Systems and methods for targeting a projectile payload
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F42B-010/60
F42B-015/01
F41G-007/00
F42B-010/00
F42B-015/00
출원번호
US-0793090
(2010-06-03)
등록번호
US-8563910
(2013-10-22)
발명자
/ 주소
Elwell, Jr., John M.
출원인 / 주소
The Charles Stark Draper Laboratory, Inc.
대리인 / 주소
Goodwin Procter LLP
인용정보
피인용 횟수 :
1인용 특허 :
29
초록▼
A projectile's payload is oriented (independently or by orientation of the projectile itself) toward a target just prior to firing (e.g., detonation of the payload), e.g., for munitions providing an increased kill and casualty area and a fire “in defilade” (left, right, backwards or at any angle) ca
A projectile's payload is oriented (independently or by orientation of the projectile itself) toward a target just prior to firing (e.g., detonation of the payload), e.g., for munitions providing an increased kill and casualty area and a fire “in defilade” (left, right, backwards or at any angle) capability.
대표청구항▼
1. A projectile, comprising: a computation module for computing at least one parameter for orienting the projectile prior to firing, at a detonation location, toward a target located on a ground to optimize the effectiveness against the target of a focused or anisotropic payload in the projectile; a
1. A projectile, comprising: a computation module for computing at least one parameter for orienting the projectile prior to firing, at a detonation location, toward a target located on a ground to optimize the effectiveness against the target of a focused or anisotropic payload in the projectile; andan adjustment mechanism for adjusting, in response to the at least one computed parameter, the projectile's orientation upon the projectile's arrival via an unguided flight at a point where the projectile is about to detonate, the adjustment mechanism for adjusting the projectile's orientation such that the payload, upon the projectile's detonation, is directed in a direction that is within one degree of the ground's slope. 2. The projectile of claim 1, wherein the computation module determines at least the projectile's location parameters relative to a projectile launcher. 3. The projectile of claim 1, wherein the computation module comprises an inertial navigation system for determining a location and attitude of the projectile relative to a projectile launcher. 4. The projectile of claim 3, wherein the navigation system comprises an accelerometer for measuring a pitch-up angle of the projectile at launch to determine target location. 5. The projectile of claim 3, wherein the navigation system comprises a magnetometer for measuring roll rate of the projectile. 6. The projectile of claim 1, wherein the computation module comprises a proximity sensor for determining at least one of a distance of the projectile from the ground or a velocity of the projectile. 7. The projectile of claim 1, wherein the computation module determines a location of the target relative to the projectile. 8. The projectile of claim 1, wherein the at least one computed parameter comprises an activation time for activating the adjustment mechanism. 9. The projectile of claim 1, wherein the computation module determines a firing time for the payload. 10. The projectile of claim 1, wherein the adjustment mechanism comprises: at least one squib; andat least one triggering mechanism for firing the at least one squib. 11. The projectile of claim 1, wherein the adjustment mechanism comprises first and second squibs, and first and second triggering mechanisms for activating the first and second squibs. 12. The projectile of claim 1, wherein the computation module comprises a comparator for comparing a pitch of the projectile with the ground's slope. 13. The projectile of claim 1, wherein the computation module comprises a comparator for comparing a roll angle of the projectile with at least one predetermined roll angle. 14. The projectile of claim 13, wherein the at least one predetermined roll angle is zero degrees with respect to a local horizon. 15. The projectile of claim 13, wherein the at least one predetermined roll angle is 180 degrees with respect to a trajectory axis in a plane of a ground surface. 16. The projectile of claim 1, wherein the projectile is selected from the group consisting of a grenade, an artillery shell, a mortar shell, a bomb, a missile, a rocket, and a small-caliber round. 17. The projectile of claim 1, wherein the payload is a warhead. 18. The projectile of claim 1, further comprising a booster. 19. A method for orienting a projectile having a payload, the method comprising: computing at least one parameter for orienting the projectile prior to firing, at a detonation location, toward a target located on a ground; andadjusting, in response to the at least one computed parameter, the projectile's orientation upon the projectile's arrival via an unguided flight at a point where the projectile is about to detonate, the adjustment of the projectile's orientation causing the payload, upon the projectile's detonation, to be directed in a direction that is within one degree of the ground's slope. 20. The method of claim 19, wherein computing the at least one parameter comprises determining at least one of the projectile's location relative to a projectile launcher, velocity, distance from the ground, roll rate, yaw orientation, or pitch orientation. 21. The method of claim 19, wherein computing the at least one parameter comprises determining a location of the target relative to the projectile. 22. The method of claim 19, wherein the computed parameter comprises a time for adjusting the projectile's orientation. 23. The method of claim 19, further comprising determining a firing time for the payload. 24. The method of claim 19, wherein the target is in defilade or otherwise obscured.
Lindner Friedrich (Lauf DEX) Sttzle Dietmar (Lauf DEX) Argyrakis Nikolaus (Nuremberg DEX), Arrangement for generating a firing signal for overflight-flying bodies.
Yates Robert E. (Huntsville AL) Leonard John P. (Huntsville AL) Alongi Robert E. (Huntsville AL), Ideal trajectory shaping for anti-armor missiles via time optimal controller autopilot.
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