WO2023124439A1 - 一种采用激光干涉探测的星模拟系统振动抑制系统及方法 - Google Patents

一种采用激光干涉探测的星模拟系统振动抑制系统及方法 Download PDF

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WO2023124439A1
WO2023124439A1 PCT/CN2022/126303 CN2022126303W WO2023124439A1 WO 2023124439 A1 WO2023124439 A1 WO 2023124439A1 CN 2022126303 W CN2022126303 W CN 2022126303W WO 2023124439 A1 WO2023124439 A1 WO 2023124439A1
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beam splitter
star
light
mirror
detection
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PCT/CN2022/126303
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French (fr)
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李金鹏
王鑫蕊
杨永兴
王赛亚
马永
张景源
韩宇
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中科院南京天文仪器有限公司
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Publication of WO2023124439A1 publication Critical patent/WO2023124439A1/zh

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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
    • G01C25/00—Manufacturing, calibrating, cleaning, or repairing instruments or devices referred to in the other groups of this subclass
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation

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  • the invention relates to the technical field of spacecraft calibration, in particular to a vibration suppression system and method for a star simulation system using laser interference detection.
  • the star sensor is the most accurate space attitude optical sensor to determine the position of the spacecraft. It has been widely used in the aerospace field.
  • the star sensor is essentially a camera, which is connected with the satellite onboard computer to obtain the star within its field of view. image, and then identify the stars observed by the camera, so as to calculate the flight position deviation and attitude deviation of the spacecraft in real time, so that the spacecraft can be corrected according to the deviation data provided by it.
  • the star simulator can strictly simulate the characteristics of the brightness, opening angle and distance of stars in the real starry sky, and improve the recognition target for the star sensor. Due to the difference between the laboratory development environment and the space orbit operation environment, there is an error in the orbit operation of the star sensor.
  • the star simulator is an environmental simulation technology implemented to calibrate this deviation.
  • the performance of the star simulator is related to the external environment. Due to the disturbance in the external environment, in order to improve the accuracy of ground calibration, it is necessary to perform vibration compensation correction on the optical path of the star simulator. In traditional star simulators, the vibration compensation and correction system is separated from the star simulation system. Compensation and correction must be performed first, followed by star map simulation. The operation process is cumbersome and has large errors.
  • the present invention proposes a star simulation system vibration suppression system and method using laser interferometric detection, which can realize the vibration correction of the optical path through the vibration compensation mirror under the same device system , and can image a star map on the target surface of the star sensor.
  • a star simulation system vibration suppression system using laser interferometric detection including a laser light source, a first beam splitter, a collimator mirror group, a second beam splitter mirror, a reflection mirror, a detection and convergence mirror group, a CCD detector, and a computer control system , jitter compensation mirror, flat beam splitter;
  • the optical path of the whole system includes a reference optical path and a detection compensation signal optical path, where:
  • Reference optical path The light emitted by the laser source passes through the first beam splitter and reaches the collimating mirror to form a parallel first beam, and the first beam passes through the second beam splitter to the reflector, and is reflected by the reflector to form the second beam to reach the detection converging mirror group, the outgoing light converges on the CCD detector to form a reference optical path;
  • the parallel first beam transmits the second beam splitter to form the third beam
  • the third beam is reflected by the shake compensation mirror and propagates to the plate beam splitter
  • the reflected beam reflected by the plate beam splitter passes through the shake compensation mirror to the second splitter
  • the fourth beam is reflected by the beam mirror, and the fourth beam propagates to the detection converging lens group and converges on the CCD detector to form a detection compensation signal optical path
  • Both the CCD detector and the shake compensation mirror are connected to the computer control system; the reference optical path and the detection compensation signal optical path converge on the CCD detector at the same time to form a vibration detection interference optical path, and the computer control system is formed according to the vibration detection interference optical path. Feedback compensation for changes in the intensity of the interferogram.
  • first star-point differentiation plate also includes a first light source, a first star-point differentiation plate, a second light source, a second star-point differentiation plate, a star sensor, a fifth light beam formed by illuminating the first star-point differentiation plate by the first light source, and a fifth light beam formed by the first star-point differentiation plate.
  • the sixth light beam formed by the second light source irradiating the second star point differentiation plate passes through the optical system corrected by the jitter compensation mirror, and forms a stable star simulation image on the target surface of the star sensor.
  • the first beam splitter includes a first beam splitter inside the first beam splitter and a second beam splitter at the bottom of the first beam splitter
  • the second beam splitter includes a second beam splitter inside the second beam splitter splitting surface
  • the light emitted by the laser light source is transmitted through the first beam splitting surface to the second beam splitting surface for total reflection to the first beam splitting surface, and reflected to the collimating mirror by the first beam splitting surface of the first beam splitter mirror
  • the parallel first beam is formed, and the first beam is reflected by the splitting surface of the second beam splitter to reach the mirror, and the second beam is reflected by the mirror to reach the detection converging lens group, and the outgoing light is converged on the CCD detector to form a reference optical path .
  • the parallel first beam transmits the beam splitting surface of the second beam splitter to form a third beam
  • the third beam is reflected by the shake compensation mirror and propagated to the plate beam splitter, reflected by the plate beam splitter, and reflected
  • the beam passes through the jitter compensation mirror to the second beam splitter, and is reflected by the splitting surface of the second beam splitter to form a fourth beam.
  • the fourth beam propagates to the detection and converging mirror group and converges on the CCD detector to form a detection and compensation signal optical path.
  • an imaging mirror group is also included, and the imaging mirror group is arranged between the laser light source and the first beam splitter mirror.
  • the first beam splitting surface of the first beam splitter is coated with a semi-transparent and semi-reflective film for the light emitted by the laser light source
  • the second beam splitting surface of the first beam splitter is coated with a full reflection film for the light emitted by the laser light source
  • the beam splitting surface of the second beam splitter is coated with a semi-transparent and semi-reflective film on the light emitted by the laser light source
  • the reflective mirror, the shake compensation mirror and the flat beam splitter are coated with a total reflection film on the light emitted by the laser light source
  • the first light splitting surface of a beam splitter is coated with a fully transparent film for the light emitted by the first light source, and the light emitted by the second light source is coated with a total reflection film
  • the light splitting face of the second beam splitter is coated with the first light source and the second light source.
  • the light emitted by the light source is uniformly coated with a fully transparent film; the light emitted by the first light source and
  • the aperture of the plate beam splitter is smaller than the light aperture of the star sensor.
  • the plate beam splitter reflects the vibration compensation signal light; Both sides of the transmission propagate to the star sensor.
  • a method for suppressing vibration of a star simulation system using laser interferometric detection The change in the intensity of the interference pattern formed by the two light paths of the reference light path and the detection compensation signal light path is measured by a CCD detector, and the amount of external vibration is calculated by a computer control system.
  • control the vibration compensation mirror to perform feedback compensation, and at the same time compensate and correct the vibration caused by the environment simulation system on the basis of star map simulation, offset the vibration effect of the light beam due to the vibration of the lens group, so that the first light source illuminates the first star
  • the fifth light beam formed by the point differentiation plate and the sixth light beam formed by the second star point differentiation plate irradiated by the second light source form a stable star simulation image on the target surface of the star sensor through the optical system corrected by the shake compensation mirror.
  • the present invention has the remarkable advantages that the shake compensation technology of the traditional star simulator is separated from the star map imaging technology, which causes the device system to be too complicated and the star map imaging operation to be too cumbersome, while the system and method increase the
  • the laser light source and the second beam splitter can realize star simulation imaging and at the same time perform optical path shake compensation and correction, thereby improving the accuracy of spacecraft attitude tracking and correction.
  • Figure 1 is a schematic diagram of the total optical path of the system
  • Fig. 2 is a schematic diagram of the reference light path
  • Fig. 3 is a schematic diagram of the detection and compensation signal optical path.
  • the vibration suppression system of the star simulation system using laser interferometric detection in this embodiment is shown in Figure 1.
  • This system mainly integrates the interference system in the star simulator system.
  • the system mainly includes a laser light source 1, a first beam splitter 2, an imaging mirror group 3, a collimator mirror group 4, a second beam splitter mirror 5, a reflector 6, a detecting and converging mirror group 7, a CCD detector 8, and computer control System 9 , shake compensation mirror 10 , flat beam splitter 11 , first light source 12 , first star point splitting plate 13 , second light source 14 , second star point splitting plate 15 , and star sensor 16 .
  • the beam splitting surface 1 of the first beam splitter is coated with a semi-transparent and semi-reflective film for the light emitted by the laser
  • the beam splitting surface 2 of the first beam splitter is coated with a total reflection film for the light emitted by the laser
  • the beam splitting surface of the second beam splitter The light emitted by the laser is coated with a semi-transparent and semi-reflective film
  • the mirror, the shake compensation mirror and the flat beam splitter are coated with a full-reflection film for the light emitted by the laser
  • the first beam splitter is coated with a fully transparent film for the light emitted by the light source 1, and the light source 2
  • the emitted light is coated with a total reflection film
  • the second beam splitter coats the light emitted by the light source 1 and the light source 2 with a fully transparent film
  • the flat beam splitter coats the light emitted by the light source 1 and the light source 2 with a fully transparent film; through this coating and the light path
  • the optical path of the whole system can be divided into two parts, which are the reference optical path and the detection compensation signal optical path.
  • the reference optical path and detection compensation signal optical path are as follows:
  • the reference optical path is shown in Figure 2: the light emitted by the laser light source is transmitted through the first beam splitter, reaches the splitting surface 2 of the first beam splitting mirror, is totally reflected to the splitting face 1 of the first beam splitting mirror, and is reflected to the collimating mirror The parallel first beam is formed and emitted, the first beam is reflected by the second beam splitter and reaches the mirror, and the second beam is reflected by the mirror to reach the detection converging mirror group, and the outgoing light is converged on the CCD detector to form a reference optical path;
  • the detection and compensation signal optical path is shown in Figure 3: the parallel first beam transmits the second beam splitter to form the third beam, the third beam is reflected by the jitter compensation mirror and propagates to the plate beam splitter, reflected by the plate beam splitter, and the reflected beam is jitter compensated
  • the mirror is reflected by the second beam splitter to form a fourth light beam, and the fourth light beam propagates to the detection converging mirror group and converges on the CCD detector to form a detection and compensation signal optical path.
  • the reference light path and the detection compensation signal light path converge on the CCD detector 8 at the same time to form a vibration detection interference light path, and feedback compensation is performed according to the intensity change of the interference pattern formed by the vibration detection interference light path.
  • the aperture of the flat mirror is smaller than the aperture of the star sensor.
  • the vibration suppression method of the star simulation system in this embodiment is as follows: measure the change in the intensity of the interference pattern formed by the reference light path and the detection compensation signal light through the CCD detector 8, calculate the external vibration amount through the computer control system, and control the vibration
  • the compensation mirror performs feedback compensation, and then offsets the vibration effect of the light beam due to the vibration of the lens group, so that the first star point differentiation plate 13 illuminated by the first light source 12 and the second star point differentiation plate 15 illuminated by the second light source 14 form
  • the fifth light beam and the sixth light beam pass through the optical system corrected by the shake compensation mirror 10, and form a stable star simulation image at the target surface of the star sensor 16.
  • This method can realize the compensation and correction of the vibration caused by the environment simulation system on the basis of the star map simulation.
  • a star simulation system vibration suppression system and method using laser interference detection the whole system is placed on the same optical platform to isolate the ground vibration, the detection compensation optical path and the star simulation optical path have no vibration between each other, and the external vibration affects the two optical paths. The influence is the same.
  • the interference reference optical path can detect external vibrations.
  • the impact of the optical element vibration caused by external environmental disturbances on the beam can be directly measured, so as to control the vibration compensation mirror to compensate in a targeted manner and improve star simulation.
  • this embodiment proposes a star simulation system vibration suppression system using laser interference detection.
  • the light emitted by the laser light source transmits the first beam splitter, is totally reflected by the second beam splitter surface of the first beam splitter, propagates to the second beam splitter, and then is reflected and transmitted by the second beam splitter to form two optical paths, wherein The second light beam reflected by the mirror is used as the reference light path, and the fourth light beam reflected by the plate beam splitter and the shake compensation mirror is used as the detection and compensation signal light.
  • the CCD detector detects the two paths of light at the same time.
  • the external vibration amount is calculated by the computer control system, and the vibration compensation mirror is controlled to perform feedback compensation, thereby offsetting the vibration effect of the light beam due to the vibration of the lens group; 2.
  • the optical path formed by the shake correction optical system can form a star map with better imaging quality on the target surface of the star sensor.
  • the present invention provides a star simulation system vibration suppression system and method using laser interference detection.
  • the main components of the device include a laser light source, a beam splitter, a star reticle, an imaging mirror group, and a collimating mirror group , Reflector, jitter compensation mirror, flat beam splitter, detection converging mirror group, CCD detector, first light source, second light source, star sensor, computer control system.
  • This method can realize the jitter compensation and correction of the star simulation system on the basis of the star map simulation;
  • the beam mirror reflection and transmission are divided into reference light and detection compensation signal light.
  • the reference light and detection compensation signal light converge to the CCD to form interference fringes.
  • the external vibration is calculated by the computer control system.
  • Control the jitter compensation mirror to perform feedback compensation, so that the optical path formed by the star point differentiation plate 1 and the star point differentiation plate 2 irradiated by the light source can form a stable star map on the target surface of the star sensor after the jitter correction of the optical system.

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Abstract

一种采用激光干涉探测的星模拟系统振动抑制系统及方法。采用激光干涉探测的星模拟系统振动抑制系统包括激光光源（1）、第一分束镜（2）、准直镜组（4）、第二分束镜（5）、反射镜（6）、探测会聚镜组（7）、CCD探测器（8）、计算机控制系统（9）、抖动补偿镜（10）、平板分光镜（11）；整个系统的光路包括参考光路和探测补偿信号光路。参考光路与探测补偿信号光路同时会聚在CCD探测器（8）上组成振动探测干涉光路，计算机控制系统（9）根据振动探测干涉光路形成的干涉图强度变化进行反馈补偿。CCD探测器（8）和抖动补偿镜（10）均与计算机控制系统（9）相连。采用激光干涉探测的星模拟系统振动抑制系统通过增加激光光源（1）及第二分束镜（5），既可以进行星模拟成像，又进行了光路抖动补偿校正，从而提高了航天器姿态跟踪校正的精度。

Description

一种采用激光干涉探测的星模拟系统振动抑制系统及方法 技术领域
本发明涉及到航天器标定技术领域，尤其涉及一种采用激光干涉探测的星模拟系统振动抑制系统及方法。
背景技术
星敏感器是确定航天器位置最精确的空间姿态光学敏感器,在航天领域得到了广泛的应用，星敏感器本质上是一个照相机，与卫星机载计算机相连，获得在其视野范围内的星图图像，然后识别由相机观测到的恒星，从而以此为参考实时计算出航天器的飞行位置偏差和姿态偏差，这样航天器可以根据其提供的偏差数据随后进行校正。
星模拟器作为实验室环境中对星敏感器进行检测及地面标定的重要部分，能够严格模拟真实星空中的恒星的亮度、张角及距离等特征，为星敏感器提高识别目标。由于实验室研制环境与空间轨道运行环境不一样，使得星敏感器在轨运行中存在误差，星模拟器是为了标定这一偏差而实施的一种环境模拟技术。同时星模拟器性能与外部环境有关，由于外部环境存在扰动，为了提升地面标定的精度，需要对星模拟器光路进行振动补偿校正。传统的星模拟器一般都是振动补偿校正系统和星模拟系统分隔开，使用时需先进行补偿校正，然后进行星图模拟，操作过程比较繁琐，且误差较大。
发明内容
这对现有技术中存在的上述问题，本发明提出了一种采用激光干涉探测的星模拟系统振动抑制系统及方法，可实现在同一个装置系统下既可以通过抖动补偿镜对光路进行抖动校正，又可以在星敏感器靶面成像星图。
为了实现上述目的，本发明采用如下技术方案：
一种采用激光干涉探测的星模拟系统振动抑制系统，包括激光光源、第一分束镜、准直镜组、第二分束镜、反射镜、探测会聚镜组、CCD探测器、计算机控制系统、抖动补偿镜、平板分光镜；整个系统的光路包括参考光路和探测补偿信号光路，其中：
参考光路：激光光源发出的光经第一分束镜到达准直镜组成平行第一光束射出，第一光束经第二分束镜到达反射镜，经反射镜反射形成第二光束到达探测会 聚镜组，出射光会聚在CCD探测器上，组成参考光路；
探测补偿信号光路：平行第一光束透射第二分束镜形成第三光束，第三光束经抖动补偿镜反射传播至平板分光镜，经过平板分光镜反射的反射光束经抖动补偿镜至第二分束镜反射形成第四光束，第四光束传播至探测会聚镜组会聚在CCD探测器上，组成探测补偿信号光路；
所述CCD探测器和抖动补偿镜均与计算机控制系统相连；所述参考光路与探测补偿信号光路同时会聚在CCD探测器上组成振动探测干涉光路，所述计算机控制系统根据振动探测干涉光路形成的干涉图强度变化进行反馈补偿。
进一步的，还包括第一光源、第一星点分化板、第二光源，第二星点分化板、星敏感器，由第一光源照射第一星点分化板形成的第五光束和由第二光源照射第二星点分化板形成的第六光束通过抖动补偿镜校正后的光学系统，在星敏感器靶面处，形成稳定的星模拟图。
进一步的，所述第一分束镜包括第一分束镜内部的第一分光面和第一分束镜底部的第二分光面，所述第二分束镜包括第二分束镜内部的分光面。
进一步的，所述参考光路中，激光光源发出的光透射过第一分光面到达第二分光面进行全反射至第一分光面，经第一分束镜的第一分光面反射至准直镜组成平行第一光束射出，第一光束被第二分束镜的分光面反射到达反射镜，经反射镜反射形成第二光束到达探测会聚镜组，出射光会聚在CCD探测器上，组成参考光路。
进一步的，所述探测补偿信号光路中，平行第一光束透射第二分束镜的分光面形成第三光束，第三光束经抖动补偿镜反射传播至平板分光镜，经过平板分光镜反射，反射光束经抖动补偿镜至第二分束镜，由第二分束镜的分光面反射形成第四光束，第四光束传播至探测会聚镜组会聚在CCD探测器上，组成探测补偿信号光路。
进一步的，还包括成像镜组，所述成像镜组设置于激光光源和第一分束镜之间。
进一步的，所述第一分束镜的第一分光面针对激光光源发出的光镀半透半反膜，所述第一分束镜的第二分光面对激光光源发出的光镀全反膜；所述第二分束镜的分光面对激光光源发出的光镀半透半反膜；所述反射镜、抖动补偿镜以及平 板分光镜对激光光源发出的光镀全反膜；所述第一分束镜的第一分光面对第一光源发出的光镀全透膜，对第二光源发出的光镀全反膜；所述第二分束镜的分光面对第一光源和第二光源发出的光均镀全透膜；所述平板分光镜对第一光源和第二光源发出的光均镀全透膜。
进一步的，所述平板分光镜的口径比星敏感器的通光口径小，一方面平板分光镜对振动补偿信号光进行反射，另一方面第一光源和第二光源发出的光从平板分光镜的两边透射传播至星敏感器。
一种采用激光干涉探测的星模拟系统振动抑制方法，通过CCD探测器测量出所述的参考光路和探测补偿信号光路两路光形成的干涉图强度的变化，经计算机控制系统计算出外部振动量，控制抖动补偿镜进行反馈补偿，在星图模拟的基础上同时对环境模拟系统造成的振动进行补偿校正，抵消光束由于透镜组的震动而产生的抖动影响，使得由第一光源照射第一星点分化板形成的第五光束和由第二光源照射第二星点分化板形成的第六光束通过抖动补偿镜校正后的光学系统，在星敏感器靶面处，形成稳定的星模拟图。
本发明与现有技术相比，显著优点为：传统星模拟器的抖动补偿技术和星图成像技术是分开的，造成装置系统过于复杂，星图成像操作过于繁琐，而该系统及方法通过增加激光光源及第二分束镜从而实现在既可以进行星模拟成像同时又进行了光路抖动补偿校正，从而提高了对航天器姿态跟踪校正的精度。
附图说明
图1是系统的总光路示意图；
图2是参考光路示意图；
图3是探测补偿信号光路示意图。
具体实施方式
下面结合附图对本发明的具体实施方式以及工作原理作进一步详细说明。
本实施例采用激光干涉探测的星模拟系统振动抑制系统如图1所示，该系统主要是在星模拟器系统中集成了干涉系统。该系统主要包括激光光源1、第一分束镜2、成像镜组3、准直镜组4、第二分束镜5、反射镜6、探测会聚镜组7、CCD探测器8、计算机控制系统9、抖动补偿镜10、平板分光镜11、第一光源12、第一星点分化板13、第二光源14、第二星点分化板15、星敏感器16。
其中第一分束镜的分光面1针对激光发出的光镀半透半反膜，第一分束镜的分光面2对激光发出的光镀全反膜；第二分束镜的分光面对激光发出的光镀半透半反膜；反射镜、抖动补偿镜以及平板分光镜对激光发出的光镀全反膜；第一分束镜对光源1发出的光镀全透膜，对光源2发出的光镀全反膜；第二分束镜对光源1和光源2发出的光镀全透膜，平板分光镜对光源1和光源2发出的光镀全透膜；通过这种镀膜和光路设计，实现在星图模拟的基础上同时对星模拟系统进行抖动补偿校正。
整个系统的光路可以分为两部分，分别是参考光路、探测补偿信号光路。参考光路和探测补偿信号光路如下：
参考光路如图2所示：激光光源发出的光透射过第一分束镜到达第一分束镜的分光面2进行全反射至第一分束镜的分光面1，经反射至准直镜组成平行第一光束射出，第一光束被第二分束镜反射到达反射镜，经反射镜反射形成第二光束到达探测会聚镜组，出射光会聚在CCD探测器上，组成参考光路；
探测补偿信号光路如图3所示：平行第一光束透射第二分束镜形成第三光束，第三光束经抖动补偿镜反射传播至平板分光镜，经过平板分光镜反射，反射光束经抖动补偿镜至第二分束镜反射形成第四光束，第四光束传播至探测会聚镜组会聚在CCD探测器上，组成探测补偿信号光路。
参考光路与探测补偿信号光路同时会聚在CCD探测器8上组成振动探测干涉光路，根据振动探测干涉光路形成的干涉图强度变化进行反馈补偿。
本实施例中，平板反射镜口径比星敏感器通光口径小，通过对平板分光镜进行镀膜，可以使得振动补偿信号光反射，光源1和光源2发出的光从两边透射传播至星敏感器进行星图成像两种功能。
本实施例的星模拟系统的振动抑制方法为：通过CCD探测器8测量出参考光路和探测补偿信号光两路光形成的干涉图强度的变化，经计算机控制系统计算出外部振动量，控制抖动补偿镜进行反馈补偿，进而抵消光束由于透镜组的震动而产生的抖动影响，使得由第一光源12照射的第一星点分化板13和第二光源14照射的第二星点分化板15形成的第五光束和第六光束通过抖动补偿镜10校正后的光学系统，在星敏感器16靶面处，形成稳定的星模拟图。该方法可实现在星图模拟的基础上同时对环境模拟系统造成的振动进行补偿校正。
本实施例一种采用激光干涉探测的星模拟系统振动抑制系统及方法，整个系统放置在同一光学平台上隔绝地面震动，探测补偿光路与星模拟光路相互之间无振动，外部振动对两个光路影响是等同的，干涉参考光路可以探测外部振动，在标定过程中可以直接测量出由于外部环境扰动造成的光学元件抖动对于光束的影响，从而控制抖动补偿镜有针对性的进行补偿，提高星模拟器整个装置地面标定的精度；并且在装置进行抖动补偿的同时，光源1和光源2直接照射第一星点分划板和第二星点分划板在星敏感器靶面处进行星图成像。
针对目前星模拟器装置没有抖动补偿技术和多视场、多功能星图成像的装置系统，本实施例提出一种采用激光干涉探测的星模拟系统振动抑制系统。通过激光光源发出的光透射第一分束镜，经第一分束镜的第二分光面全反射传播至第二分束镜，后经第二分束镜反射和透射形成两路光路，其中经反射镜反射的第二光束作为参考光路，经平板分光镜和抖动补偿镜反射的第四光束作为探测补偿信号光，CCD探测器同时探测到这两路光，根据两路光形成的干涉图强度变化，经计算机控制系统计算出外部振动量，控制抖动补偿镜进行反馈补偿，进而抵消光束由于透镜组的震动而产生的抖动影响；从而使得光源照射的星点分化板1和星点分化板2形成的光路，经过抖动校正后的光学系统可在星敏感器靶面处形成成像质量较好的星图。
本发明说明书中未作详细描述的内容属本领域专业技术人员的公知技术。
综上所述，本发明提供了一种采用激光干涉探测的星模拟系统振动抑制系统及方法，装置主要部件包括激光光源，分束镜，星点分划板，成像镜组，准直镜组，反射镜，抖动补偿镜，平板分光镜，探测会聚镜组，CCD探测器，第一光源，第二光源，星敏感器，计算机控制系统。该方法可实现在星图模拟的基础上同时对星模拟系统进行抖动补偿校正；通过激光光源发出的光经第一分束镜传播至准直镜组，出射的平行第一光束经第二分束镜反射和透射分成参考光和探测补偿信号光，参考光与探测补偿信号光会聚到CCD处形成干涉条纹，根据两路光形成的干涉图强度变化，经计算机控制系统计算出外部振动量，控制抖动补偿镜进行反馈补偿，使得光源照射的星点分化板1和星点分化板2形成的光路，经过抖动校正后的光学系统可在星敏感器靶面处形成稳定星图。
以上所述仅为本发明的较佳实施例而已，并不用以限制本发明。凡在本发明 的精神和原则之内所作的任何修改、等同替换和改进等，均应包含在本发明的保护范围之内。

Claims (9)

  1. 一种采用激光干涉探测的星模拟系统振动抑制系统，其特征在于：包括激光光源(1)、第一分束镜(2)、准直镜组(4)、第二分束镜(5)、反射镜(6)、探测会聚镜组(7)、CCD探测器(8)、计算机控制系统(9)、抖动补偿镜(10)、平板分光镜(11)；整个系统的光路包括参考光路和探测补偿信号光路，其中：
    参考光路：激光光源(1)发出的光经第一分束镜(2)到达准直镜组(4)成平行第一光束射出，第一光束经第二分束镜(5)到达反射镜(6)，经反射镜(6)反射形成第二光束到达探测会聚镜组(7)，出射光会聚在CCD探测器(8)上，组成参考光路；
    探测补偿信号光路：平行第一光束透射第二分束镜(5)形成第三光束，第三光束经抖动补偿镜(10)反射传播至平板分光镜(11)，经过平板分光镜(11)反射的反射光束经抖动补偿镜(10)至第二分束镜(5)反射形成第四光束，第四光束传播至探测会聚镜组(7)会聚在CCD探测器(8)上，组成探测补偿信号光路；
    所述CCD探测器(8)和抖动补偿镜(10)均与计算机控制系统(9)相连；所述参考光路与探测补偿信号光路同时会聚在CCD探测器(8)上组成振动探测干涉光路，所述计算机控制系统(9)根据振动探测干涉光路形成的干涉图强度变化进行反馈补偿。
  2. 根据权利要求1所述的一种采用激光干涉探测的星模拟系统振动抑制系统，其特征在于：还包括第一光源(12)、第一星点分化板(13)、第二光源(14)，第二星点分化板(15)、星敏感器(16)，由第一光源(12)照射第一星点分化板(13)形成的第五光束和由第二光源(14)照射第二星点分化板(15)形成的第六光束通过抖动补偿镜(10)校正后的光学系统，在星敏感器(16)靶面处，形成稳定的星模拟图。
  3. 根据权利要求1或2所述的一种采用激光干涉探测的星模拟系统振动抑制系统，其特征在于：所述第一分束镜(2)包括第一分束镜(2)内部的第一分光面和第一分束镜(2)底部的第二分光面，所述第二分束镜(5)包括第二分束镜(5)内部的分光面。
  4. 根据权利要求3所述的一种采用激光干涉探测的星模拟系统振动抑制系统，其特征在于：所述参考光路中，激光光源(1)发出的光透射过第一分光面到达第二分光面进行全反射至第一分光面，经第一分束镜(2)的第一分光面反射至准直镜组(4)成平行第一光束射出，第一光束被第二分束镜的分光面反射到达反射镜(6)，经反射镜(6)反射形成第二光束到达探测会聚镜组(7)，出射光会聚在CCD探测器(8)上，组成参考光路。
  5. 根据权利要求3所述的一种采用激光干涉探测的星模拟系统振动抑制系统，其特征在于：所述探测补偿信号光路中，平行第一光束透射第二分束镜(5)的分光面形成第三光 束，第三光束经抖动补偿镜(10)反射传播至平板分光镜(11)，经过平板分光镜(11)反射，反射光束经抖动补偿镜(10)至第二分束镜(5)，由第二分束镜(5)的分光面反射形成第四光束，第四光束传播至探测会聚镜组(7)会聚在CCD探测器(8)上，组成探测补偿信号光路。
  6. 根据权利要求1所述的一种采用激光干涉探测的星模拟系统振动抑制系统，其特征在于：还包括成像镜组(3)，所述成像镜组(3)设置于激光光源(1)和第一分束镜(2)之间。
  7. 根据权利要求3所述的一种采用激光干涉探测的星模拟系统振动抑制系统，其特征在于：所述第一分束镜(2)的第一分光面针对激光光源(1)发出的光镀半透半反膜，所述第一分束镜(2)的第二分光面对激光光源(1)发出的光镀全反膜；所述第二分束镜(5)的分光面对激光光源(1)发出的光镀半透半反膜；所述反射镜(6)、抖动补偿镜(10)以及平板分光镜(11)对激光光源(1)发出的光镀全反膜；所述第一分束镜(2)的第一分光面对第一光源(12)发出的光镀全透膜，对第二光源(14)发出的光镀全反膜；所述第二分束镜(5)的分光面对第一光源(12)和第二光源(14)发出的光均镀全透膜；所述平板分光镜(11)对第一光源(12)和第二光源(14)发出的光均镀全透膜。
  8. 根据权利要求2所述的一种采用激光干涉探测的星模拟系统振动抑制系统，其特征在于：所述平板分光镜(11)的口径比星敏感器(16)的通光口径小，一方面平板分光镜(11)对振动补偿信号光进行反射，另一方面第一光源(12)和第二光源(14)发出的光从平板分光镜(11)的两边透射传播至星敏感器(16)。
  9. 一种采用激光干涉探测的星模拟系统振动抑制方法，其特征在于：通过CCD探测器(8)测量出如权利要求1-8中任意一项所述的参考光路和探测补偿信号光路两路光形成的干涉图强度的变化，经计算机控制系统(9)计算出外部振动量，控制抖动补偿镜(10)进行反馈补偿，在星图模拟的基础上同时对环境模拟系统造成的振动进行补偿校正，抵消光束由于透镜组的震动而产生的抖动影响，使得由第一光源(12)照射第一星点分化板(13)形成的第五光束和由第二光源(14)照射第二星点分化板(15)形成的第六光束通过抖动补偿镜(10)校正后的光学系统，在星敏感器(16)靶面处，形成稳定的星模拟图。
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