Aerodynamic flight termination system and method
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0837587
(2010-07-16)
|
등록번호 |
US-8367993
(2013-02-05)
|
발명자
/ 주소 |
- Velez, Javier
- Klestadt, Ralph H.
|
출원인 / 주소 |
|
인용정보 |
피인용 횟수 :
5 인용 특허 :
7 |
초록
▼
A missile has a flight termination system that includes deployable lift surfaces that deploy forward of a center of gravity of the missile. When deployed, the lift surfaces cause the missile to rotate about its longitudinal axis. This rotation eventually increases in rate until the missile nears a n
A missile has a flight termination system that includes deployable lift surfaces that deploy forward of a center of gravity of the missile. When deployed, the lift surfaces cause the missile to rotate about its longitudinal axis. This rotation eventually increases in rate until the missile nears a natural roll frequency of the missile. As the missile nears or reaches its natural roll frequency, the missile's nose pitches up, angle of attack diverges and the missile tumbles, resulting in rapid termination of flight by loss of aerodynamic lift, vertical plunging and crashing. The lift surfaces may be curved surfaces that conform to the shape of a fuselage of the missile, prior to the deployment of the lift surfaces. The lift surfaces may be canted slightly relative to a missile longitudinal axis when the lift surfaces are deployed, so as to provide a sufficient rolling moment to overcome aerodynamic damping or resistance (roll drag) of the missile.
대표청구항
▼
1. A missile comprising: a fuselage; anddeployable roll-producing lift surfaces that deploy during flight from the fuselage, forward of a center of gravity of the missile;wherein the lift surfaces provide a roll moment to the missile, as part of a flight termination system to terminate flight of the
1. A missile comprising: a fuselage; anddeployable roll-producing lift surfaces that deploy during flight from the fuselage, forward of a center of gravity of the missile;wherein the lift surfaces provide a roll moment to the missile, as part of a flight termination system to terminate flight of the missile; and further comprising canards forward of the center of gravity. 2. The missile of claim 1, wherein the lift surfaces also cause the missile to pitch up when the lift surfaces are deployed. 3. The missile of claim 1, wherein the lift surfaces are curved surfaces that substantially conform to the shape of the fuselage, prior to deployment. 4. The missile of claim 1, wherein the lift surfaces are hingedly coupled to the fuselage. 5. The missile of claim 1, further comprising a mechanism for selectively releasing and deploying the lift surfaces. 6. The missile of claim 1, wherein the lift surfaces are deflected (or canted) relative to a longitudinal axis of the fuselage. 7. The missile of claim 6, wherein the lift surfaces are deflected (or canted), relative to the longitudinal axis, at an angle of 0.1 to 1 degrees. 8. The missile of claim 1, further comprising wings and fins aft of the center of gravity. 9. The missile of claim 1, wherein the flight termination system includes the lift surfaces that are located forward of the center of gravity, which cause negative to neutral pitch/yaw static stability while in the deployed position. 10. The missile of claim 1, wherein the canards are forward of the deployable roll-producing lift surfaces. 11. The missile of claim 10, wherein there are at least four of the deployable roll-producing lift surfaces. 12. The missile of claim 1, wherein the lift surfaces are deployed as a group. 13. The missile of claim 6, wherein the lift surfaces are canted, relative to the longitudinal axis, at an angle of 0.2 to 0.3 degrees. 14. The missile of claim 4, wherein the lift surfaces are curved surfaces that substantially conform to the shape of the fuselage, prior to deployment. 15. The missile of claim 14, wherein the lift surfaces are canted relative to a longitudinal axis of the fuselage. 16. The missile of claim 15, wherein the lift surfaces are canted, relative to the longitudinal axis, at an angle of 0.1 to 1 degrees. 17. The missile of claim 15, further comprising canards forward of the center of gravity;wherein the canards are forward of the deployable roll-producing lift surfaces. 18. The missile of claim 17, further comprising a mechanism for selectively releasing and deploying the lift surfaces. 19. The missile of claim 18, wherein the lift surfaces also cause the missile to pitch up when the lift surfaces are deployed.
이 특허에 인용된 특허 (7)
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Elder, Douglas J., Electromagnetic railgun projectile.
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Chung Sung K. (Dover NJ) Kline Roy W. (Newton NJ), Limited range projectile.
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Orzechowski Casimir T. (Kensington MD) Seiden Nat (Brandywine MD) Mycka ; Jr. Anthony (Waldorf MD), Method of controlling the spin rate of tube launched rockets.
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Grosso Vincent A. (Hopkinton MA), Modular aerodynamic gyrodynamic intelligent controlled projectile and method of operating same.
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White, Charles O., Ranged limited projectile using augmented roll damping.
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Cole Donald E. (Covina CA), Rolling airframe autopilot.
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Klestadt Ralph H. (Sherman Oaks CA), Rotationally mounted flexible band wing.
이 특허를 인용한 특허 (5)
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Afanasyev, Sergey Nikolaevich, Aircraft.
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Reany, Jack W.; Sanderson, Terry M., Aircraft wing with flexible skins.
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Osdon, Tal, Fin deployment system.
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Alculumbre, Michael, Projectile.
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Bae, Ju Hyun; Kim, Wan Joo, Shell.
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