Airplane horizontal tail fatigue test fixing device

Abstract

The utility model belongs to the technical field of aviation technical structure design, and relates to an aircraft horizontal tail fatigue test fixing device. Comprising a front beam, a front beam upper connector, a front beam lower connector, an upper wall plate, an end rib, a rear beam, a rear beam upper connector, a rear beam lower connector, a lower wall plate and a fixed bottom plate. Wherein the front beam, the upper wall plate, the rear beam, the lower wall plate and the end ribs define a closed box section, and the whole closed box section is fixed on the fixed bottom plate; a front beam upper joint and a front beam lower joint are respectively fixed at two end parts of the upper end of the front beam; a rear beam upper joint and a rear beam lower joint are respectively fixed at two end parts of the upper end of the rear beam; the lugs of the two front beam connectors are connected with the lugs of the fuselage horizontal tail front beam upper and lower connectors respectively, and the lugs of the two rear beam connectors are connected with the lugs of the fuselage horizontal tail rear beam upper and lower connectors respectively. The front beam, the rear beam, the upper wall plate, the lower wall plate and the rib plates are all of aluminum alloy riveting structures, cost is low, and the technology is simple. The rigidity and the force transmission characteristic of the device are high in designability, and the force transmission characteristic of the horizontal tail can be truly simulated.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the technical field of aviation technology structure design, and relates to a plane flat tail fatigue test fixing device. BACKGROUND

[0002] The plane flat tail usually needs to be subjected to fatigue test, and the flat tail is usually fixed on the bearing wall through a fixing device. In order to more truly and accurately investigate the fatigue life of the plane flat tail, the flat tail fatigue fixing device generally adopts a real tail section part structure to test the flat tail and the surrounding connecting structure together, and such a test mode leads to high cost and long test period. UTILITY MODEL CONTENT

[0003] The utility model overcomes the defects in the prior art, and provides a flat tail fixing device which has low cost, can be designed in rigidity and force transmission characteristics, can more truly simulate the force transmission characteristics of the body flat tail joint, and can fix the test piece.

[0004] Technical scheme: in order to achieve the above utility model purposes, a flat tail fatigue test fixing device is designed, which comprises a front beam, a front beam upper joint, a front beam lower joint, an upper wall plate, an end rib, a rear beam, a rear beam upper joint, a rear beam lower joint, a lower wall plate and a fixing bottom plate.

[0005] The front beam, the upper wall plate, the rear beam, the lower wall plate and the end rib enclose a closed box section, the closed box section is integrally fixed on the fixing bottom plate, and the closed box section has high bending stiffness and torsional stiffness; the upper ends of the front beam are respectively fixed with the front beam upper joint and the front beam lower joint; and the upper ends of the rear beam are respectively fixed with the rear beam upper joint and the rear beam lower joint.

[0006] The ear pieces of the two front beam joints are respectively connected with the ear pieces of the upper and lower joints of the body flat tail front beam, and the ear pieces of the two rear beam joints are respectively connected with the ear pieces of the upper and lower joints of the body flat tail rear beam. The front beam joint and the rear beam joint are simple in structure and high in bearing capacity, and can be conveniently connected with the body flat tail joint.

[0007] Further, the fixing device further comprises two partition plates, the two partition plates divide the closed box section into three small box sections, and further improve the torsional stiffness of the box section and the stability of the box section.

[0008] Further, the front beam upper joint, the front beam lower joint, the rear beam upper joint and the rear beam lower joint are alloy steel machined parts.

[0009] Further, the rear beam middle section is further provided with an elevator fixing joint.

[0010] Further, an arc-shaped strip plate is further arranged, the arc-shaped strip plate is fixed at the contact position of the upper wall plate and the lower wall plate with the fixing bottom plate, and is used for strengthening the strength of the closed box section.

[0011] Furthermore, a weight-reduction hole is provided in the middle of the fixed base plate, and the weight-reduction hole is located at the center of the enclosed box section.

[0012] In use, the simulated horizontal tail loading device is connected to the fuselage horizontal tail through the lugs of the front beam horizontal tail joint and the rear beam horizontal tail joint. The fuselage horizontal tail load is applied through the four loading joints connected to the fuselage horizontal tail, which can realistically simulate the shear, bending moment and torque of the horizontal tail under different working conditions.

[0013] Technical benefits: This utility model provides a flat-tail fatigue test fixing device. The joint and loading joint are machined alloy steel parts, which have a simple structure and high load-bearing capacity. The front beam, rear beam, upper wall plate, lower wall plate and rib plate are all aluminum alloy riveted structures, which have low cost and simple process. The rigidity and force transmission characteristics of the device can be designed to be strong, and it can simulate the force transmission characteristics of the flat-tail more realistically. Attached Figure Description

[0014] Fig. 1 Outline drawing (front-heading view) of the mounting device for fatigue testing of the aircraft horizontal stabilizer;

[0015] Fig. 2 Outline drawing (reverse heading view) of the mounting device for fatigue testing of the aircraft horizontal stabilizer;

[0016] Fig. 3 External view of the mounting device for fatigue testing of the aircraft horizontal stabilizer (internal view in the forward direction);

[0017] Among them, the front beam 1, the upper front beam joint 2, the lower front beam joint 3, the upper wall plate 4, the end rib 5, the rear beam 6, the upper rear beam joint 7, the lower rear beam joint 8, the lower wall plate 9, the fixed base plate 11, the partition 12, the fixed joint 13, and the arc-shaped strip plate 14. Detailed Implementation

[0018] To more clearly illustrate the technical solutions of the embodiments of this utility model, the present utility model will be described in detail below with reference to the accompanying drawings or specific implementation examples. It should be noted that some (but not all) of the disclosed examples are shown in the drawings. In fact, many different examples can be described, and these examples should not be construed as limited to the examples set forth herein. Rather, these examples are described to better demonstrate the positive effects of this utility model, and all aspects not detailed herein are considered to be well-known or conventional techniques in the art.

[0019] See appendix Figs. 1-3 The present invention specifically designs a flat-tail fatigue test fixing device, including a front beam 1, a front beam upper joint 2, a front beam lower joint 3, an upper wall plate 4, an end rib 5, a rear beam 6, a rear beam upper joint 7, a rear beam lower joint 8, a lower wall plate 9, and a fixing base plate 11.

[0020] The front beam 1, upper wall panel 4, rear beam 6, lower wall panel 9, and end rib 5 form a closed box section, which is fixed to the fixed base plate 11. The closed box section has high bending stiffness and torsional stiffness. The two ends of the upper part of the front beam 1 are respectively fixed with the front beam upper connector 2 and the front beam lower connector 3. The two ends of the upper part of the rear beam 6 are respectively fixed with the rear beam upper connector 7 and the rear beam lower connector 8.

[0021] The lugs of the two front beam connectors 1 are respectively connected to the upper and lower lugs of the front beam connectors of the fuselage horizontal stabilizer, and the lugs of the two rear beam connectors are respectively connected to the upper and lower lugs of the rear beam connectors of the fuselage horizontal stabilizer. The front beam connectors 1 and rear beam connectors 2 have simple structures, high load-bearing capacity, and can be easily connected to the fuselage horizontal stabilizer connectors.

[0022] In the specific implementation process, the fixing device also includes two partitions 12, which divide the enclosed box section into three smaller box sections, further improving the torsional stiffness and stability of the box sections. The upper connector 2, lower connector 3, upper connector 7, and lower connector 8 of the front beam are machined alloy steel parts. The middle section of the rear beam 6 is also equipped with an elevator fixing connector 10.

[0023] In the specific implementation process, it also includes an arc-shaped strip plate 14, which is fixed at the contact position between the upper and lower wall panels and the fixed base plate 11. The two ends of the arc-shaped strip plate 14 are respectively clamped and fixed by the fixed joints 13. The fixed joints 13 are also used for the connection and fixation between the front beam 1 and the rear beam 6 and the fixed base plate 11. This design structure can further enhance the strength of the enclosed box section.

[0024] In the specific implementation process, in order to reduce the weight of the entire flat tail loading device structure, a weight reduction hole is opened in the middle of the fixed base plate 11 without affecting the overall strength. The weight reduction hole is located at the center of the closed box section.

[0025] In the specific implementation process, by designing the bending stiffness of the front beam 1 and the rear beam 4, and the thickness of the upper wall plate 5 and the lower wall plate 6, the stiffness and force transmission characteristics of the simulated horizontal tail loading device are made the same as those of the real horizontal tail, ensuring that the load on the horizontal tail joint and the fatigue test piece of the fuselage horizontal tail joint and the connection area is consistent with the load of the real horizontal tail loading, thus ensuring the authenticity of the fatigue test loading.

[0026] The above specific embodiments or examples are only used to explain the technical solutions of this utility model and are not intended to limit this application. Parts not described in detail are considered to be conventional technical means or common knowledge in the field. It can be understood by those skilled in the art that, based on the design concept of this application, adaptive modifications can be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features. These modifications, equivalent substitutions, and adaptive improvements do not depart from the technical essence of this utility model and should all be covered within the protection scope of this application.

Claims

1. A flat-tail fatigue testing fixing device, characterized in that, Includes front beam, front beam upper joint, front beam lower joint, upper wall panel, end rib, rear beam, rear beam upper joint, rear beam lower joint, lower wall panel, and fixed base plate; The front beam, upper wall panel, rear beam, lower wall panel, and end ribs form a closed box section, which is fixed to the fixed base plate as a whole; the two ends of the upper front beam are respectively fixed with the upper front beam connector and the lower front beam connector; the two ends of the upper rear beam are respectively fixed with the upper rear beam connector and the lower rear beam connector. The lugs of the two front beam joints are connected to the upper and lower lugs of the front beam joints of the fuselage horizontal tail, respectively, and the lugs of the two rear beam joints are connected to the upper and lower lugs of the rear beam joints of the fuselage horizontal tail, respectively.

2. The flat-tail fatigue test fixing device as described in claim 1, characterized in that, The fixing device also includes two partitions that divide the enclosed box section into three smaller box sections.

3. The flat-tail fatigue test fixing device as described in claim 1, characterized in that, The front beam upper connector, front beam lower connector, rear beam upper connector, and rear beam lower connector are all machined alloy steel parts.

4. The flat-tail fatigue test fixing device as described in claim 1, characterized in that, An elevator fixing joint is also arranged on the middle section of the rear beam.

5. The flat-tail fatigue test fixing device as described in claim 1, characterized in that, It also includes an arc-shaped strip plate, which is fixed at the contact position between the upper and lower wall panels and the fixed base plate to enhance the strength of the enclosed box section.

6. The flat-tail fatigue test fixing device as described in claim 1, characterized in that, The fixed base plate has a weight reduction hole in the middle, which is located at the center of the enclosed box section.

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