Preliminary Orbit Determination Method for Deep Space Objects Based on Space-Based Autonomous Optical Observation
A target celestial body and optical technology, applied in the field of deep space exploration, can solve the problems of measurement delay, observation geometry difference, measurement discontinuity, and inability to accurately determine the orbit information of deep space targets in real time, so as to achieve a simple and easy-to-implement measurement scheme Effect
Inactive Publication Date: 2016-10-26
BEIJING INSTITUTE OF TECHNOLOGYGY
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However, due to the long distance of the deep space target, the measurement delay is caused, the observation geometry is poor, and the measurement discontinuity is caused by the occlusion of other stars and the rotation of the earth, making it impossible to accurately determine the orbit information of the deep space target in real time
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[0039] In order to better illustrate the purpose and advantages of the present invention, the content of the invention will be further described below in conjunction with the accompanying drawings and examples.
[0040] In this example, for the monitoring task of deep space celestial bodies, an optical initial orbit determination scheme based on Newtonian homotopy is given. Combining with the angle measurement information of the optical navigation camera, the Newtonian homotopy path tracking algorithm is used to solve the orbital information of the target celestial body. Preliminary Orbit Determination of Deep Space Objects with High Precision. The specific implementation method of this example is as follows:
[0041]Step 1: Connect the optical navigation camera to the detector. The detector is in orbit around the sun. The target celestial body is captured by the optical navigation camera, and the angle measurement information (right ascension β, Declination ε) is used to sol...
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The invention discloses an initial orbit determination method for a deep space target celestial body based on space-based autonomous optical observation, relates to an optical autonomous initial orbit determination method for a deep space celestial body, and belongs to the technical field of deep space detection. The method comprises the following implementation steps: 1, acquiring angle measurement information (right ascension beta and declination epsilon) of the target celestial body from a detector; 2, establishing an orbital kinetic equation of the target celestial body under a heliocentric inertia coordinate system; 3, establishing an observation condition equation set of the autonomous initial orbit determination of the detector by utilizing the angular position information of the target celestial body solved in the step 1 and known detector orbit parameter information; and 4, solving the orbital element information of the target celestial body by utilizing a Newton homotopy path following algorithm, thereby realizing initial orbit determination. According to the method disclosed by the invention, the position and speed information of the target celestial body can be accurately acquired in real time in the field of deep space probe navigation, the initial value sensitivity is reduced, the convergence rate, solving success rate and calculation efficiency are improved, and the positioning efficiency is further improved. Moreover, the method is simple in measurement device and easy to implement.
Description
technical field [0001] The invention relates to a method for preliminary orbit determination of a deep space target celestial body based on space-based autonomous optical observation, and belongs to the technical field of deep space detection. Background technique [0002] The detection and defense of small celestial bodies (such as asteroids, comets, etc.) in the future need to realize real-time positioning of celestial objects. Determination of the initial orbit is the most basic step to determine the orbit of the target celestial body. The initial determination, tracking and precise orbit determination of the target orbit can be achieved through a certain orbit determination method, and this must be based on the effective orbit parameters provided by the orbit determination method. . Therefore, constructing an orbit determination method that can efficiently and accurately determine the position and velocity of the target celestial body is the basis for the success of the...
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IPC IPC(8): G01C11/00
CPCG01C11/00G01C21/24
Inventor 高艾李兴国崔平远朱圣英徐瑞
Owner BEIJING INSTITUTE OF TECHNOLOGYGY