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Microgravity simulating spacecraft ground emitting and testing device

A space vehicle, a technology for simulating microgravity, which is applied to the ground equipment of space navigation, transportation and packaging, space navigation equipment, etc., and can solve the problems that cannot meet the installation requirements of force sensors, and the drop tower test chamber cannot resist the impact of launch force, etc. Achieve the effect of shortening the test preparation cycle, improving the rate of repeated utilization, and simplifying the experimental equipment

Inactive Publication Date: 2007-10-24
NAT UNIV OF DEFENSE TECH
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AI Technical Summary

Problems solved by technology

At present, whether the drop tower method adopts the scheme of free fall after being thrown up or directly from a high place, the drop tower test chamber cannot resist the impact of the launch force.
Moreover, to measure the component of the launch force, the force sensor must be installed on a benchmark with a certain rigidity. The existing drop tower experiment cabin is in a free state during the fall process, which cannot meet the installation requirements of the force sensor at all.

Method used

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  • Microgravity simulating spacecraft ground emitting and testing device
  • Microgravity simulating spacecraft ground emitting and testing device
  • Microgravity simulating spacecraft ground emitting and testing device

Examples

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Embodiment Construction

[0025] As shown in Fig. 1, Fig. 2 and Fig. 3, the space vehicle ground launching test device of the simulated microgravity of the present invention comprises support 1, launch tube 6 and clamp 7, and support 1 bottom is provided with four fixed base plates 11, and support 1 By fixing the bottom plate 11 on the reinforced concrete foundation, the ability of the support 1 to withstand the impact of launching is greatly improved. The support 1 has good stability and is convenient for accurate measurement. A linear guide rail 2 is vertically installed on one side of the support 1. The linear guide rail 2 A sliding launching platform 3 is installed on the top, and the launching tube 6 is fixed on the sliding launching platform 3 through a clamp 7. A buffer 5 is arranged below the sliding launching platform 3, and the buffer 5 is fixed on the reinforced concrete foundation through anchor bolts. The launch platform 3 slides up and down along the linear guide rail 2 at variable speeds,...

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Abstract

The invention relates to an analog micro weight space crafter land emitting testing device that comprises the bracket, emission barrel, fixture, erecting linear guide track at one side of the bracket, sliding emission platform on the linear guiding track, with the emission barrel fixed on the sliding emission platform through the fixture, with buffer set under the platform. It has imitable analog micro weight environment, being able to finish the traditional land emitting, with instant parameter testing function, integrating the testing device with the emission platform, strong in impact resistance ability.

Description

technical field [0001] The invention relates to a ground launch test device for a space vehicle, in particular to a space vehicle ground launch test device for simulating microgravity. Background technique [0002] The traditional fixed-point launch test method cannot meet the requirements of advanced space vehicle development for ground tests because it does not get rid of the influence of gravity. For a long time, the ground test devices of space vehicles have been carried out by manually building launch supports, launching at fixed points, and combining various test instruments for measurement. This method has disadvantages such as long construction period of launching device and testing device, only fixed-point launching, non-adjustable launching height, numerous and messy instruments, and low reuse rate of test devices. Therefore, it is of great practical significance to realize the integration of test system test functions, the diversification of test objects, the mod...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G5/00
Inventor 李圣怡戴一帆彭小强解旭辉关朝亮王建敏徐从启
Owner NAT UNIV OF DEFENSE TECH
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