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Aircraft vibration superposition fatigue strength testing system and low-rigidity load applying method thereof

A fatigue strength and testing system technology, applied in the field of aircraft testing, can solve the problems of fatigue load loading that cannot be quickly changed, complex technical paths, and high costs, and achieve high convenience and feasibility, broad application prospects, and rapid weight gain. Effect

Active Publication Date: 2022-07-05
CHINA AIRPLANT STRENGTH RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The disadvantage is that the static load can only be changed through weights, and the load cannot be changed quickly to achieve a certain frequency of fatigue load loading; the actuator is directly connected to the test piece through the loading rod, when the test piece reciprocates under the action of vibration load , it is necessary to realize the follow-up function of the loading rod through a separate control algorithm, so as to avoid the influence of reciprocating motion and realize static or fatigue loading
The disadvantage is that servo control or iterative control algorithms need to be developed separately, the technical path is complicated and the cost is high, and the final control effect is also affected by various conditions

Method used

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  • Aircraft vibration superposition fatigue strength testing system and low-rigidity load applying method thereof
  • Aircraft vibration superposition fatigue strength testing system and low-rigidity load applying method thereof
  • Aircraft vibration superposition fatigue strength testing system and low-rigidity load applying method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0040] like figure 1 As shown, the aircraft vibration superposition fatigue strength test system includes a vibration table 1 for placing aircraft specimens, a main weight 2 for applying static load, and an actuator 3 for adjusting the static load. The actuator 3 is Commercially available in the aerospace industry as a propeller;

[0041] The top of the main weight 2 is provided with a first wire rope 4, and the end of the first wire rope 4 is provided with a first steel ring 42 after passing around the first certain pulley 41. The first steel ring 42 is connected with a rubber rope 5, and the rubber rope 5 is another. One end is connected with a second steel ring 51, the second steel ring 51 is connected with the aircraft test piece placed above the vibration table 1 through a second steel wire rope 52, and the second steel ring 51 is also connected with the actuator through a third steel wire rope 6. 3 The top is connected, the third wire rope 6 goes around the second fixed...

Embodiment 2

[0043] like figure 2 As shown, the aircraft vibration superposition fatigue strength test system includes a shaking table 1 for placing aircraft specimens, a main weight 2 for applying static load, and an actuator 3 for adjusting static load;

[0044] The top of the main weight 2 is provided with a first wire rope 4, and the end of the first wire rope 4 is provided with a first steel ring 42 after passing around the first fixed pulley 41. The first steel ring 42 is connected with three rubber ropes 5, and the rubber rope 5 is another. One end is connected with a second steel ring 51, the second steel ring 51 is connected with the aircraft test piece placed above the vibration table 1 through a second steel wire rope 52, and the second steel ring 51 is also connected with the actuator through a third steel wire rope 6. 3 The top is connected, the third wire rope 6 goes around the second fixed pulley 61 and the third fixed pulley 62 in turn, the bottom of the second fixed pulle...

Embodiment 3

[0048] This embodiment is based on the low-rigidity load application method of the aircraft vibration superimposed fatigue strength test system in Embodiment 1, such as Figure 7 shown, including the following steps:

[0049] S1. Preparation:

[0050] S1-1: Determine the application direction of the static load, connect the first wire rope 4 to the aircraft specimen, and the first wire rope 4 extends along the static load application direction;

[0051] S1-2: Determine the applied amount of static load, adjust the weight of the main weight 2 according to the applied amount, and select a rubber rope 5 with appropriate stiffness. When the entire weight of the main weight 2 acts on the rubber rope 5, the rubber rope 5 The elongation is 130% of the original length;

[0052] S1-3: Determine the applied frequency of the static load, and adjust the actuating force, loading frequency and displacement of the actuator 3 according to the applied frequency;

[0053] S2. Static load app...

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Abstract

The invention discloses an aircraft vibration superposition fatigue strength testing system and a low-rigidity load applying method thereof, and belongs to the technical field of aircraft testing, and the aircraft vibration superposition fatigue strength testing system comprises a vibration table for placing an aircraft test piece, a main weight for applying a static load and an actuator cylinder for adjusting the static load. The low-rigidity load applying method comprises the following steps: S1, preparation work; s2, applying a static load; and S3, applying a dynamic load. According to the aircraft vibration superposition fatigue strength test system, an integral structure of combining the rubber rope with the actuator cylinder is adopted, and a low-rigidity fatigue load applying method is provided based on the system, so that the fatigue load can be tested only by adopting the rubber rope with proper rigidity and the actuator cylinder with proper parameters according to the requirement of the fatigue load; and fatigue load loading with a certain frequency can be realized through a simple control method, and the method has a wide application prospect.

Description

technical field [0001] The invention relates to the technical field of aircraft testing, in particular to an aircraft vibration superimposed fatigue strength testing system and a low-rigidity load applying method thereof. Background technique [0002] During the flight of the aircraft, it is often necessary to bear multiple complex loads at the same time. From the perspective of mechanics, it mainly includes dynamic loads such as vibration and shock and static loads such as static fatigue. In order to simulate the load environment of the aircraft in the air as realistically as possible in the laboratory environment, it is often necessary to apply the above two types of loads simultaneously in the aircraft ground strength test. The load application is one of the key links of the aircraft ground strength test. Whether the load can be applied correctly directly affects the reliability of the conclusion of the aircraft ground strength test. Therefore, the load application meth...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M99/00G01M7/02B64F5/60
CPCG01M99/005G01M99/007G01M7/02B64F5/60
Inventor 王彬文傅波刘海涵李凯翔何石黄文超
Owner CHINA AIRPLANT STRENGTH RES INST
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