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A fuel-saving control method for low-orbit orbiting lunar vehicles launched from lunar bases

A control method and aircraft technology, applied in the direction of aircraft, aerospace vehicles, space vehicle propulsion system devices, etc., can solve problems such as undiscovered optimal control methods and technologies for lunar orbiters, and achieve global optimality , the effect of simplicity and feasibility

Active Publication Date: 2021-10-26
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 control method and technology of the lunar orbiter launched from the lunar base

Method used

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  • A fuel-saving control method for low-orbit orbiting lunar vehicles launched from lunar bases
  • A fuel-saving control method for low-orbit orbiting lunar vehicles launched from lunar bases
  • A fuel-saving control method for low-orbit orbiting lunar vehicles launched from lunar bases

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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

A method for controlling the fuel consumption of a low-orbit orbiting spacecraft launched from a lunar base, which belongs to the field of optimal control technology for deep space exploration vehicles, adopts the indirect method based on the principle of Pontryagin's minimum value and the direct method of one-dimensional numerical search. The hybrid method combined with the above method can achieve accurate orbiting while saving fuel consumption to the greatest extent, so as to reduce the weight of the aircraft structure, increase the payload, and improve the benefits of space launch and space activities. The method provided by the present invention combines the advantages of the indirect method and the direct method: the problem is converted into a single-degree-of-freedom single-parameter search problem through the indirect method, and the direct method is specifically solved, which can ensure that the lunar surface base launches the low-orbit orbiter around the moon. The global optimality of fuel-saving control, the rapidity of the solution process, and the simplicity and feasibility of the control method in engineering implementation.

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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Patent Type & Authority Patents(China)
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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