基于时序光度信号的目标卫星状态特性估计
发布时间：2018-09-04 17:08
【摘要】：进入太空中的目标日益增多,其中最重要的一类空间目标就是卫星,从国家太空安全角度出发,对太空中的卫星尤其是他国卫星的探测与辨识成为当前的一个研究热点。针对星上观测获取的目标卫星时序图像,传统的光学目标识别跟踪算法只是利用目标的时序图像来计算目标的轨迹,但这些图像也包含了目标的很多其他相关信息,能对目标的很多参数进行反演。本文针对轨道高度在500km到1000km的中低轨卫星开展了研究。位于该高度范围类的卫星与高轨预警卫星的任务类型不同,通常不会采用自旋稳定状态实施扫面探测,加之当前三轴稳定技术已较为成熟,并得到了广泛的应用,因此中低轨卫星通常采用三轴稳定的控制状态。而当一颗三轴稳定卫星失效之后,由于没有控制系统对卫星姿态的调整,卫星通常会处于混乱翻滚的状态。而这两种运动状态的不同,将导致目标卫星反射的光通量具有不同的变化特性。本文将通过时序图像中提取到的目标卫星光度信号,对目标卫星的运动状态做出判定。当判定一颗目标卫星为正常工作状态的三轴稳定卫星,对它的特性反演就具有极大的应用价值。本文在卫星尺寸反演这一章,定义了反射率面积乘积这一物理量来表征目标卫星的尺寸。在轨大型卫星,外形尺寸在数十米到上百米;中型卫星,外形尺寸大都在几米到十几米的量级;小型卫星,尺寸在十米以下。卫星本体表面热控材料的反射率通常在0.3~0.6,卫星太阳能帆板的反射率在0.8~0.9。反演得到卫星本体表面的反射率面积乘积,就能对卫星的尺寸进行估计,进而分析其功能和用途。反演得到太阳能帆板的尺寸,就能对卫星的整星功率进行估计。本文针对星上监视在轨抵近识别侦查的应用背景,做了如下工作:1.对观测卫星所搭载的探测器的探测性能做了分析,综合考虑了平台振动、噪声对目标信号的影响。给出了观测卫星在轨抵近识别过程中,能从时序图像中实现目标检测的观测距离。2.根据目标卫星时序光度信号的频谱特性,对目标卫星的运动状态进行了判定,判定了目标卫星处于正常工作三轴稳定状态还是失效翻滚状态。3.研究了目标卫星尺寸反演的算法,提出了应用反射率面积乘积的物理量来表征卫星尺寸的概念,并通过时序图像作为输入数据,对目标卫星的尺寸进行了反演。
[Abstract]:The most important kind of space target is satellite. From the point of view of national space security, the detection and identification of satellites in space, especially from other countries, has become a hot research topic. The traditional optical target recognition and tracking algorithms only use the sequential images of the target to calculate the track of the target, but these images also contain a lot of other relevant information of the target. Many parameters of the target can be retrieved. In this paper, the orbit altitude from 500km to 1000km is studied. The missions of satellites located in this range of altitude are different from those of high-orbit early warning satellites, so they usually do not use spin stabilization state to carry out scanning surface detection. Moreover, the current triaxial stabilization technology is mature and has been widely used. Therefore, the low-altitude satellite usually adopts three-axis stable control state. When a triaxial stabilized satellite fails, the satellite is usually in a chaotic state because it has no control system to adjust the attitude of the satellite. The difference of these two motion states will result in the different characteristics of the reflected luminous flux of the target satellite. In this paper, the moving state of the target satellite is determined by the photometric signal extracted from the sequential image. When a target satellite is determined to be a triaxial stable satellite in normal working state, the inversion of its characteristics has great application value. In the chapter of satellite dimension inversion, the reflectivity area product is defined to represent the size of the target satellite. Large satellites in orbit with dimensions ranging from tens of meters to hundreds of meters; medium satellites, mostly in the order of several meters to ten meters; and small satellites, with dimensions below ten meters. The reflectivity of the thermal control material on the satellite body surface is usually 0.3 ~ 0.6 and the reflectivity of the satellite solar panel is 0.8 ~ 0.9. The reflectivity area product of satellite body surface can be obtained by inversion, and then the size of satellite can be estimated, and its function and application can be analyzed. The whole power of the satellite can be estimated by inversion of the size of the solar panel. Aiming at the application background of onboard surveillance in orbit, this paper does the following work: 1. The detection performance of the detector carried by the observation satellite is analyzed, and the influence of platform vibration and noise on the target signal is considered. The observation distance. 2. 2, which can realize target detection from sequential images, is given in the process of orbit approach recognition. According to the spectral characteristics of the time series photometric signal of the target satellite, the moving state of the target satellite is judged, and the target satellite is judged to be in the normal triaxial stable state or the failure rolling state. 3. In this paper, the algorithm of target satellite size inversion is studied, and the concept of using physical quantity of reflectivity area product to represent satellite size is put forward, and the size of target satellite is inversed by time series image as input data.
【学位授予单位】：哈尔滨工业大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V556;V474
本文编号：2222811
[Abstract]:The most important kind of space target is satellite. From the point of view of national space security, the detection and identification of satellites in space, especially from other countries, has become a hot research topic. The traditional optical target recognition and tracking algorithms only use the sequential images of the target to calculate the track of the target, but these images also contain a lot of other relevant information of the target. Many parameters of the target can be retrieved. In this paper, the orbit altitude from 500km to 1000km is studied. The missions of satellites located in this range of altitude are different from those of high-orbit early warning satellites, so they usually do not use spin stabilization state to carry out scanning surface detection. Moreover, the current triaxial stabilization technology is mature and has been widely used. Therefore, the low-altitude satellite usually adopts three-axis stable control state. When a triaxial stabilized satellite fails, the satellite is usually in a chaotic state because it has no control system to adjust the attitude of the satellite. The difference of these two motion states will result in the different characteristics of the reflected luminous flux of the target satellite. In this paper, the moving state of the target satellite is determined by the photometric signal extracted from the sequential image. When a target satellite is determined to be a triaxial stable satellite in normal working state, the inversion of its characteristics has great application value. In the chapter of satellite dimension inversion, the reflectivity area product is defined to represent the size of the target satellite. Large satellites in orbit with dimensions ranging from tens of meters to hundreds of meters; medium satellites, mostly in the order of several meters to ten meters; and small satellites, with dimensions below ten meters. The reflectivity of the thermal control material on the satellite body surface is usually 0.3 ~ 0.6 and the reflectivity of the satellite solar panel is 0.8 ~ 0.9. The reflectivity area product of satellite body surface can be obtained by inversion, and then the size of satellite can be estimated, and its function and application can be analyzed. The whole power of the satellite can be estimated by inversion of the size of the solar panel. Aiming at the application background of onboard surveillance in orbit, this paper does the following work: 1. The detection performance of the detector carried by the observation satellite is analyzed, and the influence of platform vibration and noise on the target signal is considered. The observation distance. 2. 2, which can realize target detection from sequential images, is given in the process of orbit approach recognition. According to the spectral characteristics of the time series photometric signal of the target satellite, the moving state of the target satellite is judged, and the target satellite is judged to be in the normal triaxial stable state or the failure rolling state. 3. In this paper, the algorithm of target satellite size inversion is studied, and the concept of using physical quantity of reflectivity area product to represent satellite size is put forward, and the size of target satellite is inversed by time series image as input data.
【学位授予单位】：哈尔滨工业大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V556;V474
【参考文献】
相关期刊论文 前3条
1 陈颖,刘镰斧,李在铭;一种微弱点运动目标的快速统计检测算法[J];电子学报;2001年12期
2 杨卫平,李吉成,沈振康;分层投票表决目标检测方法及其性能分析[J];红外技术;2003年06期
3 杨卫平，沈振康;红外图像序列小目标检测预处理技术[J];红外与激光工程;1998年01期
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