Low cost guiding device for projectile and method of operation
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F42B-010/06
F42B-015/01
F42B-010/64
F42B-010/04
F42B-010/26
F42B-015/10
출원번호
US-0065467
(2013-10-29)
등록번호
US-9303964
(2016-04-05)
우선권정보
IL-224075 (2012-12-31)
발명자
/ 주소
Wurzel, Gil
Malul, Assaf
출원인 / 주소
BAE SYSTEMS ROKAR INTERNATIONAL LTD.
대리인 / 주소
Pearl Cohen Zedek Latzer Baratz LLP
인용정보
피인용 횟수 :
1인용 특허 :
6
초록▼
A guiding assembly is adapted to be connected to a projectile and comprising a rear main unit adapted to be connected to the front end of the projectile, and a front main unit rotatably connected at its rear end to the front end of the rear main unit. The front main unit is adapted to rotate about a
A guiding assembly is adapted to be connected to a projectile and comprising a rear main unit adapted to be connected to the front end of the projectile, and a front main unit rotatably connected at its rear end to the front end of the rear main unit. The front main unit is adapted to rotate about a central longitudinal axis. A relative speed control unit is operable between the rear main unit and the front main unit and capable of providing spin braking force to slow the relative speed of rotation of the front main unit. An at least one guiding fin radially extends from the front main unit. The pitch angle of the fin is controllable by a return spring connected to the fin so that the pitch angle of the fin is growing as the aerodynamic pressure on the fin lowers and it is growing smaller as the aerodynamic pressure on the fin gets bigger.
대표청구항▼
1. A guiding assembly adapted to be connected to a projectile, comprising: a rear main unit adapted to be connected at its rear side to a front end of said projectile, said rear main unit having a central longitudinal axis;a front main unit rotatably connected at its rear end to a front end of said
1. A guiding assembly adapted to be connected to a projectile, comprising: a rear main unit adapted to be connected at its rear side to a front end of said projectile, said rear main unit having a central longitudinal axis;a front main unit rotatably connected at its rear end to a front end of said rear main unit and adapted to rotate about said central longitudinal axis;a relative speed control unit operable between said rear main unit and said front main unit and capable of providing spin braking force to slow the relative speed of rotation of said front main unit, wherein said braking force is controllable;a single guiding fin radially extending from said front main unit, wherein said guiding fin is shaped as a flat aerodynamic element having a fin chord extending from the front end of the fin to the rear end of the fin and residing in a plane parallel to said central longitudinal axis, said chord of said fin forms a pitch angle with said central longitudinal axis in said plane parallel to said central longitudinal axis; anda return spring, operably connected to said fin,wherein said spring is configured to allow movement correspondingly to aerodynamic pressure on the fin, andwherein said pitch angle is controllable by said spring. 2. The guiding assembly of claim 1 wherein said pitch angle of said single fin is set at a fixed angle between zero and fifteen degrees. 3. The guiding assembly of claim 1, wherein said pitch angle of said fin is adjustable to values that are not lower than zero degrees and not higher than fifteen degrees. 4. The guiding assembly of claim 1, wherein said relative speed control unit is an electrical alternator, and wherein the braking force of it is controllable by controlling the amount of electrical power consumed from the alternator. 5. The guiding assembly of claim 1, wherein the size and pitch angle of said guiding fin are big enough for causing said front main unit to spin in a rotational speed that is faster than the rotational speed of said projectile and is opposite to it in direction, when said projectile is in its trajectory. 6. The guiding assembly of claim 1, wherein said guiding fin is pivotally connected to said front main unit. 7. The guiding assembly of claim 1, wherein said guiding fin has a steering lever. 8. The guiding assembly of claim 1 wherein the pitch angle of said fin is controllable. 9. The guiding assembly of claim 8, wherein the pitch angle of said fin is growing larger as the aerodynamic pressure on the fin lowers and it is getting smaller as the aerodynamic pressure on the fin gets bigger. 10. A method for guiding a projectile along its desired trajectory, the method comprising: providing a guiding assembly to a front end of said projectile, said guiding assembly comprising: a rear main unit adapted to be connected at its rear side to a front end of said projectile, said rear main unit having a central longitudinal axis;a front main unit rotatably connected at its rear end to the front end of said rear main unit and adapted to rotate about said central longitudinal axis;a relative speed control unit operable between said rear main unit and said front main unit and capable of providing spin braking force to slow the relative speed of rotation of said front main unit, wherein said braking force is controllable;a single guiding fin radially extending from said front main unit, wherein said guiding fin is shaped as a flat aerodynamic element having a fin chord extending from the front end of the fin to the rear end of the fin and residing in a plane parallel to said central longitudinal axis, said chord of said fin form a pitch angle with said central longitudinal axis in said plane parallel to said central longitudinal axis; anda return spring, operably connected to said fin, and the spring moving correspondingly to aerodynamic pressure on the fin;launching said projectile; andcontrolling the magnitude of the rotational speed of said front main unit to be substantially equal to and opposite in direction with respect to the rotational speed of said projectile when correction to said trajectory is required and allowing said front main unit to rotate with no braking forces at said relative speed control unit at other times,wherein said pitch angle is controllable by said spring. 11. The method of claim 10 wherein said relative speed control unit is an electrical alternator. 12. The method of claim 11, further comprising: controlling the rotational speed of said front main unit by applying controllable electrical load to said alternator. 13. The method of claim 12, wherein the pitch angle of said fin is growing larger as the aerodynamic pressure on the fin lowers and it is getting smaller as the aerodynamic pressure on the fin gets bigger.
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이 특허에 인용된 특허 (6)
Sebestyen George (Weston MA) Sinclair Ronald R. (Moultonboro NH) Smith John A. (Bedford MA) Sands Timothy B. (Acton MA) Nussdorfer Theodore J. (Lexington MA), Canard control assembly for a projectile.
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