Fixture for airplane deflector test

Abstract

The utility model provides a clamp for an aircraft deflector test, and the clamp comprises a pedestal which is provided with a plurality of clamping units for clamping an aircraft deflector. The clamping unit is composed of two clamping assemblies which are the same in specification and arranged in a mirror image mode. The clamping assembly comprises a stand column and clamping parts hinged to the stand column, a clamping space is formed between the two clamping parts arranged in a mirror image mode, and the bottoms of the two clamping parts are connected with a soft body structure used for bearing the aircraft deflector. After the aircraft guide plate is placed in the clamping space of the two clamping parts, the soft body structure bears the aircraft guide plate, and along with downward movement of the aircraft guide plate, under the gravity effect of the aircraft guide plate, the soft body structure pulls the two clamping parts downwards so as to drive the two clamping parts to get close to the aircraft guide plate; the two clamping parts clamp the aircraft guide plate, in the clamping process, clamping can be completed by depending on the gravity of the aircraft guide plate, and time and labor are saved.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aircraft fairing test, in particular to a clamp for aircraft fairing test. BACKGROUND

[0002] The aircraft fairing is an important flight auxiliary device. The fairing is an auxiliary device that changes the direction of air flow and dynamics to improve the stability and control performance of the aircraft. In aircraft design, the fairing plays multiple roles such as optimizing aerodynamic layout, increasing lift area, and improving downspin airflow, thereby achieving more stable and precise flight.

[0003] The aircraft fairing needs to be tested before installation, and a clamp is needed during the test process. For example, a clamp for aircraft fairing test is disclosed in Chinese Patent No. CN216269998U. The clamp fixes the aircraft fairing actuator cylinder to ensure that it can withstand a pressure of 4.9 MPa during the sealing test, meeting the performance testing requirements for aircraft seat fairing overhaul. The connecting screw contact surface is processed into a flat surface to prevent the connecting screw from sliding during the test. The quick-release fixing pin is inserted and pulled out, making the operation convenient, the fixation firm, and the air tightness test more convenient, safe, and stable. However, the above-mentioned clamp needs to connect the adjusting screw, connecting screw, quick-release fixing pin, and pin body before clamping the aircraft fairing, which is relatively cumbersome. SUMMARY

[0004] Therefore, the main purpose of the present application is to provide a clamp for aircraft fairing test.

[0005] The technical solution adopted by the present application is as follows: a clamp for aircraft fairing test, comprising a base, a plurality of clamping units for clamping the aircraft fairing are installed on the base;

[0006] The clamping unit is composed of two clamping assemblies of the same size and mirror image arrangement. The clamping assembly includes a stand and a clamping part hinged to the stand. The mirror image arrangement of the two clamping parts has a clamping space between them, and the bottom of the two clamping parts is connected to a soft structure for carrying the aircraft fairing.

[0007] After the aircraft fairing is placed in the clamping space of the two clamping parts, the aircraft fairing is lowered to drive the two clamping parts to move closer to the aircraft fairing, so that the two clamping parts clamp the aircraft fairing.

[0008] Further, a hinge is connected between the clamping part and the stand.

[0009] Further, the clamping part comprises a first connecting rod and a second connecting rod, the first connecting rod is hinged with the second connecting rod, one end of the first connecting rod away from the second connecting rod is hinged with the stand, and one end of the second connecting rod away from the first connecting rod is connected with the soft structure.

[0010] The first connecting rod is connected with the stand through a hinge.

[0011] Further, one end of the hinge is rotationally connected with the first connecting rod, and the other end of the hinge is rotationally connected with the stand.

[0012] Further, the hinge comprises a first hinge arm and a second hinge arm, the first hinge arm is hinged with the second hinge arm, one end of the first hinge arm away from the second hinge arm is connected with the first connecting rod, and one end of the second hinge arm away from the first hinge arm is connected with the stand.

[0013] Further, the end of the second connecting rod close to the aircraft deflector is provided with a flexible pad.

[0014] Further, two clamping units are mounted on the base.

[0015] Compared with the prior art, the application has the beneficial effects that: after the aircraft deflector is placed in the clamping space of the two clamping parts, the soft structure bears the aircraft deflector, and as the aircraft deflector moves downward, the soft structure pulls the two clamping parts downward under the gravity of the aircraft deflector, so as to drive the two clamping parts to move close to the aircraft deflector, and the two clamping parts clamp the aircraft deflector, and the clamping process can be completed by relying on the gravity of the aircraft deflector, thereby saving time and effort. BRIEF DESCRIPTION OF DRAWINGS

[0016] The following drawings only schematically illustrate and explain the application, and do not serve to limit the scope of the application, in which:

[0017] Fig. 1 It is a perspective view of the application;

[0018] Fig. 2 It is a side view of the application;

[0019] Fig. 3 It is a practical state schematic view of the application.

[0020] Marked: 10. Base; 20. Clamping unit; 21. Clamping assembly; 22. Stand; 23. Clamping part; 24. Clamping space; 25. Soft structure; 26. Hinge; 27. First connecting rod; 28. Second connecting rod; 29. Second hinge arm; 30. First hinge arm; 31. Flexible pad. DETAILED DESCRIPTION

[0021] In order to make the purpose, technical scheme, design method and advantages of the present application more clear, the present application is further described in detail below with specific embodiments combined with the drawings. It should be understood that the specific embodiments described herein are only used to explain the present application and not to limit the present application.

[0022] Referring to Figs. 1-3 The present application provides a fixture for aircraft fairing test, comprising a base 10, at least two clamping units 20 for clamping the aircraft fairing are installed on the base 10;

[0023] The clamping unit 20 is composed of two clamping assemblies 21 of the same specification and mirror image arrangement; the clamping assembly 21 comprises a stand 22 and a clamping part 23 hinged to the stand 22, a clamping space 24 is provided between the two mirror image arranged clamping parts 23, and a soft structure 25 for bearing the aircraft fairing is connected to the bottom of the two clamping parts 23.

[0024] In the above, after the aircraft fairing is placed in the clamping space 24 of the two clamping parts 23, the soft structure 25 is used to bear the aircraft fairing, and as the aircraft fairing moves downward, the soft structure 25 will pull the two clamping parts 23 downward under the action of the gravity of the aircraft fairing, so as to realize the approach of the two clamping parts 23 to the aircraft fairing, and when the two clamping parts 23 contact the outer surface of the aircraft fairing, the two clamping parts 23 form clamping to the aircraft fairing.

[0025] In the above, referring to Figs. 1-3 The clamping part 23 comprises a first connecting rod 27 and a second connecting rod 28, the first connecting rod 27 is hinged to the second connecting rod 28, one end of the first connecting rod 27 away from the second connecting rod 28 is hinged to the stand 22, and one end of the second connecting rod 28 away from the first connecting rod 27 is connected to the soft structure 25; a flexible gasket 31 is provided at the end of the second connecting rod 28 close to the aircraft fairing; after the aircraft fairing is placed in the clamping space 24 of the two second connecting rods 28, the soft structure 25 is used to bear the aircraft fairing, and as the aircraft fairing moves downward, the soft structure 25 will pull the two second connecting rods 28 downward under the action of the gravity of the aircraft fairing, so as to realize the approach of the two second connecting rods 28 to the aircraft fairing, and when the two second connecting rods 28 contact the outer surface of the aircraft fairing, the two second connecting rods 28 gradually form clamping to the aircraft fairing, and the clamping force of the two second connecting rods 28 to the aircraft fairing reaches the maximum.

[0026] As an embodiment of the present application, referring to Figs. 1-3As shown, the clamping part 23 is connected with the column through a hinge 26, one end of the hinge 26 is rotatably connected with the first connecting rod 27, and the other end of the hinge 26 is rotatably connected with the column 22.

[0027] In the above, the hinge 26 comprises a first hinge arm 30 and a second hinge arm 29, the first hinge arm 30 is hinged with the second hinge arm 29, one end of the first hinge arm 30 away from the second hinge arm 29 is connected with the first connecting rod 27, and the other end of the second hinge arm 29 away from the first hinge arm 30 is connected with the column 22; when the first connecting rod 27 and the second connecting rod 28 move downward relatively under the gravity of the aircraft spoiler, the included angle between the first hinge arm 30 and the second hinge arm 29 is reduced, and when the included angle between the first hinge arm 30 and the second hinge arm 29 is the smallest, the limiting effect can be achieved, so as to avoid that the clamping part 23 excessively clamps the aircraft spoiler.

[0028] The above has described the embodiments of the present application, the above description is exemplary, not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes are obvious to those skilled in the art without departing from the scope and spirit of the described embodiments. The selection of the terms used herein is intended to best explain the principles of the embodiments, practical application or technical improvement in the market, or to enable other ordinary skilled in the art to understand the embodiments disclosed herein.

Claims

1. A fixture for testing aircraft deflectors, characterized in that, Includes a base (10), on which a plurality of clamping units (20) for clamping the aircraft deflector are mounted; The clamping unit (20) consists of two clamping components (21) of the same size and mirrored arrangement; the clamping component (21) includes a column (22) and a clamping part (23) hinged to the column (22), a clamping space (24) is provided between the two clamping parts (23) mirrored arrangement, and a soft structure (25) for supporting the aircraft deflector is connected to the bottom of the two clamping parts (23); After the aircraft deflector is placed in the clamping space (24) of the two clamping parts (23), as the aircraft deflector moves down, the two clamping parts (23) move closer to the direction of the aircraft deflector, so that the two clamping parts (23) clamp the aircraft deflector.

2. The aircraft deflector testing fixture according to claim 1, characterized in that, A hinge (26) is also connected between the clamping part (23) and the column.

3. The aircraft deflector testing fixture according to claim 1 or 2, characterized in that, The clamping part (23) includes a first link (27) and a second link (28). The first link (27) is hinged to the second link (28). The end of the first link (27) away from the second link (28) is hinged to the column (22). The end of the second link (28) away from the first link (27) is connected to the soft structure (25). A hinge (26) is connected between the first connecting rod (27) and the column (22).

4. The aircraft deflector testing fixture according to claim 3, characterized in that, One end of the hinge (26) is rotatably connected to the first connecting rod (27), and the other end of the hinge (26) is rotatably connected to the column (22).

5. The aircraft deflector testing fixture according to claim 4, characterized in that, The hinge (26) includes a first hinge arm (30) and a second hinge arm (29). The first hinge arm (30) is hinged to the second hinge arm (29). The end of the first hinge arm (30) away from the second hinge arm (29) is connected to a first connecting rod (27). The end of the second hinge arm (29) away from the first hinge arm (30) is connected to a column (22).

6. The aircraft deflector testing fixture according to claim 3, characterized in that, The second link (28) has a flexible pad (31) at the end near the aircraft deflector.

7. The aircraft deflector testing fixture according to claim 1, characterized in that, Two clamping units (20) are installed on the base (10).

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