Rapid trajectory optimization method of rocket power lowering landing process

A technology of power descent and power descent stage, which is applied to the landing devices of aerospace vehicles, motor vehicles, space navigation equipment, etc., and can solve problems such as inability to carry out engineering applications, and unable to guarantee the reliability and efficiency of the solution

Active Publication Date: 2019-11-19
BEIJING INSTITUTE OF TECHNOLOGYGY
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However, these algorithms cannot guarantee the reliability and efficiency

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  • Rapid trajectory optimization method of rocket power lowering landing process
  • Rapid trajectory optimization method of rocket power lowering landing process
  • Rapid trajectory optimization method of rocket power lowering 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 state...

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Abstract

The invention provides a rapid trajectory optimization method of a rocket power lowering landing process, discloses a fuel optimal power lowering landing rapid trajectory planning method, and belongsto the field of rocket guidance. An implementation method includes the steps that dynamics modeling and dimensional normalization are conducted on power lowering flying, and a three-dimensional dimensionless dynamics equation is established; an independent variable of the dynamics equation is changed from the time to the height; by introducing constraints required for power lowering flying, an optimal control problem of fuel optimal power lowering landing is established; a nonlinear dynamics equation in the original optimal control problem is treated as a linear dynamics equation; a part of the nonlinearity is retained and transformed into a constraint, a non-convex constraint is convexified, and a convex optimal control problem is established; the convex optimal control problem is discretized at non-uniform discrete points by using a four-order Runge-Kutta method, and a second-order cone programming problem is established; and the second-order cone programming problem is solved iteratively until converging, and trajectory planning of power lowering landing flying can be achieved. According to the rapid trajectory optimization method, the advantage of high efficiency is achieved, and the safety and the reliability of landing of the rocket power lowering stage can be improved.

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 rocket vertical landing, 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 rocket. ...

Claims

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Application Information

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IPC IPC(8): B64G1/24B64G1/62G06F17/50
CPCB64G1/242B64G1/62
Inventor 刘新福杨润秋
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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