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A kind of thermal insulation system for climate test of super-large aircraft and its parameter optimization method

A thermal insulation system and super-large technology, which are applied in the field of thermal insulation system and parameter optimization for climate testing of super-large aircraft, can solve problems such as laboratory structure and test impact, laboratory pressure relief, etc., to promote smooth development and a reliable experimental environment. , The effect of improving the portability of installation

Active Publication Date: 2022-07-01
CHINA AIRPLANT STRENGTH RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

On the other hand, the protective structure around the laboratory room is all connected by standard-sized insulation wall panels. The connection joints between the insulation wall panels increase with the increase in the volume of the laboratory space. The advantages and disadvantages of the insulation sealing method of the connection joints It is related to whether the thermal insulation and sealing function of the laboratory enclosure structure can be realized; there are holes in the enclosure structure through which the connecting cables of the equipment inside and outside the laboratory pass through, and the number of holes passing through the insulation wall increases with the increase of the laboratory environment simulation function. The hole sealing and heat preservation method is not suitable, which will lead to condensation, icing and even pressure release in the hole, which will have a significant impact on the structure and test of the laboratory

Method used

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  • A kind of thermal insulation system for climate test of super-large aircraft and its parameter optimization method
  • A kind of thermal insulation system for climate test of super-large aircraft and its parameter optimization method
  • A kind of thermal insulation system for climate test of super-large aircraft and its parameter optimization method

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Effect test

Embodiment 1

[0039] like figure 2 , 6 The shown thermal insulation system for climate testing of super-large aircraft includes thermal insulation wall panels 4, thermal insulation wall panel connecting assemblies 1 for connecting adjacent thermal insulation wall panels 4, joint seam sealing components 2 and pipe hole sealing components 3; The thermal insulation wall panel connecting assembly 1 includes a butt plate 10 and a clamping plate 11; the docking plate 10 is arranged at the joint of two adjacent insulation wall panels 4, and there are two clamping plates 11, and the two clamping plates 11 are fixedly arranged in the butt joint. The two ends of the board 10 are fixedly connected to the inner wall and the outer wall of the two adjacent thermal insulation wall panels 4 through countersunk head screws respectively;

[0040] like figure 2 , 4 , 5, the number of seam sealing assemblies 2 corresponds to the number of clamping plates 11. The seam sealing assembly 2 includes an adjusti...

Embodiment 2

[0043] What this embodiment records is the parameter optimization method of a kind of super-large aircraft climate test thermal insulation system of Embodiment 1, comprising the following steps:

[0044] S1, use the butt plate 10 to connect the adjacent two thermal insulation wall panels 4, and then use the countersunk head screws to fix the two clamping plates 11 on the same butt plate 10 with the inner and outer walls of the two adjacent thermal insulation wall panels 4; The width of the joint between the two adjacent thermal insulation wall panels 4 is controlled at 20mm;

[0045] S2. Rotate the adjustment screw 20, so that the push frame 21 pushes each push sleeve 221 to move on the corresponding sliding rod 220 under the action of the adjustment screw 20. During the movement of the push sleeve 221, the two expansion struts on the same push sleeve 221 222 expands along the length direction of the connecting rod 223, and stretches the elastic sealing plate 23, so that both ...

Embodiment 3

[0048] This embodiment differs from Embodiment 2 in that:

[0049] In step S1, the joint width between two adjacent thermal insulation wall panels 4 is controlled at 40mm;

[0050] In step S2, the number of expansion members 22 between two adjacent thermal insulation wall panels 4 is controlled to four;

[0051] In step S3, the number of sealing arc plates 321 on the same movable sleeve 320 is controlled to be three.

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Abstract

The invention discloses a thermal insulation system for super-large aircraft climate test and a parameter optimization method thereof, belonging to the technical field of aircraft testing. The seam sealing assembly and the pipe hole sealing assembly, the connecting seam sealing assembly includes an adjusting screw, a push frame, an expansion member and an elastic sealing plate, and a sealing groove and a pipe hole are arranged on the thermal insulation wall; the adjusting screw is used to adjust the push frame on the thermal insulation wall. The expansion member is used to control the expansion of the elastic sealing plate; the pipe hole sealing assembly includes a cable pipe, a sealing pressure plate and a cable pipe sealing member, the cable pipe is arranged inside the pipe hole, and the sealing pressure plate is sleeved on the cable on the pipe and connected with the thermal insulation wall plate, the cable pipe sealing member is sleeved on the cable pipe to seal the gap between the cable pipe and the pipe hole; the thermal insulation system of the invention has a reasonable structure design, sealing, The thermal insulation effect is stable and reliable.

Description

technical field [0001] The invention relates to the technical field of aircraft testing, in particular to a thermal insulation system for climate testing of super-large aircraft and a parameter optimization method thereof. Background technique [0002] Aircraft testing refers to subjecting the aircraft to climatic environmental stress under indoor simulation or outdoor natural climatic conditions, so as to obtain information on the extreme capability of the aircraft to withstand the climatic environment, and adapt to the climatic environment of the aircraft according to the development requirements, failure criteria and test data. A comprehensive evaluation is carried out to determine the degree to which the aircraft's climatic and environmental adaptability meets the requirements. [0003] As a large-scale carrying facility equipped with environmental tests, the climate laboratory can accommodate full-size aircraft and provide all-weather, time-limited high temperature, low...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): E04B1/76E04B1/80E04B1/68E04B1/61H02G3/04H02G3/22B64F5/60F16L5/02F16L5/04F16L5/08F16L59/12
CPCE04B1/762E04B1/80E04B1/7629E04B1/6801E04B1/6803E04B1/6116H02G3/0406H02G3/0462H02G3/22B64F5/60F16L5/02F16L5/04F16L5/08F16L59/121
Inventor 王彬文曹琦刘海燕苏杭吴学敏任战鹏吴敬涛
Owner CHINA AIRPLANT STRENGTH RES INST
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