US3637167A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Missile steering system
Assignee: McDonnell Douglas Corp
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Filing: 1969-11-05
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Granted: 1972-01-25
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Expires: 1989-11-05
Abstract
Abstract A missile steering system wherein high maneuverability of a missile is achieved by combined interaction of jet exhaust and movable fins on fluid flow past the missile surface. Jet exit ports are located between movable fins and selected ones are used in various steering maneuvers.
Inventors
- 👤 Herman D Froning Jr
- 👤 Dean F Hopkins
- 👤 Paul L Klevatt
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-08 02:00
CPC Classifications
F; F42; F42B; F42B10/00; F42B10/60; F42B10/66; F42B10/663; F42B10/62; F42B10/64
Claims Analysis
Total Claims: 5
Claim 1
Independent Claim
90 words
A missile steering system comprising: a tail heavy missile having its center of pressure forwardly of its center of gravity, said missile flying at an angle of attack relative to its flight path, aerodynamic fins equally spaced in quadrants and movably connected to the tail section of said missile, jet nozzle slot openings in said tail section extending in a circumferential direction about said missile between said fins, a gas source connected to said openings, means for moving selected fins as desired, and means controlling gas flow to selected openings.
Claim 2
Dependent Claim
90 words
A missile steering system comprising: a tail heavy missile having its center of pressure forwardly of its center of gravity, said missile flying at an angle of attack relative to its flight path, aerodynamic fins equally spaced in quadrants and movably connected to the tail section of said missile, jet nozzle slot openings in said tail section extending in a circumferential direction about said missile between said fins, a gas source connected to said openings, means for moving selected fins as desired, and means controlling gas flow to selected openings.
Claim 3
Dependent Claim
29 words
A missile steering system as in claim 1 wherein said gas source includes missile propulsion gases for use before burnout and an independent gas source for use after burnout.
Claim 4
Dependent Claim
42 words
A missile steering system as in claim 1 wherein fin movement and gas flow to certain nozzles is used to initiate turning movement and gas flow to other nozzles is used to compensate for overreaction of said missile in making rapid turns.
Claim 5
Dependent Claim
43 words
A missile steering system as in claim 1 wherein said gas source is a source independent from the missile propulsion source and is generating gas continuously from launch, and valve means directing said gases rearwardly and for directing gases to selected jet nozzles.
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) | 1975-01-24 | 1975-07-26 | 1976-01-25 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1979-01-24 | 1979-07-26 | 1980-01-25 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1983-01-24 | 1983-07-26 | 1984-01-25 | $7700.00 | Window Closed / Lapsed |