A method for designing a continuous thrust orbit based on an artificial synthetic gravitational potential field and its application

Abstract

A method for designing continuous thrust orbit based on artificial synthetic gravitational potential field and its application are provided. The method includes such steps as determining initial orbital parameters and target orbital parameters according to mission requirements, calculating the positions and velocities of spacecraft flight initial points and terminal points in an equatorial inertial coordinate system of a geocentric center; b, synthesizing the control force acting on the spacecraft and the geocentric force acting on the spacecraft, wherein the spacecraft only makes the virtualconic curve motion under the action of the geocentric force and the control force, and constructing the parameter model of the virtual gravitational field; c, solving the parameters of the virtual gravitational field by using an optimization algorithm, so that the maneuvering trajectory in the virtual gravitational field satisfies the constraint of the orbital boundary conditions; d, according tothe parameters of the virtual gravitational field, solving the thrust acceleration needed to realize the maneuvering orbit. The orbit design method of the invention can greatly expand the maneuveringrange of the spacecraft, realize orbit interception, rendezvous and docking in two dimensions and three dimensions, etc.

Description

Technical field [0001] The invention belongs to the aerospace field, and is a continuous thrust orbit design method based on artificial synthetic gravitational potential field and its application. Background technique [0002] With the development of propulsion technology and the increasing complexity of space missions, the design of maneuvering orbits based on continuous small thrust has attracted more and more attention. There are currently two main methods for orbit design for space missions under continuous thrust: one is based on a specific thrust, that is, assuming a thrust plan and calculating the orbit under the thrust from this. The solution includes both analytical and numerical methods. Analytical solution It can only be solved for special thrust conditions such as radial force and tangential force, so it is not universal. The numerical solution has a certain universality, but its calculation is large and time-consuming; the other is shape-based orbit design The metho...

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Problems solved by technology

Such an assumption greatly simplifies the difficulty of orbit design, but on the other hand, it also greatly reduces the scope of spacecraft maneuvering, making the designed orbit not universal

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