An Analytical Calculation Method for Route Shortcuts from TT&C Stations to Sub-satellite Points

Abstract

The invention discloses an analytical calculation method of an airway shortcut from a measurement and control station to a sub-satellite point. The method includes the steps: transforming orbit parameters of a current time point according to an earth-satellite orbit theory, and acquiring six orbit elements; transforming a coordinate of the measurement and control station into a coordinate under ageocentric orbit ascending node coordinate system; calculating a false waypoint according to the coordinate of the measurement and control station under the geocentric orbit ascending node coordinatesystem; performing extrapolation calculation according to the false waypoint and an analytical algorithm based on an intermediary orbit theory to obtain an orbit parameter of a satellite in the falsewaypoint; returning the orbit parameter of the satellite in the false waypoint to the first step to perform iteration calculation once to obtain a true waypoint; calculating an airway shortcut value through the true waypoint. According to the calculation method, compared with the prior art, the shortcoming of long calculation time of an existing integration algorithm can be overcome on the premiseof ensuring accuracy, and the airway shortcut can be rapidly and accurately calculated.

Description

technical field [0001] The invention relates to the calculation of route shortcuts. More specifically, it relates to an analytical calculation method for a route shortcut from a measurement and control station to a satellite sub-satellite point. Background technique [0002] The minimum geodetic length of the track from the ground measurement and control station to the sub-satellite point is called the route shortcut. In the calculation process of the route shortcut, the site of the ground measurement and control station and the current satellite flight parameters are generally known, and the route shortcut is calculated. [0003] The existing solution is to use the integral method to calculate the sub-satellite point of the satellite every certain time step, and then calculate the length of the geodetic line from the measurement and control station to the sub-satellite point, and calculate the geodetic line length corresponding to each sub-satellite point In comparison, a...

AI Technical Summary

Problems solved by technology

However, when the integral algorithm is used, it is necessary to extrapolate the orbital parameters of the satellite several times until the waypoint is found, and in order to ensure the calculation accuracy, it is often necessary to select a smaller calculation step size, which results in a long calculation time and cannot meet the requirements. Especially in the case of a large number of computing tasks, it is more prominent

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