[특허]Aero-wave instrument for the measurement of the optical wave-front disturbances in the airflow around airborne systems

THE BOEING COMPANY

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특허 상세정보

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Aero-wave instrument for the measurement of the optical wave-front disturbances in the airflow around airborne systems

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G06F-007/70 G06F-019/00 G06G-007/00 G06G-007/76 G01S-003/786 G01M-009/06 G01J-009/00 G02B-017/06 B64C-030/00 G01C-019/04 G02B-007/182 G02B-023/08 G02B-026/08 H04N-007/18 G02B-026/10 G02B-027/14
출원번호	US-0502015 (2014-09-30)
등록번호	US-9606214 (2017-03-28)
발명자 / 주소	Kelchner, Bryan Lee Jerkatis, Kenneth Holmes, Richard Brooks Mcnerney, Nikolaus Donaldson, Jed
출원인 / 주소	THE BOEING COMPANY
대리인 / 주소	Marshall, Gerstein & Borun LLP
인용정보	피인용 횟수 : 1 인용 특허 : 29

초록
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The aircraft includes a fuselage and at least one aerodynamic interface surface. It further includes a gimbaled mirror system which includes a mirror supported by a gimbal to receive a light beam from a light emitting source and reflect the light beam to a first periscope fold mirror. A wave front measuring system includes at least five reflective which reflects the light beam to a fast steering mirror. The fast steering mirror reflects the light beam directly to a beam splitter wherein the light beam is split into a transmitted portion and a reflected p...

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1. An aircraft, comprising: a fuselage and at least one aerodynamic interface surface;a gimbaled mirror system comprising a mirror supported by a gimbal to receive a light beam from a light emitting source and reflect the light beam to a first periscope fold mirror; anda wavefront measuring system comprising at least five reflective mirrors, comprising: a second periscope fold mirror which receives the reflected light beam directly from the first periscope fold mirror of the gimbaled mirror system,a first concave off-axis paraboloid mirror which receives the light beam reflected from the second periscope fold mirror,a first fold mirror which receives the light beam directly reflected from the first concave off-axis paraboloid mirror,a second fold mirror which receives the light beam reflected directly from the first fold mirror and a second concave off-axis paraboloid mirror which receives the light beam reflected directly from the second fold mirror, and reflects the light beam to a fast steering mirror, andwherein the fast steering mirror reflects the light beam directly to a beam splitter wherein the light beam is split into a transmitted portion and a reflected portion of the light beam. 2. The aircraft of claim 1, comprising a container for containing the gimbaled mirror system and the wavefront measuring system. 3. The aircraft of claim 1, wherein the container is secured to the aircraft. 4. The aircraft of claim 1, wherein the gimbaled mirror system and the wavefront measuring system is positioned behind a window secured to the aircraft. 5. The aircraft of claim 4, wherein the window comprises a conformal window. 6. The aircraft of claim 1, wherein the gimbaled mirror system and the wavefront measuring system is positioned at different locations on the aircraft comprising at least one of at least one of side nose barrel; dorsal mid-body, wing gun location, electro-optical targeting system location, conformal fairing, upper nose barrel and dorsal behind cockpit. 7. The aircraft of claim 1, wherein: the transmitted portion is received by a fine tracker camera coupled to an embedded processor wherein the embedded processor is coupled to the gimbaled mirror system and to the fast steering mirror to control movement of the mirror supported by the gimbal and to control movement of the fast steering mirror, andthe gimbaled mirror system and the wavefront measuring system are secured to the aircraft. 8. The aircraft of claim 7, wherein the gimbaled mirror system wherein the mirror supported by the gimbal is coupled to a gyro sensor. 9. The aircraft of claim 8, wherein the gyro sensor is coupled to the embedded processor to forward data about movement of the mirror supported by the gimbal wherein the embedded processor sends commands to the gimbal to move the mirror supported by the gimbal. 10. The aircraft of claim 7, wherein the embedded processor is coupled to the fast steering mirror and receives data from the fast steering mirror about movement of the transmitted portion of the light beam and the embedded processor sends commands to the fast steering mirror to move the fast steering mirror. 11. The aircraft of claim 1, further including a wavefront sensor receiving the reflected portion of the light beam and is coupled to another embedded processor to store data from the wavefront sensor and navigational data of the aircraft. 12. An aircraft, comprising: a fuselage and at least one aerodynamic interface surface;a gimbaled mirror system comprising a mirror supported by a gimbal to receive a light beam from a light emitting source and reflect the light beam to a wavefront measuring system comprising: a fast steering mirror which receives the light beam and reflects the light beam directly to a beam splitter, wherein the light beam is split into a transmitted portion and a reflected portion of the light beam,a fine tracker camera receives the transmitted portion and is coupled to an embedded processor,wherein the embedded processor is coupled to the gimbaled mirror system and to the fast steering mirror to control movement of the mirror supported by the gimbal and to control movement of the fast steering mirror, andwherein the gimbaled mirror system and the wavefront measuring system are secured to the aircraft. 13. The aircraft of claim 12, comprising a container for containing the gimbaled mirror system and the wavefront measuring system. 14. The aircraft of claim 13, wherein the container is secured to the aircraft. 15. The aircraft of claim 12, wherein the gimbaled mirror system and the wavefront measuring system is positioned behind a window secured to the aircraft. 16. The aircraft of claim 15, wherein the window comprises a conformal window. 17. The aircraft of claim 12, wherein the gimbaled mirror system and the wavefront measuring system is positioned at different locations on the aircraft comprising at least one of at least one of side nose barrel; dorsal mid-body, wing gun location, electro-optical targeting system location, conformal fairing, upper nose barrel and dorsal behind cockpit. 18. The aircraft of claim 12, wherein the gimbaled mirror system wherein the mirror supported by the gimbal is coupled to a gyro sensor. 19. The aircraft of claim 18, wherein the gyro sensor is coupled to the embedded processor to forward data about movement of the mirror supported by the gimbal wherein the embedded processor sends commands to the gimbal to move the mirror supported by the gimbal. 20. The aircraft of claim 12, wherein the embedded processor is coupled to the fast steering mirror and receives data from the fast steering mirror about movement of the transmitted portion of the light beam and the embedded processor sends commands to the fast steering mirror to move the fast steering mirror. 21. The aircraft of claim 12, further including a wavefront sensor receiving the reflected portion of the light beam and is coupled to another embedded processor to store data from the wavefront sensor and navigational data of the aircraft. 22. The aircraft of claim 12, further wherein the gimbaled mirror system includes a first periscope fold mirror which reflects the light beam to the wavefront measuring system comprising at least five reflective mirrors, comprising: a second periscope fold mirror which receives the reflected light beam directly from the first periscope fold mirror of the gimbaled mirror system,a first concave off-axis paraboloid mirror which receives the light beam reflected from the second periscope fold mirror,a first fold mirror which receives the light beam directly reflected from the first concave off-axis paraboloid mirror,a second fold mirror which receives the light beam reflected directly from the first fold mirror; anda second concave off-axis paraboloid mirror which receives the light beam reflected directly from the second fold mirror and reflects the light beam to the fast steering mirror. 23. A method for acquiring aero-optical disturbance data, comprising the steps of: flying an aircraft on a flight path wherein the aircraft has a gimbaled mirror system and a wavefront measuring system secured to the aircraft, wherein the gimbaled mirror system comprises: a mirror supported by a gimbal to receive a light beam from a light emitting source anda first periscope fold mirror that receives the light beam reflected from the mirror and reflects the light beam to the wavefront measuring system; andwherein the wavefront measuring system comprises at least five reflective mirrors, comprising: a second periscope fold mirror which receives the light beam directly from the first periscope fold mirror of the gimbaled mirror system,a first concave off-axis paraboloid mirror receives the light beam reflected from the second periscope fold mirror,a first fold mirror which receives the light beam reflected directly from the first concave off-axis paraboloid mirror,a second fold mirror which receives the light beam reflected directly from the first fold mirror, anda second concave off-axis paraboloid mirror which receives the light beam reflected directly from the second fold mirror and reflects the light beam to a fast steering mirror,a beam splitter receives the light beam reflected from the fast steering mirror wherein the light beam is split into a transmitted portion and a reflected portion of the light beam, anda fine tracker camera coupled to an embedded processor receives the transmitted portion of the light beam wherein the embedded processor is coupled to the gimbaled mirror system to control movement of the mirror supported by the gimbal and to the fast steering mirror to control movement of the fast steering mirror; andcollecting data regarding an aero-optic disturbance in a flow field of the aircraft with another embedded processor coupled to a wavefront sensor which receives the reflected portion of the light beam. 24. The method of claim 23 including the step of the fine tracker camera sensing movement in the transmitted portion of the light beam and in response sending a command to the fast steering mirror to move the fast steering mirror. 25. The method of claim 23 further including: the step of moving the aircraft away from the flight path toward a second flight path, wherein:the light beam moves in a field of regard of the mirror supported by the gimbal of the gimbaled mirror system and further including; wherein:the gimbal mirror system further comprises a gyro sensor coupled to the mirror supported by the gimbal and to the embedded processor such that the gyro sensor provides the embedded processor with data pertaining to movement of the mirror supported by the gimbal and the embedded processor sends commands to the gimbal to move the mirror supported by the gimbal; andthe wavefront sensor receives the reflected portion of the light beam. 26. The method of claim 25 further including the step of flying the aircraft in the second flight path wherein the wavefront sensor receives the reflected portion of the light beam. 27. The method of claim 26 further including the step of: moving the aircraft toward the flight path, wherein:the light beam moves within the field of regard for the mirror supported by the gimbal; andthe gyro sensor sends information to the embedded processor regarding movement of the mirror supported by the gimbal and the embedded processor sends control commands to the gimbal to move the mirror supported by a gimbal and the wavefront sensor receives data from the reflected portion of the light beam.

이 특허에 인용된 특허 (29)

이 특허를 인용한 특허 피인용횟수: 1

Kelchner, Bryan Lee; Jerkatis, Kenneth; Holmes, Richard Brooks; McNerney, Nikolaus; Donaldson, Jed. Aero-wave instrument for the measurement of the optical wave-front disturbances in the airflow around airborne systems. USP20180810057468.

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Aero-wave instrument for the measurement of the optical wave-front disturbances in the airflow around airborne systems

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Aero-wave instrument for the measurement of the optical wave-front disturbances in the airflow around airborne systems

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이 특허에 인용된 특허 (29)

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