Trajectory modification of a spinning projectile by controlling the roll orientation of a decoupled portion of the projectile that has actuated aerodynamic surfaces
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F42B-010/62
G01S-019/18
G01S-019/49
F41G-007/22
F42B-010/60
F42B-010/64
F42B-010/00
F41G-007/34
F41G-007/36
출원번호
US-0291450
(2014-05-30)
등록번호
US-9464876
(2016-10-11)
발명자
/ 주소
Morris, Joseph P.
Lichon, Paul
Smith, Douglas L.
출원인 / 주소
General Dynamics Ordnance and Tacital Systems, Inc.
대리인 / 주소
Shutts & Bowen LLP
인용정보
피인용 횟수 :
0인용 특허 :
15
초록▼
An apparatus and system for controlling the trajectory of a projectile having two rotationally decoupled sections, wherein the first section is rotationally decoupled from the second section. The first section of the projectile contains a navigation system. The first section also contains an actuato
An apparatus and system for controlling the trajectory of a projectile having two rotationally decoupled sections, wherein the first section is rotationally decoupled from the second section. The first section of the projectile contains a navigation system. The first section also contains an actuator by which aero-control surfaces on the second section are actuated. The second section may have external aero-spin surfaces which provide a torque counter to the rotation of the base projectile. The apparatus and system also includes embodiments having applications for nose sections of projectiles.
대표청구항▼
1. A trajectory control apparatus for a projectile, comprising: a first section including a navigation/targeting system, andan aero-control surface actuator in electronic connection with the navigation/targeting system;a second section rotationally decoupled from the first section, having an exterio
1. A trajectory control apparatus for a projectile, comprising: a first section including a navigation/targeting system, andan aero-control surface actuator in electronic connection with the navigation/targeting system;a second section rotationally decoupled from the first section, having an exterior surface, andone or more deployed or deployable aero-control surfaces in mechanical connection with the aero-control surface actuator, wherein the aero-control surfaces are rotatable and located on the second section exterior surface, andmeans for de-spinning the second section as the first section spins during the projectile's flight. 2. The trajectory control apparatus of claim 1, wherein the navigation/targeting system includes at least one of a GPS system, an inertial navigation system, an active laser seeker and a semi-active laser seeker. 3. The trajectory control apparatus of claim 1, further comprising one or more aero-spin surfaces located on the exterior surface of the second section. 4. The trajectory control apparatus of claim 1, further comprising one or more aero-spin surfaces located on an exterior surface of the first section. 5. The trajectory control apparatus of claim 4, further comprising additional one or more aero-spin surfaces located on the second section exterior surface. 6. The trajectory control apparatus of claim 1 wherein rotation of the one or more aero-control surfaces is controllable by the navigation/targeting system. 7. The trajectory control apparatus of claim 6, further comprising an aero-spin surface ring rotatable around the projectile located between the first section and the second section, wherein the aero-spin surface actuator is connected to the aero-spin surface ring so that the aero-spin surface ring may translate upon activation of the aero-spin surface actuator. 8. The trajectory control apparatus of claim 1, wherein the means for de-spinning the second section comprises a brake connected to the second section. 9. The trajectory control apparatus of claim 8, wherein at least a portion of the brake is located on or in the first section. 10. The trajectory control apparatus of claim 1, further comprising: a track located in the first section, wherein the aero-control surface actuator is connected to the track so that the track is translatable within the first section upon activation of the actuator. 11. The trajectory control apparatus of claim 1, further comprising: a ring rotatable around the projectile located between the first section and the second section wherein the aero-control surface actuator is connected to the ring so that the ring may translate upon activation of the actuator. 12. The trajectory control apparatus of claim 11, further comprising an aero-control lever arm on the second section in connection with a track and in connection with the aero-control surface. 13. The trajectory control apparatus of claim 12, further comprising a second aero-control lever arm in connection with the ring and in connection with a second aero-control surface. 14. A trajectory control apparatus for a projectile, comprising a nose section, having an exterior surface, andone or more rotatable nose aero-control surfaces located on the exterior surface of the nose section; anda first section rotationally decoupled from the nose section, having a navigation/targeting system, anda nose aero-control surface actuator for actuating the one or more nose aero-control surfaces. 15. The trajectory control apparatus of claim 14, wherein the nose section further comprises nose aero-spin surfaces on the exterior surface of the nose section. 16. The trajectory control apparatus of claim 14 further comprising a brake configured to de-spin the nose section as the first section spins during the projectile's flight. 17. A trajectory control apparatus for a projectile, comprising a nose section having an exterior surface and including: a navigation/targeting system,a nose aero-control surface actuator, andone or more adjustable nose aero-control surfaces located on the exterior surface of the nose section; anda first section rotationally decoupled from the nose section, wherein the nose aero-control surface actuator is configured to selectively rotate each of the one or more nose aero-control surfaces to modify a trajectory of the projectile. 18. The trajectory control apparatus of claim 17, wherein the nose section further comprises one or more nose aero-spin surfaces on the exterior surface of the nose section. 19. The trajectory control apparatus of claim 17, wherein the nose aero-control surface actuator and adjustment of the one or more aero-control surfaces are controllable by the navigation/targeting system. 20. The trajectory control apparatus of claim 17 further comprising a brake configured to de-spin the nose section as the first section spins during the projectile's flight.
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이 특허에 인용된 특허 (15)
Geswender,Chris E.; Hinsdale,Andrew J.; Blaha,George A.; Dryer,Richard, 2-D projectile trajectory correction system and method.
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