IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0943214
(2010-11-10)
|
등록번호 |
US-8433460
(2013-04-30)
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발명자
/ 주소 |
- Recchia, Thomas
- Toledo, Wilfredo
- Cahayla, Jason
- Scheper, Eric
|
출원인 / 주소 |
- The United States of America as Represented by the Secretary of the Army
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
4 인용 특허 :
2 |
초록
▼
An onboard sensor suite generally includes two main components: a proximity sensor suite for measuring the projectile muzzle velocity; and a pressure sensor suite for measuring the projectile airspeed. The flight velocity of the projectile can then be estimated with a high degree of accuracy using e
An onboard sensor suite generally includes two main components: a proximity sensor suite for measuring the projectile muzzle velocity; and a pressure sensor suite for measuring the projectile airspeed. The flight velocity of the projectile can then be estimated with a high degree of accuracy using either the muzzle velocity by itself or the airspeed by itself, or, in a preferred embodiment, by using both the muzzle velocity and the airspeed. The proximity sensor suite includes proximity sensors that are mounted along a projectile body; a wire harness; and an onboard computer or CPU. The pressure sensor suite includes a Pitot pressure transducer and two static pressure transducers that are mounted within the projectile body; a wire harness; and a CPU.
대표청구항
▼
1. An onboard sensor suite for use in a projectile that includes a body, a forward section, and an aft section, the onboard sensor suite comprising: a proximity sensor suite that is integrated in the projectile, and that measures a projectile muzzle velocity, V, as the projectile exits a weapon muzz
1. An onboard sensor suite for use in a projectile that includes a body, a forward section, and an aft section, the onboard sensor suite comprising: a proximity sensor suite that is integrated in the projectile, and that measures a projectile muzzle velocity, V, as the projectile exits a weapon muzzle;wherein the proximity sensor suite includes a plurality of proximity sensors that are integrated in the projectile and that independently defect egress times of the plurality of proximity sensors from the weapon muzzle;wherein the plurality of proximity sensors transmit the egress times to a central processing unit that is integrated in the projectile, and wherein the central processing unit calculates the projectile muzzle velocity, V, by dividing a distance, D, that separates the plurality of proximity sensors by a difference in the egress times;a pressure sensor suite that is integrated in the projectile, and that measures an airspeed of the projectile, A, in order to estimate a flight velocity of the projectile during flight, and to predict a projectile position for improving mid-course trajectory correction;wherein the pressure sensor suite includes a plurality of pressure sensors that are integrated in the projectile, that measure a total air pressure at one location of the projectile forward section, and that further measure a static air pressure at another location of the projectile forward section; andwherein the central processing unit calculates the projectile flight velocity by comparing the total air pressure and the static air pressure. 2. The onboard sensor suite of claim 1, wherein the plurality of proximity sensors include two proximity sensors. 3. The onboard sensor suite of claim 2, wherein the two proximity sensors are disposed along the projectile body. 4. The onboard sensor suite of claim 3, wherein each proximity sensor detects the egress time from the weapon muzzle by electromagnetically detecting a forward edge of the weapon muzzle. 5. The onboard sensor suite of claim 1, wherein the proximity sensor suite further includes a wire harness that connects the plurality of proximity sensors to the central processing unit. 6. The onboard sensor suite of claim 1, wherein the plurality of proximity sensors are mounted onto the projectile body, in close proximity to weapon the muzzle from which the projectile exits. 7. The onboard sensor suite of claim 1, wherein the central processing unit is mounted in the projectile aft section. 8. The onboard sensor suite of claim 1, wherein the pressure sensor suite further includes a wire harness that connects the plurality of pressure sensors to the central processing unit. 9. The onboard sensor suite of claim 1, wherein the plurality of pressure sensors include a Pitot pressure transducer. 10. The onboard sensor suite of claim 9, wherein the Pitot pressure transducer is located along a longitudinal, central axis of symmetry of the projectile. 11. The onboard sensor suite of claim 9, wherein the plurality of pressure sensors include two static pressure transducers that are disposed at different locations along the projectile forward section. 12. The onboard sensor suite of claim 11, wherein the central processing unit calculates an average static pressure, P, by averaging the static air pressure measured by each of the two static pressure transducers, in order to compensate for an angle of attack of the projectile; and wherein the central processing unit calculates the projectile flight velocity by comparing the average static air pressure and the total air pressure, P0. 13. The onboard sensor suite of claim 11, wherein the central processing unit calculates the projectile flight velocity by determining a flow relationship between the average static air pressure, P, the total air pressure, P0, and a free stream Mach number, M, of the projectile. 14. The onboard sensor suite of claim 13, wherein the flow relationship includes a subsonic flow relationship that is illustrated by the following equation: PoP=(1-M2γ-12)γγ-1where γ is a constant that equals 1.4 for air. 15. The onboard sensor suite of claim 13, wherein the flow relationship includes a supersonic flow relationship that is illustrated by the following equation: Minf=[(1+M2γ-12)γM2-γ-12]0.5where γ is a constant that equals 1.4 for air; and wherein the central processing unit calculates a free stream Mach, Minf, and further continuously calculates the projectile airspeed, A, according to the present equation: A=Minf×Speed of sound in air.
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