Airplane horizontal tail and vertical tail combination strength test tool

Abstract

The utility model relates to the technical field of airplane horizontal tail and vertical tail strength testing, and discloses an airplane horizontal tail and vertical tail combined strength testing tool which comprises a bottom plate, connecting frames are fixedly connected to the front side and the rear side of the outer portion of the bottom plate, and supporting assemblies used for stabilizing an airplane are fixedly connected to the tops of the connecting frames. A fixing assembly used for providing supporting force is fixedly connected to the front side of the bottom plate, a plurality of sliding plates are slidably connected to the rear side of the bottom plate, triangular vertical frames are fixedly connected to the outer portions of the sliding plates, and pressure sensors are fixedly connected to the close sides of the two triangular vertical frames. And the outer part of the pressure sensor is fixedly connected with a threaded jack. According to the utility model, loading objects with different weights are placed at different positions according to the stress condition of the horizontal tail, and the stress and the torque of the horizontal tail are simulated, so that the device is reliable in performance, not easy to loosen and in-place in safety protection.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of airplane flat tail vertical tail strength test, especially to a kind of airplane flat tail vertical tail combination strength test tool. BACKGROUND

[0002] The airplane flat tail vertical tail combination strength test tool is a special device for evaluating and verifying the ultimate load-carrying capacity and static force characteristics of the connection of the airplane tail structure (including the flat tail and the vertical tail). This test tool plays a crucial role in the design and manufacturing process of the airplane, as it can simulate the load conditions in actual flight and conduct strict strength tests on the connection joint of the flat tail and the vertical tail.

[0003] The working principle of some airplane flat tail vertical tail combination strength test tools in the prior art is to simulate the load conditions in flight. The main purpose is to ensure that the airplane meets the safety standards during the design and manufacturing process, and to ensure flight performance and safety. However, in the specific use process, the tool for flat tail and vertical tail combination test in China is relatively complex and expensive. Therefore, how to ensure accuracy, reliability and safety of the machine body tool in static test is a problem. Therefore, in view of the above problems, an airplane flat tail vertical tail combination strength test tool is proposed. UTILITY MODEL CONTENT

[0004] To make up for the above shortcomings, the utility model provides an airplane flat tail vertical tail combination strength test tool, which aims to improve the problem of how to ensure accuracy, reliability and safety of the machine body tool in static test in the prior art.

[0005] To achieve the above purpose, the utility model adopts the following technical scheme:

[0006] An airplane flat tail vertical tail combination strength test tool, comprising a bottom plate, the outer front and rear sides of the bottom plate are fixedly connected with connecting frames, the top of the connecting frame is fixedly connected with a support assembly for stabilizing the airplane, the front side of the bottom plate is fixedly connected with a fixing assembly for providing supporting force, the rear side of the bottom plate is slidingly connected with a plurality of sliding plates, the outer side of the sliding plate is fixedly connected with a triangular vertical frame, the proximal side of two triangular vertical frames is fixedly connected with a pressure sensor, the outer side of the pressure sensor is fixedly connected with a threaded jack, the outer side of the threaded jack is fixedly connected with a rocker, the top of the bottom plate is fixedly connected with a machine body, the outer side of the rocker is fixedly connected with a vertical tail, and the outer side of the vertical tail is fixedly connected with a square tube.

[0007] As a further description of the above technical scheme:

[0008] The support assembly includes support rods one, the outer part of two right side support rods one is fixedly connected with a fixed plate one, the top of two left side support rods one is fixedly connected with a fixed plate two, and the outer part of the support rod one is fixedly connected to the outer part of the connecting frame;

[0009] As a further description of the above technical solution:

[0010] The fixed assembly includes multiple connection frames, the outer part of the connection frame is fixedly connected with a support rod two, the similar side of two support rods two is fixedly connected with a connecting plate, and the outer part of the connection frame is fixedly connected to the outer part of the bottom plate.

[0011] As a further description of the above technical solution:

[0012] The outer left side of the bottom plate is fixedly connected with a motor, and the driving end of the motor is fixedly connected with a gear;

[0013] As a further description of the above technical solution:

[0014] The outer left side of the bottom plate is fixedly connected with a motor, and the driving end of the motor is fixedly connected with a gear;

[0015] As a further description of the above technical solution:

[0016] The outer part of the sliding block is fixedly connected with a rack plate, and the outer part of the sliding block is slidably connected to the inner part of the bottom plate.

[0017] As a further description of the above technical solution:

[0018] The outer part of the rack plate is in meshing connection with the outer part of the gear, and the outer part of the rack plate is slidably connected to the outer left side of the bottom plate.

[0019] As a further description of the above technical solution:

[0020] The outer part of the sliding block is fixedly connected with a rack plate, and the outer part of the sliding block is slidably connected to the inner part of the bottom plate.

[0021] The utility model has the advantages of the following beneficial effects:

[0022] 1、The utility model discloses a plastic foam is placed on the horizontal tail, and is attached to the curved surface of the horizontal tail, so that uniform force transmission is guaranteed, the wood board is placed on the plastic foam, so that the plastic foam is not damaged, the loading weight is placed on the wood board, different weights of loading weights are placed at different positions according to the stress condition of the horizontal tail, the force and torque received by the horizontal tail are simulated, and then the device can be reliable in performance, is not prone to loosening, and safety protection is in place.

[0023] 2、The utility model discloses a motor starts working, drives rack plate to carry out linear motion through gear, and rack plate carries out straight -line sliding in the slide groove through sliding block, and then can drive two triangular frames to carry out the stable test of different size aircraft through sliding plate. BRIEF DESCRIPTION OF DRAWINGS

[0024] Figure 1 A three-dimensional schematic view of a horizontal tail and vertical tail combined strength test tool for an aircraft is provided for the utility model;

[0025] Figure 2 A structure schematic view of the bottom plate of the horizontal tail and vertical tail combined strength test tool for the aircraft is provided for the utility model;

[0026] Figure 3 A structure schematic view of the screw jack of the horizontal tail and vertical tail combined strength test tool for the aircraft is provided for the utility model;

[0027] Figure 4 A structure schematic view of the plastic foam of the horizontal tail and vertical tail combined strength test tool for the aircraft is provided for the utility model;

[0028] Figure 5 A structure schematic view of the triangular frame of the horizontal tail and vertical tail combined strength test tool for the aircraft is provided for the utility model.

[0029] LEGEND:

[0030] 1, bottom plate, 2, connecting frame, 3, support rod one, 4, fixed plate one, 5, link frame, 6, support rod two, 7, connecting plate, 8, fixed plate two, 9, sliding plate, 10, triangular frame, 11, pressure sensor, 12, screw jack, 13, rocker, 14, fuselage, 15, vertical tail, 16, square tube, 17, horizontal tail, 18, plastic foam, 19, wooden board, 20, loading weight, 21, motor, 22, gear, 23, sliding block, 24, slide groove, 25, rack plate. DETAILED DESCRIPTION

[0031] The technical solutions in the embodiments of the utility model will be clearly and completely described below with reference to the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the protection scope of the utility model.

[0032] REFERENCE Figures 1 to 3The utility model provides a kind of aircraft horizontal tail vertical tail combination strength test tool, including bottom plate 1, bottom plate 1 is the basic platform of entire test tool, usually adopt high-strength steel or aluminum alloy to manufacture, to ensure enough load capacity and stability. The outside of bottom plate 1 is fixedly connected with connecting frame 2 in front and back, for supporting and positioning the support assembly above. The design of connecting frame 2 considers structural strength and installation convenience. The top of connecting frame 2 is fixedly connected with support assembly for firming aircraft, for firming aircraft horizontal tail vertical tail combination. Support assembly includes support rod one 3, provides necessary support for aircraft horizontal tail vertical tail combination. These support rod one 3 are usually made of high-strength metal pipe, to bear load generated during test. The outside of two right side support rod one 3 is fixedly connected with fixed plate one 4, and the top of two left side support rod one 3 is fixedly connected with fixed plate two 8, and fixed plate one 4 and fixed plate two 8 are fixedly connected on right side and left side support rod one 3 respectively, for enhancing the stability and carrying capacity of structure. These plates are usually made of solid material, such as steel plate or aluminum alloy plate. The outside of support rod one 3 is fixedly connected in the outside of connecting frame 2, and the front side of bottom plate 1 is fixedly connected with fixed assembly for providing support force, and fixed assembly includes multiple link frames 5, for further enhancing the structural strength of fixed assembly. Link frame 5 is usually made of metal material, to ensure enough strength and durability. The outside of link frame 5 is fixedly connected with support rod two 6, to enhance the stability of overall structure. The design of support rod two 6 considers cooperation with link frame 5 and force transmission efficiency. The side similar to two support rod two 6 is fixedly connected with connecting plate 7, for enhancing the coherence and carrying capacity of structure;

[0033] The connecting plate 7 is usually made of solid metal material. The outer part of the adapter frame 5 is fixedly connected to the outer part of the base plate 1, and the rear side of the base plate 1 is slidingly connected with multiple sliding plates 9 for adjusting the position of the test tool or adapting to different sizes of aircraft parts. The design of the sliding plate 9 considers the flexibility and convenience of operation. The outer part of the sliding plate 9 is fixedly connected with a triangular stand 10 for providing additional support and stability. The design of the triangular stand 10 considers the rigidity and durability of the structure. The proximal side of each of the two triangular stands 10 is fixedly connected with a pressure sensor 11 for monitoring the force change during the test. The design of the pressure sensor 11 considers the accuracy and response speed. The outer part of the pressure sensor 11 is fixedly connected with a threaded jack 12 for applying adjustable pressure to the test object. The design of the threaded jack 12 considers the convenience of operation and the accuracy of pressure control. The outer part of the threaded jack 12 is fixedly connected with a rocker 13 for manually operating the threaded jack 12 to achieve fine adjustment of the test pressure. The design of the rocker 13 considers ergonomics and the comfort of operation. The top of the base plate 1 is fixedly connected with a fuselage 14 simulating the main structure of the aircraft to provide a realistic environment for testing. The design of the fuselage 14 considers the similarity to the actual aircraft structure and the needs of the test. The outer part of the rocker 13 is fixedly connected with a vertical tail 15 simulating the tail structure of the aircraft for specific strength tests. The design of the vertical tail 15 considers the shape and size of the simulated real aircraft tail. The outer part of the vertical tail 15 is fixedly connected with a square tube 16. When the rocker on the threaded jack 12 is rocked, the threaded jack 12 is elongated to apply force to the square tube 16, and the square tube 16 uniformly transmits the force to the vertical tail 15;

[0034] Referring to Figures 3 to 5 The outer left side of the base plate 1 is fixedly connected with a motor 21 as a power source to provide the necessary driving force for the test tool. The design of the motor 21 considers the power output and the accuracy of control. The driving end of the motor 21 is fixedly connected with a gear 22 for converting the rotary motion of the motor into linear motion or other forms of mechanical motion. The design of the gear 22 considers the transmission efficiency and durability. The outer left side of the base plate 1 is provided with a sliding groove 24 at the upper and lower ends for guiding the movement trajectory of the sliding block 23. The design of the sliding groove 24 considers the smoothness and accuracy of the movement. The inner part of the sliding groove 24 is slidingly connected with multiple sliding blocks 23, which can freely move within the sliding groove to adapt to different test requirements. The design of the sliding block 23 considers the wear resistance and flexibility of movement;

[0035] The outer part of the sliding block 23 is fixedly connected with the rack plate 25, which is in meshing connection with the gear 22, converting the rotary motion of the motor 21 into linear motion of the sliding block 23. The design of the rack plate 25 takes into account the matching accuracy and smoothness of the motion. The outer part of the sliding block 23 is slidingly connected to the inside of the bottom plate 1, and the outer part of the rack plate 25 is in meshing connection with the outer part of the gear 22. The outer part of the rack plate 25 is slidingly connected to the outer left side of the bottom plate 1. The vertical tail 15 is fixedly connected to the left and right sides of the horizontal tail 17, which is used to enhance the stability of the structure or simulate some features of the tail of the aircraft. The design of the horizontal tail 17 takes into account the coordination with the vertical tail 15 and the overall structure. The top of the horizontal tail 17 is fixedly connected with the plastic foam 18, which is used to buffer the impact force or simulate the specific characteristics of the surface of the aircraft. The design of the plastic foam 18 takes into account the elasticity and durability of the material. The top of the plastic foam 18 is fixedly connected with the wooden board 19, which provides a flat and solid platform for the loading weight 20. The design of the wooden board 19 takes into account the carrying capacity and stability. The top of the wooden board 19 is fixedly connected with the loading weight 20, which is used to simulate various loads on the aircraft during flight. The design of the loading weight 20 takes into account the uniformity of the weight distribution and the needs of the test.

[0036] Working principle: First, the main body structure of the aircraft fuselage 14 and the tail structure of the aircraft vertical tail 15 are installed on the support rod 1 and the support rod 2, which are stably supported by the connecting frame 2 and the bottom plate 1. At the same time, the horizontal tail 17 is fixed on both sides of the vertical tail 15 to enhance the stability of the overall structure. Then, the motor 21 starts to work, driving the rack plate 25 to move linearly through the gear 22. The rack plate 25 slides linearly in the sliding groove 24 through the sliding block 23, which in turn drives the two triangular frames 10 to test different sizes of aircraft stably. During the test, the threaded jack 12 is operated through the rocker 13 to apply adjustable pressure to the square tube 16, which uniformly transmits the force to the vertical tail 15 and the horizontal tail 17, simulating various loads on the aircraft during flight.

[0037] At the same time, the pressure sensor 11 monitors the changes in force during the test, providing feedback information to adjust the operation of the motor 21 and the pressure applied by the threaded jack 12, ensuring the accuracy and reliability of the test. After the test is completed, the sliding plate 9 can be adjusted to adapt the test tooling to different sizes of aircraft parts, improving the versatility and applicability of the test tooling. The horizontal tail 17 is placed with the foam 18, which is in contact with the curved surface of the horizontal tail 17, ensuring uniform transmission of force. The foam 18 is placed on the wooden board 19, which can prevent the foam 18 from being crushed. The wooden board 19 is placed on the loading weight 20, which is placed at different positions according to the force on the horizontal tail 17, simulating the force and torque on the horizontal tail 17.

[0038] Finally, it should be noted that: the above only for the preferred embodiments of the present application, and is not intended to limit the present application, although the foregoing embodiments of the present application has been described in detail, for the skilled in the art, it still can be modified, or for part of the technical features of the equivalent replacement, the spirit and principles of the present application, made any modification, equivalent replacement, improvement, etc., should be included within the scope of the present application.

Claims

1. An airplane horizontal and vertical tail combination strength test tooling, comprising a base plate (1), characterized in that: The outer front and rear sides of the bottom plate (1) are fixedly connected with connecting frames (2), the top of the connecting frame (2) is fixedly connected with a support assembly for stabilizing the airplane, the front side of the bottom plate (1) is fixedly connected with a fixing assembly for providing supporting force, the rear side of the bottom plate (1) is slidably connected with a plurality of sliding plates (9), the outer side of the sliding plate (9) is fixedly connected with a triangular vertical frame (10), the proximal side of two triangular vertical frames (10) is fixedly connected with a pressure sensor (11), the outer side of the pressure sensor (11) is fixedly connected with a threaded jack (12), the outer side of the threaded jack (12) is fixedly connected with a rocker (13), the top of the bottom plate (1) is fixedly connected with a fuselage (14), the outer side of the rocker (13) is fixedly connected with a vertical tail (15), the outer side of the vertical tail (15) is fixedly connected with a square tube (16).

2. The horizontal and vertical tail combination strength test tooling for an aircraft as defined in claim 1, wherein: The support assembly comprises a support rod one (3), the outer side of two right support rod ones (3) is fixedly connected with a fixed plate one (4), the top of two left support rod ones (3) is fixedly connected with a fixed plate two (8), and the outer side of the support rod one (3) is fixedly connected to the outer side of the connecting frame (2).

3. The horizontal and vertical tail combination strength test tooling for an aircraft as defined in Claim 1, wherein: The fixing assembly comprises a plurality of link frames (5), the outer side of the link frame (5) is fixedly connected with a support rod two (6), the proximal side of two support rod twos (6) is fixedly connected with a connecting plate (7), and the outer side of the link frame (5) is fixedly connected to the outer side of the bottom plate (1).

4. The horizontal and vertical tail combination strength test tooling for an aircraft as defined in Claim 1, wherein: The outer left side of the bottom plate (1) is fixedly connected with a motor (21), and the driving end of the motor (21) is fixedly connected with a gear (22).

5. The combined horizontal and vertical tail strength test fixture of Claim 4, wherein: The outer left side of the bottom plate (1) is fixedly connected with a motor (21), and the driving end of the motor (21) is fixedly connected with a gear (22).

6. The horizontal and vertical tail combination strength test tooling for an aircraft as defined in claim 5, wherein: The outer side of the sliding block (23) is fixedly connected with a rack plate (25), and the outer side of the sliding block (23) is slidably connected to the inner side of the bottom plate (1).

7. The combined horizontal and vertical tail strength test fixture of Claim 6, wherein: The outer side of the gear (22) is meshedly connected with the outer side of the rack plate (25), and the outer side of the rack plate (25) is slidably connected to the outer left side of the bottom plate (1).

8. The horizontal and vertical tail combination strength test tooling for an aircraft as defined in Claim 1, wherein: The outer side of the vertical tail (15) is fixedly connected with a horizontal tail (17) on the left and right sides, the top of the horizontal tail (17) is fixedly connected with a plastic foam (18), the top of the plastic foam (18) is fixedly connected with a wooden board (19), and the top of the wooden board (19) is fixedly connected with a heavy load (20).

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