Zero-bias lasting day number determination method suitable for navigation inclined orbit satellite

Abstract

The invention provides a zero-bias lasting day number determination method suitable for a navigation inclined orbit satellite. The zero-bias lasting day number determination method comprises the steps that an included angle between the ecliptic plane and the orbit plane is worked out according to the orbit ascending node right ascension and the orbit inclined angle of the navigation inclined orbit satellite; the arc section of the sun on the ecliptic during the satellite zero-bias period is obtained according to the included angle between the ecliptic plane and the orbit plane as well as an included angle between the sun vector in the dynamic deflection zero-bias condition and the orbit plane; and the satellite zero-bias lasting day number is determined according to the arc section of the sun on the ecliptic during the satellite zero-bias period. According to the zero-bias lasting day number determination method suitable for the navigation inclined orbit satellite, the satellite zero-bias lasting day number can be worked out through geometrical analysis according to the two orbit elements of the satellite during the orbit design period and after the design is completed; and the method is simple in calculation and little in required orbit information and meanwhile also can be reversely applied to orbit design under constraint of the zero-bias lasting day number.

Description

technical field [0001] The invention relates to a method for determining the continuous days of satellite zero offset, which is suitable for navigation inclined orbit satellites whose yaw attitude control adopts a strategy of combining dynamic offset and zero offset. Background technique [0002] The navigation IGSO\MEO satellite orbit is an inclined orbit with an inclination angle of 55°. In order to meet the power supply requirements of the whole satellite, continuous measurement and control of yaw attitude is required, that is, yaw dynamic offset. However, when the angle between the sun vector and the orbital plane is small, the yaw angular velocity is large, and the yaw control torque provided by the reaction wheel is also large. Due to the limited torque of the wheel control, the control accuracy will be reduced during the rapid change of yaw, which will affect the precision requirements of the sailboard tracking the sun. Therefore, the yaw zero offset is used when the ...

AI Technical Summary

Problems solved by technology

[0004] At present, the existing method for calculating the duration of the zero offset of the navigation inclined orbit satellite is based on the six orbital elements of the satellite (characterizing the position of the orbit in space and the position of the satellite in the orbit) through numerical calculations to obtain the satellite zero offset The duration of the setting, that is, after the satellite orbit design is completed, the position of the satellite on the orbit can be calculated after it is completely determined. Therefore, the original method is complicated to calculate, requires a lot of orbit information, and orbit extrapolation is required in the calculation

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