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
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[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
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[0154] The stopping criterion parameter is set to
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[0156] The stopping criterion parameter of discrete point update is
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[0158] The initial and final state...
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