Patent US303672A successfully refreshed from Google Patents.
Patent US4508293A successfully refreshed from Google Patents.
US4508293A
Expired / Lapsed
US
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Seeker-body decoupling system
Assignee: Hughes Missile Systems Co
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Filing: 1982-07-12
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Granted: 1985-04-02
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Expires: 2002-07-12
Abstract
Abstract An improved airframe body decoupling system for a body gimballed sensor on an interceptor aircraft or guided missile. Body rate gyro information is employed for internal decoupling so as to eliminate decoupling match sensitivity to receiver errors. The true measure of sensor position from the gimballed antenna potentiometer is differentiated and then externally decoupled to produce the desired line-of-sight rate for use by the guidance/control section of the proportional navigation guidance system.
Inventors
- 👤 Richard W. Jones
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-28 17:10
CPC Classifications
F; F41; F41G; F41G7/00; F41G7/20; F41G7/22; F41G7/2273; F41G7/2286; F41G7/2213; F41G7/2253; F41G7/226; G; G05; G05D; G05D1/00; G05D1/12
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
246 words
A method for body motion decoupling of a body gimballed antenna in a proportional navigation missile guidance system for a missile airframe, said guidance system comprising a track loop, a guidance/control section and a body rate gyro having a body rate output ψ, said track loop having inputs representing body angle ψ and LOS angle δ and deriving antenna angle θ, said track loop including a loop gain K.sub.ε and measurement errors which together comprise a receiver, said method comprising the steps of: combining angles δ and θ at a first combining point to provide an output signal ε representing the antenna pointing error; multiplying the angle ε by said measurement errors and said loop gain to provide a first measured LOS rate σ' at the output of said receiver; combining LOS rate σ' and body rate ψ' at a second combining point to provide antenna command signal β c =σ'-ψ'; applying said command signal to a gimbal rate servo to position said antenna, the output of said gimbal rate servo being the antenna position with respect to the airframe or look angle β where β=σ"-ψ'; coupling said body angle ψ and said look angle β at a third combining point to provide said antenna angle θ; differentiating said look angle β to provide σ"-ψ'; and combining said body rate ψ' with σ"-ψ' at a fourth combining point to provide a refined second LOS rate σ" for use by said guidance/control section of said guidance system.
Claim 2
Independent Claim
246 words
A method for body motion decoupling of a body gimballed antenna in a proportional navigation missile guidance system for a missile airframe, said guidance system comprising a track loop, a guidance/control section and a body rate gyro having a body rate output ψ, said track loop having inputs representing body angle ψ and LOS angle δ and deriving antenna angle θ, said track loop including a loop gain K.sub.ε and measurement errors which together comprise a receiver, said method comprising the steps of: combining angles δ and θ at a first combining point to provide an output signal ε representing the antenna pointing error; multiplying the angle ε by said measurement errors and said loop gain to provide a first measured LOS rate σ' at the output of said receiver; combining LOS rate σ' and body rate ψ' at a second combining point to provide antenna command signal β c =σ'-ψ'; applying said command signal to a gimbal rate servo to position said antenna, the output of said gimbal rate servo being the antenna position with respect to the airframe or look angle β where β=σ"-ψ'; coupling said body angle ψ and said look angle β at a third combining point to provide said antenna angle θ; differentiating said look angle β to provide σ"-ψ'; and combining said body rate ψ' with σ"-ψ' at a fourth combining point to provide a refined second LOS rate σ" for use by said guidance/control section of said guidance system.
Claim 3
Dependent Claim
23 words
The method recited in claim 1 wherein said body rate ψ is multiplied by decoupling gain G I prior to combining with σ'.
Claim 4
Dependent Claim
23 words
The method recited in claim 2 wherein said body rate ψ is multiplied by decoupling gain G E prior to combining with σ"-ψ'.
Claim 5
Dependent Claim
53 words
The method recited in claim 3 wherein said gimbal rate servo includes a servo rate loop and said missile guidance system includes an autopilot for controlling the missile airframe, wherein the response time of said servo rate loop is in the order of ten times faster than the response time of said autopilot/airframe.
Claim 6
Dependent Claim
20 words
The method recited in claim 4 wherein said decoupling gains G I and G E have a value of unity.
Claim 7
Dependent Claim
266 words
Apparatus for decoupling body motion in a proportional navigation missile guidance system having a body gimballed antenna, a track loop signal processor and a guidance/control section which includes an autopilot for controlling the missile airframe, said track loop having inputs representing LOS angle σ and antenna angle θ, the receiver output of said track loop being a measured of LOS rate σ', the LOS angle being applied to a gimbal rate servo, the output of said servo being a measure of the antenna look angle β where β is a function of LOS angle σ and missile body angle ψ, in the form β=σ"-ψ', the look angle being combined with the body angle ψ to provide said antenna angle θ, wherein the improvement comprises: a first combining point connected between the output of said receiver and said servo; a body rate gyro having an output signal ψ' coupled to said first combining point to combine body rate ψ' with LOS rate σ' at the input of said rate servo, thereby internally decoupling said body rate from said track loop; a differentiator coupled to the output of said rate servo to differentiate the look angle signal σ"-ψ' to provide σ"-ψ'; a second combining point connected to the output of said differentiator; said body rate gyro being coupled to said second combining point to combine body rate ψ' with σ"-ψ', thereby externally decoupling said body rate from said track loop; whereby the output of said second combining point is a refined LOS rate σ" which is adapted to be employed by said guidance/control section of said guidance system.
Claim 8
Dependent Claim
266 words
Apparatus for decoupling body motion in a proportional navigation missile guidance system having a body gimballed antenna, a track loop signal processor and a guidance/control section which includes an autopilot for controlling the missile airframe, said track loop having inputs representing LOS angle σ and antenna angle θ, the receiver output of said track loop being a measured of LOS rate σ', the LOS angle being applied to a gimbal rate servo, the output of said servo being a measure of the antenna look angle β where β is a function of LOS angle σ and missile body angle ψ, in the form β=σ"-ψ', the look angle being combined with the body angle ψ to provide said antenna angle θ, wherein the improvement comprises: a first combining point connected between the output of said receiver and said servo; a body rate gyro having an output signal ψ' coupled to said first combining point to combine body rate ψ' with LOS rate σ' at the input of said rate servo, thereby internally decoupling said body rate from said track loop; a differentiator coupled to the output of said rate servo to differentiate the look angle signal σ"-ψ' to provide σ"-ψ'; a second combining point connected to the output of said differentiator; said body rate gyro being coupled to said second combining point to combine body rate ψ' with σ"-ψ', thereby externally decoupling said body rate from said track loop; whereby the output of said second combining point is a refined LOS rate σ" which is adapted to be employed by said guidance/control section of said guidance system.
Claim 9
Dependent Claim
39 words
The apparatus recited in claim 6 wherein said gimbal rate servo comprises a servo rate loop, the response time of said servo rate loop being in the order of ten times faster than the response time of said autopilot/airframe.
Claim 10
Dependent Claim
26 words
The apparatus recited in claim 6 wherein the input signal to said gimbal rate servo is β c =σ'-ψ', the positioning command signal for said antenna.
References Cited (Backward Citations)
US2826380A
Cited
US2710729A
Cited
US3008668A
Cited
US3351303A
Cited
US3323757A
Cited
US3111088A
Cited
US3309963A
Cited
US3362658A
Cited
US3260205A
Cited
US3443476A
Cited
US3504247A
Cited
US3424010A
Cited
US3523659A
Cited
US3527429A
Cited
US3578796A
Cited
US3603532A
Cited
US3690596A
Cited
US3636324A
Cited
US3657524A
Cited
US3741500A
Cited
US3843075A
Cited
US3897918A
Cited
US4016469A
Cited
US4029270A
Cited
US4054254A
Cited
US4136844A
Cited
US4196380A
Cited
US4396878A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1988-04-01 | 1988-10-01 | 1989-04-02 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1992-04-01 | 1992-10-01 | 1993-04-02 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1996-04-01 | 1996-10-01 | 1997-04-02 | $7700.00 | Window Closed / Lapsed |