The invention provides a morning orbit satellite and a sun attitude calculation method and a guiding method thereof, and belongs to the technical field of satellite attitudes, the sun attitude calculation method comprises the following steps: calculating a component r1, r2, r3, r4 of a position vector, pointing to the earth, of the morning orbit satellite in an inertial system according to the number of satellite orbits at the current moment; and the component v1 of the velocity vector of the satellite relative to the earth under the inertial system; according to the current time, calculating a component r2 of a position vector of the satellite pointing to the sun under the inertial system; determining an attitude rotation matrix Cri of a target coordinate system OrXrYrZr for attitude control relative to an inertial system OiXiYiZi according to the component r1 and the component r2, and converting the attitude rotation matrix Cri into a corresponding quaternion qri; and based on the component v1 and the related position vector, determining the angular velocity omega ri of the target coordinate system OrXrYrZr relative to the inertial system OiXiYiZi. Through the processing scheme disclosed by the invention, the sun alignment is guided while the earth orientation is ensured, the energy level of the whole satellite is improved, and the available time of earth operation is prolonged.
本发明提供了一种晨昏轨道卫星及其对日姿态计算方法、导引方法,属于卫星姿态技术领域,对日姿态计算方法包括根据当前时刻的卫星轨道根数,计算晨昏轨道卫星指向地球的位置矢量在惯性系下的分量r1,以及卫星相对地球的速度矢量在惯性系下的分量v1;根据当前时间,计算卫星指向太阳的位置矢量在惯性系下的分量r2;根据分量r1和分量r2确定用于姿态控制的目标坐标系OrXrYrZr相对惯性系OiXiYiZi的姿态旋转矩阵Cri,并将其转换为相应的四元数qri;基于分量v1和相关位置矢量,确定目标坐标系OrXrYrZr相对惯性系OiXiYiZi的角速度ωri。通过本公开的处理方案,在保证对地定向的同时导引对日,提高整星能源水平,且提高了对地作业可用时长。
Terminator orbit satellite and sun attitude calculation method and guiding method thereof
晨昏轨道卫星及其对日姿态计算方法、导引方法
2022-07-29
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
Attitude control of satellite in elliptic orbit
Engineering Index Backfile | 1967
|Attitude adjustment calculation method for guiding centering of main speed reducer
European Patent Office | 2023
|Orbit attitude control device, and method of controlling orbit attitude
European Patent Office | 2017
|Orbit attitude control device, and method of controlling orbit attitude
European Patent Office | 2016
|