Patent US4573648A successfully refreshed from Google Patents.
US4573648A
Expired / Lapsed
US
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Ram air combustion steering system for a guided missile
Assignee: Lockheed Martin Tactical Systems Inc
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Filing: 1983-01-20
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Granted: 1986-03-04
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Expires: 2003-01-20
Abstract
Abstract An open-ended diffusion chamber and an adjacent combustion chamber located in the nose of a projectile to receive ram air that ignites a solid fuel material within the combustion chamber. A pair of oppositely disposed lateral steering ports are provided aft of the combustion chamber and are interconnected therewith via a diverting valve that is controllable to selectively divert the escaping combustion gases from the combustion chamber to one or both of the steering ports to thereby change or maintain the trajectory course of the projectile after firing.
Inventors
- 👤 Richard C. Morenus
- 👤 Alson C. Frazer
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-31 20:36
CPC Classifications
F; F42; F42B; F42B10/00; F42B10/60; F42B10/66; F42B10/663
Claims Analysis
Total Claims: 12
Claim 1
Independent Claim
115 words
A directional steering system for a guided missile comprising: means defining the nose end of said missile; means within said nose means for receiving ram air therein; means within said nose means adjacent said ram air receiving means for providing combustible fuel; means within said nose means defining a combustion chamber wherein ram air ignites said fuel; means within said nose means and aft of said combustion chamber defining lateral thrust steering ports to provide escape paths for combustion gases from said combustion chambers means to the external environment; means within said nose means for selectively diverting combustion gases generated within said combustion chamber means to one or more of said lateral thrust steering ports.
Claim 2
Dependent Claim
115 words
A directional steering system for a guided missile comprising: means defining the nose end of said missile; means within said nose means for receiving ram air therein; means within said nose means adjacent said ram air receiving means for providing combustible fuel; means within said nose means defining a combustion chamber wherein ram air ignites said fuel; means within said nose means and aft of said combustion chamber defining lateral thrust steering ports to provide escape paths for combustion gases from said combustion chambers means to the external environment; means within said nose means for selectively diverting combustion gases generated within said combustion chamber means to one or more of said lateral thrust steering ports.
Claim 3
Dependent Claim
33 words
A steering system as in claim 1, wherein said combustible fuel means comprises a quantity of solid fuel formed to have a surface exposed to said ram air in said combustion chamber means.
Claim 4
Dependent Claim
36 words
A steering system as in claim 1, wherein said diverting means includes an electrically controllable vane mechanism that is rotatable to completely block no more than one of sad lateral thrust steering ports at a time.
Claim 5
Independent Claim
108 words
A system for directionally controlling a fired projectile over its flight path comprising: means at the nose end of said projectile for defining a compression chamber having one end open for receiving ram air; a pair of oppositely disposed jet ports extending from said compression chamber means to opposite sides of said projectile; means defining a solid combustible fuel within said compression chamber means and being ignited by said ram air to produce combustion gases; valve means between said compression chamber means and said jet ports for responsively diverting the flow of combustion gases to each of said jet ports to control the steering direction of said projectile.
Claim 6
Independent Claim
108 words
A system for directionally controlling a fired projectile over its flight path comprising: means at the nose end of said projectile for defining a compression chamber having one end open for receiving ram air; a pair of oppositely disposed jet ports extending from said compression chamber means to opposite sides of said projectile; means defining a solid combustible fuel within said compression chamber means and being ignited by said ram air to produce combustion gases; valve means between said compression chamber means and said jet ports for responsively diverting the flow of combustion gases to each of said jet ports to control the steering direction of said projectile.
Claim 7
Dependent Claim
66 words
A system as in claim 4, wherein said compression chamber means includes an internal wall surface which is formed by a solid fuel material, and further wherein, said solid fuel material is ignited by said ram air within said compression chamber means and generates combustion gases that are forced towards said pair of jet ports to escape therefrom and thereby provide steering thrust to said projectile.
Claim 8
Dependent Claim
41 words
A system as in claim 5, wherein said compression chamber means is generally cylindrically shaped and lies longitudinally concentric with the major axis of said projectile and further wherein said jet ports extend radially with respect to said compression chamber means.
Claim 9
Dependent Claim
39 words
A system as in claim 6, wherein said valve means comprises a partially cylindrical vane element on a rotatable base that is electrically controlled and wherein said element is mounted for axial rotation along the axis of said projectile.
Claim 10
Dependent Claim
51 words
A system as in claim 6, wherein said vane element is at least large enough to block one of said jet ports when located between it and said combustion chamber means and sufficiently small enough to leave both said jet ports open when equal thrust is desired at each jet port.
Claim 11
Dependent Claim
41 words
A system as in claim 4, wherein said compression chamber means is generally cylindrical shaped and lies longitudinally concentric with the major axis of said projectile and further wherein said jet ports extend radially with respect to said compression chamber means.
Claim 12
Dependent Claim
39 words
A system as in claim 8, wherein said valve means comprises a partially cylindrical vane element on a rotatable base that is electrically controlled and wherein said element is mounted for axial rotation along the axis of said projectile.
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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) | 1989-03-03 | 1989-09-02 | 1990-03-04 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1993-03-03 | 1993-09-02 | 1994-03-04 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1997-03-03 | 1997-09-02 | 1998-03-04 | $7700.00 | Window Closed / Lapsed |