Geometric method for determining space target initial orbit through optical telescope common-view observation and system

Abstract

The invention belongs to the technical field of space target data processing, and discloses a geometric method for determining a space target initial orbit through optical telescope common-view observation and a system, which directly solve target position information through employing the geometric method in a triangle formed by a space target and two observation stations based on binocular telescope common-view observation data, and directly solve speed information of the target by using a difference method according to the continuity of an observed quantity. The geometric method specifically comprises the following steps of: synchronizing the time of two pieces of observation data through adopting an interpolation method; calculating the distance of the target in a triangle ABS by usinga geometric approach; and acquiring a position vector of the target through utilizing the azimuth and distance information. Compared with a vector method in the prior art, the geometric method has the advantages that two unknown numbers are solved by two equations in the geometric method, two unknown numbers are solved by three equations in the vector method, the geometric method is accurate, andthe solution is unique. The invention further provides a position difference method for solving the speed, and the whole solving process completely gets rid of a mechanical equation; and the positiondifference method has obvious advantages for an orbital transfer target.

Description

technical field [0001] The invention belongs to the technical field of space object data processing, and in particular relates to a geometric method and system for determining the initial orbit of a space object through common-view observation of an optical telescope. Background technique [0002] There are two concepts in orbit determination of space targets, initial orbit calculation in the sense of short arc and orbit improvement in the sense of long arc—precise orbit determination. Determining the initial orbit is the most basic problem in celestial mechanics, and the more classic ones are the Laplace and Gauss methods. These two methods are the mechanical equations for solving the two-body problem composed of the space target and the central celestial body. Although these methods have been continuously improved over time, the problems of convergence and large errors for some specific targets have not been substantially changed. For some low-earth orbit satellites and ...

AI Technical Summary

Problems solved by technology

Although the vector method can also use the difference method to solve the velocity, but because the distance deviation of the vector method is unstable, the velocity deviation will also have uncertainty

[0012] The difficulty in solving the above problems and defects is: Laplace and Gauss methods are both short-arc orbit determination at a single optical observation station. If you still use a single-station short-arc orbit determination, it is difficult to significantly improve the orbit determination accuracy and stability

The guide to solve the problem is to adopt different observation modes. The most effective method is radar observation, but radar observation consumes too much energy and runs too expensive

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