Movable airfoil deflection assessment test load loading device installed on stabilizer

Abstract

The invention relates to a load loading device for installing a movable airfoil deflection assessment test on a stabilizer. The load loading device comprises a force bearing frame, a test piece, a force bearing wall, a lateral supporting beam, a bottom supporting stand column, a rotary loading frame, a position control actuator cylinder and a movable airfoil loading actuator cylinder. The bearing frame is rectangular, the top of the bearing frame is connected with the stabilizer loading actuator cylinder, a test piece is arranged in the bearing frame and comprises a stabilizer and a movable wing surface, and the stabilizer loading actuator cylinder is downwards connected with the stabilizer and is perpendicular to the stabilizer; the load-bearing wall is connected to one end of the load-bearing frame, and the stabilizing plane is fixed on the load-bearing wall; the lateral supporting beam is connected to the stand column on one side of the force bearing frame, and the position control actuator cylinder is connected to the lateral supporting beam. The bottom end of the bottom supporting stand column is connected to the bottom of the force bearing frame and located below the test piece; the rotary loading frame is arranged in the force bearing frame, the bottom of the rotary loading frame is hinged to the top end of the bottom supporting stand column and connected with the position control actuator cylinder, the top of the rotary loading frame is connected with the movable wing surface loading actuator cylinder, and the movable wing surface loading actuator cylinder is downwards connected with the movable wing surface.

Description

Technical Field

[0001] This application belongs to the technical field of aircraft movable wing surface deflection function assessment tests, and specifically relates to a load loading device for aircraft movable wing surface deflection assessment tests installed on a stabilizer surface. Background Art

[0002] The movable wing surface generates corresponding aerodynamic forces through deflection and is a moving control surface for manipulating the flight attitude of an aircraft. The test for assessing the deflection function of the movable wing surface is an important part of aircraft tests.

[0003] In the assessment test of the movable wing surface deflection function, in order to truly reproduce the boundary conditions of the movable wing surface during aircraft flight and ensure the reliability of test results, the movable wing surface is mostly installed on the corresponding stabilizer surface and corresponding aerodynamic simulation loads are applied, requiring the loads applied on the movable wing surface to be perpendicular to the movable wing surface.

[0004] Currently, when conducting the assessment test of the movable wing surface deflection function, it is mostly necessary to install the test load loading device on the ground track. It is difficult to implement under the condition of lacking a ground track. The installation of the ground track requires a large space site, and the test is restricted to be carried out only in a specific space site, which is not conducive to the flexible implementation of the test. Moreover, it is adjusted in a top-loading manner for the test load loading device to make the loads applied on the movable wing surface perpendicular to the movable wing surface, resulting in poor stability.

[0005] In view of the existence of the above technical defects, this application is proposed. Summary of the Invention

[0006] The purpose of this application is to provide a load loading device for aircraft movable wing surface deflection assessment tests installed on a stabilizer surface to overcome or mitigate at least one aspect of the known technical defects.

[0007] The technical solution of this application is as follows:

[0008] A load loading device for aircraft movable wing surface deflection assessment tests installed on a stabilizer surface includes a load-bearing frame, a test piece, a load-bearing wall, a lateral support beam, a bottom support column, a rotary loading frame, a position control actuator, and a movable wing surface loading actuator;

[0009] The load-bearing frame is rectangular, with a stabilizer surface loading actuator connected to the top. A test piece is arranged inside it. The test piece includes a stabilizer surface and a movable wing surface. The stabilizer surface loading actuator is connected downward to the stabilizer surface and is perpendicular to the stabilizer surface;

[0010] The load-bearing wall is connected to one end of the load-bearing frame, and the stabilizer surface is fixed on the load-bearing wall;

[0011] The lateral support beam is connected to the column on one side of the load-bearing frame, and the position control actuator is connected thereto;

[0012] The bottom of the bottom support column is connected to the bottom of the load-bearing frame and is located below the test piece.

[0013] The rotary loading frame is arranged inside the load-bearing frame. Its bottom is hinged to the top of the bottom support column and is also connected to the position control actuator. Its top is connected to the movable wing loading actuator, and the movable wing loading actuator is connected downward to the movable wing.

[0014] The side of the rotary loading frame facing away from the lateral support beam is an open structure.

[0015] According to at least one embodiment of the present application, in the movable wing deflection assessment test load loading device installed on the stabilizer surface described above, the load-bearing frame includes a bottom frame, a top frame arranged above the bottom frame, and columns connected to both sides of the bottom frame and the top frame.

[0016] The load-bearing frame can be welded by I-beams. Cross beams, longitudinal beams, and diagonal braces are arranged between its bottom frame, top frame, and columns on both sides.

[0017] According to at least one embodiment of the present application, in the movable wing deflection assessment test load loading device installed on the stabilizer surface described above, the load-bearing wall can be composed of a group of columns. Cross beams, longitudinal beams, and diagonal braces are arranged between the columns, and a load-bearing plate is arranged at the position connected to the stabilizer surface. The root of the stabilizer surface is fixed to the load-bearing plate by long rod bolts.

[0018] According to at least one embodiment of the present application, in the movable wing deflection assessment test load loading device installed on the stabilizer surface described above, the lateral support beam is connected to the column on one side of the load-bearing frame through multiple horizontal support rods.

[0019] According to at least one embodiment of the present application, in the movable wing deflection assessment test load loading device installed on the stabilizer surface described above, between the bottom of the rotary loading frame and the top of the bottom support column, a pin joint is used through a single and double ear structure with a pin shaft.

[0020] According to at least one embodiment of the present application, in the movable wing deflection assessment test load loading device installed on the stabilizer surface described above, the position control actuator is connected downward to the rotary loading frame.

[0021] According to at least one embodiment of the present application, in the movable wing deflection assessment test load loading device installed on the stabilizer surface described above, when the position control actuator has no stroke, the rotary loading frame deflects outward to reach the outermost deflection angle required for test loading. When the rotary loading frame deflects inward and abuts against the lateral support beam, it deflects inward to reach the innermost deflection angle required for test loading.

[0022] According to at least one embodiment of the present application, in the load loading device for the movable wing surface deflection assessment test installed on the stabilizer surface, the test piece is a wing with a flap, where the wing box section is the stabilizer surface and the flap is the movable wing surface;

[0023] The flap includes a main flap and a fairing;

[0024] The movable wing surface loading actuator is divided into a main flap loading actuator and a fairing loading actuator, which are respectively connected to the main flap and the fairing.

[0025] The present application has at least the following beneficial technical effects:

[0026] Provide a load loading device for the movable wing surface deflection assessment test installed on the stabilizer surface. The design and the load-bearing wall support and fix the stabilizer surface of the test piece. During the test, the stabilizer surface loading actuator can load the required load on the stabilizer surface, and the movable wing surface loading actuator can load the required load on the movable wing surface. When the movable wing surface deflects, the position control actuator can drive the rotating loading frame to rotate, adjust the attitude of the rotating loading frame, change the direction of the movable wing surface loading actuator, and keep the movable wing surface loading actuator perpendicular to the movable wing surface to simulate the boundary conditions of the movable wing surface during the flight of the aircraft and ensure the accuracy of the test results. Description of the Drawings

[0027] Figure 1 is a schematic diagram of the load loading device for the movable wing surface deflection assessment test installed on the stabilizer surface provided by the embodiment of the present application;

[0028] Figure 2 is a partial schematic diagram of the load loading device for the movable wing surface deflection assessment test installed on the stabilizer surface provided by the embodiment of the present application in cooperation with the flap with a wing;

[0029] Wherein:

[0030] 1 - load-bearing frame; 2 - test piece; 3 - load-bearing wall; 4 - lateral support beam; 5 - bottom support column; 6 - rotating loading frame; 7 - position control actuator; 8 - movable wing surface loading actuator.

[0031] For better illustration of this embodiment, some contents in the drawings are omitted, enlarged or reduced, which are only for illustrative purposes and should not be construed as a limitation to the present application. Detailed Embodiments

[0032] To make the technical solutions and their advantages of this application clearer, the following will further describe the technical solutions of this application clearly and completely in conjunction with the accompanying drawings. It can be understood that the specific embodiments described herein are only partial embodiments of this application, which are only used to explain this application and not to limit this application. It should be noted that for the convenience of description, only the parts related to this application are shown in the drawings, and other related parts can refer to the general design.

[0033] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should have the ordinary meanings understood by those of ordinary skill in the art to which this application belongs. The "including" used in the description of this application means that the concept appearing before this word covers the concepts listed after this word and their equivalents, without excluding other related concepts.

[0034] In addition, the words indicating directions used in the description of this application are only used to indicate the relative directions or position relationships. When the absolute position of the object being described changes, its relative position relationship may also change accordingly. It should also be noted that unless otherwise clearly specified and limited, the words such as "installation" and "connection" used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium. Those skilled in the art can understand their specific meanings in this application according to the specific situation.

[0035] A test load loading device for evaluating the deflection of a movable airfoil installed on a stabilizer surface, as Figure 1 shown, includes a load-bearing frame 1, a test piece 2, a load-bearing wall 3, a lateral support beam 4, a bottom support column 5, a rotary loading frame 6, a position control actuator 7, and a movable airfoil loading actuator 8.

[0036] The load-bearing frame 1 is rectangular and can be placed flat on the ground, horizontal with the ground.

[0037] The load-bearing frame 1 can be designed to include a bottom frame, a top frame provided above the bottom frame, and columns connected to both sides of the bottom frame and the top frame.

[0038] The load-bearing frame 1 can be welded by I-beams. To increase the structural stability, cross beams, longitudinal beams, diagonal braces and other structures can be provided between its bottom frame, top frame and the columns on both sides.

[0039] The top of the load-bearing frame 1 is connected to a stabilizer surface loading actuator. The test piece 2 is arranged inside it. The test piece includes a stabilizer surface and a movable airfoil. The movable airfoil is installed on the stabilizer surface and can be deflected under the drive of an actuating mechanism. The stabilizer surface loading actuator is connected downward to the stabilizer surface and can be connected to the stabilizer surface through a loading rod system and is perpendicular to the stabilizer surface.

[0040] The load-bearing wall 3 is connected to one end of the load-bearing frame 1, and the stabilizer surface is fixed on the load-bearing wall 3.

[0041] The load-bearing wall 3 can be composed of a group of columns. To increase the structural stability, structures such as cross beams, longitudinal beams, and diagonal braces can be arranged between its columns, and a load-bearing plate can be set at the position connected to the stabilizer surface for fixed connection with the stabilizer surface. Specifically, the root of the stabilizer surface can be designed to be fixed on the load-bearing plate through long rod bolts.

[0042] The lateral support beam 4 is connected to the columns on one side of the load-bearing frame 1 and is horizontal with the ground. Specifically, it can be connected to the columns on one side of the load-bearing frame 1 through multiple horizontal support rods, and a position control actuator 7 is connected thereto.

[0043] The bottom end of the bottom support column 5 is connected to the bottom of the load-bearing frame 1 and is located below the test piece 2.

[0044] The rotary loading frame 6 is arranged inside the load-bearing frame 1, and the bottom is hinged to the top end of the bottom support column 5. Specifically, it can be hinged through a single-ear and double-ear structure with a pin shaft, and is connected to the position control actuator 7. The top is connected to the movable wing surface loading actuator 8. The movable wing surface loading actuator 8 is connected downward to the movable wing surface, and can be connected to the movable wing surface through a loading rod system.

[0045] For the convenience of installation, the side of the rotary loading frame 6 facing away from the lateral support beam 4 can be designed as an open structure, such as Figure 2 shown.

[0046] In the movable wing surface deflection assessment test load loading device installed on the stabilizer surface disclosed in the above embodiment, it is designed that the load-bearing wall 3 supports and fixes the stabilizer surface of the test piece 2. During the test, the stabilizer surface loading actuator can load the required load on the stabilizer surface, and the movable wing surface loading actuator 8 can load the required load on the movable wing surface. And when the movable wing surface deflects, the position control actuator 8 can drive the rotary loading frame 6 to rotate, adjust the attitude of the rotary loading frame 6, change the direction of the movable wing surface loading actuator 8, so that the movable wing surface loading actuator 8 is perpendicular to the movable wing surface, to simulate the boundary conditions of the movable wing surface during the flight of the aircraft and ensure the accuracy of the test results.

[0047] In the movable wing surface deflection assessment test load loading device installed on the stabilizer surface disclosed in the above embodiment, the overall load is borne by the load-bearing frame 1 located outside, and the load applied by the actuator is converted into internal frame forces. The load-bearing frame 1 can be directly placed on the ground for testing without the need for a specific space site for installing ground rails, which is convenient for the flexible implementation of the test.

[0048] In the test load loading device for the movable wing surface deflection assessment installed on the stabilizer surface disclosed in the above embodiments, the stabilizer surface loading actuator, the position control actuator 7, and the movable wing surface loading actuator 8 can be connected to the connected components through single and double ear structures with a pin shaft. As for the specific quantity and its distribution position, it can be designed according to actual needs. In addition, in order to be able to detect the magnitude of the load applied by the actuator, a dynamometer can be provided on the piston rod.

[0049] The position control actuator 7 can be designed to be connected downward to the rotary loading frame 6 to adjust the rotary loading frame 6 in the form of pulling load, replacing the existing form of top load, which can ensure the stability and safety of the rotary loading frame 6 during the rotation process. In addition, in order to avoid the system from experiencing catastrophic instability and causing damage to the test piece 2, a zero margin design is adopted. When the position control actuator 7 has no stroke, that is, when the piston rod of the position control actuator 7 is fully retracted, the rotary loading frame 6 deflects outward to reach the outermost deflection angle required for the test loading. When the rotary loading frame 6 deflects inward and abuts against the lateral support beam 4, it deflects inward to reach the innermost deflection angle required for the test loading. Through physical limiting, the rotary loading frame 6 is prevented from deflecting excessively and tipping over.

[0050] In a specific example, the test piece 2 is a wing with a flap. Among them, the wing box section is the stabilizer surface, the flap is the movable wing surface, and the flap further includes a main flap and a fairing. The movable wing surface loading actuator 8 is divided into a main flap loading actuator and a fairing loading actuator, which are respectively connected to the main flap and the fairing, and are respectively used to load the main flap and the fairing during the test, as Figure 2 shown.

[0051] So far, the technical solution of the present application has been described in combination with the preferred embodiments shown in the drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the protection scope of the present application.

Claims

1. A load loading device for a movable wing surface deflection test installed on a stabilizer, characterized in that: It comprises a load-bearing frame (1), a test piece (2), a load-bearing wall (3), a lateral support beam (4), a bottom support column (5), a rotating loading frame (6), a position control actuator (7), and a movable wing surface loading actuator (8); The load-bearing frame (1) is rectangular, with a stabilizer loading actuator connected to the top, and a test piece (2) arranged inside the frame. The test piece (2) includes a stabilizer and a movable wing surface. The stabilizer loading actuator is connected downward to the stabilizer and is perpendicular to the stabilizer. The load-bearing wall (3) is connected to one end of the load-bearing frame (1), and the stabilizer surface is fixed on the load-bearing wall (3); The lateral support beam (4) is connected to a column on one side of the load-bearing frame (1), and a position control actuator (7) is connected to the lateral support beam (4); The bottom end of the bottom support column (5) is connected to the bottom of the load-bearing frame (1) and is located below the test piece (2); The rotating loading frame (6) is arranged in the load-bearing frame (1), the bottom is hinged to the top of the bottom supporting column (5), and is connected to the position control actuator (7), and the top is connected to the movable wing surface loading actuator (8), and the movable wing surface loading actuator (8) is connected downward to the movable wing surface; The side of the rotating loading frame (6) facing away from the lateral support beam (4) is an open structure.

2. The load loading device for the movable wing surface deflection test installed on the stabilizer according to claim 1 is characterized in that: The load-bearing frame (1) comprises a bottom frame, a top frame arranged above the bottom frame, and columns connected to both sides of the bottom frame and the top frame; The load-bearing frame (1) can be welded from I-beams, and cross beams, longitudinal beams and diagonal braces are arranged between the bottom frame, the top frame and the columns on both sides.

3. The load loading device for the movable wing surface deflection test installed on the stabilizer according to claim 2 is characterized in that: The load-bearing wall (3) may be composed of a group of columns, wherein cross beams, longitudinal beams and diagonal braces are arranged between the columns, and a load-bearing plate is arranged at a position connected with the stabilizer surface, and the root of the stabilizer surface is fixed to the load-bearing plate by long-rod bolts.

4. The load loading device for the movable wing surface deflection test installed on the stabilizer according to claim 3 is characterized in that: The lateral support beam (4) is connected to a column on one side of the load-bearing frame (1) via a plurality of horizontal support rods.

5. The load loading device for the movable wing surface deflection test installed on the stabilizer according to claim 4 is characterized in that: The bottom of the rotating loading frame (6) and the top of the bottom supporting column (5) are hinged by a pin through a single-double-ear structure.

6. The load loading device for the movable wing surface deflection test installed on the stabilizer according to claim 5, characterized in that: The position control actuator (7) is downwardly connected to the rotation loading frame (6).

7. The load loading device for the movable wing surface deflection test installed on the stabilizer according to claim 6, characterized in that: When the position control actuator (7) has no stroke, the rotating loading frame (6) deflects outwards to reach the outermost deflection angle required for the test loading, and when the rotating loading frame (6) deflects inwards to abut against the lateral support beam (4), it deflects inwards to reach the innermost deflection angle required for the test loading.

8. The load loading device for the movable wing surface deflection test installed on the stabilizer according to claim 7, characterized in that: The test piece (2) is a wing with flaps, wherein the wing box section is a stabilizer and the flaps are movable wing surfaces; The flaps include main flaps and guide vanes; The movable wing surface loading actuator (8) is divided into a main flap loading actuator and a guide vane loading actuator, which are connected to the main flap and the guide vane respectively.

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