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Rocket launching combustion gas flow impact simulation test device

A simulation test and rocket launch technology, applied in the direction of aerodynamic test, measuring device, machine/structural component test, etc., can solve the problems of complex structure of the test system, high R&D investment cost, long test cycle, etc., to improve the application range, reduced R&D time, and the effects of short test times

Active Publication Date: 2017-12-01
BEIJING INST OF SPACE LAUNCH TECH +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to solve the problems existing in the existing rocket launch gas flow impact simulation test system, such as long development cycle, long test cycle, long calculation cycle, complex structure of the test system, high research and development investment cost, etc., the present invention innovatively proposes a rocket launch gas flow The impact simulation test device effectively replaces the existing scale-down test plan and loading test plan, thereby effectively solving the problems of long test cycle, long calculation cycle, complex test system structure, and R&D investment cost in the existing technology through a simple test device structure. advanced questions

Method used

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  • Rocket launching combustion gas flow impact simulation test device
  • Rocket launching combustion gas flow impact simulation test device

Examples

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Comparison scheme
Effect test

Embodiment 1

[0028] Embodiment 1: Using the present invention for quick detection and verification of adjustable gas flow field

[0029] Such as figure 1 , 2 , 3, the present invention is based on a flat launch system, and has innovatively developed a rocket launch gas flow impact simulation test device, which includes a test bench 1, a test frame 2, a test plate 3, and a conical head guide rod 4 , engine 5 and fixed bracket 6, the upper surface of test bench 1 has a bar-shaped chute, in the present embodiment, the upper surface of test bench 1 has two parallel bar-shaped chutes, the test frame 2 The bottom end is placed in the chute. The test frame 2 includes two symmetrical L-shaped side plates and a crossbeam. A crossbeam is arranged between the two L-shaped side plates. The bottom end of each L-shaped side plate is matched with the two strip-shaped chute on the test frame 2, and through this matching structure, the test frame 2 can slide on the test bench plate 1, but the distance be...

Embodiment 2

[0032] Embodiment 2: Using the present invention for rapid verification of gas flow impact attitude

[0033] Such as figure 1, 2 , 3, on the basis of Embodiment 1, the device also includes an adjustment screw 10, the adjustment screw 10 is fixedly connected with the test board 3 and the test frame 2 at the same time, after determining the horizontal and vertical inclination angles of the test board, the present invention passes The adjusting screw 10 locks the test board 3 on the test frame 2 . Moreover, the device also includes a height-adjusting gasket 11, which is arranged between the test bench 1 and the test frame 2, and the height of the test frame can be adjusted by changing the number of the height-adjusting gasket 11, and then adjusted. Test the height of board 3. The structure of the conical head guide rod 4 connected to the centering of the nozzle of the engine 5 is combined with the angle adjustment of the test board 3 on the test frame 2 .

[0034] In the impl...

Embodiment 3

[0036] Embodiment 3: Applying the present invention to pressure testing under the impact environment of high-temperature gas flow

[0037] Such as figure 1 , 2 , 3, on the basis of embodiment one and embodiment two, the rocket launch gas flow impact simulation test device involved in the present embodiment also includes a single introduction pipe 7, and the sensor 9 is connected with one end of the single introduction pipe 7, and the single introduction pipe 7 The other end of the tube 7 is fixedly connected to the inner surface of the test board 3; the device also includes an adapter 8 for connecting the sensor 9 and the single lead tube 7, the sensor 9 is connected to one end of the adapter 8, and the other end of the adapter 8 is fixed Connect the single guide tube 7.

[0038] During the implementation of this embodiment, one end of the adapter 8 is first connected to the single lead tube 7, and the other end is connected to the sensor 9, and then the exposed end of the s...

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Abstract

The invention discloses a rocket launching combustion gas flow impact simulation test device, which comprises a test bed plate, a test rack, a test plate, a tapered head guide rod, an engine and a fixed support, wherein the upper surface of the test bed plate is provided with a bar-shaped sliding groove; the bottom end of the test rack is arranged in the sliding groove; the test bed plate and the test rack are fixedly connected through a bolt; the test plate is fixed on the test rack; the tapered head guide rod is provided with a tapered head front end and a flat head tail end, the tapered head front end abuts against the outer side surface of the test plate, and the flat head tail end is connected with a nozzle of the engine; the inner side surface of the test plate is fixedly connected with a sensor; and the engine is fixed on the fixed support. The rocket launching combustion gas flow impact simulation test device has the outstanding advantages of short production cycle, short test time, simple structure, low cost and the like.

Description

technical field [0001] The invention relates to the technical field of launch gas dynamics, and more specifically, the invention is a rocket launch gas flow impact simulation test device. Background technique [0002] Launch gas dynamics is one of the sub-disciplines of professional aerodynamics. Like aerodynamics as the "forerunner" of aerospace technology, it plays a preliminary role in the field of rocket launch technology, especially in the research and development of rocket launch technology. Launch gas dynamics guide launch technology research and development is mainly reflected in two aspects: First, in the launch technology program demonstration stage, provide parameters such as gas flow impact, ablation force, and thermal overall environment that affect the launch system and rocket, and clarify the impact of gas flow , the distribution range and intensity of the specific environment of ablation force and heat; second, in the specific development stage of the launch ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/00G01M9/08
CPCG01M9/00G01M9/08
Inventor 陈劲松杜小坤陆江刘杰王玉波贺娜曾玲芳王帅
Owner BEIJING INST OF SPACE LAUNCH TECH
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