A missile full-missile double-station parallel reliability test device based on comprehensive stress

Abstract

The application provides a missile full-missile double-table parallel reliability test device based on comprehensive stress, and relates to the technical field of missile testing. The structure comprises a plurality of vibration test tables and a clamping mechanism, a test wall of the vibration test table is in abutment with a side wall of the missile along the length direction of the missile, and the clamping mechanism is arranged on one side of the vibration test table close to the missile; the feeding assembly comprises a lifting mechanism, a moving piece and a feeding piece, the feeding piece is used for placing the missile to be tested, the lifting mechanism can be lifted to above the test wall of the vibration test table, the moving piece can move the feeding piece to the position of the test wall of the vibration test table, and the lifting mechanism can be lowered to the position of the test wall of the vibration test table so that the side wall of the missile to be tested along the length direction is in abutment with the test wall. The device can greatly simplify the cumbersome steps of feeding and discharging during testing, thereby effectively improving the testing efficiency, and has the advantages of high automation degree.

Description

Technical Field

[0001] This specification relates to the field of missile testing technology, and more specifically, to a missile full-missile dual-stage parallel excitation reliability test device based on comprehensive stress. Background Technology

[0002] It is understood that among the many types of missiles, surface-to-air missiles and air-to-air missiles (missiles launched from aircraft to attack aerial targets) encounter one of the most complex vibration environments. From launch to flight, surface-to-air and air-to-air missiles experience dynamic environments such as "flight-on-hook vibration," and this complex external force is a significant factor contributing to missile launch failure. Since surface-to-air and air-to-air missiles generally undergo transportation, storage, and use stages throughout their lifespan, they are affected by various environmental factors, including temperature, humidity, and both inevitable and accidental vibrations and impacts. Among these, "flight-on-hook vibration" is the most concerning in terms of its severity and persistence. While a missile's parameters are normal when stationary, its performance cannot be predicted once launched. Therefore, an instrument capable of simulating the various dynamic environments a missile experiences after launch is needed. Vibration platforms serve as such simulation testing equipment.

[0003] Currently, existing equipment for missile testing involves multiple steps, including loading, clamping, testing, unclamping, and unloading. During testing, multiple missiles from each batch typically need to be sampled for testing, requiring a large number of missiles to be tested daily. The aforementioned steps are cumbersome, resulting in a significant reduction in testing efficiency. Summary of the Invention

[0004] The purpose of this specification is to provide a missile full-missile dual-stage parallel excitation reliability test device based on comprehensive stress, which can solve the problem.

[0005] The embodiments described in this specification are implemented as follows:

[0006] A missile full-missile dual-stage parallel excitation reliability test device based on comprehensive stress, used for testing missiles, includes test components and loading components;

[0007] The testing assembly includes several vibration test benches and a clamping mechanism. The test wall of the vibration test bench abuts against the side wall of the missile along its length. The clamping mechanism is located on the side of the vibration test bench closer to the missile.

[0008] The loading assembly includes a lifting mechanism, a moving part, and a loading part. The loading part is used to place the missile to be tested. The lifting mechanism can be raised to the test wall of the vibration test bench. The moving part can move the loading part to the position of the test wall of the vibration test bench. The lifting mechanism can be lowered to the position of the test wall of the vibration test bench so that the side wall of the missile to be tested along its length abuts against the test wall.

[0009] The embodiments described in this specification have at least the following advantages or beneficial effects:

[0010] Compared with existing technologies, this missile full-missile dual-stage parallel excitation reliability test device based on comprehensive stress, by setting up the aforementioned loading component, uses a lifting mechanism and moving parts to load and unload materials, which greatly simplifies the cumbersome loading and unloading steps during testing, thereby effectively improving testing efficiency. Moreover, by setting up the loading and testing components, the device can, during the vibration testing of one missile, simultaneously unload the previously tested missile and prepare to load the next missile to be tested. Therefore, the device has the advantages of high automation and high testing efficiency. Attached Figure Description

[0011] To more clearly illustrate the technical solutions of the embodiments of this specification, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this specification and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0012] Figure 1 This is a schematic diagram of the dual-stage parallel-excitation reliability test device for the entire missile based on comprehensive stress, as provided in this specification.

[0013] Figure 2 This is a schematic diagram illustrating the interaction between the test components and the feeding components provided in this manual.

[0014] Figure 3 This is a schematic diagram of the structure of the test components provided in this specification;

[0015] Figure 4 This is a structural diagram of the feeding assembly provided in this manual;

[0016] Figure 5 This is a schematic diagram showing the installation position of the lifting rack provided in this manual;

[0017] Figure 6 This is a schematic diagram illustrating the interaction between the control rack and control gear provided in this manual.

[0018] Figure 7 This is a schematic diagram showing the location of the temperature control unit provided in this manual.

[0019] Icons: 1. Test chamber; 2. Vibration test bench; 3. Support roller; 4. Clamping mechanism; 41. Rotating shaft; 42. Bending strip; 43. Clamping roller; 44. Limiting post; 5. Moving part; 61. First support part; 62. Second support part; 71. Lifting frame; 72. Feeding component; 73. Placement strip; 81. Drive motor; 83. Lifting rack; 91. Transmission rod; 92. Clamping gear; 93. Control gear; 94. Control rack; 10. Temperature control unit; 11. Humidity control unit. Detailed Implementation

[0020] To make the objectives, technical solutions, and advantages of the embodiments in this specification clearer, the technical solutions in the embodiments of this specification will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this specification, and not all embodiments. Generally, the components of the embodiments of this specification described and shown in the accompanying drawings can be arranged and designed in various different configurations.

[0021] Therefore, the following detailed description of the embodiments provided in the accompanying drawings is not intended to limit the scope of the claimed specification, but merely represents selected embodiments of the specification. All other embodiments obtained by those skilled in the art based on the embodiments in this specification without inventive effort are within the scope of protection of this specification.

[0022] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0023] In the description of the embodiments in this specification, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," indicating orientation or positional relationships, are based on the orientation or positional relationships shown in the accompanying drawings, or the orientation or positional relationships commonly used when the product is in use. These are used only for the convenience of describing this specification and for simplifying the description, and do not indicate or imply that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this specification. Furthermore, the terms "first," "second," and "third," etc., are used only for distinguishing descriptions and should not be construed as indicating or implying relative importance.

[0024] Furthermore, the use of terms such as "horizontal," "vertical," and "suspended" does not imply that the component must be absolutely horizontal or suspended, but rather that it can be slightly tilted. For example, "horizontal" simply means that its direction is more horizontal relative to "vertical," and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0025] In the description of the embodiments in this specification, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this specification according to the specific circumstances.

[0026] Please refer to Figures 1 to 7 The missile full-missile dual-stage parallel excitation reliability test device based on comprehensive stress provided in one embodiment of this specification is used to test missiles and mainly includes a test component and a loading component.

[0027] The test assembly includes several vibration test benches 2 and a clamping mechanism 4. The test wall of the vibration test bench 2 abuts against the side wall of the missile along its length direction, and the clamping mechanism 4 is disposed on the side of the vibration test bench 2 close to the missile.

[0028] The loading assembly includes a lifting mechanism, a moving part, and a loading part 72. The loading part 72 is used to place the missile to be tested. The lifting mechanism can be raised to the test wall of the vibration test bench 2. The moving part can move the loading part 72 to the position of the test wall of the vibration test bench 2. The lifting mechanism can be lowered to the position of the test wall of the vibration test bench 2 so that the side wall of the missile to be tested along its length direction abuts against the test wall.

[0029] Specifically, by setting up the aforementioned loading assembly, which uses a lifting mechanism and moving parts to load and unload materials, the cumbersome loading and unloading steps during testing can be greatly simplified, thereby effectively improving testing efficiency. Furthermore, by incorporating both the loading and testing assemblies, the device allows the loading assembly to unload the previously tested missile and prepare for loading the next missile during vibration testing. Therefore, the device boasts advantages in both high automation and high testing efficiency.

[0030] In this embodiment, the testing assembly includes a first vibration test bench 2 and a second vibration test bench 2. The first vibration test bench 2 and the second vibration test bench 2 are spaced apart along the length direction of the missile, and the test walls of the first vibration test bench 2 and the second vibration test bench 2 respectively abut against the two ends of the missile along its length direction.

[0031] Specifically, the above-mentioned device is equipped with two vibration test benches 2. As can be seen, when monitoring, the missile can be placed on the two vibration test benches 2 to achieve the effect of simultaneous vibration testing on both benches.

[0032] In this embodiment, the above-mentioned device also includes a test chamber 1. The test component and the feeding component are disposed in the test chamber 1, and the vibration test bench 2 is fixed on the side wall of the test chamber 1 away from the missile. The test chamber 1 is also provided with a temperature control unit 10 and a humidity control unit 11, which can control the temperature and humidity in the test chamber 1 respectively.

[0033] It is evident that by combining two vibration test benches 2, a temperature control unit 10, and a humidity control unit 11, the actual test field can be simulated from multiple dimensions. That is, the comprehensive stress of multiple dimensions such as temperature, humidity, and vibration is used to replace the traditional single stress. It is clear that the above setup can greatly improve the realism of the test and achieve better simulation results.

[0034] In this embodiment, two curved bars 42 are symmetrically arranged at one end of the vibration test bench 2 near the missile. The two curved bars 42 cooperate to clamp the missile. A rotating shaft 41 is provided at the end of the curved bar 42 away from the missile. The rotating shaft 41 passes through the vibration test bench 2 along the length direction of the missile, and the two ends of the rotating shaft 41 are respectively connected to the fixed ends of the curved bars 42 located on both sides of the vibration test bench 2.

[0035] A transmission rod 91, a clamping gear 92, and a control gear 93 are provided between the two vibration test benches 2. The clamping gear 92 is sleeved on the transmission rod 91 and meshes with the control gear 93. The two ends of the transmission rod 91 are respectively connected to the opposite ends of the rotating shaft 41 provided on the two vibration test benches 2. The clamping gear 92 rotates under the drive of the control gear 93 to drive the transmission rod 91 to rotate. The transmission rod 91 can drive the rotating shaft 41 to rotate so that the bent bar 42 clamps or releases the missile.

[0036] In this embodiment, the bent bar 42 includes a first connecting part, a clamping part, and a second connecting part. The first connecting part and the second connecting part are convex in shape. The two ends of the clamping part are respectively connected to the ends of the first connecting part and the second connecting part that are closer to the missile. The ends of the first connecting part and the second connecting part that are farther away from the missile are respectively connected to the two ends of the rotating shaft 41. The gap width between the first connecting part and the second connecting part is adapted to the width of the vibration test bench 2. When the bent bar 42 formed by the cooperation of the first connecting part, the clamping part, and the second connecting part rotates about the rotating shaft 41, the vibration test bench 2 can be in the gap formed by the first connecting part and the second connecting part so as not to hinder the rotation of the bent bar 42.

[0037] In this embodiment, the clamping part is fitted with a clamping roller 43 to improve the clamping stability of the bent strip 42.

[0038] In this embodiment, the convex side of the two symmetrically arranged curved strips 42 is far away from the missile. The two symmetrically arranged curved strips 42 can cooperate to form a missile clamping area, further improving the stability of clamping the missile.

[0039] In this embodiment, a support roller 3 is embedded on the side of the vibration test bench 2 near the missile, and a rotating shaft is provided in the groove of the support roller embedded in the vibration test bench 2. The direction of the rotating shaft is consistent with the width direction of the vibration test bench 2. The rotating shaft can pass through the support roller along the length direction of the support roller. The two ends of the rotating shaft are respectively fixed in the through holes of the opposite side walls of the groove. It can be seen that the above arrangement can reduce the friction between the vibration test bench 2 and the missile during vibration testing, and at the same time, it can further improve the simulation realism of the real scene.

[0040] In this embodiment, one transmission rod 91 is provided for each bent bar 42, and two transmission rods 91 are provided for each of the two bent bars 42, namely the first transmission rod 91 and the second transmission rod 91. The first clamping gear 92 and the second clamping gear 92 are respectively sleeved on the first transmission rod 91 and the second transmission rod 91. The control gear 93 meshes with the first clamping gear 92 or the second clamping gear 92. When the first clamping gear 92 and the second clamping gear 92 are meshed, under the drive of the control gear 93, the first clamping gear 92 and the second clamping gear 92 rotate relative to each other, that is, rotate towards each other or rotate away from each other, thereby controlling the two bent bars 42 to move towards each other or rotate away from each other, and thus controlling the two bent bars 42 to clamp or release the missile.

[0041] In this embodiment, in order to enable the control gear 93 to mesh with the first clamping gear 92 or the second clamping gear 92, a lifting member is provided, and the control gear 93 is sleeved on the lifting member so that the setting height of the control gear 93 is adapted to the setting height of the first clamping gear 92 or the second clamping gear 92.

[0042] In this embodiment, the two corners of the vibration test platform located on the rotation path of the bending bar 42 are set as wedge surfaces or rounded corners to further avoid the bending bar 42 being obstructed by the vibration test platform, while also achieving the requirement of lightweight design.

[0043] In this embodiment, the two vibration test platforms are symmetrically arranged on the bottom wall of the test chamber 1.

[0044] In this embodiment, a limit post 44 is provided on the rotation path of the curved strip 42 away from the missile. This method limits the opening gap between the two curved strips 42, thereby preventing large opposing rotation angles between the two curved strips 42, thus improving the control effect of the control gear 93 and reducing control difficulty.

[0045] In this embodiment, the movable component includes a first support portion 61, a second support portion 62, and a movable portion 5. The first support portion 61 is arranged in the same direction as the length direction of the missile. The two ends of the second support portion 62 are respectively connected to the first support portion 61 and the movable portion 5. The movable portion 5 can reciprocate linearly along the length direction of the missile, and the second support portion 62 can reciprocate linearly under the action of the movable portion 5.

[0046] In this embodiment, a slide rail is provided on the bottom wall of the test chamber 1. The length direction of the slide rail is consistent with the length direction of the missile being held. The moving part 5 is slidably connected to the slide rail. That is, the moving part 5 moves back and forth in a straight line along the slide rail, which can drive the second support part 62 to move back and forth in a straight line along the slide rail, thereby driving the first support part 61 to move back and forth in a straight line.

[0047] The second support portion 62 is L-shaped, and there are two of them. The two second support portions 62 are spaced apart, and the short horizontal part of the L-shape is fixedly connected to the side wall of the first support portion 61 away from the moving part 5.

[0048] In this embodiment, the lifting mechanism includes a lifting frame 71. The first support portion 61 is provided with a lifting through hole. One end of the lifting frame 71 passes through the lifting through hole and is connected to the loading component 72. A control rack 94 is provided on the side of the loading component 72 away from the first support portion 61. The control rack 94 can engage with the control gear 93 when the loading component 72 moves between the two vibration test benches 2. The lifting frame 71 drives the control rack 94 to descend to the side away from the missile. Under the action of the lifting frame 71 descending, the control rack 94 drives the control gear 93 to rotate, thereby driving the curved bar 42 to clamp the missile to be tested. In this embodiment, the lifting frame 71 includes a vertical part and a horizontal part. One end of the vertical part is connected to the horizontal part, and the other end of the vertical part passes through the lifting through hole and is connected to the loading component 72.

[0049] In this embodiment, the lifting frame 71 has two vertically spaced sections, that is, the two ends of the horizontal section are connected to the two vertical sections respectively. When the lifting frame 71 moves up and down, the horizontal section can prevent stress from concentrating at the position of the lifting through hole (that is, when it descends to the maximum extent, the horizontal section can distribute the weight of the missile to the first support section 61), and also plays the role of limiting the descent height.

[0050] In this embodiment, when the loading component 72 rises above the height of the vibration test bench 2, the moving part 5 can drive the loading component 72 to move above the vibration test bench 2. At this time, the lifting frame 71 descends. When the loading component 72 descends above the clamping gear 92, and the two sections of the missile are placed on the support rollers, the control rack 94 on the side of the loading component 72 away from the first support part 61 meshes with the control gear 93. The lifting frame 71 continues to descend, and the control rack 94 can drive the control gear 93 to rotate, thereby driving the bent strip 42 to rotate, so that the two bent strips 42 rotate. 2. The missile is clamped by the opposite rotation. After the test is completed, the lifting frame 71 rises in the direction of the first support part 61. The control rack 94 drives the control gear 93 to rotate again (in the opposite direction of rotation during descent), thereby driving the bent bar 42 to rotate. The two bent bars 42 rotate in opposite directions to release the missile. At this time, the lifting frame 71 continues to rise in the direction of the first support part 61. The missile is lifted by the loading part 72. The moving part 5 moves the loading part 72 in a straight line. Then, the unloading step is completed by the descent of the lifting frame 71.

[0051] In this embodiment, a drive motor 81 is provided on the first support part 61, and a lifting rack 83 is provided on the vertical part. The lifting rack 83 meshes with the drive gear of the drive motor 81, and the vertical part moves up and down along the height direction of the vibration test bench 2 under the meshing action of the drive motor 81 and the lifting rack 83.

[0052] In this embodiment, the lifting rack 83 is set in the same direction as the vertical part.

[0053] In this embodiment, a drive motor 81 is fixedly installed on the side of the first support 61 near the horizontal part. The drive motor 81 drives the gear to rotate under the action of the driving force. Through the meshing action of the gear and the lifting rack 83, the vertical part is driven to rise and fall.

[0054] In this embodiment, the first support 61 may be provided with two, three or more lifting frames 71, and a number of drive motors 81 are provided accordingly.

[0055] In this embodiment, the feeding component 72 is a horizontal frame shape, and the central hollow area of ​​the feeding component 72 can correspond to the position of the clamping gear 92.

[0056] In this embodiment, the feeding component 72 is arranged in the shape of a horizontal frame, which allows the missile to be placed horizontally and allows the position of the moving part 5 and the control rack 94 to be accurately observed through its central hollow area, thereby making the feeding position more accurate.

[0057] In this embodiment, the feeding component 72 is provided with a plurality of placement strips 73 on the side near the first support part 61. The placement strips 73 are preferably V-shaped or U-shaped to improve the placement stability of the missile to be tested (or the missile to be unloaded).

[0058] In this embodiment, the mounting position of the loading component 72 is adapted to the mounting position of the vibration test platform, that is, both the loading component 72 and the vibration test platform are located in the length direction of the held missile.

[0059] The above are merely preferred embodiments of this specification and are not intended to limit this specification. Various modifications and variations can be made to this specification by those skilled in the art. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of this specification should be included within the scope of protection of this specification.

Claims

1. A missile full-missile dual-stage parallel-excitation reliability test device based on comprehensive stress, used for testing missiles, characterized in that, Includes testing components and loading components; The test assembly includes a vibration test bench and a clamping mechanism. The test wall of the vibration test bench abuts against the side wall of the missile along its length, and the clamping mechanism is located on the side of the vibration test bench closer to the missile. The loading assembly includes a lifting mechanism, a moving part, and a loading part. The loading part is used to place the missile to be tested. The lifting mechanism can be raised to the test wall of the vibration test bench. The moving part can move the loading part to the position of the test wall of the vibration test bench. The lifting mechanism can be lowered to the position of the test wall of the vibration test bench so that the side wall of the missile to be tested along its length abuts against the test wall. The testing assembly includes a first vibration test bench and a second vibration test bench, which are spaced apart along the length of the missile. The test walls of the first vibration test bench and the second vibration test bench respectively abut against the two ends of the missile along its length. The vibration test bench is symmetrically provided with two curved bars at one end near the missile. The two curved bars cooperate to clamp the missile. A rotating shaft is provided at the end of the curved bar away from the missile. The rotating shaft passes through the vibration test bench along the length of the missile, and the two ends of the rotating shaft are respectively connected to the fixed ends of the curved bars located on both sides of the vibration test bench. A transmission rod, a clamping gear, and a control gear are provided between the two vibration test benches. The clamping gear is sleeved on the transmission rod and meshes with the control gear. The two ends of the transmission rod are respectively connected to the opposite ends of the rotating shafts of the two vibration test benches. The clamping gear rotates under the drive of the control gear to drive the transmission rod to rotate. The transmission rod can drive the rotating shaft to rotate so that the bent bar clamps or releases the missile. The movable component includes a first support part, a second support part, and a movable part. The first support part is arranged in the same direction as the length direction of the missile. The two ends of the second support part are respectively connected to the first support part and the movable part. The movable part can reciprocate linearly along the length direction of the missile, and the second support part can reciprocate linearly under the action of the movable part. The lifting mechanism includes a lifting frame. The first support portion is provided with a lifting through hole. One end of the lifting frame passes through the lifting through hole and is connected to the loading component. A control rack is provided on the side of the loading component away from the first support portion. The control rack can mesh with the control gear when the loading component moves between the two vibration test benches. The lifting frame drives the control rack to descend to the side away from the missile. Under the action of the lifting frame descending, the control rack drives the control gear to rotate so as to drive the curved bar to clamp the missile to be tested.

2. The missile full-missile dual-stage parallel-excitation reliability test device based on comprehensive stress according to claim 1, characterized in that, A limit post is provided on the curved bar away from the rotation path of the missile.

3. The missile full-missile dual-stage parallel-excitation reliability test device based on comprehensive stress according to claim 1, characterized in that, The lifting frame includes a vertical part and a horizontal part. One end of the vertical part is connected to the horizontal part, and the other end of the vertical part passes through the lifting through hole and is connected to the loading component.

4. The missile full-missile dual-stage parallel-excitation reliability test device based on comprehensive stress according to claim 3, characterized in that, A drive motor is provided on the first support part, and a lifting rack is provided on the vertical part. The lifting rack meshes with the drive gear of the drive motor, and the vertical part moves up and down along the height direction of the vibration test bench under the meshing action of the drive motor and the lifting rack.

5. The missile full-missile dual-stage parallel-excitation reliability test device based on comprehensive stress according to claim 1, characterized in that, The feeding component is a horizontal frame shape, and the central hollow area of ​​the feeding component corresponds to the location of the clamping gear.

6. The missile full-missile dual-stage parallel-excitation reliability test device based on comprehensive stress according to claim 1, characterized in that, It also includes a test chamber, in which the test components and the feeding components are disposed, and the vibration test bench is fixed to the side wall of the test chamber on the side away from the missile. The test chamber is also equipped with a temperature control unit and a humidity control unit, which can control the temperature and humidity inside the test chamber respectively.

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