Strength testing device with simultaneous application of multiple linkage composite loads

Abstract

The present invention discloses a multi-linkage composite load synchronous application strength testing device. It solves the technical problems in the prior art such as the single load application method and the inability to synchronously apply composite loads. The device includes a connecting mechanism and a load application mechanism, and the load application mechanism includes a torsional load application structure, a load transfer structure and a multi-linkage testing structure. The load transfer structure includes a special-shaped load-bearing plate and a torsional load transfer assembly, and the torsional load transfer assembly includes a connecting chuck and a torque plug-in. By controlling the rotation of the torsional load transfer assembly, a pure torsional load application mode or a conversion mode in which torsional motion is converted into a radial load can be selectively realized to achieve multi-directional load detection. The present invention also provides a composite load synchronous application function. By adjusting the geometric positions of the torque plug-in and the load adjustment plate on the connecting chuck, a single drive source is used to synchronously activate the torsional load path and the radial load path, thereby achieving the synchronous application of torsional load and radial load.

Description

Technical Field

[0001] The present invention relates to the technical field of material strength testing, and in particular to a strength testing device for synchronously applying multiple linkage composite loads. Background Art

[0002] At present, there are relevant technical solutions for the strength testing of UAV structural parts. For example, Chinese patent document CN221394064U discloses a UAV structural strength testing device, which includes a protective component, a testing platform, a positioning component and a strength testing component. Among them, the positioning component includes a mounting plate and two movable parts, and the movable parts are arranged in a cross-like manner up and down. Each movable part includes a drive motor, a drive wheel, a driven wheel, a slider and a clamping plate. During the test, the clamping plates are driven to move relative to each other by starting the drive motor, so that the clamping plates are centered and pressure is applied to the UAV frame, and then the strength testing component applies a load to the part to be tested, and the deformation of the frame under different loads is recorded.

[0003] Although the above-mentioned existing technologies can realize automatic positioning and strength detection of UAV frames and avoid the deviation that may be caused by manual positioning, they still have the following technical defects:

[0004] First, the load application method is single. The device mainly applies vertical loads through cylinders and pressure pieces, which cannot simulate the complex stress conditions such as torsional loads and multi-directional loads that composite cabins may encounter in actual use, and the test conditions are relatively limited.

[0005] Secondly, there is a lack of testing capabilities for combined loads. In practical applications, composite cabins often experience multiple types of loads simultaneously, such as radial impact forces and torsional moments caused by eccentric impact points. Existing technologies are unable to simultaneously apply different types of loads, making it impossible to accurately simulate realistic combined load conditions.

[0006] Thirdly, the test efficiency needs to be improved. When strength testing in different directions is required, the existing technology requires re-adjusting the position of the test component or re-installing the test piece, which is cumbersome and takes a long test cycle.

[0007] In addition, the existing technology lacks an effective load conversion mechanism, which makes it impossible to flexibly switch from one load mode to another, limiting the diversity and comprehensiveness of the test.

[0008] Therefore, the existing technology urgently needs a composite cabin strength testing device that can realize multi-directional load detection, simultaneous application of composite loads, and has efficient testing capabilities to meet the increasingly complex testing needs of composite structural parts. Summary of the Invention

[0009] The purpose of the present invention is to solve the deficiencies of the prior art and to provide a composite material cabin multi-linkage strength testing device that can realize multi-directional load detection and simultaneous application of composite loads.

[0010] In order to solve the above problems, the present invention provides a multi-link strength testing device for detecting the strength characteristics of a composite material cabin, comprising:

[0011] a connecting mechanism for fixedly connecting the composite cabin to the testing device;

[0012] A load applying mechanism for applying a load to the composite cabin, comprising: a torsional load applying structure for applying a torsional load to the composite cabin; a load transferring structure for transferring the load to the composite cabin; and a multi-linkage testing structure for converting torsional motion into a radial load.

[0013] The load transfer structure includes: a special-shaped load-bearing plate with at least two opposing load-bearing surfaces on its side wall; a torsional load transfer assembly including a connecting chuck and two torque plug-ins, wherein the torque plug-ins are installed at both ends of the diameter of the connecting chuck and can contact the two load-bearing surfaces respectively to generate thrust;

[0014] The multi-linkage test structure includes: a load transfer column, which is arranged on the connection chuck and faces the special-shaped load-bearing plate; a load adjustment plate, which has an inclined surface and is fixedly arranged on the end of the load transfer column; and a load adjustment wheel, which is fixedly connected to the edge of the special-shaped load-bearing plate.

[0015] By controlling the rotation of the torsional load transfer assembly, it is possible to selectively implement: a pure torsional load application mode or a conversion mode in which torsional motion is converted into a radial load, thereby achieving multi-directional load detection of the composite cabin.

[0016] Based on this technical solution, the special-shaped load-bearing plate has at least two opposing, outwardly convex curved sidewalls arranged symmetrically around the center, with load-bearing surfaces located at the head and tail of each curved sidewall. Multiple load-adjusting wheels are provided on the plate. This ensures uniform load distribution in all directions, improving load transfer stability and test data reliability.

[0017] Preferably, the torsional load applying structure includes a torque wrench, which is driven by a square head. Compared with a circular drive, it has better torque transmission effect and anti-slip performance, ensuring the accuracy of load application.

[0018] Furthermore, the multi-linkage test structure has a dual-mode working mode:

[0019] Direct torsion mode: The torque plug is located at the bottom end of the curved side wall, the load adjustment plate and the load adjustment wheel remain separated, and pure torsional torque is applied to the special-shaped load-bearing plate only through the contact between the torque plug and the load-bearing surface;

[0020] Torsion-radial conversion mode: The torque plug is separated from the load-bearing surface, the inclined surface of the load adjustment plate is in tangential contact with the load adjustment wheel, and the load adjustment wheel rolls along the inclined surface to convert the torsional motion into radial extrusion force.

[0021] The beneficial effect of dual-mode operation: load mode switching can be achieved through simple position adjustment, avoiding complex mechanical modification.

[0022] Optionally, the torque adjustment structure adopts one of a motor-driven linear motion module, a pneumatic linear actuator, a hydraulic cylinder drive device, a manual screw adjustment mechanism, or a servo electric cylinder, providing flexibility for tests with different precision requirements and automation levels.

[0023] The present invention also provides a composite load synchronous application test device for simulating the strength characteristics of a composite cabin under composite loads, comprising:

[0024] a connecting mechanism for fixedly connecting the composite cabin to the testing device;

[0025] A load applying mechanism for applying a load to the composite cabin, comprising: a torsional load applying structure for applying a torsional load to the composite cabin; a load transferring structure for transferring the load to the composite cabin; and a multi-linkage testing structure for converting torsional motion into a radial load.

[0026] The load transfer structure includes: a special-shaped load-bearing plate with at least two opposing load-bearing surfaces on its side wall; a torsional load transfer assembly including a connecting chuck and two torque plug-ins, wherein the torque plug-ins are installed at both ends of the diameter of the connecting chuck and can contact the two load-bearing surfaces respectively to generate thrust;

[0027] The multi-linkage test structure includes: a load transfer column, which is arranged on the connection chuck and faces the special-shaped load-bearing plate; a load adjustment plate, which has an inclined surface and is fixedly arranged on the end of the load transfer column; and a load adjustment wheel, which is fixedly connected to the edge of the special-shaped load-bearing plate.

[0028] By adjusting the geometric positions of the torque plug-in and the load adjustment plate on the connection chuck, a single drive source can simultaneously activate the torsional load path and the radial load path, achieving the synchronous application of torsional load and radial load, and the load ratio can be adjusted by geometric parameters.

[0029] Based on this technical solution, the ratio of torsional load to radial load is adjusted by adjusting the bevel angle of the load adjustment plate, adjusting the geometric ratio of the torque plug and load adjustment plate, and controlling the rotation amplitude of the connecting chuck. This meets the simulation requirements of different combined load conditions and is more adaptable than traditional methods with fixed ratios.

[0030] By adjusting the position of the load transfer column, unidirectional loads can be applied in the zero, 90, 180, and 270 degree directions. This enables comprehensive load testing capabilities, enabling strength testing in all four major directions with a single installation, eliminating the tedious process of multiple repositioning and calibration required with traditional methods.

[0031] Furthermore, the rapid drive mechanism features rapid loading, load retention, and rapid unloading capabilities, simulating the instantaneous nature of an impact, maintaining the load for a set time, and preventing secondary impacts. This realistically reproduces the time history of the impact load, providing accurate testing conditions for evaluating the impact resistance of composite cabins.

[0032] Optionally, a deformation measurement device is included to monitor the deformation characteristics of the composite cabin under combined loads in real time. Combining a high-precision displacement sensor and strain gauge measurement system, load-displacement curves and stress-strain relationships can be simultaneously obtained with micron-level measurement accuracy, providing comprehensive data support for material mechanical property analysis and structural optimization design.

[0033] Compared with the prior art, the present invention has the following beneficial effects:

[0034] The present invention achieves a technological breakthrough from traditional single load testing to multi-directional composite load testing through a multiple linkage test structure. The geometric conversion principle of inclined plane constraint and rolling mechanism is adopted to efficiently convert torsional motion into radial load. Through the design of dual-mode working mode, the test device can flexibly switch between pure torsional load application mode and torsional-radial conversion mode, and strength data in multiple directions can be obtained in a single test. The function of synchronous application of composite loads enables the device to simulate complex working conditions such as impact, providing a reliable technical means for the safety assessment of composite cabins. The entire device has a compact structure and is easy to operate. It avoids the tedious process of repeated disassembly and positioning in traditional tests, and greatly reduces testing costs and labor input. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1 This is a schematic structural diagram of the composite cabin of the present invention;

[0036] Figure 2 It is a structural schematic diagram of the present invention;

[0037] Figure 3 for Figure 2 A partial enlarged view of point Ⅰ in the middle is a schematic diagram showing the contact between the stress adjustment plate and the stress adjustment wheel in Example 1;

[0038] Figure 4 This is a structural diagram of the force transmission structure of Example 1 of the present invention;

[0039] Figure 5 A schematic plan view of the anisotropic connection plate generating unidirectional stress in the multiple linkage test structure according to embodiment 1 of the present invention;

[0040] Figure 6 This is a planar schematic diagram of embodiment 1 of the present invention, in which only the torque plug-in unit transmits torsional stress to the anisotropic connecting plate;

[0041] Figure 7 This is a planar schematic diagram of the simultaneous application of composite loads in Example 2 of the present invention.

[0042] Reference numerals:

[0043] Main test objects: composite cabin 01, threaded through hole 02;

[0044] Integral tooling components: cabin connecting plate 10, connecting hole 11; end fixing device 20; load applying device 30;

[0045] Device subcomponents: unidirectional load applying structure 31, torsional load applying structure 32, load transfer structure 33, multiple linkage test structure 34;

[0046] Subdivided components: torque wrench 321, torque adjustment structure 322, special-shaped force plate 331, curved side wall 3311, force surface 332, torsional load transfer assembly 333, connecting chuck 3331, torque plug-in 3332, load transfer column 341, load adjustment plate 342, load adjustment wheel 343. DETAILED DESCRIPTION

[0047] Example 1: A multi-link strength testing device:

[0048] Test object and overall tooling composition:

[0049] See also Figure 1 and Figure 2 The test device of this embodiment is used to test the strength characteristics of the composite cabin 01 under load. The outer peripheral wall of the composite cabin 01 is provided with multiple threaded through holes 02 for connecting and fixing with other parts of the drone.

[0050] See also Figure 2 and Figure 3The overall tooling includes: a cabin connecting plate 10 that is detachably connected to both ends of the composite cabin 01; an end fixing device 20 for fixing and mounting one end of the composite cabin 01; a load applying device 30 for applying a load to the other end of the composite cabin 01; and an independently configured deformation measurement device (not shown in the figure). The cabin connecting plate 10 serves as the interface component between the tooling and the cabin. Its shape matches the shape of the port of the composite cabin 01. It is provided with multiple screw holes on its circumference and multiple connecting holes 11 on its end face. The screw holes are used to cooperate with the threaded through holes 02 at the end of the composite cabin 01 to achieve connection and fixation; the connecting holes 11 are used for end face fixation or connection with the load applying device 30.

[0051] See also Figure 4 and Figure 5 , the overall structure of the load applying device 30:

[0052] The load applying device 30 is the core component of this testing device, which has the function of applying load to the composite material cabin 01 and realizing multi-directional detection, including: a unidirectional load applying structure 31, which detects the deformation characteristics of the composite material cabin 01 under unidirectional load; a torsional load applying structure 32, which detects the strength characteristics of the composite material cabin 01 under torsional load; a load transfer structure 33, which transfers the external load to the composite material cabin 01 and is connected to the cabin connecting plate 10 through bolt connectors; a multiple linkage test structure 34, which realizes linkage testing of multi-directional loads.

[0053] The unidirectional load applying structure 31 may be a suitable force transmitting member, such as a hook, fixedly or detachably mounted on the load transmitting structure 33 .

[0054] The torsional load application structure 32 includes: a support and installation frame (not shown); a torque wrench 321 detachably connected to the load transfer structure 33, which can directly display the applied torque value; and a torque adjustment structure 322 for gradually applying or unloading torque to the torque wrench 321.

[0055] The torque adjustment structure 322 can adopt a variety of mature technical solutions, such as a motor-driven linear motion module, a pneumatic linear actuator, a hydraulic cylinder drive device, a manual screw adjustment mechanism or a servo electric cylinder.

[0056] See also Figures 3 to 6 , detailed construction of the load transfer structure:

[0057] The load transfer structure 33 is a key link in load transfer, including: a special-shaped load-bearing plate 331, which has a central axis and is detachably connected to the cabin connecting plate 10 through connectors such as bolts or fasteners, and its central axis is collinear with the central axis of the composite cabin 01; a torsional load transfer component 333, which is responsible for transferring the torsional load.

[0058] The special-shaped load-bearing plate 331 has at least two opposite and outwardly protruding arc-shaped side walls 3311 , and each arc-shaped side wall 3311 is provided with a load-bearing surface 332 at its head and tail.

[0059] The torsional load transfer assembly 333 includes: a connecting chuck 3331 , which is detachably connected to the head of the torque wrench 321 ; and two torque plug-ins 3332 , which are installed at both ends of the diameter of the connecting chuck 3331 and are arranged toward the cabin connecting plate 10 .

[0060] The two torque plug-ins 3332 can respectively contact the two force-bearing surfaces 332 to generate thrust, thereby applying a torsional load to the composite cabin 01 .

[0061] Torsional load transfer working process:

[0062] See also Figures 3 to 6 By rotating the torque wrench 321, the two torque inserts 3332 are rotated via the connecting chuck 3331. The torque inserts 3332 rotate along the curved sidewalls 3311, pushing the force-bearing surface 332 at the connection of the curved sidewalls 3311. This gradually increases the contact force between the torque inserts 3332 and the force-bearing surface 332. The thrust generated by this contact force drives the special-shaped force-bearing plate 331 to rotate, thereby generating torque that is transmitted to the composite cabin 01. To ensure stable and reliable torque transmission, the connecting chuck 3331 is provided with a central shaft that is externally fixed to support the connecting chuck 3331 and ensure its stable rotation.

[0063] Detailed construction of the multi-link test structure:

[0064] See also Figures 5 and 6 The multiple linkage test structure 34 cooperates with the torsional load application structure 32, including: a load transfer column 341, which is arranged on the connecting chuck 3331 and faces the special-shaped force plate 331, and is used to transmit unidirectional torque; a load adjustment plate 342, which has an inclined surface at a specific angle and is fixedly arranged on one end of the load transfer column 341 close to the special-shaped force plate 331; a load adjustment wheel 343, which can rotate freely and is axially fixedly connected to the edge of the special-shaped force plate 331, and its arc surface forms a tangential contact with the inclined surface of the load adjustment plate 342.

[0065] Working principle of the multi-link test structure:

[0066] The core technical principle of the multi-linkage test structure 34 is to convert the rotational torque of the connecting chuck 3331 into radial unidirectional pressure on the special-shaped force plate 331 through geometric constraints and contact mechanics principles.

[0067] Initial contact status:

[0068] The arc surface of the load adjustment wheel 343 forms tangential contact with the inclined surface of the load adjustment plate 342 at a specific point, and the normal force at the contact point is perpendicular to the tangential direction.

[0069] Force decomposition and transmission:

[0070] When the connecting chuck 3331 generates a torsional moment, the moment is transferred to the load adjustment plate 342 through the load transfer column 341. Due to the geometric constraints of the inclined surface, the force acting on the contact point can be decomposed into:

[0071] The tangential component of force along the inclined plane (driving the wheels to roll);

[0072] The normal component of force perpendicular to the inclined plane (producing a squeezing effect).

[0073] Motion conversion process:

[0074] The load-adjusting wheel 343 rolls from the lower end to the upper end under the inclined plane constraint. The vertical displacement of the wheel center during rolling is: Δh = r·θ·sin(α), where r is the wheel radius, θ is the rotation angle, and α is the inclined plane angle.

[0075] Due to the rigid connection between the wheel and the special-shaped load-bearing plate 331, the plate produces corresponding radial displacement, which is converted into a unidirectional compressive load on the cabin 01 under the constraint of the plate.

[0076] The multi-link test structure has a unique dual-mode working mode:

[0077] Mode 1: Direct twist mode:

[0078] The torque plug-in 3332 is located at the bottom end of the arc-shaped side wall 3311, and the load adjustment plate 342 and the load adjustment wheel 343 remain separated (gap δ > 0). In this mode, pure torsional torque is applied to the special-shaped load-bearing plate 331 only through the contact between the torque plug-in 3332 and the load-bearing surface 332.

[0079] Mode 2: Torsional-Radial Conversion Mode:

[0080] The torque insert 3332 rotates in the opposite direction relative to Mode 1, separating the torque insert 3332 from the load-bearing surface 332. The lower end of the inclined surface of the load adjustment plate 342 comes into tangential contact with the load adjustment wheel 343. As the rotation continues, the load adjustment wheel 343 rolls upward along the inclined surface, converting the torsional motion into a radial extrusion force, as described above.

[0081] The multi-link test structure has the following technical advantages:

[0082] Load mode switching: geometric design enables smooth transition from torsional load to unidirectional compressive load to avoid sudden load changes;

[0083] Force amplification effect: Utilizing the wedge principle of the inclined surface, a small torsional moment can be converted into a larger radial pressure, thereby improving detection sensitivity;

[0084] Multi-directional testing: By adjusting the angular position of the connecting chuck 3331, unidirectional loads can be applied to the special-shaped load-bearing plate 331 in different directions, thus achieving all-round strength testing;

[0085] Precise displacement control: By controlling the torsion angle, the displacement of the load adjustment wheel 343 on the inclined plane can be precisely controlled, thereby precisely controlling the magnitude of the applied unidirectional load. Combined with real-time monitoring of the deformation measurement device, rapid detection based on displacement control can be achieved.

[0086] Preferably, the shaped load-bearing plate 331 is centrally symmetrically arranged, with multiple load adjustment wheels 343 provided thereon. The curved sidewall 3311 is provided with multiple faces, each facing each other. In this embodiment, the curved sidewall 3311 has four faces, and four load adjustment wheels 343 are provided, one located between each adjacent curved sidewall 3311. Accordingly, the torque wrench 321 is driven by a square head.

[0087] Based on the above-mentioned multiple linkage structure design, the multiple linkage test structure 34 can realize multi-directional edge unidirectional load testing without adjusting the posture of the composite cabin 01, which not only enriches the diversity of strength testing but also ensures the testing efficiency.

[0088] Displacement control mode:

[0089] Initial direction detection: The deformation measurement device is used to record the cabin deformation δa when the target load is reached.

[0090] Multi-directional detection: Using the deformation variable δa as the displacement control target, the same deformation variable can be quickly achieved by precisely controlling the rolling distance of the load adjustment wheel 343 on the inclined surface.

[0091] Fast positioning mechanism:

[0092] Using the known target deformation value, the required torsion angle θtarget can be directly calculated, avoiding the iterative process of re-loading and deformation measurement, significantly improving detection efficiency and reducing test time.

[0093] Multi-directional consistency guarantee:

[0094] Through a unified displacement control algorithm, the detection conditions in all directions (0°, 90°, 180°, 270°) are consistent, eliminating the systematic errors caused by repeated clamping and recalibration, and ensuring the comparability of multi-directional detection results.

[0095] Multi-directional detection implementation steps:

[0096] When implementing multi-directional detection:

[0097] S1 Structural separation: separating the torsional load applying structure 32 from the load transmitting structure 33 . Specifically, the operation is to loosen the sheathed connection between the connecting chuck 3331 and the torque wrench 321 , so that the connecting chuck 3331 can rotate freely.

[0098] S2 Direction Adjustment: Manually rotate the connecting chuck 3331 to reverse the orientation. Since the shaped load-bearing plate 331 has four load adjustment wheels 343 corresponding to the 0°, 90°, 180°, and 270° positions, the load adjustment plate 342 on the connecting chuck 3331 must be rotated to the position corresponding to the load adjustment wheel 343 in the desired orientation. For example, rotate 90° from the 0° position to the 90° position to ensure that the load adjustment plate 342 is correctly aligned with the load adjustment wheel 343 in the desired orientation.

[0099] S3 Structural reset: restore the connection state between the torsional load applying structure 32 and the load transmitting structure 33, and re-fit the connecting chuck 3331 and the torque wrench 321 to ensure that the connection is firm and reliable and can effectively transmit torque.

[0100] S4 Repeat the test: Repeat the load application and deformation measurement steps in the new orientation. Using the target deformation δa obtained in the first test as the displacement control reference, the torque adjustment mechanism 322 precisely controls the rotation angle of the torque wrench 321, causing the load adjustment wheel 343 to produce the same rolling displacement on the inclined surface. This applies the same radial load in the new orientation, ensuring consistency and comparability of the test data from multiple directions.

[0101] Circular operation: Repeat steps S1-S4 to complete the full range of strength testing in four directions (0°, 90°, 180°, 270°) in sequence, and obtain complete strength characteristic data of the composite cabin 01 under loads in different directions.

[0102] Example 2: Composite load synchronous application test device:

[0103] Overall structural composition

[0104] This embodiment improves upon Example 1 by enabling the simultaneous and rapid application of unidirectional and torsional loads, simulating the strength characteristics of a cabin under instantaneous combined loads such as impact. (See 2.) The testing apparatus primarily comprises: a shaped load-bearing plate 331, a torsional load transfer assembly 333, a load transfer column 341, a load adjustment plate 342, a load adjustment wheel 343, and a synchronous trigger mechanism. The connections between these components are the same as in Example 1.

[0105] Torsional load transfer path: The torsional load transfer assembly 333 maintains the same structure as in Example 1, including a connecting chuck 3331 and two torque plugs 3332. The torque plugs 3332 apply a torsional moment to the special-shaped load-bearing plate 331 by pushing the load-bearing surface 332, which is then transferred to the composite cabin 01.

[0106] Unidirectional load transfer path: The load transfer column 341 is mounted on the connecting chuck 3331, the load adjustment plate 342 is fixedly mounted on the end of the load transfer column 341, and the load adjustment wheel 343 is fixedly connected to the edge of the special-shaped load-bearing plate 331. Unlike Example 1, this embodiment applies a torsional torque to the special-shaped load-bearing plate 331 while also applying a unidirectional radial load to the special-shaped load-bearing plate 331.

[0107] Principle and process of synchronous load application:

[0108] All drawings, especially Figure 7 This embodiment achieves the simultaneous application of torsional and unidirectional loads by precisely adjusting the positions of the torque insert 3332 and the load adjustment plate 342. By adjusting the relative positions of the torque insert 3332 and the load adjustment plate 342 on the connecting chuck 3331, when the connecting chuck 3331 rotates, the torque insert 3332 simultaneously contacts the load-bearing surface 332 and the load adjustment plate 342 simultaneously contacts the load adjustment wheel 343 in the selected direction. Both load paths are activated simultaneously, achieving the simultaneous application of a combined load.

[0109] When the connecting chuck 3331 rotates by angle θ, the torque plug 3332 pushes on the load-bearing surface 332, generating a torsional moment T. The load adjustment plate 342 pushes the load adjustment wheel 343 along the inclined surface, generating a radial load F. These two loads are simultaneously transmitted to the composite cabin 01. During a real collision, the cabin 01 typically experiences both a torsional component (torsional moment caused by eccentric impact point or impact angle) and a radial component (direct radial impact force). This embodiment simulates the combined force characteristics of a collision by simultaneously applying these two load components.

[0110] Load control and rapid application:

[0111] The ratio of torsional load T to radial load F can be adjusted by adjusting the bevel angle α of the load adjustment plate 342, adjusting the geometric ratio of the torque insert 3332 to the load adjustment plate 342, and controlling the rotational amplitude of the connecting chuck 3331. The load ratio is calculated as follows: T / F = k (impact load characteristic coefficient).

[0112] To simulate the transient characteristics of an impact, this embodiment employs a rapid drive mechanism to apply load. Specifically, a pneumatic or hydraulic rapid actuator drives the connecting chuck 3331, achieving a load rise time of ≤10ms and an adjustable peak load duration of 10-50ms. By controlling the operating characteristics of the drive mechanism, rapid loading (simulating the transient characteristics of an impact), load retention (maintaining the load for a set time), and rapid unloading (avoiding secondary impact effects) are achieved.

[0113] Direction selection and technical advantages:

[0114] In this embodiment, the position of the load transfer post 341 can be adjusted to apply a unidirectional load in the 0° direction (simulating a frontal impact), 90° (simulating a side impact), 180° (simulating a rear impact), or 270° (simulating a side impact). Load application in different directions can be achieved by repositioning the load transfer post 341 and the load adjustment plate 342, or by using a rotatable mounting mechanism for the load transfer post 341.

[0115] Compared with Example 1, this embodiment has the following technical advantages: real impact simulation (simultaneous application of torsional load and unidirectional load to accurately simulate the composite force characteristics of the impact condition); load synchronization (natural synchronization of the two loads is achieved through position adjustment, and the structure is simple and reliable); rapid response capability (the load rise time can be controlled at the millisecond level to meet the rapid characteristic requirements of the impact load); load controllability (through geometric parameter adjustment, the load ratio can be controlled to adapt to different impact conditions); simplified structure (compared with complex synchronization mechanisms, the synchronization function can be achieved only through position adjustment).

[0116] This embodiment is particularly suitable for: verification of the impact resistance of UAV cabins, damage assessment due to drops and impacts during transportation, failure mode research of composite materials under combined impact loads, safety assessment of cabin structures under accidental impact conditions, and simulation verification of impact load conditions during the product design phase.

Claims

1. A multi-link strength testing device for detecting the strength characteristics of a composite material cabin (01), characterized in that: include: A connecting mechanism for fixedly connecting the composite cabin (01) to the testing device; A load applying mechanism for applying a load to a composite material cabin (01), comprising: a torsional load applying structure (32) for applying a torsional load to the composite material cabin (01); a load transferring structure (33) for transferring the load to the composite material cabin (01); and a multi-linkage testing structure (34) for converting torsional motion into a radial load. The load transfer structure (33) comprises: a special-shaped load-bearing plate (331) having at least two opposite load-bearing surfaces (332) on its side wall; a torsional load transfer assembly (333) comprising a connecting chuck (3331) and two torque plug-ins (3332), wherein the torque plug-ins (3332) are mounted at both ends of the diameter of the connecting chuck (3331) and can respectively contact the two load-bearing surfaces (332) to generate thrust; The multi-linkage test structure (34) comprises: a load transfer column (341) provided on the connection chuck (3331) and facing the special-shaped load-bearing plate (331); a load adjustment plate (342) having an inclined surface and fixedly provided at the end of the load transfer column (341); and a load adjustment wheel (343) fixedly connected to the edge of the special-shaped load-bearing plate (331), wherein the arc surface of the load adjustment wheel forms tangential contact with the inclined surface of the load adjustment plate (342). By controlling the rotation of the torsional load transfer assembly (333), it is possible to selectively achieve: A pure torsional load application mode when the torque plug-in (3332) contacts the load-bearing surface (332) and the load adjustment plate (342) is separated from the load adjustment wheel (343), or a conversion mode in which torsional motion is converted into a radial load when the torque plug-in (3332) is separated from the load-bearing surface (332) and the load adjustment plate (342) is in contact with the load adjustment wheel (343), thereby realizing multi-directional load detection of the composite cabin (01).

2. The multiple linkage strength testing device according to claim 1, characterized in that: The special-shaped load-bearing plate (331) has at least two arc-shaped side walls (3311) that are opposite and convex outward and are arranged in a centrally symmetrical manner. The load-bearing surface (332) is arranged at the head and tail of each arc-shaped side wall (3311). A plurality of load adjustment wheels (343) are arranged thereon.

3. The multiple linkage strength testing device according to claim 1, characterized in that: The torsional load applying structure (32) comprises a torque wrench (321), and the torque wrench (321) is driven by a square head.

4. The multiple linkage strength testing device according to claim 2, characterized in that: The multi-link test structure has a dual-mode working mode: Direct torsion mode: the torque plug-in (3332) is located at the bottom end of the arc-shaped side wall (3311), the load adjustment plate (342) and the load adjustment wheel (343) remain separated, and a pure torsion moment is applied to the special-shaped load-bearing plate (331) only through the contact between the torque plug-in (3332) and the load-bearing surface (332); Torsion-radial conversion mode: the torque plug-in (3332) is separated from the force-bearing surface (332), the inclined surface of the load adjustment plate (342) and the load adjustment wheel (343) are in tangential contact, and the load adjustment wheel (343) rolls along the inclined surface to convert the torsional motion into radial extrusion force.

5. The multiple linkage strength testing device according to claim 1, characterized in that: The torsional load applying structure (32) further comprises a torque adjusting structure (322), wherein the torque adjusting structure (322) adopts one of a motor-driven linear motion module, a pneumatic linear actuator, a hydraulic cylinder driving device, a manual screw adjustment mechanism or a servo electric cylinder.

6. A composite load synchronous application test device for simulating the strength characteristics of a composite cabin under composite loads, characterized in that: include: A connecting mechanism for fixedly connecting the composite cabin (01) to the testing device; A load applying mechanism for applying a load to a composite material cabin (01), comprising: a torsional load applying structure (32) for applying a torsional load to the composite material cabin (01); a load transferring structure (33) for transferring the load to the composite material cabin (01); and a multi-linkage testing structure (34) for converting torsional motion into a radial load. The load transfer structure (33) comprises: a special-shaped load-bearing plate (331) having at least two opposite load-bearing surfaces (332) on its side wall; a torsional load transfer assembly (333) comprising a connecting chuck (3331) and two torque plug-ins (3332), wherein the torque plug-ins (3332) are mounted at both ends of the diameter of the connecting chuck (3331) and can respectively contact the two load-bearing surfaces (332) to generate thrust; The multiple linkage test structure (34) comprises: a load transfer column (341) provided on the connection chuck (3331) and facing the special-shaped load-bearing plate (331); a load adjustment plate (342) having an inclined surface and fixedly provided at the end of the load transfer column (341); and a load adjustment wheel (343) fixedly connected to the edge of the special-shaped load-bearing plate (331). By adjusting the relative positions of the torque plug-in (3332) and the load adjustment plate (342) on the connecting chuck (3331), when the connecting chuck (3331) rotates, the torque plug-in (3332) contacts the force-bearing surface (332) and the load adjustment plate (342) also contacts the load adjustment wheel (343) in the selected direction. The two load paths are activated at the same time, thereby achieving the synchronous application of the torsional load and the radial load, and the load ratio can be adjusted by the geometric parameters.

7. The composite load synchronous application test device according to claim 6, characterized in that: The ratio of the torsional load to the radial load is adjusted by adjusting the bevel angle of the load adjustment plate (342), adjusting the geometrical size ratio of the torque plug (3332) and the load adjustment plate (342), and controlling the rotation amplitude of the connecting chuck (3331).

8. The composite load synchronous application test device according to claim 6, characterized in that: By adjusting the position of the load transfer column (341), a unidirectional load can be applied in the 0° direction, the 90° direction, the 180° direction or the 270° direction.

9. The composite load synchronous application test device according to claim 6, characterized in that: The test device also includes a fast driving mechanism, which has the functions of fast loading, load holding and fast unloading, and is used to simulate the instantaneous characteristics of the impact, maintain the load effect for a set time and avoid the influence of secondary impact.

10. The composite load synchronous application test device according to any one of claims 6 to 9, characterized in that: It also includes a deformation measuring device for real-time monitoring of the deformation characteristics of the composite material cabin (01) under the action of composite loads.

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