Method for automatically managing a homing device mounted on a projectile, in particular on a missile
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F41G-007/22
F41G-007/00
출원번호
US-0113519
(2012-04-16)
등록번호
US-9234723
(2016-01-12)
우선권정보
FR-11 01320 (2011-04-28)
국제출원번호
PCT/FR2012/000146
(2012-04-16)
§371/§102 date
20131028
(20131028)
국제공개번호
WO2012/146835
(2012-11-01)
발명자
/ 주소
De Picciotto, Francois
출원인 / 주소
MBDA FRANCE
대리인 / 주소
Duane Morris LLP
인용정보
피인용 횟수 :
0인용 특허 :
26
초록▼
According to the invention, the projectile (1) is provided with a strapdown homing device (2), said device having a lock-on phase during which the latter attempts to detect a target (C), and including an viewing direction (3), said viewing direction (3) being fixed with respect to the projectile (1)
According to the invention, the projectile (1) is provided with a strapdown homing device (2), said device having a lock-on phase during which the latter attempts to detect a target (C), and including an viewing direction (3), said viewing direction (3) being fixed with respect to the projectile (1) and extending along the longitudinal axis (4) of the latter, said projectile (1) further comprising control means (8) for automatically controlling said projectile (1) so as to cause the longitudinal axis (4) thereof, in flight and during the lock-on phase of the homing device (2), to trace a circle, the radius of which increases in time, until the target (C) is detected.
대표청구항▼
1. Method for automatically managing a strapdown homing device (2), which is mounted on a guided projectile (1), wherein said homing device executes a detection phase until a target (C) is detected, wherein said detection phase comprises utilizing a viewing direction (3), said viewing direction (3)
1. Method for automatically managing a strapdown homing device (2), which is mounted on a guided projectile (1), wherein said homing device executes a detection phase until a target (C) is detected, wherein said detection phase comprises utilizing a viewing direction (3), said viewing direction (3) being fixed relative to the guided projectile (1) and being directed along the longitudinal axis (4) thereof, wherein a field of view during the detection phase is around the longitudinal axis (4) of said projectile (1), wherein the guided projectile (1) is subjected simultaneously to two controls designed to cause a variation on the one hand in the angle (αv) between a direction vector associated with the longitudinal axis of the guided projectile and a first projectile axis, and on the other hand in the angle (αw) between said direction vector and a second projectile axis, respectively, these two projectile axes defining a plane (P) which is perpendicular to the longitudinal axis (4) of the guided projectile (1), and the two controls are such that said angular variations (αv, αw) are oscillatory. 2. Method according to claim 1, wherein said angular variations (αv, αw) are sinusoidal. 3. The method according to claim 1, wherein the guided projectile is an air missile. 4. The method according to claim 1, wherein said angular variations (αv, αw) are sinusoidal and shifted by π/2 in order to trace a circular field of view. 5. The method according to claim 4, wherein said angular variations (αv, αw) increase over time. 6. The method according to claim 1, wherein said angular variations (αv, αw) increase over time. 7. A guided projectile provided with a strapdown homing device (2), wherein said homing device executes a detection phase during flight until a target (C) is detected, wherein said detection phase comprises utilizing a viewing direction (3), said viewing direction (3) being fixed relative to the guided projectile (1) and being directed along the longitudinal axis (4) thereof, wherein said homing device comprises automatic control means (8) for automatically controlling said guided projectile (1), wherein said automatic control means (8) are formed so as to subject the guided projectile (1) simultaneously to controls designed to cause a variation on the one hand in the angle (αv) between a direction vector associated with the longitudinal axis of the guided projectile and a first projectile axis and on the other hand in the angle (αw) between said direction vector and a second projectile axis, respectively, these two projectile axes defining a plane (P) which is perpendicular to the longitudinal axis (4) of the guided projectile (1), and in that these two controls are such that said angular variations (αv, αw) are oscillatory. 8. A guided projectile according to claim 7, wherein said angular variations (αv, αw) are sinusoidal. 9. A guided projectile according to claim 7, wherein said automatic control means (8) form part of an automatic control system (6) of said guided projectile (1). 10. A guided projectile according to claim 7, wherein the guided projectile is an air missile. 11. The guided projectile according to claim 7, wherein said angular variations (αv, αw) are sinusoidal and shifted by π/2 in order to trace a circular field of view. 12. The guided projectile according to claim 11, wherein said angular variations (αv, αw) increase over time. 13. The guided projectile according to claim 7, wherein said angular variations (αv, αw) increase over time. 14. A guided projectile provided with a strapdown homing device (2), wherein said homing device executes a detection phase during flight until a target (C) is detected, wherein said detection phase comprises utilizing a viewing direction (3), said viewing direction (3) being fixed relative to the guided projectile (1) and being directed along the longitudinal axis (4) thereof, wherein said homing device comprises automatic control means (8) for automatically controlling said guided projectile (1), wherein said automatic control means (8) are formed so as to subject the guided projectile (1) to controls designed to cause a variation on an angle (αv) between a direction vector associated with the longitudinal axis of the guided projectile and a first projectile axis, wherein the first projectile axis is perpendicular to the longitudinal axis (4) of the guided projectile (1), wherein the controls are such that said angular variation (αv) is oscillatory. 15. The guided projectile according to claim 14, wherein said angular variation (αv) increases over time.
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이 특허에 인용된 특허 (26)
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