Method and system for adjusting the flight path of an unguided projectile, with compensation for jittering deviation
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F41G-007/00
F41F-003/04
F41F-003/00
F42B-015/01
F42B-015/00
F42B-012/00
F42B-030/00
출원번호
US-0128654
(2005-05-13)
등록번호
US-7467761
(2008-12-23)
우선권정보
IL-162027(2004-05-17)
발명자
/ 주소
Yehezkeli,Oded
Kunreich,Irad
출원인 / 주소
Rafael Armament Development Authority Ltd
대리인 / 주소
Ohlandt, Greeley, Ruggiero & Perle, L.L.P.
인용정보
피인용 횟수 :
3인용 특허 :
13
초록▼
A method for adjusting the flight path of an unguided projectile, which comprises the steps of: (a) Measuring the magnitude and direction of the jittering of a projectile launch tube, at an ejection time of a projectile from the launch tube; (b) Measuring a velocity deviation of the projectile from
A method for adjusting the flight path of an unguided projectile, which comprises the steps of: (a) Measuring the magnitude and direction of the jittering of a projectile launch tube, at an ejection time of a projectile from the launch tube; (b) Measuring a velocity deviation of the projectile from a nominal velocity; (c) Measuring an angular deviation of the sight of the launch tube, being equal to the angular deviation between a line coinciding with the direction of gravity and a line passing through the center of the launch tube and the center of the sight; (d) Determining a compensating impulse vector to be applied to the projectile during an initial flight path thereof based on the magnitude and direction of the jittering, velocity deviation and angular deviation; and (e) Applying the compensating impulse vector to the projectile by activating a flight correction unit, the thrust developed by the flight correction unit suitable for adjusting the flight path of the projectile by a magnitude and direction substantially equal to that of the compensating impulse vector.
대표청구항▼
What is claimed is: 1. A method for adjusting the flight path of a projectile, comprising: a) Measuring the magnitude and direction of the uttering of a projectile launch tube, at an ejection time of a projectile from said launch tube; b) Measuring a velocity deviation of said projectile from a nom
What is claimed is: 1. A method for adjusting the flight path of a projectile, comprising: a) Measuring the magnitude and direction of the uttering of a projectile launch tube, at an ejection time of a projectile from said launch tube; b) Measuring a velocity deviation of said projectile from a nominal velocity; c) Measuring an angular deviation of the sight of said launch tube, being equal to the angular deviation between a line coinciding with the direction of gravity and a line passing through the center of the launch tube and the center of the sight; d) Determining a compensating impulse vector to be applied to said projectile during an initial flight path thereof based on the magnitude and direction of said uttering, velocity deviation and angular deflection; and e) Applying said compensating impulse vector to said projectile by activating a flight correction unit, the thrust developed by said flight correction unit adjusts the flight path of said projectile by a magnitude and direction substantially equal to that of said compensating impulse vector. 2. The method according to claim 1, wherein said projectile impacts a desired target by continuing on a corrected flight path, following a one-time non-continuous activation of said flight correction unit. 3. The method according to claim 2, wherein activation of the flight correction unit is within a period of approximately 0.2 seconds following said ejection time. 4. The method according to claim 1, wherein the flight correction unit comprises a plurality of pyrotechnic thrusters provided with said projectile. 5. A system for adjusting the flight path of a projectile, comprising: a) A projectile provided with a flight correction unit for adjusting the flight path of said projectile; b) Launching means for said projectile; c) Means for measuring, at an ejection time of a projectile from said launching means, the magnitude and direction of jittering of said launching means, of velocity deviation of said projectile from a nominal velocity, and of an angular deflection of a line passing through the center of said launching means and the center of the sight of said launching means from a line coinciding with the direction of gravity; d) Means for processing data acquired from said measuring means and for generating from said processed data a compensating impulse vector; e) Communication means between said launching means and said projectile for transmitting a signal to said projectile representative of said generated compensating impulse vector; and f) Means for determining an activation time of said flight correction unit, such that the thrust developed by said flight correction unit adjusts the flight path of said projectile by a magnitude and direction substantially equal to that of said compensating impulse vector. 6. The system according to claim 5, wherein the flight correction unit comprises a plurality of pyrotechnic thrusters, each of said thrusters being mounted at a different angular disposition with respect to the longitudinal axis of the projectile such that the axis of each of said thrusters crosses the longitudinal axis of the projectile. 7. The system according to claim 6, wherein the means for determining the activation time of said thrusters is a device for measuring the angular displacement of the projectile about its longitudinal axis from said ejection time to a predetermined flight path correction time. 8. The system according to claim 7, wherein the device comprises: a) a rotatable disc provided with an intermediate portion and a weighted portion on the rim thereof having a thickness greater than that of said intermediate portion, said disc normally separated from an abutment surface connected to the projectile body and said weighted portion adapted for limiting the angular velocity of said disc; b) opaque and transmissive sections formed in said intermediate portion; and c) a light detector connected to said projectile body for emitting and detecting light passing through said opaque and transmissive sections, said disc being pressed against said abutment surface during acceleration of the projectile within a launch tube and being separated therefrom following cessation of said acceleration at said ejection time, said projectile body and said light detector connected thereto rotating about the longitudinal axis of the projectile at a faster rate than said disc, detected light passing through a transmissive section being indicative of an incremental angular displacement of said projectile body. 9. The system according to claim 6, further comprising means for preventing rotation of the projectile within a launching tube, prior to the ejection time. 10. A launcher system, comprising: a) A launch tube; b) Means for launching a projectile from said launch tube in a ballistic trajectory; c) Means for measuring, at an ejection time of said projectile from said launch tube, the magnitude and direction of jittering of said launch tube, of velocity deviation of said projectile from a nominal velocity, and of an angular deviation of the sight of said launch tube between a line coinciding with the direction of gravity and a line passing through the center of said launch tube and the center of said sight; d) Means for processing data acquired from said measuring means and for generating from said processed data a compensating impulse vector; and e) Communication means between said data processing means and a projectile system for transmitting a signal to said projectile representative of said generated compensating impulse vector, thrust developed by a flight correction unit carried by said projectile in flight adjusting the flight path of said projectile by a magnitude and direction substantially equal to that of said compensating impulse vector. 11. An unguided projectile system, comprising: a) A projectile for being launched in a ballistic trajectory; b) Communication means for receiving from a launcher system a signal representative of a compensating impulse vector which compensates for, at the ejection time of a projectile from a launch tube, the uttering of said launch tube, a velocity deviation of said projectile from a nominal velocity, and an angular deviation of the sight of said launch tube between a line coinciding with the direction of gravity and a line passing through the center of said launch tube and the center of said sight; c) A device for measuring the angular displacement of the projectile about its longitudinal axis from said ejection time to a predetermined flight path correction time; and d) Two or more pyrotechnic thrusters, each of said thrusters being mounted at a different angular disposition with respect to the longitudinal axis of the projectile such that the axis of each of said thrusters crosses the longitudinal axis of the projectile, wherein two of said thrusters are activated at said predetermined flight path correction time, such that the thrust developed thereby adjusts the flight path of said projectile by a magnitude and direction substantially equal to that of said compensating impulse vector. 12. Projectile system according to claim 11, further comprising processing means for receiving said compensating impulse vector from said communication means and for synchronizing ignition of two of said thrusters at a predetermined flight path correction time, the adjusted flight path thereby essentially coinciding with a nominal flight path. 13. Projectile system according to claim 12, wherein an adjusted impulse vector is generated by means of the projectile processing means, said adjusted impulse vector being based on said compensating impulse vector and on an incremental impulse vector which compensates for the angular displacement of the projectile measured by said device, two of said thrusters being activated at said predetermined flight path correction time, such that the thrust developed thereby adjusts the flight path of said projectile by a magnitude and direction substantially equal to that of said compensating impulse vector. 14. Projectile system according to claim 11, wherein the projectile is formed with elements that radially protrude from the projectile fuselage, said elements being inserted within complementary grooves formed within said launch tube during loading of the projectile within the launcher, and being adapted for preventing rotation of the projectile within said launch tube, prior to the ejection time.
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