7/00; F41G7/20; F41G7/22; F41G7/2213; F42; F42B; F42B30/00; F42B30/006; G; G05; G05D; G05D1/00; G05D1/12
Claims Analysis
Total Claims: 11
Claim 1
Independent Claim
158 words
A system for proportionally navigating an airframe to a target wherein the airframe is maneuvered by an onboard flight control system, including body rate gyros for detecting the movement of the airframe relative to a fixed reference, comprising: a sensor for detecting the target; gimbal means rigidly connected to the airframe for carrying the sensor for pivotal movement in the pitch and yaw planes of the airframe; drive means for pivoting the sensor in the pitch and yaw planes; means for providing signals representative of the angular rate of motion of the sensor in the pitch and yaw planes; gimbal track loop means responsive to the output of the sensor and to the signal providing means for generating a track loop signal and controlling the drive means to cause the sensor to track the target; and decoupling means for removing the movement of the airframe from the track loop signal utilizing the output of the body rate gyros.
Claim 2
Independent Claim
158 words
A system for proportionally navigating an airframe to a target wherein the airframe is maneuvered by an onboard flight control system, including body rate gyros for detecting the movement of the airframe relative to a fixed reference, comprising: a sensor for detecting the target; gimbal means rigidly connected to the airframe for carrying the sensor for pivotal movement in the pitch and yaw planes of the airframe; drive means for pivoting the sensor in the pitch and yaw planes; means for providing signals representative of the angular rate of motion of the sensor in the pitch and yaw planes; gimbal track loop means responsive to the output of the sensor and to the signal providing means for generating a track loop signal and controlling the drive means to cause the sensor to track the target; and decoupling means for removing the movement of the airframe from the track loop signal utilizing the output of the body rate gyros.
Claim 3
Dependent Claim
28 words
A system according to claim 1 wherein the decoupling means removes the movement of the airframe from the track loop signal external to the gimbal track loop means.
Claim 4
Dependent Claim
27 words
A system according to claim 1 wherein the decoupling means removes the movement of the airframe from the track loop signal internal to the track loop means.
Claim 5
Dependent Claim
25 words
A system according to claim 1 wherein the signal providing means includes: a tachometer; and means for drivingly connecting the tachometer with the drive means.
Claim 6
Dependent Claim
25 words
A system according to claim 1 wherein the signal providing means includes: a potentiometer; and means for drivingly connecting the potentiometer with the drive means.
Claim 7
Dependent Claim
28 words
A system according to claim 1 and further comprising cage loop means for pivoting the sensor according to look angle command signals received from an onboard guidance circuit.
Claim 8
Dependent Claim
15 words
A system according to claim 1 wherein the decoupling means includes a bias cancel circuit.
Claim 9
Dependent Claim
30 words
A system according to claim 6 wherein the cage loop means includes means for providing signals representative of the angular position of the sensor in the pitch and yaw planes.
Claim 10
Independent Claim
140 words
A method of proportionally navigating an airframe to a target wherein the airframe is maneuvered by an onboard flight control system based upon signals received from a target sensor, the flight control system including body rate gyros for detecting the movement of the airframe relative to a fixed reference, comprising: mounting the sensor for pivotal movement in the pitch and yaw planes of the airframe on a gimbal assembly rigidly connected to the airframe; generating a track signal representative of the angular rate of motion and the angular position of the sensor in the pitch and yaw planes; pivoting the sensor in the pitch and yaw planes to track the target utilizing the track signal and the output of the sensor; and removing the motion of the airframe from the track signal utilizing the output of the body rate gyros.
Claim 11
Independent Claim
140 words
A method of proportionally navigating an airframe to a target wherein the airframe is maneuvered by an onboard flight control system based upon signals received from a target sensor, the flight control system including body rate gyros for detecting the movement of the airframe relative to a fixed reference, comprising: mounting the sensor for pivotal movement in the pitch and yaw planes of the airframe on a gimbal assembly rigidly connected to the airframe; generating a track signal representative of the angular rate of motion and the angular position of the sensor in the pitch and yaw planes; pivoting the sensor in the pitch and yaw planes to track the target utilizing the track signal and the output of the sensor; and removing the motion of the airframe from the track signal utilizing the output of the body rate gyros.
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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) | 1986-08-01 | 1987-01-31 | 1987-08-02 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1990-08-01 | 1991-01-31 | 1991-08-02 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1994-08-01 | 1995-01-31 | 1995-08-02 | $7700.00 | Window Closed / Lapsed |