초록 ▼

Satellite attitude control methods for use during orbit raising operations to follow a predefined thrust trajectory that meets geometric constraints imposed by sensor and/or telemetry and control antenna fields of view while optimizing the sun angle on the solar array. The method uses low thrust ele

Satellite attitude control methods for use during orbit raising operations to follow a predefined thrust trajectory that meets geometric constraints imposed by sensor and/or telemetry and control antenna fields of view while optimizing the sun angle on the solar array. The method uses low thrust electric propulsion for geosynchronous satellite orbit raising from a transfer orbit to the final geosynchronous orbit. In implementing the methods, a predefined thrust trajectory is generated that is designed to raise a satellite from a transfer orbit to a geosynchronous orbit. A direction-cosines matrix, or quaternion, is generated that aligns a thrust vector defined in the satellite body frame with the predefined thrust trajectory and rotates the satellite body about that vector. Attitude control is performed in accordance with the direction-cosines matrix to align the thrust vector defined in the satellite body frame with the predefined thrust trajectory and rotate the satellite body about that vector to optimize the sun angle on the solar array.

대표청구항 ▼

[ What is claimed is:] [1.]1. A satellite attitude control method for use with a satellite having a solar array, comprising the steps of:generating predefined thrust trajectory or thrust-vector profile that is designed to raise a satellite from a transfer orbit to a geosynchronous orbit;generating a

[ What is claimed is:] [1.]1. A satellite attitude control method for use with a satellite having a solar array, comprising the steps of:generating predefined thrust trajectory or thrust-vector profile that is designed to raise a satellite from a transfer orbit to a geosynchronous orbit;generating a direction-cosines matrix that is used to alien a thrust vector defined in the satellite body frame with the predefined thrust trajectory or thrust-vector profile and that is used to rotate the satellite body about the generated thrust vector to an optimal attitude; andactuating the attitude control system in accordance with the direction-cosines matrix to align the thrust vector defined in the satellite body frame with the predefined thrust trajectory or thrust-vector profile and rotate the satellite body about that vector to an optimal attitude.