A trajectory planning method for spacecraft orbit change in different planes
A trajectory planning and spacecraft technology, which is applied in the direction of aerospace vehicles, space vehicle guidance devices, aircraft, etc., to achieve scientific methods, wide application value, and good manufacturability
Active Publication Date: 2022-04-15
BEIHANG UNIV +1
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[0003] Purpose of the invention: The purpose of the present invention is to provide a trajectory planning method for spacecraft different-plane orbit changes to solve the problem of space vehicle trajectory planning for different-plane orbit changes, so that the spacecraft can enter the circle with the largest orbital radius in the event of a failure. track
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[0028] Such as figure 1 As shown, the present invention provides a method for planning orbits of different planes of a spacecraft, the method comprising the following steps:
[0029] (1) Step 1: Obtain the corresponding parameters of the trajectory planning method according to the actual parameters of the spacecraft and the mission situation;
[0030] (2) Step 2: Establish a convex optimization problem for spacecraft orbit change;
[0031] (3) Step 3: Given the initial guess, the model compensation method is used to iteratively solve the convex optimization problem of the spacecraft's orbit change in different planes;
[0032] The "actual parameters and mission conditions of the spacecraft" described in step 1 are specifically:
[0033] The maximum thrust T of the spacecraft, the initial mass of the spacecraft m 0 , the second consumption of the spacecraft Δm, the flight time of the spacecraft t f .
[0034] The "corresponding parameters of the trajectory planning method"...
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The present invention provides a trajectory planning method for orbital change of a spacecraft, the steps of which are as follows: Step 1: Obtain the corresponding parameters of the trajectory planning method according to the actual parameters of the rocket and the mission situation; Step 2: Establish a convex optimization problem under the condition of a rocket failure; Step 3: Given the initial guess, the model compensation method is used to iteratively solve the convex optimization problem in the case of rocket failure. Through the above steps, the near-circular orbit planning method based on convex optimization under the condition of rocket failure can effectively solve the problem of rocket entering orbit under the condition of failure, and quickly generate the circular orbit with the largest radius that the rocket can enter and the corresponding trajectory within a certain period of time The method of the present invention is scientific, good in manufacturability, and has wide popularization and application value.
Description
technical field [0001] The invention provides a trajectory planning method for a spacecraft changing orbits in different planes, and belongs to the technical field of trajectory planning in aerospace technology. Background technique [0002] In recent years, with the increasing development of science and technology, the demand for satellite launch resources is increasing. Therefore, the spacecraft is required to have online autonomous trajectory planning capabilities, so as to reduce the workload of mission design before the launch of the spacecraft, reduce the launch cycle, and improve the success rate of the mission. For the traditional launch mode, a lot of pre-mission design work is required, and it is difficult to deal with flight trajectory deviation and some emergencies after launch. For the traditional control method of spacecraft orbit change in different planes, it cannot plan the trajectory of the spacecraft. When the spacecraft trajectory deviates greatly from t...
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IPC IPC(8): B64G1/24
CPCB64G1/242
Inventor 张冉郝泽明李惠峰师鹏程晓明禹春梅
Owner BEIHANG UNIV