US4645139A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Procedure for steering a low-speed missile, weapon system and missile for implementation of the procedure
Assignee: Airbus Group SAS
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Filing: 1982-06-03
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Granted: 1987-02-24
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Expires: 2002-06-03
Abstract
Abstract A procedure for steering a missile launched at low speed from a tube, with the missile being equipped with a propulsion unit system of the type with a propellant fuel charge. The procedure is characterized by the fact that the above-mentioned propulsion unit system is determined and arranged in such a way that it can simultaneously impart to the missile axial propulsive thrust and maneuver forces for steering by force and that the variation of the position of the center of gravity of the missile on its axis as a function of the burn-up of the propellant charge is such that, when the missile leaves the tube, the center of gravity passes through the line of action of the above-mentioned maneuver forces and that, during its flight, makes it possible for torques to develop which generate aerodynamic angles of attack and which produce maneuver forces which are added to those of steering by force.
Inventors
- 👤 Jean Guillot
- 👤 Jacques Raynaud
- 👤 Michel Maree
- 👤 Robert Vaillant
- 👤 Jean Ansaldi
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-07 14:52
CPC Classifications
F; F42; F42B; F42B10/00; F42B10/60; F42B10/66; F42B10/665; F02; F02K; F02K9/00; F02K9/80
Claims Analysis
Total Claims: 12
Claim 1
Independent Claim
232 words
A missile for launching from a launching tube; the missile including a combat payload and a propulsion system of the propulsive fuel load type; the propulsion system comprising a first propulsive means arranged in the rear of the missile, the combustion of the first propulsive means being terminated before the missile exits from the launching tube, the first propulsive means imparting a low initial speed to the missile when the missile exits from the launching tube, and a second propulsive means including lateral nozzles for enabling steering of the missile by force and arranged for simultaneously imparting to the missile during flight of the missile axial propulsive thrust and maneuver forces for steering by force; the combat payload, the first propulsive means and the second propulsive means being arranged in the missle so that when the missile exits from the launching tube after combustion of the first propulsive means, the center of gravity of the missile is positioned in a plane transverse to the longitudinal axis of the missile and including the maneuver forces, and during the flight of the missile and progressive combustion of the second propulsive means, the position of the center of gravity of the missile moves rearwardly along the longitudinal axis of the missle thereby enabling the generation of aerodynamic torques for producing maneuver forces which are added to the maneuver forces provided for the steering by force.
Claim 2
Dependent Claim
232 words
A missile for launching from a launching tube; the missile including a combat payload and a propulsion system of the propulsive fuel load type; the propulsion system comprising a first propulsive means arranged in the rear of the missile, the combustion of the first propulsive means being terminated before the missile exits from the launching tube, the first propulsive means imparting a low initial speed to the missile when the missile exits from the launching tube, and a second propulsive means including lateral nozzles for enabling steering of the missile by force and arranged for simultaneously imparting to the missile during flight of the missile axial propulsive thrust and maneuver forces for steering by force; the combat payload, the first propulsive means and the second propulsive means being arranged in the missle so that when the missile exits from the launching tube after combustion of the first propulsive means, the center of gravity of the missile is positioned in a plane transverse to the longitudinal axis of the missile and including the maneuver forces, and during the flight of the missile and progressive combustion of the second propulsive means, the position of the center of gravity of the missile moves rearwardly along the longitudinal axis of the missle thereby enabling the generation of aerodynamic torques for producing maneuver forces which are added to the maneuver forces provided for the steering by force.
Claim 3
Dependent Claim
38 words
A missile according to claim 1, wherein the second propulsive means is mounted in the forward portion of the missile and at least a portion of the combat payload is located in the rearward portion of the missile.
Claim 4
Dependent Claim
36 words
A missile according to claim 2, wherein the combat payload includes a main charge portion located in the rearward portion of the missile and an auxiliary charge portion located in the forward portion of the missile.
Claim 5
Dependent Claim
18 words
A missile according to claim 2, wherein the combat payload is located forwardly of the first propulsive means.
Claim 6
Dependent Claim
32 words
A missile according to claim 3, wherein the main charge portion is located forwardly of the first propulsive means and the auxiliary charge portion is located forwardly of the second propulsive means.
Claim 7
Dependent Claim
29 words
A missile according to claim 1, wherein the combat payload includes at least a main charge portion, the main charge portion being located forwardly of the first propulsive means.
Claim 8
Dependent Claim
27 words
A missile according to claim 6, wherein the combat payload includes an auxiliary charge portion, the auxiliary charge portion being located forwardly of the second propulsive means.
Claim 9
Dependent Claim
25 words
A missile according to claim 1, wherein the second propulsive means is arranged for burning symmetrically with respect to the longitudinal axis of the missile.
Claim 10
Dependent Claim
28 words
A missile according to claim 1, wherein the missile is roll stabilized and the second propulsive means includes at least four lateral nozzles for enabling steering by force.
Claim 11
Dependent Claim
30 words
A missile according to claim 1, wherein the missile auto-rotates about the longitudinal axis thereof and the second propulsive means includes only two lateral nozzles for enabling steering by force.
Claim 12
Dependent Claim
16 words
A weapon system according to claim 1, further comprising a launching tube for launching the missile.
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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) | 1990-02-23 | 1990-08-25 | 1991-02-24 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1994-02-23 | 1994-08-25 | 1995-02-24 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1998-02-23 | 1998-08-25 | 1999-02-24 | $7700.00 | Window Closed / Lapsed |