A Time-Domain Control Method for Spacecraft Orbit Rolling

Abstract

The invention provides a method for controlling a rolling time domain of a flight orbit of a spacecraft. The method comprises the following steps of dividing a whole orbital transferring maneuvering orbit in a time domain into N powered flight segments which are guided by an open loop and (N-1) unpowered free gliding segments; during the periods of gliding, determining the orbit by GNSS / BD2, updating the executing state and re-planning and re-solving tasks to produce a control instruction of a next powered flight segment by a central computer, and performing rolling optimization on the maneuvering trajectory of an orbit in each time domain according to the time sequence of the flight, so as to reduce accumulated errors generated by the open loop guiding control and realize a large closed loop for controlling the whole orbit. The method disclosed by the invention has the advantages of being high in accuracy, wide in application scope, easy in engineering practice and the like.

Description

technical field [0001] The invention relates to the field of orbit control of spacecraft, in particular to a method for controlling the flight orbit of a spacecraft in the rolling time domain. Background technique [0002] Spacecraft orbit maneuver control is the most important maneuvering task in spaceflight, and it is the basis for space operations such as orbit acquisition, orbit maintenance, rendezvous and docking, on-orbit service, approach observation, and deep space exploration. In actual engineering, most spacecraft use continuous thrust engines. [0003] With the development and maturity of advanced aerospace technologies such as high-performance on-board computers, on-board accelerometers, online thrust calibration, autonomous mission planning, and autonomous navigation, the orbital maneuver control method of spacecraft has also changed from the traditional method of using satellite-earth loop remote control. The open-loop control method has gradually evolved into...

AI Technical Summary

Problems solved by technology

[0006] Therefore, the existing spacecraft orbit closed-loop control method relies heavily on the on-board accelerometer. Although the orbit control accuracy is high, it has a limited service life, is not suitable for long-term on-orbit missions, and requires ground telemetry for online calibration. The engineering implementation is complicated. and other shortcomings

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