Burnup minimization control method for launching low-orbit circumlunar aircraft in lunar surface base

A control method and technology for aircraft, which are applied to aircraft, spaceflight aircraft, and spaceflight aircraft propulsion system devices, etc., can solve problems such as optimal control methods and technologies for undiscovered lunar orbiters, and ensure global optimality , Simple and feasible effect

Active Publication Date: 2020-12-22
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

Up to now, no literature has been found that specifically discusses the optimal

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  • Burnup minimization control method for launching low-orbit circumlunar aircraft in lunar surface base
  • Burnup minimization control method for launching low-orbit circumlunar aircraft in lunar surface base
  • Burnup minimization control method for launching low-orbit circumlunar aircraft in lunar surface base

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Embodiment Construction

[0039] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary persons in the art without creative efforts belong to the protection scope of the present invention.

[0040] Such as figure 1 As shown, a method for controlling the fuel consumption of a low-orbit lunar orbiter launched from a lunar base, which specifically includes the following steps:

[0041] Such as figure 2 As shown in the figure, the ascent and turn of the low-orbit lunar spacecraft launched on the lunar surface, the flight height and longitudinal distance of the spacecraft are small compared to the radius of the moon. When designing the algorithm, the lunar surface is regarded as a plane, and t...

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Abstract

The invention provides a burnup minimization control method for launching a low-orbit circumlunar aircraft in a lunar surface base, and belongs to the technical field of deep space exploration aircraft optimal control. The control method adopts a mixed method combining an indirect method based on the Pontryagin minimum principle and a direct method of one-dimensional numerical value search to achieve accurate orbit injection, save fuel consumption to the maximum extent, so the structural weight of the aircraft is reduced, the loaded load is increased, and the benefits of spaceflight launchingand space activities are improved. According to the method, the advantages of the indirect method and the direct method are combined; a problem is converted into a single-degree-of-freedom single-parameter searching problem through the indirect method, and is specifically solved through the direct method; and the global optimality of minimum burnup control in the process of launching the low-orbitcircumlunar aircraft in the lunar surface base, the rapidity of the solving process and the simplicity and feasibility of the control method in engineering implementation can be ensured.

Description

technical field [0001] The invention belongs to the technical field of optimal control of deep-space exploration aircraft, and specifically relates to an optimal control method for a low-orbit moon-circling aircraft launched from a lunar surface base. Background technique [0002] The launch of the lunar orbiter at the lunar base is of great significance to the lunar exploration project and the third step of the three steps of "circling-falling-back" in my country's lunar exploration. Optimizing the control laws and corresponding trajectories of the aircraft's lift-off and orbiting process can save fuel consumption to the greatest extent, reduce the structural weight of the aircraft, expand the flight range, and expand the mission range. It has always been a key technology that has attracted much attention in aerospace engineering. . Up to now, no literature has been found that specifically discusses the optimal control method and technology of the lunar orbiter launched fr...

Claims

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Application Information

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IPC IPC(8): B64G1/00B64G1/10B64G1/40G06F17/11G06F17/13G06F17/15
CPCB64G1/105B64G1/40G06F17/11G06F17/13G06F17/15B64G1/1071B64G1/2427
Inventor 韩艳铧洪军停张勇
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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