Fatigue test device for horizontal tail connection structure
By designing a fatigue test device for a flat-tail connection structure, simulating its installation status on the machine and applying a load, the problem of difficulty in evaluating the fatigue performance of a flat-tail connection structure in the prior art is solved, fatigue characteristics assessment and dangerous parts are achieved, and a basis for design improvement and maintenance are provided.
Patent Information
- Application Number
- CN202422367115.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-09-27
- Publication Date
- 2025-06-24
- Estimated Expiration
- 2034-09-27
AI Technical Summary
The prior art lacks effective fatigue test implementation plans, making it difficult to assess the fatigue performance of the flat-tail connection structure.
A fatigue testing device for a flat-tail connection structure is designed, including a flat-tail counterfeit A, a vertical tail counterfeit B and a loading adapter mechanism C. By simulating the installation state of the flat-tail connection structure on the machine, and applying loads in the Fx and Fz directions.
The fatigue characteristics of the flat-tail connection structure are evaluated, and the fatigue hazardous parts are determined, providing a basis for design improvement and maintenance. It also has the advantages of lightweight structural design and easy installation.
Smart Images
Figure CN223014909U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to, but is not limited to, the technical field of helicopter fatigue test, and particularly relates to a fatigue test device for a horizontal tail connection structure. Background Art
[0002] During the flight of a helicopter, the horizontal tail plays a role in improving the angle of attack stability of the helicopter, and is crucial for the balance of the helicopter in flight.
[0003] The horizontal tail connection structure is an important component connecting the horizontal tail and the vertical tail. For the connection structure between the horizontal tail and the vertical tail, no effective fatigue test implementation plan has been proposed yet. Summary of the Utility Model
[0004] The purpose of the utility model: To solve the above problems, embodiments of the utility model provide a fatigue test device for a horizontal tail connection structure to solve the problem that for the horizontal tail connection structure, there is currently a lack of an effective fatigue test implementation plan, resulting in difficulty in evaluating the fatigue performance of the horizontal tail connection structure.
[0005] The technical solution of the utility model: Embodiments of the utility model provide a fatigue test device for a horizontal tail connection structure, including: a horizontal tail dummy A, a vertical tail dummy B, and a loading transfer mechanism C; the test piece of the horizontal tail connection structure includes four horizontal tail connection angle pieces.
[0006] Wherein, the horizontal tail dummy A includes an intermediate airfoil section with a curved bottom end, and transition sections symmetrically distributed on both sides of the intermediate airfoil section. A columnar loading connection part is provided at the end of each transition section, and each loading connection part is fixedly connected to a set of loading transfer mechanism C.
[0007] The vertical tail dummy B includes a horizontal tail connection part at the upper section and a test bench connection part at the lower section. A step is formed in the connection area between the horizontal tail connection part and the test bench connection part along the course direction. The top surface of the horizontal tail connection part is set as a curved end, which is matched with the curved bottom end of the horizontal tail dummy A; by installing four horizontal tail connection angle pieces at the four corners of the two side end faces of the vertical tail dummy B respectively, the vertical tail dummy B is fixedly connected to the intermediate airfoil section of the horizontal tail dummy A; it is used to simulate the installation structure of the horizontal tail connection structure on the aircraft through the horizontal tail dummy A and the vertical tail dummy B.
[0008] Optionally, in the fatigue test device for a horizontal tail connection structure as described above,
[0009] The two side end faces of the horizontal tail connection part in the vertical tail dummy B along the course direction are set as arc surfaces, and open structures are provided at the front and rear ends along the course direction. Four horizontal tail connection angle pieces are fixedly installed on the two side walls of the front and rear open structures respectively.
[0010] Optionally, in the fatigue test device for the horizontal tail connection structure as described above,
[0011] In the horizontal tail connection part of the vertical tail dummy B, a groove is further provided inside the front and rear opening structures, and rivet holes for connecting the horizontal tail connection angle pieces are provided on both the opening structure and the groove, and the horizontal tail connection angle pieces are fixed by riveting.
[0012] Optionally, in the fatigue test device for the horizontal tail connection structure as described above,
[0013] On both sides of the rear opening structure of the horizontal tail connection part of the vertical tail dummy B, step areas with angular depressions are respectively provided;
[0014] The sides of the four horizontal tail connection angle pieces respectively match the outer shape surfaces at the four corners of the horizontal tail connection part, and the top surfaces of the four horizontal tail connection angle pieces match the curved surface bottom ends of the middle airfoil section of the horizontal tail dummy A; so as to form a curved surface mounting structure with the horizontal tail connection part through its side surface, and form a curved surface mounting structure with the middle airfoil section of the horizontal tail dummy A through its top surface.
[0015] Optionally, in the fatigue test device for the horizontal tail connection structure as described above, the loading transfer mechanism C includes: a loading seat C1, a transfer rod C2, a spherical plain bearing C3 and a limit nut C4;
[0016] Among them, a screw rod is provided at the end of the columnar loading connection part on the horizontal tail dummy A, the loading seat C1 is sleeved on the screw rod of the columnar loading connection part through its central through hole, and is fixedly connected by using the limit nut C4, and a spherical plain bearing C3 is arranged in the central through hole; the loading seat C1 is respectively provided with transfer rods C2 in the reverse course direction and the vertical upward direction for connecting the loading mechanism.
[0017] Optionally, in the fatigue test device for the horizontal tail connection structure as described above,
[0018] The fatigue test device is used to fixedly connect the overall fatigue test device to the test bench through the connection holes and bolts provided on the lower test bench connection part of the vertical tail dummy B during the test, and respectively connect the corresponding loading mechanisms through the transfer rods C2 to apply the test load.
[0019] Advantages of the present utility model: An embodiment of the present utility model provides a fatigue test device for a horizontal tail connection structure. The main structure includes: a horizontal tail dummy A, a vertical tail dummy B, and a loading transfer mechanism C. In addition, the test piece of the horizontal tail connection structure includes four horizontal tail connection angle pieces. When using this fatigue test device to perform the fatigue test of the horizontal tail connection structure, the installation surface of the horizontal tail and the horizontal tail connection structure on the aircraft is simulated through the horizontal tail dummy A; the curved surface installation form of the vertical tail and the horizontal tail connection structure on the aircraft is realized through the vertical tail dummy B; the loading transfer mechanism C is matched with the horizontal tail dummy B, and the load application in the Fx and Fz directions is accurately realized. By using the fatigue test device provided by the embodiment of the present utility model, the installation state of the horizontal tail connection structure with the horizontal tail, vertical tail, etc. on the aircraft is simulated, and the load is applied on both sides of the horizontal tail dummy, providing a basis for fatigue life assessment, and also determining the fatigue dangerous parts of the horizontal tail connection structure, providing a basis for design improvement and maintenance. In addition, the technical solution of the embodiment of the present utility model not only accurately simulates the installed state of the horizontal tail connection structure, but also has the advantages of light structural design and convenient installation. Description of the Drawings
[0020] The drawings are used to provide a further understanding of the technical solution of the present utility model, and constitute a part of the specification. Together with the embodiments of the present application, they are used to explain the technical solution of the present utility model, and do not constitute a limitation to the technical solution of the present utility model.
[0021] Figure 1 It is a schematic structural diagram of a fatigue test device for a horizontal tail connection structure provided by an embodiment of the present utility model;
[0022] Figure 2 is Figure 1 A schematic structural diagram of the horizontal tail dummy in the fatigue test device provided by the illustrated embodiment;
[0023] Figure 3 is Figure 1 A schematic structural diagram of the vertical tail dummy in the fatigue test device provided by the illustrated embodiment;
[0024] Figure 4 is Figure 1 A combined structural diagram of the vertical tail dummy and the test piece of the horizontal tail connection structure in the fatigue test device provided by the illustrated embodiment;
[0025] Figure 5 is Figure 1 A schematic structural diagram of the loading transfer mechanism in the fatigue test device provided by the illustrated embodiment. Detailed Embodiments
[0026] To make the objectives, technical solutions, and advantages of the present utility model clearer and more understandable, the embodiments of the present utility model will be described in detail below with reference to the accompanying drawings. It should be noted that, without conflict, the embodiments and features in the embodiments in this application can be combined arbitrarily with each other.
[0027] As described in the above background art, the importance of the horizontal tail connection structure during helicopter flight has been explained; however, for the horizontal tail connection structure, there is currently a lack of an effective fatigue test implementation plan, resulting in the problem that it is difficult to evaluate the fatigue performance of the horizontal tail connection structure.
[0028] To achieve the objective of evaluating the fatigue performance of the helicopter horizontal tail connection structure, the embodiments of the present utility model provide a fatigue test device for the horizontal tail connection structure. By using this fatigue test device, the fatigue characteristics of the horizontal tail connection structure can be obtained, providing a basis for fatigue life assessment, and the fatigue critical parts of the horizontal tail connection structure can also be determined, providing a basis for design improvement and maintenance.
[0029] The present utility model provides the following specific embodiments that can be combined with each other. For the same or similar concepts or processes, they may not be repeated in some embodiments.
[0030] Figure 1 FIG. is a schematic structural diagram of a fatigue test device for a horizontal tail connection structure provided by an embodiment of the present utility model. The main structure of the fatigue test device for the horizontal tail connection structure provided by the embodiments of the present utility model includes: a horizontal tail dummy A, a vertical tail dummy B, and a loading transfer mechanism C; the test piece of the horizontal tail connection structure includes four horizontal tail connection angle pieces. Figure 2 For Figure 1 FIG. is a schematic structural diagram of the horizontal tail dummy in the fatigue test device provided by the illustrated embodiment. Figure 3 For Figure 1 FIG. is a schematic structural diagram of the vertical tail dummy in the fatigue test device provided by the illustrated embodiment. Figure 4 For Figure 1 FIG. is a schematic combined structural diagram of the vertical tail dummy and the test piece of the horizontal tail connection structure in the fatigue test device provided by the illustrated embodiment.
[0031] As Figures 1 to 4 In the structure of the fatigue test device shown, the horizontal tail dummy A includes an intermediate airfoil section with a curved bottom end, and transition sections symmetrically distributed on both sides of the intermediate airfoil section integrally. A columnar loading connection part is provided at the end of each transition section, and each loading connection part is fixedly connected to a set of loading transfer mechanisms C.
[0032] In the fatigue test device provided by the embodiment of the present utility model, the vertical tail dummy B includes a horizontal tail connection part located in the upper section and a test bench connection part located in the lower section. A step is formed in the connection area between the horizontal tail connection part and the test bench connection part along the course direction. The top surface of the horizontal tail connection part is set as a curved surface end, which is matched with the curved surface bottom end of the horizontal tail dummy A. Four horizontal tail connection angle pieces are respectively installed at the four corners of the two side end faces of the vertical tail dummy B to fixedly connect the middle airfoil section of the vertical tail dummy B and the horizontal tail dummy A; it is used to simulate the installation structure of the horizontal tail connection structure on the aircraft through the horizontal tail dummy A and the vertical tail dummy B.
[0033] In one implementation manner of the embodiment of the present utility model, as Figure 3 and Figure 4 shown, the two side end faces of the horizontal tail connection part of the vertical tail dummy B along the course direction are set as arc surfaces, and open structures are provided at the front and rear ends along the course direction. Four horizontal tail connection angle pieces are fixedly installed on the two side walls of the front and rear open structures respectively.
[0034] In this implementation manner, the horizontal tail connection part of the vertical tail dummy B is also provided with grooves located inside the front and rear open structures, and rivet holes for connecting the horizontal tail connection angle pieces are provided on both the open structures and the grooves. The horizontal tail connection angle pieces are fixed by riveting.
[0035] Furthermore, step areas with angular depressions are respectively provided on both sides of the rear open structure of the horizontal tail connection part of the vertical tail dummy B.
[0036] Correspondingly, the side surfaces of the four horizontal tail connection angle pieces respectively match the outer shape surfaces of the four corners of the horizontal tail connection part, and the top surfaces of the four horizontal tail connection angle pieces match the curved surface bottom end of the middle airfoil section of the horizontal tail dummy A; so as to form a curved surface installation structure through its side surface and the four corners of the horizontal tail connection part, and form a curved surface installation structure through its top surface and the middle airfoil section of the horizontal tail dummy A.
[0037] In one implementation manner of the embodiment of the present utility model, the loading transfer mechanism C of the fatigue test device includes: a loading seat C1, a transfer rod C2, a spherical plain bearing C3 and a limit nut C4; as Figure 5 shown, it is Figure 1 the structural schematic diagram of the loading transfer mechanism in the fatigue test device provided by the embodiment shown.
[0038] In this implementation manner, as Figure 1 and Figure 5 shown, a screw rod is provided at the end of the columnar loading connection part on the horizontal tail dummy A. The loading seat C1 is sleeved on the screw rod of the columnar loading connection part through its central through hole and is fixedly connected by using the limit nut C4, and a spherical plain bearing C3 is arranged inside the central through hole; the loading seat C1 is respectively provided with a transfer rod C2 in the reverse course direction and the vertical upward direction for connecting the loading mechanism.
[0039] Based on the specific structure of the fatigue test device for the horizontal tail connection structure provided in the above embodiments of the present utility model, in the test using this fatigue test device, the overall fatigue test device is fixedly connected to the test bench through the connection holes and bolts opened on the connection part of the lower test bench of the vertical tail dummy B, and the corresponding loading mechanisms are respectively connected through the transfer rods C2 to apply the test load.
[0040] The fatigue test device for the horizontal tail connection structure provided in the embodiments of the present utility model, the main structure includes: a horizontal tail dummy A, a vertical tail dummy B, and a loading transfer mechanism C; in addition, the test piece of the horizontal tail connection structure includes four horizontal tail connection angle pieces. When using this fatigue test device to perform the fatigue test of the horizontal tail connection structure, the installation surface of the horizontal tail and the horizontal tail connection structure on the aircraft is simulated through the horizontal tail dummy A; the curved surface installation form of the vertical tail and the horizontal tail connection structure on the aircraft is realized through the vertical tail dummy B; the loading transfer mechanism C is matched with the horizontal tail dummy B to accurately apply the loads in the Fx and Fz directions. By using the fatigue test device provided in the embodiments of the present utility model, the installation state of the horizontal tail connection structure with the horizontal tail, vertical tail, etc. on the aircraft is simulated, and the loads are applied on both sides of the horizontal tail dummy, providing a basis for fatigue life assessment, and also can determine the fatigue dangerous parts of the horizontal tail connection structure, providing a basis for improving the design and maintenance. In addition, the technical solution of the embodiments of the present utility model not only accurately simulates the installed state of the horizontal tail connection structure, but also has the advantages of light structure design and convenient installation.
[0041] The implementation manner of the fatigue test device for the horizontal tail connection structure provided in the embodiments of the present utility model is schematically described below through a specific embodiment.
[0042] Embodiment
[0043] This embodiment provides a fatigue test device for a horizontal tail connection structure. Referring to Figures 1 to 5 as shown, this fatigue test device is mainly composed of three parts: a horizontal tail dummy A, a vertical tail dummy B, and a loading transfer mechanism C; among them, the loading transfer mechanism C includes: a loading seat C1, a transfer rod C2, a spherical plain bearing C3, and a lock nut C4.
[0044] The specific structures and the mutual connection relationships of the horizontal tail dummy A, the vertical tail dummy B, and the loading transfer mechanism C in this embodiment have been described in detail in the above embodiments, so they will not be repeated here.
[0045] During installation, the radian at the bottom end of the curved surface in the horizontal tail dummy part A coincides with the upper surface of the horizontal tail connection structure. Four through holes on the plane of the middle airfoil section of the horizontal tail dummy part A are respectively connected and fixed to the holes on the front, rear, left, and right horizontal tail connection structures through bolts; the side of the horizontal tail connection structure contacts the vertical tail dummy part B, and the four horizontal tail connection structures are respectively fixed on the vertical tail dummy part B through rivets; the loading transfer mechanism C passes through the cylinders at both ends of the horizontal tail dummy part A, and is tightly connected using a limit nut C4, a bushing, etc.
[0046] During the test, the lower part of the vertical tail dummy part B is fixed to the test bench through the cooperation of bolts and holes, and then the load is applied through the connection of the transfer rod and the loading mechanism, etc.
[0047] The fatigue test device for the horizontal tail connection structure provided by this embodiment, on the one hand, simulates the coincidence of the installation curved surface of the horizontal tail and the horizontal tail connection structure on the aircraft through the horizontal tail dummy part A, which also meets the installation dimension requirements and the need to apply loads on both sides of the horizontal tail; on the other hand, the vertical tail dummy part B realizes the simulation of the curved surface installation form of the vertical tail and the horizontal tail connection structure on the aircraft; on the further hand, the loading transfer mechanism C matches with the horizontal tail dummy part B, and accurately realizes the load application in the Fx and Fz directions, where Fx is along the helicopter's heading and Fz is the direction perpendicular to the chord plane. This embodiment provides a reasonable and effective fatigue test device, accurately simulating the on-aircraft installation states of the horizontal tail, the horizontal tail connection structure, and the vertical tail, etc., and accurately realizing the application of loads on both sides through the loading mechanism.
[0048] Although the disclosed embodiments of the present utility model are as above, the content is only the embodiments adopted for facilitating the understanding of the present utility model, and is not used to limit the present utility model. Any person skilled in the art within the scope of the present utility model can make any modifications and changes in the form and details of the implementation without departing from the spirit and scope disclosed by the present utility model. However, the patent protection scope of the present utility model shall still be subject to the scope defined by the appended claims.
Claims
1. A fatigue test device for a horizontal tail connection structure, characterized in that: include: Horizontal tail dummy (A), vertical tail dummy (B) and loading transfer mechanism (C); The test piece of the horizontal tail connection structure includes four horizontal tail connection angle pieces; The horizontal tail dummy (A) comprises an intermediate airfoil section having a curved bottom end, and transition sections symmetrically distributed on both sides of the intermediate airfoil section, each end of the transition section is provided with a columnar loading connection portion, and each loading connection portion is fixedly connected to a set of loading adapter mechanisms (C); The vertical tail dummy (B) comprises a horizontal tail connecting part located at the upper section and a test bench connecting part located at the lower section, the connecting area between the horizontal tail connecting part and the test bench connecting part forms a step along the heading direction, the top end surface of the horizontal tail connecting part is set as a curved end, which matches the curved bottom end of the horizontal tail dummy (A); the vertical tail dummy (B) is fixedly connected to the middle wing section of the horizontal tail dummy (A) by installing horizontal tail connecting corner pieces at the four corners of the end surfaces on both sides of the vertical tail dummy (B); and the installation structure of the horizontal tail connecting structure on the aircraft is simulated by the horizontal tail dummy (A) and the vertical tail dummy (B).
2. The fatigue testing device for the horizontal tail connection structure according to claim 1, characterized in that: The end surfaces of the horizontal tail connection part of the vertical tail dummy (B) along the heading direction are arranged as arc surfaces, and the front and rear ends along the heading direction are arranged with opening structures, and four horizontal tail connection angle pieces are fixedly installed through the two side walls of the front and rear opening structures.
3. The fatigue testing device for the horizontal tail connection structure according to claim 2, characterized in that: The horizontal tail connection part in the vertical tail dummy (B) is also provided with grooves located inside the front and rear opening structures, and rivet holes for connecting the horizontal tail connection angle pieces are opened on the opening structures and the grooves, and the horizontal tail connection angle pieces are fixed by riveting.
4. The fatigue testing device for the horizontal tail connection structure according to claim 3 is characterized in that: The two sides of the rear opening structure of the horizontal tail connecting part in the vertical tail dummy (B) are respectively provided with step areas with recessed corners; The side surfaces of the four horizontal tail connection angle pieces respectively match the outer shape surfaces of the four corners of the horizontal tail connection part, and the top surfaces of the four horizontal tail connection angle pieces match the curved bottom end of the middle wing section of the horizontal tail dummy (A); so as to form a curved surface installation structure with the four corners of the horizontal tail connection part through their side surfaces, and form a curved surface installation structure with the middle wing section of the horizontal tail dummy (A) through their top surfaces.
5. The fatigue testing device for a horizontal tail connection structure according to any one of claims 1 to 4, characterized in that: The loading and switching mechanism (C) comprises: a loading seat (C1), a switching rod (C2), a joint bearing (C3) and a limiting nut (C4); The end of the columnar loading connection part on the horizontal tail dummy (A) is provided with a screw rod, the loading seat (C1) is sleeved on the screw rod of the columnar loading connection part through its central through hole, and is fixedly connected by a limit nut (C4), and a joint bearing (C3) is built in the central through hole; the loading seat (C1) is respectively provided with a transfer rod (C2) in the reverse heading direction and the vertical upward direction for connecting the loading mechanism.
6. The fatigue testing device for the horizontal tail connection structure according to claim 5, characterized in that: The fatigue test device is used to fix the entire fatigue test device on the test bench through the connection holes and bolts provided on the connection part of the lower section of the vertical tail dummy (B) during the test, and to connect the corresponding loading mechanisms respectively through the adapter rods (C2) to apply the test load.