Rotational control actuation system for guiding projectiles
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F42B-010/26
B64C-013/00
F42B-010/00
출원번호
US-0942995
(2010-11-09)
등록번호
US-9939238
(2018-04-10)
발명자
/ 주소
Sowle, Zak
Vasudevan, Srikanth
Birch, Matthew C.
출원인 / 주소
Orbital Research Inc.
대리인 / 주소
Kolkowski, Brian
인용정보
피인용 횟수 :
1인용 특허 :
12
초록▼
A projectile incorporates one or more spoiler-tabbed spinning disks to effect flow around the projectile and thus impart steering forces and/or moments. The spoiler tabs may be deployed only during steering phases of travel thus minimizing the drag penalty associated with steering systems. The disks
A projectile incorporates one or more spoiler-tabbed spinning disks to effect flow around the projectile and thus impart steering forces and/or moments. The spoiler tabs may be deployed only during steering phases of travel thus minimizing the drag penalty associated with steering systems. The disks are driven by motors and informed and controlled by sensors and electronic control systems. The spoiler tabs protrude through the surface of the projectile only for certain angles of spin of the spinning disk. For spin-stabilized projectiles, the disks spin at substantially the same rate as the projectile, but the disks may function in fin-stabilized projectiles as well. Any number of such spinning flow effector disks may be incorporated in a projectile, with the manner of functional coordination differing slightly for even and odd numbers of disks.
대표청구항▼
1. A guided projectile having an outer surface, the guided projectile comprising at least one spinning disk having an axle, the spinning disk comprising or being asymmetrically shaped to comprise at least one flow-effecting spoiler,the axle of the spinning disk being positioned within the projectile
1. A guided projectile having an outer surface, the guided projectile comprising at least one spinning disk having an axle, the spinning disk comprising or being asymmetrically shaped to comprise at least one flow-effecting spoiler,the axle of the spinning disk being positioned within the projectile such that, by the rotation of the spinning disk, the spoiler deploys to protrude from the outer surface of the guided projectile only for some angles of spin of the spinning disk so as to exert a steering force and/or moment on the guided projectile. 2. The guided projectile of claim 1, wherein the projectile is a spin-stabilized projectile. 3. The guided projectile of claim 2, wherein the at least one spinning disk spins up from being stopped in a body-fixed reference frame of the spin-stabilized projectile to spinning at about 18,000 rpm within 10 revolutions of the projectile. 4. The guided projectile of claim 1, wherein the guided projectile comprises an even number of spinning disks, two or greater, each being shaped to comprise at least one flow-effecting spoiler and each spinning disk being positioned within the projectile such that each spoiler protrudes from the outer surface of the guided projectile for some angles of spin of each spinning disk so as each to exert a steering force on the guided projectile. 5. The guided projectile of claim 4, wherein the spoilers are deployed periodically by the spinning of the disks, and the orientation of the periodic deployment of the spoilers is such that each spoiler deploys normal to a desired turning plane andone flow effector disk's phase is shifted positive and an opposite flow effector disk's phase is shifted negative resulting in a net steering force and/or moment on the guided projectile. 6. The guided projectile of claim 1, wherein the guided projectile comprises an odd number of spinning disks, three or greater, each being shaped to comprise at least one flow-effecting spoiler and each spinning disk being positioned within the projectile such that each spoiler protrudes from the outer surface of the guided projectile for some angles of spin of each spinning disk so as each to exert a steering force on the guided projectile. 7. The guided projectile of claim 6, wherein the spoilers are deployed periodically by the spinning of the disks, and the orientation of the periodic deployment of the spoilers is such that at least some of the spoilers are in turn deployed parallel to a desired turning plane. 8. The guided projectile of claim 1, wherein the spin frequency and phase of the rotational position of the at least one spinning disk are measured or determined by a rotary encoder, a synchro, a resolver, a rotary potentiometer, or a rotary variable differential transformer. 9. The guided projectile of claim 1, having a circular error probable (CEP) of less than 10 meters for projectile ranges greater than 18 kilometers. 10. A guided projectile having an outer surface, the guided projectile comprising at least one spinning disk having an axle, the spinning disk comprising or being asymmetrically shaped to comprise at least one flow-effecting spoiler,one or more sensors used to determine the spin frequency and spin orientation of the projectile,at least one sensor used to detect the frequency or phase of the spinning disk,at least one motor used to spin the at least one spinning disk, andat least one controller used to control the at least one motor based at least in part on measurements from the projectile spin sensor(s) and the disk sensor(s),the axle of the spinning disk being positioned within the projectile such that, by the rotation of the spinning disk, the spoiler deploys to protrude from the outer surface of the guided projectile only for some angles of spin of the spinning disk so as to exert a steering force and/or moment on the guided projectile. 11. The guided projectile of claim 10, wherein the projectile is a spin-stabilized projectile. 12. The guided projectile of claim 10, wherein the guided projectile comprises an even number of spinning disks, two or greater, each being shaped to comprise at least one flow-effecting spoiler and each spinning disk being positioned within the projectile such that each spoiler protrudes from the outer surface of the guided projectile for some angles of spin of each spinning disk so as each to exert a steering force on the guided projectile. 13. The guided projectile of claim 12, wherein the spoilers are deployed periodically by the spinning of the disks, and the orientation of the periodic deployment of the spoilers is such that each spoiler deploys normal to a desired turning plane andone flow effector disk's phase is shifted positive and an opposite flow effector disk's phase is shifted negative resulting in a net steering force and/or moment on the guided projectile. 14. The guided projectile of claim 10, wherein the guided projectile comprises an odd number of spinning disks, three or greater, each being shaped to comprise at least one flow-effecting spoiler and each spinning disk being positioned within the projectile such that each spoiler protrudes from the outer surface of the guided projectile for some angles of spin of each spinning disk so as each to exert a steering force on the guided projectile. 15. The guided projectile of claim 14, wherein the spoilers are deployed periodically by the spinning of the disks, and the orientation of the periodic deployment of the spoilers is such that at least some of the spoilers are in turn deployed parallel to a desired turning plane.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (12)
Geswender,Chris E.; Hinsdale,Andrew J.; Blaha,George A.; Dryer,Richard, 2-D projectile trajectory correction system and method.
Seidel Wolfgang,DEX ; Guischard Frank,DEX, Method for autonomous guidance of a spin-stabilized artillery projectile and autonomously guided artillery projectile for realizing this method.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.