Method for controlling spacecraft attitude directing constraint attitude maneuver

Abstract

The invention relates to an independent method for controlling spacecraft attitude directing constraint attitude maneuver, belonging to the technical field of spacecraft attitude control. The method comprises the following steps of: constructing a navigation function V related to the motion of the tail end point of a current pointing vector r of a sensor on a unit spherical surface S by taking the tail end point of a target pointing vector rd of the sensor as a target point position, taking the tail end point of the current pointing vector r as a current position and taking a spherical doom formed by a pointing constraint as a barrier region; designing a control torque expression according to the navigation function, and regulating the amplitude of a control torque by changing control torque parameters to drive the spacecraft to make the sensor point to the target vector rd; and driving the spacecraft to rotate in the vector direction of the sensor by an angle theta after the sensor points to the target vector rd, so that a complete attitude maneuver process of the spacecraft is realized. According to the method, pointing avoidance of the barrier region can be processed definitely, a local minimum value can be avoided for a plurality of barrier constraints simultaneously, safe maneuver of the spacecraft to a target attitude is ensured, the requirement of boundedness on an executing mechanism is met, and independent control over spacecraft directing constraint attitude maneuver is realized.

Description

technical field [0001] The invention belongs to the technical field of spacecraft attitude control, and relates to a method for autonomous attitude maneuvering control subject to pointing constraints. Background technique [0002] With the development of spacecraft technology and the diversification of space missions, it is sometimes necessary to install weak light sensitive devices (such as infrared telescopes, star sensors, etc.) on spacecraft to complete specific detection tasks. These instruments are very sensitive to the light of strong celestial bodies, especially the sun. If the necessary measures are not taken to prevent the light from entering the sensitive components, it is easy to cause damage to the sensitive components. During attitude maneuvering, it is common practice to turn off these devices, but in some cases, these instruments are still required to be in working condition, which requires the invention of pointing avoidance methods for attitude maneuvering....

AI Technical Summary

Problems solved by technology

However, the area pointing constraint is not processed. During the execution, the pointing axis is kept away from the obstacle pointing as far as possible. It is difficult to tell whether the pointing has entered the obstacle area centered on the obstacle pointing.

In addition, for multiple pointing constraints, the method has local solutions

[0006] In general, in the existing attitude maneuvering control methods for pointing constraints, there is no clear method for avoiding the problem of obstacle areas. In addition, the elimination of local minima and the consideration of actuators are useful for multi-obstacle constraints. bounded method does not appear

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