Eccentricity ratio freezing common-rail double-pulse control intermediate rail determination method

Abstract

The invention discloses an eccentricity ratio freezing common-rail double-pulse control intermediate orbit determination method. The method is specifically implemented according to the following steps: 1, determining a pre-control satellite orbit at an intermediate moment of first orbital transfer; 2, calculating the position and speed of a satellite when the orbit is not changed at the intermediate moment of the first orbit change; 3, determining a satellite orbit after secondary orbit transfer intermediate time control; 4, confirming the control type, the control quantity and the control phase of a double-pulse track; 5, respectively calculating a track eccentricity ratio variable quantity, a track flat semi-major axis variable quantity, a first track control actual speed increment and asecond track control actual speed increment; 6, calculating a satellite speed vector after the first orbital transfer intermediate time control; 7, determining a double-pulse control middle arc section track. By means of the method, the available working arc section of the orbit in the spacecraft control period can be improved, and certain economic benefits are achieved for on-orbit operation ofthe spacecraft.

Description

technical field [0001] The invention belongs to the technical field of spacecraft measurement and control, and relates to an intermediate orbit determination method for eccentricity freezing co-orbit dual-pulse control. Background technique [0002] The eccentricity freezing orbit, by constraining the half-field axis a, eccentricity e, and perigee argument ω, realizes that the satellite orbit has the same height when passing through the same latitude circle, and ensures that the payload on the satellite has stable working conditions. It has been widely used at present. For this type of track, track control is generally realized by double-pulse track change. During the implementation of typical dual-pulse orbit control, multiple batches of same-orbit dual-pulse control are required considering constraints such as thruster configuration and control objectives on the satellite, that is, two orbit changes are performed within one orbit, including co-direction and reverse orbit c...

AI Technical Summary

Problems solved by technology

[0003] For the above two typical double-pulse control orbits, due to the short interval of double-pulse control, and usually the radian is outside the tracking interval of the station in my country, the observation data of the middle orbit is insufficient or even has no observation data at all, so it is difficult to determine the orbit after the event Directly determine the trajectory of the arc segment between the double-pulse controls

[0004] The available working time of the payload during the satellite’s in-orbit operation is very precious. Some payload data needs to be used in conjunction with the satellite orbit. For example, the satellite’s ground imaging needs to use the satellite orbit data for image correction and frame processing. There is no precise orbit in the pulse control interval, which will make the load data unusable in this arc segment, resulting in waste of resources

Images