Manned lunar exploration task orbit design system
A design system and orbit calculation technology, applied in design optimization/simulation, geometric CAD, special data processing applications, etc., can solve problems such as the inability to consider the coupling constraints of multiple tasks and the inability to improve the efficiency of task design, and achieve the goal of improving design efficiency. Effect
Active Publication Date: 2021-11-16
63919 TROOPS PLA
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Problems solved by technology
STK is limited to a single mission design and cannot consider the coupling constraints between multiple missions. The orbit design is too general to improve the efficiency of mission design
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[0024] The specific implementation manners of the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. The following examples are used to illustrate the present invention, but are not intended to limit the scope of the present invention.
[0025] The orbit design system (platform) for the manned lunar exploration mission provided in this embodiment mainly designs a multi-level platform architecture and implements specific functions under each level architecture. In order to realize the mission of manned lunar exploration, it is necessary to consider the design of the mission window. On this basis, the orbit design of different missions is carried out. The platform mainly includes the lunar window calculation subsystem, the lunar orbit deployment subsystem, the unmanned lunar orbit subsystem, The human ring moon subsystem and the manned moon landing subsystem. The functions of each subsystem include paramete...
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The invention relates to a manned lunar exploration task orbit design system. The system comprises a lunar landing window calculation subsystem, a lunar orbit deployment subsystem, an unmanned lunar roundabout subsystem, a manned lunar roundabout subsystem and a manned lunar landing subsystem. Each subsystem is formed by combining a window calculation module, a general transfer orbit calculation module, a free return orbit design module, a moon-earth return transfer orbit design module, a three-pulse transfer orbit design module and the like. When different tasks are designed, the system can consider constraint coupling between the tasks; a lunar landing window can be calculated, and a feasible lunar landing window is given on the premise that a specific track is not designed; a design initial value does not need to be provided, and only a design parameter, a constraint parameter and a range of traversal time are provided, so that a user can use conveniently; and the initial value and the high-precision result are displayed separately, high-precision calculation is performed on the basis of the reasonable initial value, and the design efficiency is improved.
Description
technical field [0001] The invention belongs to the technical field of manned lunar exploration mission orbit design, and in particular relates to a manned lunar exploration mission orbit design system. Background technique [0002] The manned lunar exploration orbit design is an important content of the manned lunar exploration mission demonstration. The manned lunar mission orbit design method involves the earth-moon transfer mission of manned aircraft and unmanned aircraft, including general transfer orbit, free return Orbit and fixed-point return orbit. Among them, the general transfer orbit and the free return orbit need to be orbitally matched with the launch mission, and the free return orbit and the fixed-point return orbit need to change orbits in different planes to achieve full lunar surface arrival and fixed-point return at any time respectively. Generally, the transfer orbit, free return orbit and fixed-point return orbit can use the conic curve splicing method...
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Patent Timeline
Login to View More IPC IPC(8): G06F30/20G06F30/12G06F111/04
CPCG06F30/20G06F30/12G06F2111/04Y02T90/00
Inventor 周晚萌吕纪远彭祺擘张海联武新峰倪庆
Owner 63919 TROOPS PLA