Overturn-preventing aircraft empennage test piece tool
By using a self-balancing design with an arc-shaped guide rail and a counterweight swing component in the tooling of the aircraft tail fin test piece, the overturning problem of the tail fin test piece was solved, achieving the effects of passive anti-overturning and lightweighting.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-29
- Publication Date
- 2026-03-10
AI Technical Summary
Existing aircraft tail fin test fixtures pose a risk of tipping over during static strength tests or demonstrations, especially lightweight structural support frames which are easily damaged under external forces.
The design employs an arc-shaped guide rail and a counterweight swing component. Utilizing the principle of gravity balance, when the fixture tilts, the swing component slides on the guide rail to adjust its balance position, counteracting the overturning tendency and achieving passive anti-overturning.
The self-balancing mechanism effectively prevents the tail fin test piece from overturning, enhances its anti-overturning capability, reduces the risk of damage, and features a lightweight structure, rapid response, and requires no external energy source.
Smart Images
Figure CN223982671U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to the technical field of aircraft test piece tooling, particularly relates to an overturn-preventing aircraft tail wing test piece tooling. BACKGROUND
[0002] Different test toolings need to be manufactured for model assembly test or model support frame needs to be made for convenient model display during the aircraft model test stage, since the models of aircraft are different, one tooling cannot be adapted to all test pieces, so corresponding test piece toolings need to be set for different parts of the aircraft;
[0003] The aircraft tail wing test tooling is used for mounting the aircraft tail wing on the support frame for ground static strength test and sample display support, since multiple test piece toolings need to be prepared, therefore, the tooling structure is mostly welded from hollow steel pipes, which can ensure the overall strength of the support frame and reduce the overall weight, facilitating the carrying of the staff, when installing, the tail wing assembly is connected with the support frame through the girder and the pivot using bolts, so that the concentrated load is transmitted to the tail wing support frame during the static strength test.
[0004] However, the prior art has some problems: during the static strength test or display, the tail wing test piece is hung on the support frame, and the load is relatively concentrated, and the structure of the economical support frame is mostly light structure, therefore, when the support frame is disturbed by external force, there is a risk of overturning, which causes damage to the tail wing test piece, therefore, we propose an overturn-preventing aircraft tail wing test piece tooling. UTILITY MODEL CONTENTS
[0005] In view of the deficiencies in the prior art, the utility model provides an overturn-preventing aircraft tail wing test piece tooling, which is provided with an arc-shaped guide rail and a swing piece with counterweight at the bottom, utilizes the passive gravity balance principle, when the tooling is disturbed by external force and the angle deviates, utilizes the free sliding characteristics of the swing piece on the arc-shaped rail, and automatically finds a new balance position through gravity, so that the purpose of preventing overturning is achieved.
[0006] The utility model discloses a kind of overturn-preventing aircraft tail wing test piece toolings, including base, the bottom of the base is fixedly connected with footing, the base is fixedly connected with support frame, the quantity of the support frame is two, two The support frame is symmetrical, two The support frame is fixedly connected with mounting plate between, the mounting plate is fixedly connected with connecting seat, the connecting seat is used to install tail wing test piece, the base is provided with guide rail, the guide rail is arranged in arc, the guide rail is slidably connected with swing piece, the swing piece is provided with counterweight, the quantity of the counterweight is multiple groups.
[0007] Optionally, the number of guide rails is two sets, the two sets of guide rails are symmetrically distributed, and support rods are provided between the two ends of the guide rails and the base.
[0008] Optionally, the guide rail has a hollow area inside, a sliding groove inside, a guide groove on the guide rail, the guide groove communicating with the sliding groove, and end caps fixedly connected to both ends of the guide rail.
[0009] Optionally, a baffle is provided inside the guide rail, a damper is provided between the baffle and the end cover, and a spring is provided on the outside of the damper.
[0010] Optionally, the swinging component includes a support rod and a connecting rod. A rotating shaft is fixedly connected to the support rod, and rollers are rotatably connected to both sides of the rotating shaft. The rollers are in rolling connection with a sliding groove. The support rod is located at both ends of the connecting rod and is inserted into a counterweight.
[0011] Optionally, a limiting hole is provided on the support rod, a limiting pin is inserted into the limiting hole, a tension spring is sleeved on the outside of the limiting pin, one end of the tension spring is fixedly connected to the branch, and the other end of the tension spring is fixedly connected to the limiting pin.
[0012] Compared with the prior art, the beneficial effects of this utility model are as follows:
[0013] 1. When the aircraft tail fin test fixture is subjected to external forces, the force on the tail fin will cause the entire fixture to tilt. At this time, the oscillating components mounted on the curved guide rails on both sides will automatically slide in the opposite direction of the load due to gravity, thereby increasing the balance arm. The movement of the oscillating components will generate a counter-torque, thereby counteracting the overturning tendency caused by the tail fin load, until the two torques are balanced and the fixture returns to stability. When the external force is removed, the oscillating components will slide back to their initial position due to gravity. The entire process is a completely passive response, requiring no additional drive, and relies on gravity self-balancing to achieve anti-overturning.
[0014] 2. By setting guide rails on both sides of the base, the swinging component slides on both guide rails simultaneously. On the one hand, the double guide rail structure forms a stable force couple balance, which can distribute the load, avoid stress concentration on one side, and improve the overall anti-overturning ability. On the other hand, the connecting rod forces the sliders on both sides to move synchronously, ensuring that the counterweight is always adjusted symmetrically and eliminating the risk of off-center load caused by asynchronous movement. Attached Figure Description
[0015] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.
[0016] Figure 1 This is a schematic diagram of the overall structure provided by this utility model.
[0017] Figure 2 This is a schematic diagram of the guide rail structure provided by this utility model.
[0018] Figure 3 This is a schematic diagram of the damper structure provided by this utility model.
[0019] Figure 4 This is a schematic diagram of the swing component structure provided by this utility model.
[0020] Figure 5 This is a schematic diagram of the limiting pin structure provided by this utility model.
[0021] Figure 6 This is a schematic diagram of the working state of the tension spring provided by this utility model.
[0022] In the diagram: 1. Base; 11. Foot; 12. Support frame; 13. Mounting plate; 14. Connecting seat; 2. Guide rail; 21. Slide groove; 22. Guide groove; 3. End cover; 31. Baffle; 32. Damper; 33. Spring; 4. Swing component; 41. Support rod; 42. Rotating shaft; 43. Roller; 44. Connecting rod; 5. Counterweight; 51. Limiting hole; 52. Limiting pin; 53. Tension spring. Detailed Implementation
[0023] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.
[0024] like Figures 1 to 6 The tooling for an anti-overturning aircraft tail fin test component shown includes a base 1, with feet 11 fixedly connected to the bottom of the base 1, and two support frames 12 fixedly connected to the base 1. The two support frames 12 are symmetrical, and a mounting plate 13 is fixedly connected between the two support frames 12. A connecting seat 14 is fixedly connected to the mounting plate 13 for mounting the tail fin test component. A guide rail 2 is provided on the base 1. The guide rail 2 is arc-shaped, and a swinging component 4 is slidably connected to the guide rail 2. A counterweight 5 is provided on the swinging component 4. The number of counterweights 5 is multiple.
[0025] Furthermore, the base 1 is welded from several hollow tubular components, and several sets of feet 11 are welded to the lower end of the base 1 to fix the base 1 to the ground, forming a stable support to resist the multidimensional forces during the test. Secondly, the arc-shaped guide rail 2 works in conjunction with the swing component 4 to automatically change the balance torque according to the force on the test piece, realizing real-time adaptive overturning protection, which has higher adjustment accuracy and response speed compared with the traditional fixed counterweight method. Furthermore, the modular multi-set counterweight blocks 5 can adjust the total amount of counterweight according to the test requirements, which can meet the lightweight testing requirements of small tail wings and also cope with the high load conditions of large tail wings.
[0026] In addition, the special geometric setting of the arc-shaped guide rail 2 makes the lever arm change non-linearly when the counterweight 5 moves, which can provide a larger torque adjustment range within a limited stroke and improve space utilization.
[0027] Finally, the entire system adopts a purely mechanical structure, requiring no external energy or complex control system, which ensures reliability and reduces maintenance costs.
[0028] Specifically, there are two sets of guide rails 2, which are symmetrically distributed. Support rods are provided between the two ends of the guide rails 2 and the base 1.
[0029] Furthermore, the two sets of guide rails 2 form a stable spatial truss structure with the base 1 through the support rods, which improves the overall rigidity and is used to resist the torsional load during the test. The symmetrical layout of the guide rail 2 system and the swinging component 4 with the connecting structure work together to ensure that the balance torque is always evenly distributed and avoid the risk of eccentric load caused by unilateral force.
[0030] The synergistic effect of the dual guide rails 2 expands the adjustment range of the counterweight 5, enabling the system to adapt to the testing requirements of larger tail fins, while enhancing its ability to buffer sudden impact loads. The support rods not only strengthen the load-bearing capacity of the guide rails 2 but also optimize the force transmission path, allowing the entire anti-rollover system to maintain a lightweight design while possessing higher reliability and stability.
[0031] Specifically, the guide rail 2 has a hollow area inside, a sliding groove 21 is provided inside the guide rail 2, a guide groove 22 is provided on the guide rail 2, the guide groove 22 is connected to the sliding groove 21, and end caps 3 are fixedly connected to both ends of the guide rail 2.
[0032] Furthermore, the hollow area achieves lightweighting while ensuring structural strength, reducing the overall weight burden of the tooling.
[0033] The cooperation between the internal slide groove 21 and the roller 43 ensures the smoothness of the movement of the swinging component 4, reduces friction loss, and improves the dynamic response speed. The guide groove 22 provides linear guidance for the support rod 41, so that the counterweight system always maintains a stable movement trajectory. The end caps 3 set at both ends serve as limiting structures to prevent the swinging component 4 from accidentally derailing and have a sealing and protective function.
[0034] Specifically, a baffle 31 is provided inside the guide rail 2, a damper 32 is provided between the baffle 31 and the end cover 3, and a spring 33 is provided on the outside of the damper 32.
[0035] Furthermore, the baffle 31 acts as a buffer barrier, intervening in advance when the swinging component 4 approaches its limit position. When the swinging component 4 contacts the baffle 31, the damper 32 absorbs the impact energy at the end of the swinging component 4, avoiding rigid collisions. The spring 33 provides a progressive rebound force, ensuring that the counterweight 5 decelerates smoothly and resets gently. This allows the guide rail 2 system to maintain its guiding function while also providing buffering and shock absorption performance. It prevents mechanical damage caused by overshoot of the swinging component 4 and reduces vibration interference during the test. Especially under conditions of sudden loading or rapid unloading of the tail fin, this structure can significantly reduce the vibration of the tooling, protect the contact surface of the guide rail 2 and the roller 43, and extend the service life of the tooling.
[0036] Specifically, the swinging component 4 includes a support rod 41 and a connecting rod 44. A rotating shaft 42 is fixedly connected to the support rod 41. Rollers 43 are rotatably connected to both sides of the rotating shaft 42. The rollers 43 are in rolling connection with the slide groove 21. The support rod 41 is located at both ends of the connecting rod 44. The support rod 41 is inserted into the counterweight 5.
[0037] Furthermore, the swing component 4 adopts a modular design, consisting of a rigid support rod 41 and connecting rods 44 connecting both sides to form the main frame. The support rod 41 has a fixed pivot 42 in the middle and rollers 43 installed symmetrically at both ends. Low-friction rolling is achieved in the slide groove 21 through the combination of pivot 42 and rollers 43. The extended end of the support rod 41 is provided with a standardized insertion interface, which can quickly install and remove counterweights 5 of different specifications.
[0038] Specifically, a limiting hole 51 is provided on the support rod 41, a limiting pin 52 is inserted into the limiting hole 51, and a tension spring 53 is sleeved on the outside of the limiting pin 52. One end of the tension spring 53 is fixedly connected to the branch, and the other end of the tension spring 53 is fixedly connected to the limiting pin 52.
[0039] Furthermore, when the limiting pin 52 is inserted into the preset hole of the support rod 41, it can quickly lock the position of the counterweight 5, ensuring that the counterweight does not undergo accidental displacement during the test. The elastic preload of the tension spring 53 can maintain the stable engagement of the limiting pin 52. On the one hand, it can effectively suppress the pin shaft movement under vibration conditions and avoid balance failure caused by loosening. On the other hand, the counterweight can be dynamically adjusted without auxiliary tools, which significantly improves the test efficiency.
[0040] When in use, pull the limiting pin 52, and the limiting pin 52 will disengage from the limiting hole 51. Insert the counterweight 5 into the limiting hole 51, release the limiting pin 52, and the limiting pin 52 will automatically reset under the tension of the tension spring 53, passing through the counterweight 5 and completing the limiting of the counterweight 5. The operation is simple and convenient, improving the efficiency of disassembly and assembly.
[0041] Working principle: When the aircraft tail test fixture is subjected to an external force, the force on the tail will cause the entire fixture to tilt. At this time, the swinging component 4, installed on the two curved guide rails 2, will automatically slide in the opposite direction of the load due to gravity, thereby increasing the balance arm. The movement of the swinging component 4 will generate a reverse torque, thereby counteracting the overturning tendency caused by the tail load, until the two torques are balanced and the fixture returns to stability. When the external force is removed, the swinging component 4 will slide back to its initial position due to gravity. The entire process is a completely passive response, requiring no additional drive, and relies on gravity self-balancing to achieve anti-overturning.
[0042] The above description of the embodiments is only for the purpose of helping to understand the method and core idea of this utility model. It should be noted that for those skilled in the art, several improvements and modifications can be made to this utility model without departing from the principle of this utility model, and these improvements and modifications also fall within the protection scope of the claims of this utility model.
Claims
1. An anti-rollover aircraft tail test piece fixture comprising a base (1), characterised in that: The bottom of the base (1) is fixedly connected with a ground foot (11), the base (1) is fixedly connected with a support frame (12), the number of the support frame (12) is two, two support frames (12) are symmetrical parts, two support frames (12) are fixedly connected with a mounting plate (13), the mounting plate (13) is fixedly connected with a connecting seat (14), the connecting seat (14) is used for installing a tail wing test piece, the base (1) is provided with a guide rail (2), the guide rail (2) is arranged in an arc shape, the guide rail (2) is slidably connected with a swing piece (4), the swing piece (4) is provided with a counterweight block (5), and the number of the counterweight block (5) is multiple groups.
2. The anti-rollover aircraft tail test piece fixture of claim 1, wherein: The number of the guide rail (2) is two groups, the two groups of guide rails (2) are symmetrically distributed, and support rod pieces are arranged between the two ends of the guide rail (2) and the base (1).
3. The anti-rollover aircraft tail test piece fixture of claim 1, wherein: The inside of the guide rail (2) forms a hollow area, the inside of the guide rail (2) is provided with a sliding groove (21), the guide rail (2) is provided with a guide groove (22), the guide groove (22) is in communication with the sliding groove (21), and the both ends of the guide rail (2) are fixedly connected with an end cover (3).
4. The anti-rollover aircraft tail test piece fixture of claim 1, wherein: The inside of the guide rail (2) is provided with a baffle (31), the baffle (31) and the end cover (3) are provided with a damper (32), and the outside of the damper (32) is provided with a spring (33).
5. The anti-rollover aircraft tail test piece fixture of claim 1, wherein: The swing piece (4) comprises a support rod (41) and a connecting rod (44), the support rod (41) is fixedly connected with a rotating shaft (42), the both sides of the rotating shaft (42) are rotatably connected with a roller (43), the roller (43) is rotatably connected with the sliding groove (21), the support rod (41) is located at the both ends of the connecting rod (44), and the support rod (41) is inserted with the counterweight block (5).
6. The anti-rollover aircraft tail test piece fixture of claim 5, wherein: The support rod (41) is provided with a limiting hole (51), the limiting hole (51) is inserted with a limiting pin (52), the outside of the limiting pin (52) is sleeved with a tension spring (53), one end of the tension spring (53) is fixedly connected with a branch, and the other end of the tension spring (53) is fixedly connected with the limiting pin (52).