High-dynamic centrifuge overload simulation test device

A simulation test and high dynamic technology, applied in the direction of aircraft component testing, etc., can solve the problems of inability to simulate the overload of the aircraft, limited movement space, and limited slack of the rope traction device, so as to solve the coupling problem of attitude and overload, increase the Large movement space, solving the effect of complex structure

Pending Publication Date: 2020-01-14
GENERAL ENG RES INST CHINA ACAD OF ENG PHYSICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The aircraft simulation experiment device disclosed above is mainly for flight performance testing under a single attitude or coupling of three attitudes, it is difficult to simulate the structural performance of the aircraft in a large overload environment, and it is impossible to continuously simulate the overload of the aircraft
The rope traction parallel robot and the centrifuge simulation device disclosed above can realize the large overload man

Method used

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  • High-dynamic centrifuge overload simulation test device
  • High-dynamic centrifuge overload simulation test device
  • High-dynamic centrifuge overload simulation test device

Examples

Experimental program
Comparison scheme
Effect test

Example Embodiment

[0051] Example 1, such as figure 1 Shown

[0052] A high-dynamic centrifugal overload simulation test device, including:

[0053] Provide the first degree of freedom device with static overload for test piece 5;

[0054] The second degree of freedom device 4 that provides the yaw rotation motion for the test piece 5;

[0055] The third degree of freedom device for the rolling and rotating movement of the test piece 5; the test piece 5 is placed on the third degree of freedom device, and the second degree of freedom device 4 is used for the degree of freedom control of the third degree of freedom device; the first degree of freedom device Used for the degree of freedom control of the second degree of freedom device 4.

Example Embodiment

[0056] Example 2, such as figure 1 Shown

[0057] The difference between this embodiment and Embodiment 1 is that the first degree of freedom device includes:

[0058] The main power mechanism for driving the rotation of the main arm system 3;

[0059] Main arm system 3; the power output end of the power mechanism is connected with the main arm system 3.

[0060] As the power element, the main power mechanism is arranged at the lower end of the structure. It adopts a direct drive mode and is directly connected to the main arm system 3 to achieve centrifugal rotation. This reduces other transitional connection structures and shortens the power transmission path; and the upper end of the main power mechanism is screwed It is connected with the civil foundation 1 to carry the main boom system 3 and its upper parts, avoiding the addition of redundant carrying mechanisms and shortening the axial size of the whole machine. This arrangement makes the whole machine simple, compact in structu...

Example Embodiment

[0061] Example 3, such as figure 1 Shown

[0062] The difference between this embodiment and Embodiment 1 is that the first degree of freedom device further includes:

[0063] Civil construction foundation 1; civil construction foundation 1 is formed into upper and lower layers (here refers to upper and lower cavities), in which the main power mechanism is fixed on the lower layer of civil construction foundation 1; here generally refers to the main power The housing part of the mechanism is fixedly installed on the foundation;

[0064] Instrument cabin 6; The instrument cabin 6 is placed on the upper part of the rotation center of the main boom system 3; this is generally a fixed installation;

[0065] Universal coupling 7; instrument compartment 6, universal coupling 7, second degree of freedom device 4, third degree of freedom device placed on the upper layer of civil foundation 1; connection of universal coupling 7 and instrument compartment 6 ; Here are generally set up from top...

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Abstract

The invention discloses a high-dynamic centrifuge overload simulation test device. The high-dynamic centrifuge overload simulation test device comprises a first freedom degree device for providing static overloads for a test piece, a second freedom degree device for providing the yaw rotating movement for the test piece, and a third freedom degree device for providing the rolling rotating movementfor the test piece. The test piece is arranged on the third freedom degree device, and the second freedom degree device is used for freedom degree control of the third freedom degree device. The first freedom degree device is used for freedom degree control of the second freedom degree device. According to the three-axis acceleration of a centrifugal machine resultant acceleration simulation aircraft, specifically, through rapid changing of the main arm system rotation speed, rapid changing of the centrifugal machine resultant acceleration value is achieved. Through rapid changing of the rotation direction of the second freedom degree device, and rapid changing of centrifugal machine resultant acceleration in the aircraft three-axis projection direction is achieved; and accordingly dynamic simulation of aircraft test piece three-axis acceleration changes is achieved, and continuous rapid dynamic changing overloads are accurately provided.

Description

technical field [0001] The invention belongs to the technical field of simulation test devices, in particular to a high dynamic centrifugal overload simulation test device. Background technique [0002] In order to verify whether the aircraft has good flight performance in actual flight, it is necessary to test the performance of the aircraft on the ground. The high dynamic flight environment is a flight mode in which the structure of the aircraft is under severe stress. It is necessary to test the structure of the aircraft in this environment. Performance, providing effective and reliable technical indicators and test data for actual air flight. [0003] The actual flight process of a highly dynamic aircraft often involves various factors such as the three-axis overload acceleration and the acceleration rate of change, but the current aircraft performance test devices are mostly concentrated in the following two aspects: [0004] In terms of independent simulation testing ...

Claims

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Application Information

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IPC IPC(8): B64F5/60
CPCB64F5/60
Inventor 蒋春梅洪建忠尹娇妹李明海张建全陈磊赵世鹏余小勇刘谦陈胜来杨敏
Owner GENERAL ENG RES INST CHINA ACAD OF ENG PHYSICS
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