US4542870A
Expired / Lapsed
US
⏱️ 0.0 years remaining
SSICM guidance and control concept
Assignee: United States, ARMY TEH, Secretary of
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Filing: 1983-08-08
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Granted: 1985-09-24
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Expires: 2003-08-08
Abstract
Abstract The guidance scheme utilizes wide beam width semi-active RF sensors, a prsion roll altitude reference, and a controlled grade pitch, yaw and roll rate gyros to deliver high quality homing guidance information to a spin stabilized controlled missile. A filtering system is utilized to eliminate errors caused by body roll signals generated due to the spin of the missiles. The nutational motion is used to calibrate the sensors. Impulsive maneuvers are utilized to intercept incoming ballistic targets.
Inventors
- 👤 W. Max Howell
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-03 11:17
CPC Classifications
F; F41; F41G; F41G7/00; F41G7/20; F41G7/22; F41G7/226; F41G7/2266; F41G7/222; F41G7/2273; F41G7/2286
Claims Analysis
Total Claims: 3
Claim 1
Independent Claim
117 words
In a missile guidance system for guiding a spin stabilized controlled missile towards a target by proportional navigation, the improvement comprising the method of utilizing fixed body mounted sensors for detecting the relative direction of the target and producing an output signal proportional thereto; generating a rate signal which is proportional to body angle rates of the missile; utilizing filters to separate body motions from target motions in the rate signal; producing a filtered rate signal proportional to the body angle rates; combining the filtered rate signal with the output signal of the sensors for deriving an error signal with respect to guidance of the missile towards the target; and utilizing nutational motion to calibrate said sensors.
Claim 2
Dependent Claim
117 words
In a missile guidance system for guiding a spin stabilized controlled missile towards a target by proportional navigation, the improvement comprising the method of utilizing fixed body mounted sensors for detecting the relative direction of the target and producing an output signal proportional thereto; generating a rate signal which is proportional to body angle rates of the missile; utilizing filters to separate body motions from target motions in the rate signal; producing a filtered rate signal proportional to the body angle rates; combining the filtered rate signal with the output signal of the sensors for deriving an error signal with respect to guidance of the missile towards the target; and utilizing nutational motion to calibrate said sensors.
Claim 3
Dependent Claim
26 words
A method as set forth in claim 1 further comprising the steps of utilizing impulsive maneuvering of the missile which is responsive to the error signal.
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) | 1988-09-23 | 1989-03-25 | 1989-09-24 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1992-09-23 | 1993-03-25 | 1993-09-24 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1996-09-23 | 1997-03-25 | 1997-09-24 | $7700.00 | Window Closed / Lapsed |