Yaw maneuvering control method and system of spacecraft by using virtual sun vector

Abstract

The invention relates to a yaw maneuvering control method and system of a spacecraft by using a virtual sun vector. The yaw maneuvering control method comprises the steps that a vector expression of areal sun vector in an orbit coordinate system of the spacecraft is obtained; the included angle between the real sun vector and an orbital plane is calculated according to the expression of the realsun vector, and a Beta angle of the real solar vector is obtained; a threshold valve interval for one or more Beta angles is preset, the corresponding relationship between a Beta angle of the virtualsun vector and the Beta angle of the real solar vector which are set in the preset threshold valve interval is set; when the Beta angle of the real sun vector enters into the set threshold valve interval, the virtual sun vector is started to be calculated in real time according to the Beta angles of the real sun vector and the virtual sun vector; a target yaw angle of the spacecraft is calculatedaccording to the virtual sun vector; and according to an own attitude control system of the spacecraft, a yaw maneuvering angle of the spacecraft is controlled in real time to track the target yaw angle, and the yaw maneuvering control of the spacecraft implemented by using the virtual sun vector is realized.

Description

technical field [0001] The invention relates to the technical field of spacecraft dynamics and control systems in aerospace engineering, in particular to a spacecraft yaw maneuver control method and system using a virtual sun vector. Background technique [0002] Most spacecraft use single-degree-of-freedom sail panels. In order to maintain a good incident angle of the solar panel and avoid the heat-dissipating surface from being exposed to the sun during orbit, the attitude control strategy of yaw maneuver is often adopted, which is achieved by maneuvering around the yaw axis of the star. Directing to the sun and pointing to the ground, the normal line of the sailboard is parallel to the direction of the sun through the rotation of the sailboard, so as to ensure the energy supply. Typical on-orbit spacecraft implementing yaw maneuvering strategies include: TOPEX (Ocean Terrain Environment) satellites (orbital inclination angle i=63.1°, orbital height h=1334km), GPS satellit...

AI Technical Summary

Problems solved by technology

For the actuator of the jet control principle, it will lead to a large consumption of propellant, and for the actuator of the angular momentum exchange principle, it will lead to a higher angular momentum envelope requirement

In addition, spacecraft often carry some loads with pointing requirements. When the spacecraft yaws and maneuvers, it needs to rotate a large azimuth angle to maintain its own pointing requirements. If the yaw maneuvering angle is too large, it may exceed the azimuth angle of the load. The rotation range will cause the load task to fail; if the yaw maneuver angular velocity is too large, it may exceed the upper limit of the azimuth angular velocity of the load, which will also cause the load task to fail

Images