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1.发明申请AERO-WAVE INSTRUMENT FOR THE MEASUREMENT OF THE OPTICAL WAVE-FRONT DISTURBANCES IN THE AIRFLOW AROUND AIRBORNE SYSTEMS 审中-公开用于测量AIRBORNE系统中的气流中的光波前扰动的AERO-WAVE INSTRUMENT公开(公告)号：US20160255253A1
公开(公告)日：2016-09-01
申请号：US14501854
申请日：2014-09-30
申请人： THE BOEING COMPANY
发明人： Bryan Lee Kelchner , Kenneth Jerkatis , Richard Brooks Holmes , Nikolaus McNerney , Jed Donaldson
CPC分类号： H04N5/2254 , F41G3/22 , G01J2009/002 , G01S3/786 , G01S7/497 , G01S17/58 , G01S17/66 , G01S17/95 , G02B7/1821 , G02B17/0605 , G02B23/08 , G02B26/008 , G02B26/0816 , G02B27/14 , H04B10/112 , H04B10/1125 , Y02A90/19
摘要： 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.
摘要翻译： 航空光学干扰测量系统包括由云台支撑的反射镜，用于接收来自发光源的光束，将光束反射到第一潜望镜折射镜，并将光束直接反射到第二潜望镜折射镜。 第一凹入离轴抛物面镜接收从第二潜望镜折射镜反射的光束，并且由此第一折射镜接收从第一凹入离轴抛物面反射镜直接反射的光束。 第二折叠镜接收直接从第一折叠镜反射的光束。 第二凹轴离轴抛物面镜接收从第二折射镜直接反射的光束，其将光束反射到快速转向镜。 耦合到嵌入式处理器的精细跟踪摄像机接收来自快速转向镜的光束的一部分。 嵌入式处理器控制快速转向镜和万向节的运动。
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2.发明申请AERO-WAVE INSTRUMENT FOR THE MEASUREMENT OF THE OPTICAL WAVE-FRONT DISTURBANCES IN THE AIRFLOW AROUND AIRBORNE SYSTEMS 有权用于测量AIRBORNE系统中的气流中的光波前扰动的AERO-WAVE INSTRUMENT公开(公告)号：US20160252603A1
公开(公告)日：2016-09-01
申请号：US14502015
申请日：2014-09-30
申请人： The Boeing Company
发明人： Bryan Lee Kelchner , Kenneth Jerkatis , Richard Brooks Holmes , Nikolaus Mcnerney , Jed Donaldson
IPC分类号： G01S3/786 , G02B23/08 , G02B17/06 , G01J9/00 , H04N7/18 , B64C30/00 , G01C19/04 , G02B7/182 , G02B26/08
CPC分类号： G01S3/786 , B64C30/00 , G01C19/04 , G01J9/00 , G01M9/06 , G02B7/1821 , G02B17/061 , G02B17/0657 , G02B17/0663 , G02B23/08 , G02B26/0816 , G02B26/105 , G02B27/14 , H04N7/183
摘要： 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 portion of the light beam.
摘要翻译： 飞机包括机身和至少一个空气动力学界面。 它还包括万向反射镜系统，其包括由万向节支撑的反射镜，以接收来自发光源的光束并将光束反射到第一潜望镜折射镜。 波前测量系统包括将光束反射到快速转向镜的至少五个反射镜。 快速转向镜将光束直接反射到分束器，其中光束被分裂成光束的透射部分和反射部分。
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公开(公告)号：US10057468B2
公开(公告)日：2018-08-21
申请号：US14501854
申请日：2014-09-30
申请人： THE BOEING COMPANY
发明人： Bryan Lee Kelchner , Kenneth Jerkatis , Richard Brooks Holmes , Nikolaus McNerney , Jed Donaldson
IPC分类号： G02B26/08 , H04N5/225 , F41G3/22 , H04B10/112 , G02B7/182 , G02B17/06 , G02B23/08 , G01S3/786 , G01S7/497 , G01S17/58 , G01S17/95 , G02B26/00 , G02B27/14 , G01S17/66 , G01J9/00
CPC分类号： H04N5/2254 , F41G3/22 , G01J2009/002 , G01S3/786 , G01S7/497 , G01S17/58 , G01S17/66 , G01S17/95 , G02B7/1821 , G02B17/0605 , G02B23/08 , G02B26/008 , G02B26/0816 , G02B27/14 , H04B10/112 , H04B10/1125 , Y02A90/19
摘要： 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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公开(公告)号：US09606214B2
公开(公告)日：2017-03-28
申请号：US14502015
申请日：2014-09-30
申请人： THE BOEING COMPANY
发明人： Bryan Lee Kelchner , Kenneth Jerkatis , Richard Brooks Holmes , Nikolaus Mcnerney , Jed Donaldson
IPC分类号： G06F7/70 , G06F19/00 , G06G7/00 , G06G7/76 , G01S3/786 , G01M9/06 , G01J9/00 , G02B17/06 , B64C30/00 , G01C19/04 , G02B7/182 , G02B23/08 , G02B26/08 , H04N7/18 , G02B26/10 , G02B27/14
CPC分类号： G01S3/786 , B64C30/00 , G01C19/04 , G01J9/00 , G01M9/06 , G02B7/1821 , G02B17/061 , G02B17/0657 , G02B17/0663 , G02B23/08 , G02B26/0816 , G02B26/105 , G02B27/14 , H04N7/183
摘要： 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 portion of the light beam.
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