US4522357A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Ram air steering system for a guided missile
Assignee: Lockheed Martin Tactical Systems Inc
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Filing: 1983-01-19
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Granted: 1985-06-11
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Expires: 2003-01-19
Abstract
Abstract An opening in the nose of a missile allows entry of ram air during missile flight to a central chamber. Oppositely oriented steering jets are interconnected with the aft end of the central chamber and escaping ram air provides lateral steering thrust forces. A movable diverting means controls the direction that the escaping ram air is diverted and thereby controls the steering forces.
Inventors
- 👤 William R. Bains
- 👤 Calhoun W. Sumrall
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 13:15
CPC Classifications
F; F42; F42B; F42B10/00; F42B10/60; F42B10/66; F42B10/663; F41; F41G; F41G7/00
Claims Analysis
Total Claims: 5
Claim 1
Independent Claim
138 words
A system for directionally controlling a fired projectile spinning at a predetermined rate in a predetermined direction when traveling over its flight path comprising: means at the nose end of said projectile for defining a cylindrical chamber having one end open for receiving ram air; a pair of oppositely disposed air passages extending from said chamber means to opposite sides of said projectile; means between said chamber means and said passages for responsively diverting said ram air in a predetermined direction through at least one of said passages to control the steering direction of said projectile; and wherein said diverting means is rotationally driven to rotate at said predetermined rate in a direction opposite to said predetermined direction in order to maintain said diverting means in a predetermined spacial location to effect a particular steering force thrust vector.
Claim 2
Independent Claim
138 words
A system for directionally controlling a fired projectile spinning at a predetermined rate in a predetermined direction when traveling over its flight path comprising: means at the nose end of said projectile for defining a cylindrical chamber having one end open for receiving ram air; a pair of oppositely disposed air passages extending from said chamber means to opposite sides of said projectile; means between said chamber means and said passages for responsively diverting said ram air in a predetermined direction through at least one of said passages to control the steering direction of said projectile; and wherein said diverting means is rotationally driven to rotate at said predetermined rate in a direction opposite to said predetermined direction in order to maintain said diverting means in a predetermined spacial location to effect a particular steering force thrust vector.
Claim 3
Dependent Claim
24 words
A system as in claim 1, wherein said steering force thrust vector varies in amplitude at a rate which is twice the predetermined rate.
Claim 4
Dependent Claim
205 words
A ram air steering system for a guided missile comprising: means on the forward end of said missile defining a nose portion thereof; means within said nose means concentric with the central axis of said missile for allowing ram air to enter the interior of said nose means; means within said nose means for diverting said entered ram air to the external environment in a lateral direction to said central axis, thereby producing lateral steering thrust forces on said missile; said diverting means includes a pair of oppositely oriented openings positioned aft of said entering means on said nose means and respective air passages interconnecting said openings with the interior of said nose means to allow said ram air to pass therethrough; said diverting means further includes valve means for selectively controlling the amount of air to be diverted to respective air passages; and said valve means includes a partially cylindrically shaped element mounted for relative rotation about its axis coaxial with said central axis of said missile and said element contains a first surface portion that may be selectively positioned to block one of said passages and a second surface portion that diverts the entered ram air to at least one of said passages.
Claim 5
Dependent Claim
205 words
A ram air steering system for a guided missile comprising: means on the forward end of said missile defining a nose portion thereof; means within said nose means concentric with the central axis of said missile for allowing ram air to enter the interior of said nose means; means within said nose means for diverting said entered ram air to the external environment in a lateral direction to said central axis, thereby producing lateral steering thrust forces on said missile; said diverting means includes a pair of oppositely oriented openings positioned aft of said entering means on said nose means and respective air passages interconnecting said openings with the interior of said nose means to allow said ram air to pass therethrough; said diverting means further includes valve means for selectively controlling the amount of air to be diverted to respective air passages; and said valve means includes a partially cylindrically shaped element mounted for relative rotation about its axis coaxial with said central axis of said missile and said element contains a first surface portion that may be selectively positioned to block one of said passages and a second surface portion that diverts the entered ram air to at least one of said passages.
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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) | 1988-06-10 | 1988-12-10 | 1989-06-11 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1992-06-10 | 1992-12-10 | 1993-06-11 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1996-06-10 | 1996-12-10 | 1997-06-11 | $7700.00 | Window Closed / Lapsed |