Trajectory control method for vertical recovery landing section of rocket

Abstract

The invention discloses a trajectory control method for a vertical recovery landing section of a rocket. A new optimization problem is obtained by weighted summation of objective functions in two convex optimization problems, compared with a traditional guidance method, two optimization objectives are solved at the same time, the calculation amount is reduced while the optimization performance is ensured, a the difficulty in considering uncertainty and disturbance is also reduced; meanwhile, a convex optimization method and a robust model predictive control algorithm are combined, an original non-convex feasible region is converted into a convex feasible region, under the condition that atmospheric disturbance existing in the vertical recovery process is considered, global optimality of understanding is effectively guaranteed, and meanwhile, the defect of a model predictive control algorithm in the aspect of calculation time is overcome.

Description

technical field [0001] The invention belongs to the technical field of navigation guidance and control, and in particular relates to a trajectory control method for a rocket vertical recovery landing section. Background technique [0002] Today, the main vehicle humans use to go into space is a multi-stage launch vehicle, in which the sub-stages of the launch vehicle are gradually separated in chronological order during flight. Most of these rocket sub-stages are for one-time use. After the launch mission is completed, the rocket body and equipment will be discarded, making the launch cost of the space launch vehicle high. No matter whether the launch is successful or not, the rocket will not be able to be used again, seriously affecting the The scale and efficiency of human development of space. At present, rocket recovery and reuse technology is one of the main means to reduce rocket launch costs, and the problem of rocket vertical recovery and landing guidance under comp...

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Problems solved by technology

[0003] To sum up, since the existing control algorithm is a single-objective method, other constraints usually need to be added to achieve a single objective, which will lead to the fact that when there is actually a solution that satisfies the single objective and can land near the target point, the solver does not Misjudgment of the infeasibility of the problem will result in the failure of the rocket to land at the target position; in addition, the existing methods cannot handle the complex non-convex constraints at this stage well, and the inability to find the target caused by atmospheric disturbances in the outside world. problems such as reaching a feasible solution or greatly reducing the landing accuracy

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