A Coplanar Circular Orbit Autonomous Orbit Transfer Guidance Method for Satellites with Limited Thrust
A technology of transfer guidance and autonomous orbit, which is applied in the direction of aerospace vehicle guidance devices, etc., can solve the problems of large calculation amount, limited engine thrust amplitude, lack of autonomy in the orbit transfer process, etc., to achieve small calculation amount and strong practical application value Effect
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specific Embodiment approach 1
[0028] Specific implementation mode 1: A satellite limited thrust coplanar circular orbit autonomous orbit transfer guidance method of this embodiment, the principle of the method is as follows figure 1 , 2 As shown, its specific process is as follows: A satellite limited thrust coplanar circular orbit autonomous orbit transfer guidance method, which is implemented in the following steps:
[0029] Step 1: Establish satellite orbit dynamics model;
[0030] Step 2: According to the initial orbit parameters, target orbit parameters and the initial conditions of the launch window, use the speed gain guidance to enter the first thrust action section under the effect of the engine's limited thrust to make the satellite enter the designed elliptical taxiing orbit, and then turn off the engine. And make the speed of the satellite equal to the speed of the pole of the elliptical sliding orbit when the engine is turned off;
[0031] Step 3: After the satellite enters the elliptical taxiing orb...
specific Embodiment approach 2
[0035] Specific embodiment two: this embodiment is different from specific embodiment one in that: this embodiment is a specific description of step one in specific embodiment one, and the satellite orbit dynamics model in said step one is in polar coordinate system Expressed, the polar coordinate system used in the orbital dynamics model is as image 3 As shown, its specific form is: taking the satellite orbit plane as the polar coordinate plane, taking the center of the earth as the coordinate pole, the distance r between the satellite and the center of the earth in the orbit plane as the polar diameter, and taking the direction vector of the earth center pointing to the satellite as the polar axis , The angle θ between the current polar diameter and the polar diameter at the initial maneuvering moment is the polar angle, and the counterclockwise direction is positive. The velocity can be decomposed into the radial velocity v through the polar coordinate system r And tangentia...
specific Embodiment approach 3
[0039] Specific embodiment three: This embodiment is different from specific embodiments one or two in that: this embodiment is a specific description of step two, that is, a specific description of the first thrust stage in the orbit transfer process. The process is: such as Figure 4 As shown, the second step is specifically:
[0040] 1. Mathematical model of velocity gain guidance:
[0041] Such as Figure 4 As shown, the current speed of the satellite at time t is defined as v, and the speed required to reach the set elliptical sliding orbit is v R , The speed at which the satellite needs gain is v g , The mathematical model of velocity gain guidance is:
[0042] v g =v R -v
[0043] Where v=[v r v θ ] T , Where v r And v θ Respectively represent the radial velocity and tangential velocity of the satellite in the polar coordinate system, and the superscript T represents the transposition of the matrix;
[0044] As in the first thrust stage, such as Figure 5 As shown, the target ...
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