A Phase Control Method for Coplanar Elliptical Formation of Spacecraft in Short Distance

Abstract

The invention discloses a phase control method for a coplanar elliptical formation of short-distance spacecraft. The method is based on the parameters of the Hill equation of relative motion dynamics according to the phase requirements of the coplanar elliptical formation of the short-distance spacecraft coplanar ellipse orbiting configuration. Solution, under the premise of a certain control amount (value, the same below) ΔV, use the tangent value tanΔΘ of the phase change amount to find the binary continuous function of the control timing Θ (that is, the phase angle before control, the same below) and the control direction φ The method of extreme value derives the relationship between the phase change amount ΔΘ, the control amount ΔV, the control timing Θ and the control direction φ, and obtains the conditions for ΔΘ to take the extreme value. Finally, a practical conclusion is obtained: when the phase angle to be changed is an acute angle, the lateral or reverse lateral control efficiency is the highest. At this time, the relationship between the control amount ΔV and the control timing Θ satisfies ΔV=0.5nb sinΘ (n is the average angular velocity of the reference satellite, b is the semi-minor axis of the relative motion ellipse before control), and the phase after control is π / 2 (when Θ is in the first and second quadrants) or -π / 2 (when Θ is in the third and fourth quadrants).

Description

technical field [0001] The invention relates to the technical field of relative motion of satellites in orbital dynamics, in particular to a phase control strategy in the control of a coplanar elliptical formation configuration of short-distance spacecraft. Background technique [0002] For short-distance coplanar elliptical formation spacecraft, the phase control is the key to realize the inter-group satellite configuration, and how to realize the control of the minimum control amount under the premise of the required target configuration is a practical problem that we need to solve urgently Therefore, it is necessary to theoretically deduce the relationship between the phase change amount ΔΘ, the control amount ΔV, the control timing Θ, and the control direction φ. [0003] At present, the kinematics method is mostly used in the control strategy of the coplanar elliptical formation configuration in the relative motion of short-distance spacecraft. The principle of the kin...

AI Technical Summary

Problems solved by technology

The principle of the kinematics method is simple and the calculation accuracy is high, but it requires high-precision numerical integration to plan its control strategy, which requires a large amount of calculation and requires the absolute orbit data of the satellite as input. Orbital measurement information is largely unusable in this method

Moreover, for the kinematics method, there is no simpler analytical method that can clearly and intuitively obtain the change value of the control variable to its relative elliptical motion parameter, and it is impossible to use the analytical solution to plan the most fuel-efficient control strategy

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