An aircraft component test fixture

Abstract

This utility model discloses an aircraft component testing fixture, belonging to the field of fixture technology, comprising: a first clamping mechanism disposed on a support frame; and a second clamping mechanism connected to the first clamping mechanism; the first clamping mechanism is used to clamp components in the horizontal direction, and components of different sizes can be clamped by operating the power component of the first clamping mechanism; the second clamping mechanism is used to clamp small-sized components when the first clamping mechanism stops operating; the first clamping mechanism can clamp large-sized components during testing, and the clamping distance can be adjusted by operating the power component of the first clamping mechanism; for small-sized components, the second clamping mechanism can be used to clamp the small-sized components after operating the first clamping mechanism, thus making the entire testing fixture more versatile and able to meet the testing needs of most components.

Description

Technical Field

[0001] This utility model relates to the field of fixture technology, specifically to a test fixture for aircraft parts. Background Technology

[0002] During aircraft component performance testing, fixtures are used to test the components. Every component in an aircraft needs to undergo repeated testing and inspection before actual installation, during which fixtures are used to secure the components.

[0003] The prior art, Chinese utility model patent application number: CN202420756200.9, discloses an aircraft component test fixture, which sets multiple telescopic rods in the horizontal and vertical planes, adjusts the telescopic rods in the corresponding directions according to the shape of the test component, and then controls the telescopic rods to clamp the test component. Since each telescopic rod is controlled separately, the operation is cumbersome each time it is adjusted.

[0004] Therefore, this application designs a highly versatile fixture for holding aircraft parts during testing. Summary of the Invention

[0005] To address the problems of the prior art, this utility model provides an aircraft component testing fixture, comprising: a first clamping mechanism, wherein the first clamping mechanism is disposed on a support frame;

[0006] A second clamping mechanism is connected to the first clamping mechanism;

[0007] The first clamping mechanism is used to clamp parts in the horizontal direction. By operating the power component of the first clamping mechanism, parts of different sizes can be clamped.

[0008] The second clamping mechanism is used to clamp small-sized parts when the first clamping mechanism stops operating.

[0009] Furthermore, the first clamping mechanism includes: a power unit, a clamping unit, and a guide unit;

[0010] The power unit is connected to the top of the support frame via a base;

[0011] The movable part of the power unit is connected to one end of the clamping part, and the other end of the clamping part is connected to the guide part;

[0012] The guide portion is located on the opposite side of the power unit and is connected to the top of the support frame;

[0013] The second clamping mechanism is connected to the clamping part.

[0014] Furthermore, the power unit includes: a first lead screw, a slider, a mounting plate, and a connecting arm;

[0015] The mounting plate is located between the base and the guide portion and is connected to the top of the support frame, with a gap between the mounting plate and the base;

[0016] The first lead screw passes through the base, one end of the first lead screw is provided with a handle, and the other end of the first lead screw is rotatably connected to the mounting plate;

[0017] The slider is sleeved on the first lead screw and is threadedly connected to the first lead screw;

[0018] The other side of the slider is connected to the clamping part via the connecting arm.

[0019] Furthermore, the clamping part includes: a first clamping block and a second clamping block;

[0020] The first clamping block and the second clamping block are arranged symmetrically.

[0021] One end of both the first clamping block and the second clamping block is hinged to both sides of the slider via the connecting arm;

[0022] The other ends of the first clamping block and the second clamping block are inserted into the guide portion;

[0023] The second clamping mechanism is connected to the side of both the clamping block and the second clamping block.

[0024] Furthermore, the guide portion includes: a guide rod and a support block;

[0025] Two support blocks are provided and arranged symmetrically, and the support blocks are connected to the top of the support frame;

[0026] The guide rod is disposed between the support blocks, and the two ends of the guide rod are respectively connected to the support block on the same side;

[0027] The other ends of both the first clamping block and the second clamping block are sleeved on the guide rod.

[0028] Furthermore, the second clamping mechanism includes: a second lead screw, an extrusion block, and a limiting plate;

[0029] The first clamping block and the second clamping block are provided with through holes, and the extrusion block is sleeved in the through holes;

[0030] The limiting plate has a U-shaped structure rotated 90° in the horizontal direction. The limiting plate is connected to the outer side of the first clamping block and the second clamping block respectively. The limiting plate is located on both sides of the through hole.

[0031] The second lead screw passes through the limiting plate and is rotatably connected to the extrusion block on the same side.

[0032] The beneficial effects of this utility model are:

[0033] The first clamping mechanism can clamp large-sized parts during testing. The clamping distance can be adjusted by operating the power component of the first clamping mechanism. For small-sized parts, after operating the first clamping mechanism, the second clamping mechanism can be used to clamp the small-sized parts. Thus, the entire experimental fixture has higher versatility and can meet the testing needs of most parts. Moreover, the operation process is simple. By operating the first clamping mechanism, large-sized parts can be placed on the fixture without separate adjustment. Attached Figure Description

[0034] Figure 1 A three-dimensional structural schematic diagram of the aircraft component testing fixture provided by this utility model;

[0035] Figure 2 A side view of the aircraft component testing fixture provided by this utility model;

[0036] Figure 3 A top-view structural diagram of the aircraft component testing fixture provided by this utility model.

[0037] Figure label:

[0038] In the diagram: 1 is the support frame, 2 is the first lead screw, 3 is the slider, 4 is the mounting plate, 5 is the connecting arm, 6 is the first clamping block, 7 is the second clamping block, 8 is the guide rod, 9 is the support block, 10 is the second lead screw, 11 is the pressing block, and 12 is the limiting plate. Detailed Implementation

[0039] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0040] Please see Figure 1-3 This utility model provides a test fixture for aircraft parts, comprising:

[0041] A first clamping mechanism is disposed on the support frame 1;

[0042] The first clamping mechanism includes: a power unit, a clamping unit, and a guide unit;

[0043] The power unit is connected to the top of the support frame via a base;

[0044] The movable part of the power unit is connected to one end of the clamping part, and the other end of the clamping part is connected to the guide part;

[0045] The guide portion is located on the opposite side of the power unit and is connected to the top of the support frame 1;

[0046] The second clamping mechanism is connected to the clamping part.

[0047] The power unit includes: a first lead screw 2, a slider 3, a mounting plate 4, and a connecting arm 5;

[0048] The mounting plate 4 is located between the base and the guide portion, and is connected to the top of the support frame 1. A gap is left between the mounting plate 4 and the base.

[0049] The first lead screw 2 passes through the base and is threadedly connected to the base. One end of the first lead screw 2 is provided with a handle, and the other end of the first lead screw 2 is rotatably connected to the mounting plate 4 through a bearing.

[0050] The slider 3 is sleeved on the first lead screw 2 and is threadedly connected to the first lead screw 2;

[0051] The other side of the slider 3 is connected to the clamping part via the connecting arm 5.

[0052] The first lead screw can be rotated by operating the handle, which in turn causes the slider to move on the first lead screw, thereby causing the clamping part to move.

[0053] The clamping part includes: a first clamping block 6 and a second clamping block 7;

[0054] The first clamping block 6 and the second clamping block 7 are arranged symmetrically.

[0055] One end of the first clamping block 6 and the second clamping block 7 are respectively hinged to the two sides of the slider 3 by the connecting arm 5 through pins;

[0056] The other ends of the first clamping block 6 and the second clamping block 7 are inserted into the guide portion;

[0057] The second clamping mechanism is connected to the side of both the clamping block and the second clamping block 7.

[0058] When the slider moves, it drives the connecting arm to move, which in turn drives the first clamping block and the second clamping block to move along the guide section, thereby adjusting the distance between the first clamping block and the second clamping block.

[0059] The guide section includes: a guide rod 8 and a support block 9;

[0060] Two support blocks 9 are provided and are arranged symmetrically. The support blocks 9 are connected to the top of the support frame 1.

[0061] The guide rod 8 is disposed between the support blocks 9, and the two ends of the guide rod 8 are respectively connected to the support block 9 on the same side;

[0062] The other ends of the first clamping block 6 and the second clamping block 7 are both sleeved on the guide rod 8;

[0063] The guide rod serves to guide the movement of the first clamping block and the second clamping block.

[0064] A second clamping mechanism is connected to the first clamping mechanism;

[0065] The first clamping mechanism is used to clamp parts in the horizontal direction. By operating the power component of the first clamping mechanism, parts of different sizes can be clamped.

[0066] The second clamping mechanism is used to clamp small-sized parts when the first clamping mechanism stops operating.

[0067] The second clamping mechanism includes: a second lead screw 10, a pressing block 11, and a limiting plate 12;

[0068] The first clamping block 6 and the second clamping block 7 are provided with through holes, and the pressing block 11 is sleeved in the through holes;

[0069] The limiting plate 12 has a U-shaped structure that is rotated 90° in the horizontal direction. The limiting plate 12 is connected to the outer side of the first clamping block 6 and the second clamping block 7 respectively. The limiting plate 12 is located on both sides of the through hole.

[0070] The second lead screw 10 passes through the limiting plate 12 and is rotatably connected to the extrusion block 11 on the same side.

[0071] When the first lead screw is operated, the distance between the first clamping block and the second clamping block can be adjusted according to the size of the component, so as to meet the testing of large-sized components. When replacing small-sized components, the distance between the first clamping block and the second clamping block is first adjusted by adjusting the first lead screw, and then the small-sized component is clamped by operating the second lead screw.

[0072] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A test fixture for aircraft parts, characterized in that, include: A first clamping mechanism is disposed on a support frame; A second clamping mechanism is connected to the first clamping mechanism; The first clamping mechanism is used to clamp parts in the horizontal direction. By operating the power component of the first clamping mechanism, parts of different sizes can be clamped. The second clamping mechanism is used to clamp small-sized parts when the first clamping mechanism stops operating.

2. The aircraft component testing fixture according to claim 1, characterized in that, The first clamping mechanism includes: a power unit, a clamping unit, and a guide unit; The power unit is connected to the top of the support frame via a base; The movable part of the power unit is connected to one end of the clamping part, and the other end of the clamping part is connected to the guide part; The guide portion is located on the opposite side of the power unit and is connected to the top of the support frame; The second clamping mechanism is connected to the clamping part.

3. The aircraft component testing fixture according to claim 2, characterized in that, The power unit includes: a first lead screw, a slider, a mounting plate, and a connecting arm; The mounting plate is located between the base and the guide portion and is connected to the top of the support frame, with a gap between the mounting plate and the base; The first lead screw passes through the base, one end of the first lead screw is provided with a handle, and the other end of the first lead screw is rotatably connected to the mounting plate; The slider is sleeved on the first lead screw and is threadedly connected to the first lead screw; The other side of the slider is connected to the clamping part via the connecting arm.

4. The aircraft component testing fixture according to claim 3, characterized in that, The clamping part includes: a first clamping block and a second clamping block; The first clamping block and the second clamping block are arranged symmetrically. One end of both the first clamping block and the second clamping block is hinged to both sides of the slider via the connecting arm; The other ends of the first clamping block and the second clamping block are inserted into the guide portion; The second clamping mechanism is connected to the side of both the clamping block and the second clamping block.

5. The aircraft component testing fixture according to claim 4, characterized in that, The guide section includes: a guide rod and a support block; Two support blocks are provided and arranged symmetrically, and the support blocks are connected to the top of the support frame; The guide rod is disposed between the support blocks, and the two ends of the guide rod are respectively connected to the support block on the same side; The other ends of both the first clamping block and the second clamping block are sleeved on the guide rod.

6. The aircraft component testing fixture according to claim 4, characterized in that, The second clamping mechanism includes: a second lead screw, an extrusion block, and a limiting plate; The first clamping block and the second clamping block are provided with through holes, and the extrusion block is sleeved in the through holes; The limiting plate has a U-shaped structure rotated 90° in the horizontal direction. The limiting plate is connected to the outer side of the first clamping block and the second clamping block respectively. The limiting plate is located on both sides of the through hole. The second lead screw passes through the limiting plate and is rotatably connected to the extrusion block on the same side.

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