Spacecraft coplanar formation accompanying-flight configuration control method

Abstract

The invention relates to a spacecraft coplanar formation accompanying-flight configuration control method. The spacecraft coplanar formation accompanying-flight configuration control method comprises that in dependence on analytical solutions of a C-W equation, an expression of geometric parameters of the configuration is obtained; in the expression, geometric parameters representing relative movement characteristics serve as control objects, and the control objects comprise an ellipse center radial position xc, an ellipse center transverse position yc, an ellipse semi-minor axis b and a phase [theta] of a spacecraft on a relative movement ellipse; and the control objects are controlled based on a minimum fuel control theory. By employing the spacecraft coplanar formation accompanying-flight configuration control method, fuel can be saved, and the spacecraft coplanar formation accompanying-flight configuration control method is suitable for controlling on-board independent coplanar formation configurations of micro / nano-satellites in the magnitude of hundred meters to tens of kilometers, having satellite-to-satellite real-time relative measurement and constrained by resources.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a control method for a space vehicle coplanar formation accompanying flight configuration. Background technique [0002] With the continuous development of aerospace technology and the continuous expansion of spacecraft application fields, the distributed satellite system has turned from concept to practical application. Micro-nano satellites with multiple functional distribution and information interconnection can replace large satellites to carry out space missions through coordinated control. They have strong flexibility and system damage resistance, and have significant advantages in development cycle and development cost. Application prospects. At present, all countries in the world are actively carrying out related technology research and application exploration of distributed satellite systems. [0003] Formation flight is the dynamic basis of distributed satellite sy...

AI Technical Summary

Problems solved by technology

At present, scholars and engineers often use the analytical solution of the C-W equation to analyze the relative motion characteristics of the accompanying spacecraft. The "Micro-Nano Satellite Coplanar Accompanying Relative Motion Ellipse Short" published in Volume 35, Issue 5 of China Space Science and Technology in 2015 Semi-Axis Most Fuel-Efficient Control" and "The Most Fuel-Effective Control Problem of Relative Motion Ellipse Phase with Co-planar Accompanied Flight" published in Volume 35, Issue 6, introduced the research on the most fuel-efficient control problem of the ellipse's semi-minor axis and the phase on the ellipse, but still There is no complete theory for configuration control using the analytical solution of the C-W equation

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