A spacecraft soft landing simulation experiment device and simulation method

A technology for simulating experimental devices and simulation methods, which is applied in the field of soft landing physical simulation tests of aerospace landers and spacecraft soft landing simulating experimental devices, can solve problems such as lack, achieve low cost-effectiveness, stable performance, and avoid expensive Effect

Active Publication Date: 2018-01-16
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

However, at present, the research work on the ground experiment of spacecraft soft landing is quite scarce, and relevant theories and technologies are in urgent need of development.

Method used

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  • A spacecraft soft landing simulation experiment device and simulation method
  • A spacecraft soft landing simulation experiment device and simulation method
  • A spacecraft soft landing simulation experiment device and simulation method

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Embodiment Construction

[0031] The present invention provides a spacecraft soft landing simulation experiment device and simulation method. In order to make the purpose, technical scheme and effect of the present invention clearer and clearer, the present invention is further described in detail with reference to the accompanying drawings and examples. It should be pointed out that the specific implementations described here are only used to explain the present invention, not to limit the present invention.

[0032] Such as figure 1 As shown, the spacecraft soft landing simulation experiment device of the present invention includes a small-angle inclined platform 3, and the lower side of one end of the small-angle inclined platform 3 is connected with a small hydraulic synchronous adjustment system 4, and the small hydraulic synchronous adjustment system 4 is used to adjust The angle of the small-angle inclined platform 3; the small-angle inclined platform 3 is provided with a lander simulation part ...

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Abstract

The invention discloses a spacecraft soft landing simulation experimental device, which comprises a small angle inclined platform. A small hydraulic synchronous adjustment system is connected with a lower side of one end of the small angle inclined platform. The upper end of the small angle inclined platform is provided with a lander simulation. The lower surface of the lander simulator is provided with a floating air cushion; the upper surface of the lander simulator is attached with a light fluorescent reflector; a cold air thrust nozzle is disposed on the lateral of the lander simulator. The device also comprises a binocular computer vision system. The device utilizes an air flotation simulator and the small angle inclined platform to simulate a landing process, attitude and trajectory control in the final stage of a soft landing task of the spacecraft. The device also provides a simulation method. The experimental device can be used to verify the attitude, trajectory and landing point control performance of the landing simulator during soft landing.

Description

technical field [0001] The invention belongs to the technical fields of mechanics, control, aviation, etc., and specifically refers to a spacecraft soft landing simulation experiment device and simulation method, which can be applied to the physical simulation test of aerospace lander soft landing. Background technique [0002] With the rapid development of space science and technology, the pace of human exploration of space is accelerating. The first prerequisite for realizing missions to explore near-Earth planets and even deep space is to land precisely on the surface of celestial bodies, such as the soft landing of the moon and Mars probes. The space exploration project has huge complexity, and there are still many uncertain factors in each task link, which makes the landing spacecraft prone to insufficient landing accuracy and even mission failure. The development of future aerospace technology, especially deep space exploration missions, requires the development of hi...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G7/00
CPCB64G7/00
Inventor 文浩成龙金栋平
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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