[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)	G02B-026/08 H04N-005/225 F41G-003/22 H04B-010/112 G02B-007/182 G02B-017/06 G02B-023/08 G01S-003/786 G01S-007/497 G01S-017/58 G01S-017/95 G02B-026/00 G02B-027/14 G01S-017/66 G01J-009/00
출원번호	US-0501854 (2014-09-30)
등록번호	US-10057468 (2018-08-21)
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 : 0 인용 특허 : 26

초록
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An aero-optical disturbance measurement system includes a mirror supported by a gimbal for receiving a light beam from a light emitting source, reflecting the light beam to a first periscope fold mirror and therefrom reflecting the light beam directly to a second periscope fold mirror. A first concave off-axis paraboloid mirror receives the light beam reflected from second periscope fold mirror and therefrom a first fold mirror receives the light beam reflected directly from first concave off-axis paraboloid mirror. A second fold mirror receives the light beam reflected directly from the first fold mirror. A second concave off-axis paraboloid mirror receives the light beam reflected directly from second fold mirror which reflects the light beam to a fast steering mirror. A fine tracker camera coupled to an embedded processer receives portion of light beam from fast steering mirror. Embedded processor controls movement of fast steering mirror and gimbal.

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1. An aero-optical disturbance measurement system, comprising: a mirror supported by a gimbal for receiving a light beam from a light emitting source and reflecting the light beam emitted from the light emitting source to a first periscope fold mirror;a second periscope fold mirror positioned to receive the light beam reflected directly from the first periscope fold mirror;a first concave off-axis paraboloid mirror positioned to receive the light beam reflected from the second periscope fold mirror;a first fold mirror positioned to receive the light beam reflected directly from the first concave off-axis paraboloid mirror;a second fold mirror positioned to receive the light beam reflected directly from the first fold mirror;a second concave off-axis paraboloid mirror positioned to receive the light beam reflected directly from the second fold mirror and reflecting the light beam to a fast steering mirror; anda fine tracker camera coupled to an embedded processer wherein: the fine tracker camera receives a transmitted portion of the light beam from the fast steering mirror;the embedded processor is coupled to the fast steering mirror such that the embedded processor controls movement of the fast steering mirror; andthe embedded processor is coupled to the gimbal and controls the movement of the mirror supported by the gimbal. 2. The aero-optical disturbance measurement system of claim 1, further including a gyro sensor coupled to the mirror supported by the gimbal so as to sense mirror motion wherein the gyro sensor is coupled to communicate movement of the mirror supported by the gimbal to the embedded processor. 3. The aero-optical disturbance measurement system of claim 2, wherein: the mirror supported by the gimbal is positioned behind a window of an aircraft through which the light beam from the light emitting source passes; andthe window is positioned at different locations on the aircraft comprising at least one of a side nose barrel, a dorsal mid-body, a wing gun location, an electro-optical targeting system location, a conformal fairing, an upper nose barrel and a dorsal behind cockpit. 4. The aero-optical disturbance measurement system of claim 1, wherein the angle of incidence of the light beam with the first periscope fold mirror is approximately 45 degrees. 5. The aero-optical disturbance measurement system of claim 1, further including a first intermediate mirror fold mirror positioned to receive the beam of light reflected directly from the second periscope fold mirror with an angle of incidence of approximately 45 degrees and reflects the beam directly to a second intermediate fold mirror which receives the beam of light at approximately 45 degrees of incidence. 6. The aero-optical disturbance measurement system of claim 5, wherein the first concave off-axis paraboloid mirror receives the light beam directly reflected from the second intermediate fold mirror. 7. The aero-optical disturbance measurement system claim 6, wherein a first fold mirror receives the beam of light reflected directly from the first concave off-axis paraboloid mirror and reflects the beam of light directly to a second fold mirror. 8. The aero-optical disturbance measurement system of claim 7, wherein a second concave off-axis paraboloid mirror receives the light beam reflected directly from the second fold mirror. 9. The aero-optical disturbance measurement system of claim 1, wherein the fast steering mirror operates with an angular stroke length within a range of +1.5 degrees and −1.5 degrees and angular resolution of 60 deg/sec in azimuth and elevation. 27. An aero-optical disturbance measurement system, comprising: a mirror supported by a gimbal for receiving a light beam from a light emitting source and reflecting the light beam emitted from the light emitting source to a first periscope fold mirror;a second periscope fold mirror positioned to receive the light beam reflected directly from the first periscope fold mirror;a first concave off-axis paraboloid mirror positioned to receive the light beam reflected from the second periscope fold mirror;a first fold mirror positioned to receive the light beam reflected directly from the first concave off-axis paraboloid mirror;a second fold mirror positioned to receive the light beam reflected directly from the first fold mirror;a second concave off-axis paraboloid mirror positioned to receive the light beam reflected directly from the second fold mirror and reflecting the light beam to a fast steering mirror; anda beam splitter which receives the light beam reflected directly from the fast steering mirror wherein the beam splitter splits the light beam into a transmitted portion and a reflected portion. 28. The aero-optical disturbance measurement system of claim 27, wherein the angle of incidence of the light beam with the first periscope fold mirror is approximately 45 degrees. 29. The aero-optical disturbance measurement system of claim 27, further including a first intermediate mirror fold mirror positioned to receive the beam of light reflected directly from the second periscope fold mirror with an angle of incidence of approximately 45 degrees and reflects the beam directly to a second intermediate fold mirror which receives the beam of light at approximately 45 degrees of incidence. 30. The aero-optical disturbance measurement system of claim 29, wherein the first concave off-axis paraboloid mirror receives the light beam directly reflected from the second intermediate fold mirror. 31. The aero-optical disturbance measurement system claim 30, wherein a first fold mirror receives the beam of light reflected directly from the first concave off-axis paraboloid mirror and reflects the beam of light directly to a second fold mirror. 32. The aero-optical disturbance measurement system of claim 31, wherein a second concave off-axis paraboloid mirror receives the light beam reflected directly from the second fold mirror. 33. The aero-optical disturbance measurement system of claim 27, further including a fine tracker camera coupled to an embedded processer wherein: the fine tracker camera receives the transmitted portion of the light beam from the fast steering mirror;the embedded processor is coupled to the fast steering mirror such that the embedded processor controls movement of the fast steering mirror; andthe embedded processor is coupled to the gimbal and controls the movement of the mirror supported by the gimbal. 34. The aero-optical disturbance measurement system of claim 33, further including a gyro sensor coupled to the mirror supported by the gimbal so as to sense mirror motion wherein the gyro sensor is coupled to communicate movement of the mirror supported by the gimbal to the embedded processor. 35. The aero-optical disturbance measurement system of claim 34, wherein: the mirror supported by the gimbal is positioned behind a window of an aircraft through which the light beam from the light emitting source passes; and the window is positioned at different locations on the aircraft comprising at least one of a side nose barrel, a dorsal mid-body, a wing gun location, an electro-optical targeting system location, a conformal fairing, an upper nose barrel and a dorsal behind cockpit. 36. The aero-optical disturbance measurement system of claim 33, wherein the fast steering mirror operates with an angular stroke length within a range of +1.5 degrees and −1.5 degrees and angular resolution of 60 deg/sec in azimuth and elevation. 42. The aero-optical disturbance measurement system of claim 27, further including a first wavefront sensor fold mirror receiving the reflected portion directly from the beam splitter and directly reflecting the reflected portion to an achromatic pupil relay. 43. The aero-optical disturbance measurement system of claim 42, further including a wavefront sensor comprising a lenslet array positioned to receive the reflected portion directly from the achromatic pupil relay and focusing the reflected portion to a focal plane array camera. 44. The aero-optical disturbance measurement system of claim 43, further including: another embedded processor coupled to the wavefront sensor which collects data from the wavefront sensor and navigational data generated by an aircraft; andthe disturbance measurement system containing the wavefront sensor is configured to conformally mount to the aircraft. 45. The aero-optical disturbance measurement system of claim 43, wherein the array comprises a set of lenslets of at least 16 by 16. 46. An aero-optical disturbance measurement system, comprising: a mirror supported by a gimbal for receiving a light beam from a light emitting source and reflecting the light beam emitted from the light emitting source to a fast steering mirror;a beam splitter which receives the light beam reflected directly from the fast steering mirror wherein the beam splitter splits the light beam into a transmitted portion and a reflected portion; anda fine tracker camera coupled to an embedded processer wherein: the fine tracker camera receives the transmitted portion of the light beam from the fast steering mirror;the embedded processor is coupled to the fast steering mirror such that the embedded processor controls movement of the fast steering mirror; andthe embedded processor is coupled to the gimbal and controls the movement of the mirror supported by the gimbal. 47. The aero-optical disturbance measurement system of claim 46, further includes: a first periscope fold mirror receiving the light beam source directly from the mirror supported by the gimbal;a second periscope fold mirror positioned to receive the light beam reflected directly from the first periscope fold mirror;a first concave off-axis paraboloid mirror positioned to receive the light beam reflected from the second periscope fold mirror;a first fold mirror positioned to receive the light beam reflected directly from the first concave off-axis paraboloid mirror;a second fold mirror positioned to receive the light beam reflected directly from the first fold mirror; anda second concave off-axis paraboloid mirror positioned to receive the light beam reflected directly from the second fold mirror and reflecting the light beam to the fast steering mirror. 48. The aero-optical disturbance measurement system of claim 47, wherein the angle of incidence of the light beam with the first periscope fold mirror is approximately 45 degrees. 49. The aero-optical disturbance measurement system of claim 47, further including a first intermediate mirror fold mirror positioned to receive the beam of light reflected directly from the second periscope fold mirror with an angle of incidence of approximately 45 degrees and reflects the beam directly to a second intermediate fold mirror which receives the beam of light at approximately 45 degrees of incidence. 50. The aero-optical disturbance measurement system of claim 49, wherein the first concave off-axis paraboloid mirror receives the light beam directly reflected from the second intermediate fold mirror. 51. The aero-optical disturbance measurement system claim 50 wherein a first fold mirror receives the beam of light reflected directly from the first concave off-axis paraboloid mirror and reflects the beam of light directly to a second fold mirror. 52. The aero-optical disturbance measurement system of claim 51 wherein a second concave off-axis paraboloid mirror receives the light beam reflected directly from the second fold mirror. 53. The aero-optical disturbance measurement system of claim 46 wherein the fast steering mirror operates with an angular stroke length within a range of +1.5 degrees and −1.5 degrees and angular resolution of 60 deg/sec in azimuth and elevation. 61. The aero-optical disturbance measurement system of claim 46, further including a first wavefront sensor fold mirror receiving the reflected portion directly from the beam splitter and directly reflecting the reflected portion to an achromatic pupil relay. 62. The aero-optical disturbance measurement system of claim 61, further including a wavefront sensor comprising a lenslet array positioned to receive the reflected portion directly from the achromatic pupil relay and focusing the reflected portion to a focal plane array camera. 63. The aero-optical disturbance measurement system of claim 62, further including: another embedded processor coupled to the wavefront sensor which collects data from the wavefront sensor and navigational data generated by an aircraft; and the disturbance measurement system containing the wavefront sensor is configured to conformally mount to an aircraft. 64. The aero-optical disturbance measurement system of claim 62, wherein the array comprises a set of lenslets of at least 16 by 16.

이 특허에 인용된 특허 (26)

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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 (26)

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