Patent US3614027A successfully refreshed from Google Patents.
US3614027A
Expired / Lapsed
US
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Pneumatic resolver for missile control
Assignee: United States Department of the Army
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Filing: 1969-07-08
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Granted: 1971-10-19
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Expires: 1989-07-08
Abstract
Abstract A pneumatic attitude control system for an artillery-type missile which is spin stabilized during flight. The control system includes a sensor portion which is roll stabilized and, thus, will not roll with the missile. Thus, attitude angles measured by the roll stabilized sensors will be space fixed. Control valves for providing restoring torques on the missile are mounted on the rotating part of the missile for rotation therewith. A resolution system is provided for resolving the space-fixed signals from the roll-stabilized sensors into the rolling missile''s coordinate system for desired operation of the control valves.
Inventors
- 👤 Charles Lynn Lewis
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-09 10:02
CPC Classifications
F; F42; F42B; F42B10/00; F42B10/60; F42B10/66; F42B10/663; Y; Y10; Y10T; Y10T137/00; Y10T137/206; Y10T137/2065; Y10T137/2071
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
76 words
An attitude control system for a missile having spinning and nonspinning portions, said attitude control system including: a. sensing means carried in said nonspinning portion and disposed for sensing the attitude of said missile and generating space-fixed signals indicative thereof; b. resolver means disposed for resolving said attitude signals into the coordinate system of said spinning portion; c. control means disposed for receiving said resolved signals for utilization thereof to provide resorting torques on said missile.
Claim 2
Dependent Claim
76 words
An attitude control system for a missile having spinning and nonspinning portions, said attitude control system including: a. sensing means carried in said nonspinning portion and disposed for sensing the attitude of said missile and generating space-fixed signals indicative thereof; b. resolver means disposed for resolving said attitude signals into the coordinate system of said spinning portion; c. control means disposed for receiving said resolved signals for utilization thereof to provide resorting torques on said missile.
Claim 3
Dependent Claim
36 words
An attitude control system as set forth in claim 1 including pulse duration modulation means connected between said resolver means and said control means to transform said signals into pulses for actuation of said control means.
Claim 4
Dependent Claim
26 words
An attitude control system as set forth in claim 2 wherein said sensing means includes a pneumatic gyro disposed for generating signals indicative of missile attitude.
Claim 5
Dependent Claim
79 words
An attitude control system as set forth in claim 3 wherein said resolver means includes: a. a plurality of fluid amplifiers connected to said gyro to receive input signals therefrom; each of said amplifiers having a pair of output channels; b. cam means carried on said spinning portion of said missile for coaction with the outputs of predetermined ones of said fluid amplifiers for generating back pressures therein, said pressures varying in response to rotation of said spinning portion.
Claim 6
Dependent Claim
31 words
An attitude control system as set forth in claim 4 wherein said cam means includes a pair of tracks having surfaces of varying depths, said surfaces varying in a sinusoidal manner.
Claim 7
Dependent Claim
93 words
An attitude control system as set forth in claim 5 wherein a first plurality of fluid amplifiers are disposed for providing signals for control of said missile in a first attitude plane, and a second plurality of fluid amplifiers are disposed for providing signals for attitude control in a second plane, said first plurality of fluid amplifiers having predetermined ones thereof provided with outputs disposed adjacent the first of said cam tracks, said second plurality of fluid amplifiers having predetermined ones thereof provided with outputs disposed adjacent the second of said cam tracks.
Claim 8
Dependent Claim
78 words
An attitude control system as set forth in claim 6 wherein said first and second plurality of amplifiers includes: a. pickoff means connected to the output of said predetermined ones of said fluid amplifiers intermediate said cam and the body of said fluid amplifiers; and, b. a plurality of fluid summing amplifiers having said pickoff means connected across the inlet thereof; c. an output summing amplifier having the outputs of said summing amplifier connected across the inlet thereof.
Claim 9
Dependent Claim
30 words
An attitude control system as set forth in claim 7 wherein said pulse duration modulation means is connected to the outputs of said output summing amplifiers to receive signals therefrom.
Claim 10
Dependent Claim
37 words
An attitude control system as set forth in claim 8 including fluidic slipring means connected between said spinning and nonspinning portions of said missile to transfer signals from said pulse duration modulation means to said control 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) | 1974-10-18 | 1975-04-19 | 1975-10-19 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-10-18 | 1979-04-19 | 1979-10-19 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-10-18 | 1983-04-19 | 1983-10-19 | $7700.00 | Window Closed / Lapsed |