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A Fast Trajectory Optimization Method for Rocket Powered Descent and Landing Process

A technology of dynamic descent and dynamic descent section, which is applied in design optimization/simulation, aerospace vehicle landing devices, motor vehicles, etc., and can solve problems that cannot be applied in engineering, and cannot guarantee the reliability and efficiency of the solution.

Active Publication Date: 2021-04-09
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Abstract
  • Description
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  • Application Information

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Problems solved by technology

However, these algorithms cannot guarantee the reliability and efficiency of the solution, and cannot be used in engineering applications at present.

Method used

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  • A Fast Trajectory Optimization Method for Rocket Powered Descent and Landing Process
  • A Fast Trajectory Optimization Method for Rocket Powered Descent and Landing Process
  • A Fast Trajectory Optimization Method for Rocket Powered Descent and Landing Process

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Embodiment Construction

[0151] In order to better illustrate the purpose and advantages of the present invention, the content of the invention will be further described below in conjunction with the accompanying drawings and examples.

[0152] In order to verify the feasibility of the method, a rocket-powered descent landing mission is selected for verification. The initial mass of the rocket is m 0 =23000kg, dry mass is m dry =15000kg, engine specific impulse is I sp =360s, aerodynamic drag coefficient C D =1.3, the reference area is S ref =9m 2 , the maximum thrust of the engine is T max = 300kN. Thrust adjustable range is 40% ~ 100% T max .and let r scale =1000m, v scale = 100m / s, and m scale = m 0 . Select the number of discrete points as 121. Additionally, the trust region radius is set to

[0153]

[0154] The stopping criterion parameter is set to

[0155]

[0156] The stopping criterion parameter of discrete point update is

[0157]

[0158] The initial and final stat...

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Abstract

Fast trajectory optimization method for rocket-powered descent landing process. The invention discloses a fast trajectory planning method for fuel-optimized power descent and landing, which belongs to the field of rocket guidance. The realization method of the present invention is as follows: carry out dynamic modeling and dimension normalization to the powered descent flight, establish the three-dimensional dimensionless dynamic equation; convert the independent variable of the dynamic equation from time to height; Constraints, establish the optimal control problem of fuel-optimized power descent landing; process the nonlinear dynamic equation in the original optimal control problem into a linear dynamic equation; retain part of the nonlinearity and transform it into constraints. Convexize the non-convex constraints to establish a convex optimal control problem; use the fourth-order Runge-Kutta method to discretize it at non-uniform discrete points to establish a second-order cone programming problem; solve the second-order cone programming problem iteratively, Until convergence, that is, the trajectory planning of powered descent landing flight is realized. The invention has the advantages of high efficiency and can improve the landing safety and reliability of the rocket power descent section.

Description

technical field [0001] The invention belongs to the field of rocket guidance, and relates to a trajectory planning method for the power descent section of a vertical landing of a rocket, in particular to a fuel-optimized fast trajectory planning method based on convex optimization. Background technique [0002] In recent years, reusable rockets have attracted a lot of attention worldwide. This can greatly reduce the cost of rocket launches, and make it easier and faster to perform a launch mission. In the process of realizing the precise landing of the rocket, the dynamic descent stage guidance plays an extremely important role. [0003] The trajectory planning problem of fuel-optimal powered descent landing is a typical optimal control problem. In order to improve the anti-jamming ability and maneuverability of the rocket during the power descent stage, it is necessary to solve this non-convex optimal control problem in real time to realize the precise landing of the rock...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24B64G1/62G06F30/20
CPCB64G1/242B64G1/62
Inventor 刘新福杨润秋
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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