On orbit imaging of two celestial bodies based on deep space explorer and its application

ZOU Xin; GU Zheng; CHEN Li-ping; WANG Tong; XUE Bo

doi:10.3788/OPE.20152310.2761

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On orbit imaging of two celestial bodies based on deep space explorer and its application

Modern Applied Optics | 更新时间：2020-08-13

- On orbit imaging of two celestial bodies based on deep space explorer and its application
- Optics and Precision Engineering Vol. 23, Issue 10, Pages: 2761-2767(2015)
- 作者机构：
  
  北京空间飞行器总体设计部, 北京 100094
- 作者简介：
- 基金信息：
- DOI：10.3788/OPE.20152310.2761
  CLC： V557;V248.1
- Received：14 April 2015，
  
  Revised：26 May 2015，
  
  Published：25 October 2015
- 稿件说明：
移动端阅览
邹昕, 顾征, 陈丽平等. 基于深空探测器的在轨天体合影成像及应用[J]. 光学精密工程, 2015,23(10): 2761-2767

ZOU Xin, GU Zheng, CHEN Li-ping etc. On orbit imaging of two celestial bodies based on deep space explorer and its application[J]. Editorial Office of Optics and Precision Engineering, 2015,23(10): 2761-2767
邹昕, 顾征, 陈丽平等. 基于深空探测器的在轨天体合影成像及应用[J]. 光学精密工程, 2015,23(10): 2761-2767 DOI： 10.3788/OPE.20152310.2761.

ZOU Xin, GU Zheng, CHEN Li-ping etc. On orbit imaging of two celestial bodies based on deep space explorer and its application[J]. Editorial Office of Optics and Precision Engineering, 2015,23(10): 2761-2767 DOI： 10.3788/OPE.20152310.2761.

摘要

提出了基于深空探测器对太空中的目标天体合影成像的新策略。首先

基于相机的性能参数建立视场模型

然后对天体和探测器轨道动力学模型、探测器姿态数据以及光照条件进行综合分析

最终确定了拍摄用相机以及成像时刻与成像姿态等成像策略。以探月三期月地高速再入返回飞行任务的设计为例

研究计算了对地月合影的拍摄相机、成像时刻与成像姿态

并利用在轨探测效果仿真系统进行了仿真验证。结果表明:该成像策略能够根据预定的天体合影的构图要求便捷地计算出拍摄条件

结果准确、角度偏差在1°范围内。该成像策略还成功应用于探月三期月地高速再入返回飞行器的实际任务中

在距离月球1.40×10

km和距离地球3.91×10

km处

获得了我国航天史上首张地月合影图像

为后续深空探测器在轨天体合影提供了参考依据。

Abstract

The new imaging strategy based on a deep space explorer was proposed for two celestial bodies on-orbit operation. A field of view model was established based on the performance parameters of a camera. Then

the orbit dynamic model of celestial bodies and the explorer

attitude data of the explorer

and illumination condition were analyzed synthetically. Finally

the camera of shooting

the time of imaging and the attitude of imaging were defined. By taking the design of circumlunar return and reentry spacecraft of the 3rd phase of China lunar exploration program as an example

the camera

imaging time

and the attitude of imaging were calculated. The imaging strategy was verified using the on-orbit exploration effect simulation system. The results show that the strategy can obtain imaging conditions expediently and accurately based on the requirement of composition of projected celestial body and the angular deviation is in the range of 1°. The imaging strategy for two celestial bodies was successfully applied to circumlunar return and reentry spacecraft. By accurate imaging

the earth-lunar images are achieved at lunar distance of 1.40×10

km and at earth distance of 3.91×10

km for the first time in space history in China. This imaging strategy might be used as a reference for two celestial bodies based on the deep space explorer on-orbit operation.

关键词

Keywords

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