KR101163489B1 - Simulated load test rig using deflection method for deploying wing system - Google Patents

Abstract

The present invention is a simulated load test device for deploying wings using displacement, more specifically, a deployment type using displacement for verifying the deployment performance of the wing deployment device by simulating aerodynamic loads applied vertically and horizontally to a vehicle having a deployment wing. It is an object to provide a simulated load tester for wings.
To this end, the present invention is characterized in that it comprises a lower plate for mounting the test body, and a pair of inclined plates which are installed on both upper surfaces of the lower plate and which can be tilted toward the center of the lower plate. Provided is a simulated load tester for deployable wing using displacement.

Description

Simulated Load Tester for Displaced Wings Using Displacement {SIMULATED LOAD TEST RIG USING DEFLECTION METHOD FOR DEPLOYING WING SYSTEM}

The present invention is a simulated load test device for deploying wing using displacement, more specifically to simulate the aerodynamic load that is added vertically and horizontally to an aircraft having a deploying wing to determine the displacement used to verify the deployment performance of the wing deployment device The present invention relates to a simulated load test apparatus for the deployed wing.

In general, when a flying vehicle having a deployable wing is dropped from an aircraft, horizontal and vertical loads act on the wing while the wing of the flying vehicle is deployed. In order to perform the wing tester performance test of a vehicle with such a deployed wing, a device capable of simulating the desired horizontal and vertical loads on a moving wing is required. However, since it is very difficult to add a desired load to a moving object with a conventional load adding device, the present invention has been proposed to easily implement this.

The conventional simulated load tester mainly simulates only horizontal loads and cannot simulate vertical loads. In addition, in some cases, the test was performed in a state in which the impact load when the wing was fully deployed was transmitted to the test body as it was because the aircraft did not satisfy the boundary condition when the aircraft was dropped from the aircraft, causing damage to the test body.

However, not only the horizontal load but also the vertical load acts on the aircraft actually dropped from the aircraft, and the impact at the time of wing deployment acts as a force to move the aircraft forward and backward.

Therefore, for more accurate testing, a simulated load test apparatus capable of simulating conditions similar to the actual conditions has been required for a vehicle having a deployed wing.

SUMMARY OF THE INVENTION The present invention has been made to solve the above-mentioned problems, and mechanically modulates the vertical load of the aerodynamic load acting on the deployable wing through a combination of the positional displacement of the deployable wing, the design of the inclined profile and the roller size. It is an object of the present invention to provide a simulated load testing device for a deployed wing using displacement that can accurately simulate and simulate a horizontal load using a spring.

In order to achieve the above object, the present invention provides a simulated load test apparatus for a deployable wing using a displacement for testing the load acting on the wing of the flying body having a deployable wing, and the lower plate for mounting the test body and It is installed on both sides of the lower plate, characterized in that it comprises a pair of inclined plate that can be tilted toward the center of the lower plate.

In addition, each of the brackets provided on the outer lower surface of the pair of inclined plate, characterized in that the bracket has a plurality of vertically arranged holes that can adjust the inclination of the pair of inclined plate.

In addition, the support for supporting the lower plate, and is installed on the support, characterized in that it comprises a linear guide for relieving the impact load through the boundary condition simulation when the deployment wing of the test body is completed.

In addition, it characterized in that it comprises a spring fixing rod which can be mounted in the center of the upper surface of the lower plate to mount a spring for simulating the horizontal load of the test body.

According to the simulated load test apparatus for the deployed wing using the displacement according to the present invention, the horizontal load and the vertical load can be simulated independently and simultaneously, and the load can be changed by simple operation.

In addition, the accuracy of the test can be increased by effectively relieving impact loads by simulating boundary conditions similar to those of free flight during wing deployment.

Figure 1 is a detailed configuration of the simulated load test apparatus of the present invention using a displacement wing.
2 is a conceptual view of the deployment test operation of the simulated load tester of the deployment type wing using the present inventors displacement.
3 is a view showing the roller state before the blade deployment and after the blade deployment of the simulated load tester of the deployment-type blade using the inventors displacement.

Hereinafter, with reference to the accompanying drawings, a preferred embodiment of the simulated load test device of the developed wing using the displacement according to the present invention.

Figure 1 is a detailed configuration of the simulated load test device of the deployable wing using the displacement of the inventor, Figure 2 is a conceptual diagram of the development test operation of the simulated load test device of the deployable wing using the displacement of the present invention, Figure 3 It is a figure which shows the roller state before a wing | blade deployment and after a wing | blade deployment of the simulated load test apparatus of the deployed wing | blade.

As shown in FIG. 1, the present invention provides a lower plate 20 on which a test body 100 having a deployable wing 110 is mounted, a support 120 including a linear guide 70, and a deployable wing of the test body. A pair of inclination plate 10 on which the 110 is placed, and a bracket 40 for adjusting the inclination angle of the inclination plate 10 are included.

The lower plate 20 is installed on the support 120 and is formed in a substantially rectangular shape, and a front mounting surface 130 on which the test body 100 can be mounted is installed on the front upper surface, and around the center of the lower plate 20. The spring fixing rod 60, which can be mounted to the spring used when simulating the horizontal load with respect to the test body 100 is installed to protrude.

In addition, a pair of linear guides 70 on the upper surface of the support 120 to mitigate the impact by simulating the boundary condition at the completion of deployment of the wing 110 of the test body are installed in parallel with each other. The lower surface of the 20 is installed in the linear guide 70 so that linear movement is possible. In other words, the impact generated when the developed wing 110 of the test object is completed deployment causes the lower plate 20 to linearly move, thereby mitigating the impact.

In addition, a plurality of pedestals 30 for supporting the inclined plate 10 are respectively provided on both sides of the upper surface of the lower plate 20, and the inclined plate 10 is hinged on the plurality of pedestals 30.

In addition, a first support member 80 and a second support member 90 for supporting the inclined plate 10 are coupled to the bottom surface of the lower plate 20 in a substantially 'B' shape, and the second support member One end of the 90 is coupled to the bracket 40 installed on the inclined plate 10.

A pair of brackets 40 are respectively provided on the outer lower surface of the inclined plate 10, and a plurality of holes are drilled in the vertical direction, and are used to adjust the inclination of each inclined plate 10. In other words, when the second support member 90 is coupled to the uppermost hole of the plurality of holes of the bracket 40, the inclination of the inclined plate 10 is reduced, and the second support is disposed at the lowermost hole. When the member 90 is coupled, the inclination of the inclined plate 10 becomes large.

Hereinafter will be described the test body 100 applied to the simulated load test device of the deployed wing using the displacement according to the present invention and the theory applied to the test device.

The test body 100 includes two stages of development units as described in the specification of the patent application No. 10-2009-0118675 filed by the present inventor, the first stage deployment unit is installed inside the test body 100 The developed wing 110 is to be partially deployed by a spring, and the second stage deployment unit has a mechanism to fully deploy the developed wing 110 by an electric motor installed inside the test body 100.

In addition, the theory applied to the test apparatus will be described. There are two methods for simulating the load conditions acting on the structure. First, the unit load method that simulates the load condition by applying direct load to the structure, and second, the displacement occurs when the load is applied. There is a unit displacement method that simulates. In the present invention, the second unit displacement method is used.

Next, the method for obtaining a displacement in the unit displacement method will be described.

[Figure 1]

(E: modulus of elasticity I: second moment in cross section)

The aerodynamic data from the analysis is given as the distribution load as shown in [a] (a), and it is assumed that this distribution load affects only the moment where the body and the expandable wing 110 are combined. Do it. The moment generated at the portion where the body and the expandable wing 110 of the test body 100 is coupled can be obtained through integration as shown in [Fig. 1] (b), and generates an equivalent moment as the result of this calculation. The concentrated load can be obtained from the aerodynamic center or cantilever end point as shown in Fig. 1 (b) and (c).

In particular, the displacement (δ) due to the load at the end of the cantilever beam can be easily obtained from the equation (Fig. 1) (c). Using this displacement (δ), the inclination of the inclined surface 10 of the test apparatus can be appropriately adjusted. Formation enables load simulation using the unit displacement method.

Hereinafter, the test method of the simulated load test apparatus for the deployable wing using the displacement according to the present invention will be described.

After calculating the working load (P) applied when the test specimen 100 is applied to the actual situation, calculate the displacement (δ) using the equation shown in [Figure 1] (c). The obtained displacement δ is applied to the height of the inclined plate 10 of the present invention to adjust the angle of the inclined plate using the bracket 40. The rollers 50 are installed at both ends of the developed wing 110 of the test body and placed on the inclined plate 10. And one end of the spring for simulating the horizontal load is mounted on the spring fixing rod (60), the other end is installed on the ring by installing a ring on the lower end of the deployment wing (110).

In order to accurately simulate the vertical load by using the displacement (δ) according to the working load (P), the size of the roller 50 is installed on both ends of the deployed wing and the bracket 40 of the inclined plate 10 Adjust the angle In addition, the simulation of the horizontal load is achieved by adjusting the stiffness coefficient of the spring.

Thereafter, the first stage deployment unit and the second stage deployment unit of the test body 100 are operated. As a result of the operation, the developed wing 110 of the test body is raised along the inclined plate 110 by drawing a circular arc, as shown in FIG. 3, wherein the vertical load is inclined by the inclination, and the horizontal load is simulated by the spring. .

In addition, the impact load at the completion of deployment by the two-stage deployment unit is transmitted to the test body 100, wherein the lower plate 20 on which the test body 100 is mounted is freely linearly moved along the linear guide 70. The impact load can be alleviated by simulating boundary conditions.

In the above description of the preferred embodiment of the present invention, the present invention is not limited thereto, and a person of ordinary skill in the art may have various modifications without departing from the technical spirit of the present invention described in the claims of the present invention. Changes will be possible.

DESCRIPTION OF SYMBOLS 10 Inclined board 20 Lower board 30 Support base 40 Bracket
50: roller 60: spring fixing rod 70: linear guide 80: first support member
90: second support member 100: test body 110: deployment type wings
120: support 130: mount

Claims (4)

As a simulated load tester of the deployable wing using displacement for testing the load acting upon the wing deployment of the aircraft with the deployable wing,
A lower plate 20 for mounting the test body 100,
A pair of inclined plates 10 installed on both upper surfaces of the lower plate 20 and capable of tilt adjustment toward the center of the lower plate;
It includes brackets 40 are respectively installed on the outer lower surface of the pair of inclined plate 10,
The bracket (40) is a simulated load test device using a displacement wing having a plurality of vertically arranged holes that can adjust the inclination of the pair of inclined plate (10). delete The method of claim 1,
And the support 120 for supporting the lower plate 20,
Installed on the support 120 when the deployment wing 110 of the test body 100 is completed deployment, using a displacement, characterized in that it comprises a linear guide 70 to mitigate the impact load by simulating boundary conditions Simulated load tester for deployment wing. The method of claim 1,
Simulated load testing device of a deployment type wing using displacement, characterized in that it comprises a spring fixing rod (60) to mount a spring for simulating a horizontal load with respect to the test body (100) in the center of the lower plate (20) .

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