Missile whole-missile double-platform shunt excitation reliability test device based on comprehensive stress

Abstract

The invention provides a missile full-missile double-platform shunt excitation reliability testing device based on comprehensive stress, and relates to the technical field of missile testing. The structure comprises a plurality of vibration test tables and clamping mechanisms, the test walls of the vibration test tables abut against the side wall of the missile in the length direction, and the clamping mechanisms are arranged on the sides, close to the missile, of the vibration test tables; the feeding assembly comprises a lifting mechanism, a moving part and a feeding part, the feeding part is used for placing a to-be-tested missile, the lifting mechanism can be lifted to the position above the test wall of the vibration test bed, and the moving part can move the feeding part to the position where the test wall of the vibration test bed is located; the lifting mechanism can descend to the position of the test wall of the vibration test bench so that the side wall of the to-be-tested missile in the length direction can abut against the test wall. The device can greatly simplify the tedious steps of feeding, discharging and the like in the testing process, so that the testing efficiency is effectively improved, and the device has the advantage of being high in automation degree.

Description

Technical Field

[0001] The present specification relates to the field of missile testing technology, and in particular to a missile full-missile dual-stage parallel excitation reliability test device based on comprehensive stress. Background Art

[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) are among the missiles that encounter the most complex vibration environment. From launch to flight, surface-to-air missiles and air-to-air missiles will encounter dynamic environments such as "flying vibration", and this complex external force is one of the important factors causing missile launch failures; since surface-to-air missiles and air-to-air missiles generally go through transportation, storage and use stages during their entire life cycle from leaving the factory to launching to the target, they will be affected by various environmental factors during these stages, in addition to factors such as temperature, humidity and heat, there are also inevitable and accidental vibrations, impacts and other dynamic forces, and the severity and persistence of "flying vibration" are the most worthy of attention; if the missile is stationary, its various parameters are normal, once launched, it is impossible to predict whether the performance is still good, and an instrument that can simulate the various dynamic environments that the missile is subjected to after launch is needed. The role played by the vibration platform is a kind of simulation test equipment;

[0003] At present, the equipment used for missile testing in the prior art includes multiple steps such as loading, clamping, testing, unclamping, unloading, etc. During the test, usually multiple samples of each batch of missiles need to be tested, and a large number of missiles need to be tested every day. The above steps are cumbersome to operate, resulting in a significant reduction in test efficiency.

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

[0005] The embodiments of 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, including a test component and a feeding component;

[0007] The test assembly includes a plurality of vibration test benches and a clamping mechanism, wherein a test wall of the vibration test bench abuts against a side wall of the missile along its length direction, and the clamping mechanism is arranged on a side of the vibration test bench close 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 where the test wall of the vibration test bench is located. The lifting mechanism can be lowered to the position where the test wall of the vibration test bench is located so that the side wall of the missile to be tested along its length direction abuts against the test wall.

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

[0010] Compared with the prior art, the missile full-missile dual-stage parallel excitation reliability test device based on comprehensive stress can greatly simplify the cumbersome steps of loading and unloading during testing by setting the above-mentioned loading assembly, and using the lifting mechanism and the moving parts to move and load materials, thereby effectively improving the test efficiency. Moreover, by setting the loading assembly and the test assembly, the above-mentioned device can also unload the missile that has completed the previous test and prepare for loading the next missile to be tested during the vibration test of a missile. It can be seen that the above-mentioned device has the advantages of high automation and high test efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] In order to more clearly illustrate the technical solutions of the embodiments of this specification, the drawings required for use in the embodiments will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present specification and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without paying any creative work.

[0012] Figure 1 The schematic diagram of the structure of the missile full-missile dual-station parallel excitation reliability test device based on comprehensive stress provided in this manual;

[0013] Figure 2 A schematic diagram of the cooperation between the test assembly and the feeding assembly provided in this manual;

[0014] Figure 3 A schematic diagram of the structure of the test components provided for this specification;

[0015] Figure 4 A schematic diagram of the structure of the feeding assembly provided for this manual;

[0016] Figure 5 A schematic diagram of the location of the lifting rack provided in this manual;

[0017] Figure 6 A schematic diagram of the coordination of the control rack and the control gear provided in this manual;

[0018] Figure 7 This is a schematic diagram of the setting position 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 bar; 43. Clamping roller; 44. Limiting column; 5. Moving part; 61. First supporting part; 62. Second supporting part; 71. Lifting frame; 72. Loading part; 73. Placing bar; 81. Driving 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 DESCRIPTION

[0020] In order to make the purpose, technical solutions and advantages of the embodiments of this specification more clear, the technical solutions in the embodiments of this specification will be clearly and completely described below in conjunction with the drawings in the embodiments of this specification. Obviously, the described embodiments are part of the embodiments of this specification, not all of the embodiments. Generally, the components of the embodiments of this specification described and shown in the drawings here can be arranged and designed in various different configurations.

[0021] Therefore, the following detailed description of the embodiments of the present specification provided in the accompanying drawings is not intended to limit the scope of the present specification claimed for protection, but merely represents selected embodiments of the present specification. Based on the embodiments in the present specification, all other embodiments obtained by ordinary technicians in the field without creative work are within the scope of protection of the present specification.

[0022] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, it does not need to be further defined and explained in the subsequent drawings.

[0023] In the description of the embodiments of this specification, it should be noted that if the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inside", "outside", etc. appear, the orientation or position relationship indicated is based on the orientation or position relationship shown in the drawings, or the orientation or position relationship in which the product of this specification is usually placed when used. It is only for the convenience of describing this specification and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore cannot be understood as a limitation on this specification. In addition, if the terms "first", "second", "third", etc. appear, they are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0024] In addition, the use of terms such as "horizontal", "vertical", and "overhanging" does not mean that the components must be absolutely horizontal or overhanging, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0025] In the description of the embodiments of this specification, it is also necessary to explain that, unless otherwise clearly specified and limited, the words "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be fixedly connected, detachably connected, or integrally connected; it can be mechanically connected or electrically connected; it can be directly connected, or indirectly connected through an intermediate medium, or it can be internal communication between two components. For ordinary technicians in this field, the specific meanings of the above terms in this specification can be understood according to specific circumstances.

[0026] Please refer to Figures 1 to 7 , a missile full-missile dual-station 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 feeding component;

[0027] The test assembly includes a plurality of vibration test benches 2 and a clamping mechanism 4, wherein 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 arranged on a 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 table 2. The moving part can move the loading part 72 to the position of the test wall of the vibration test table 2. The lifting mechanism can be lowered to the position of the test wall of the vibration test table 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 the above-mentioned loading assembly, the lifting mechanism and the moving part cooperate to move and load and unload, which can greatly simplify the cumbersome steps of loading and unloading during testing, thereby effectively improving the test efficiency. Moreover, by setting the loading assembly and the test assembly, the above-mentioned device can unload the missile that has completed the previous test and prepare for loading the next missile to be tested during the vibration test of a missile. It can be seen that the above-mentioned device has the advantages of high automation and high test efficiency.

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

[0031] Specifically, the above device is provided with two vibration test benches 2. It can be seen that during monitoring, the missile can be placed on the two vibration test benches 2 to achieve the effect of performing vibration tests on both benches in parallel.

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

[0033] It can be seen that by setting up 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 traditional single stress is replaced by the comprehensive stress of multiple dimensions such as temperature, humidity and vibration. It can be seen that the above setting method can greatly improve the authenticity of the test and achieve a better simulation effect.

[0034] In this embodiment, two curved bars 42 are symmetrically arranged at one end of the vibration test platform 2 close to the missile, and the two curved bars 42 cooperate to clamp the missile, and a rotating shaft 41 is arranged at one end of the curved bar 42 away from the missile, and the rotating shaft 41 penetrates the vibration test platform 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 bar 42 located on both sides of the vibration test platform 2;

[0035] A transmission rod 91, a clamping gear 92 and a control gear 93 are arranged between the two vibration test platforms 2. The clamping gear 92 is sleeved on the outside of the transmission rod 91, and the clamping gear 92 is engaged with the control size. The two ends of the transmission rod 91 are respectively connected to the opposite ends of the rotating shaft 41 arranged on the two vibration test platforms 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 bending bar 42 clamps or releases the missile.

[0036] In this embodiment, the above-mentioned 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 close to the missile, and the ends of the first connecting part and the second connecting part away from the missile are respectively connected to the two ends of the rotating shaft 41. The width of the gap between the first connecting part and the second connecting part is adapted to the width of the above-mentioned vibration test platform 2. When the bent bar 42 formed by the first connecting part, the clamping part and the second connecting part rotates around the rotating shaft 41, the above-mentioned vibration test platform 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 above-mentioned bent bar 42.

[0037] In this embodiment, a clamping roller 43 is disposed on the outer cover of the clamping portion to enhance the clamping stability of the bent bar 42 .

[0038] In this embodiment, the convex side of the two symmetrically arranged curved bars 42 is away from the missile, and the two symmetrically arranged curved bars 42 can cooperate to form a clamping area for the missile, 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 platform 2 close to the missile, and a rotating shaft is provided in the groove in which the support roller is embedded in the vibration test platform 2. The setting direction of the rotating shaft is consistent with the width direction of the vibration test platform 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 on the opposite side walls of the groove. It can be seen that the above-mentioned setting method can reduce the friction between the vibration test platform 2 and the missile during the vibration test, and at the same time can further improve the simulation reality of the real scene.

[0040] In this embodiment, one transmission rod 91 is correspondingly arranged for one bent bar 42, and two transmission rods 91 are correspondingly arranged for two bent bars 42, namely, a first transmission rod 91 and a second transmission rod 91. A first clamping gear 92 and a second clamping gear 92 are correspondingly sleeved on the first transmission rod 91 and the second transmission rod 91. The control gear 93 is meshed with the first clamping gear 92 or the second clamping gear 92, and the first clamping gear 92 and the second clamping gear 92 are meshed. At this time, 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 achieving the effect of controlling the two bent bars 42 to move towards each other or rotate away from each other, and then achieving the effect of controlling the two bent bars 42 to clamp or release the missile.

[0041] In this embodiment, in order to make the control gear 93 mesh with the first clamping gear 92 or the second clamping gear 92, a lifting member is provided, and the above-mentioned control gear 93 is mounted on the lifting member so that the setting height of the control gear 93 is compatible with 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 curved bar 42 are configured as wedge surfaces or rounded corners to further prevent the curved bar 42 from being obstructed by the vibration test platform while meeting the requirement of lightweight.

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

[0044] In this embodiment, a limit post 44 is provided on the rotation path of the curved strip 42 away from the missile. In this way, the loose gap between the two curved strips 42 can be limited, thereby preventing the two curved strips 42 from rotating at a large angle away from each other, thereby enhancing the control function of the control gear 93 and reducing the control difficulty.

[0045] In this embodiment, the movable part includes a first supporting part 61, a second supporting part 62 and a movable part 5. The setting direction of the first supporting part 61 is consistent with the length direction of the missile. The two ends of the second supporting part 62 are respectively connected to the first supporting part 61 and the movable part 5. The movable part 5 can move back and forth in a straight line along the length direction of the missile, and the second supporting part 62 can move back and forth in a straight line under the action of the movable part 5.

[0046] In this embodiment, a slide rail is correspondingly arranged on the bottom wall of the test box 1, and the length direction of the above-mentioned slide rail is consistent with the length direction of the clamped missile. The above-mentioned moving part 5 is slidably connected with the above-mentioned slide rail, that is, the above-mentioned moving part 5 reciprocates linearly along the direction of the slide rail, which can drive the second support part 62 to reciprocate linearly along the direction of the slide rail, thereby driving the above-mentioned first support part 61 to reciprocate linearly.

[0047] The second supporting portion 62 is L-shaped, and there are two second supporting portions 62 . The two second supporting portions 62 are arranged at intervals, and the short horizontal portion of the L-shape is fixedly connected to the side wall of the first supporting portion 61 away from the moving portion 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 member 72, and a control rack 94 is provided on the side of the loading member 72 away from the first support portion 61, and the control rack 94 can mesh with the control gear 93 when the loading member 72 moves between the two vibration test tables 2, and the lifting frame 71 drives the control rack 94 to descend to the side away from the missile, and the control rack 94 drives the control gear 93 to rotate under the descending action of the lifting frame 71 to drive the curved bar 42 to clamp the missile to be tested. In this embodiment, the lifting frame 71 includes a vertical portion and a horizontal portion, one end of the vertical portion is connected to the horizontal portion, and the other end of the vertical portion passes through the lifting through hole and is connected to the loading member 72.

[0049] In this embodiment, the above-mentioned lifting frame 71 has two vertical parts arranged at intervals, that is, the two ends of the horizontal part are respectively connected to the two vertical parts. When the above-mentioned lifting frame 71 is lifted and lowered, the setting of the horizontal part can avoid stress concentration at the position of the lifting through hole (that is, when it is lowered to the maximum limit, the horizontal part can share the gravity of the missile to the first support part 61), and at the same time it also plays a role in limiting the descending height.

[0050] In this embodiment, when the above-mentioned loading piece 72 is raised to a height above the vibration test bench 2, the moving part 5 can drive the loading piece 72 to move to the top of the vibration test bench 2. At this time, the lifting frame 71 descends. When the loading piece 72 descends to the top of the clamping gear 92, the two sections of the missile are placed on the supporting rollers. The control rack 94 provided on the side of the loading piece 72 away from the first supporting part 61 is meshed with the control gear 93, and the lifting frame 71 continues to descend. The control rack 94 can drive the control gear 93 to rotate, thereby driving the bending bar 42 to rotate, so that the two bending bars 4 2 rotates towards each other to clamp the missile. After the test is completed, the lifting frame 71 rises in the direction of the first support portion 61, and the control rack 94 drives the control gear 93 to rotate again (in the opposite direction of rotation when descending), thereby driving the curved bars 42 to rotate, so that the two curved 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 portion 61, and the missile is lifted by the loading member 72. The loading member 72 is driven to move linearly by the movement of the moving portion 5, and then the lifting frame 71 is lowered to complete the unloading step.

[0051] In this embodiment, a driving motor 81 is provided on the first supporting portion 61, and a lifting rack 83 is provided on the vertical portion. The lifting rack 83 is meshed with the driving gear of the driving motor 81. The vertical portion is lifted and moved along the height direction of the vibration test table 2 under the meshing action of the driving motor 81 and the lifting rack 83.

[0052] In this embodiment, the arrangement direction of the lifting rack 83 is consistent with the arrangement direction of the vertical portion.

[0053] In this embodiment, a driving motor 81 is fixedly provided on one side of the first supporting portion 61 close to the horizontal portion. The driving motor 81 drives the gear to rotate under the action of the driving force, and drives the vertical portion to rise and fall through the meshing action of the gear and the lifting rack 83.

[0054] In this embodiment, two, three or more lifting frames 71 may be disposed on the first supporting portion 61 , and a plurality of driving motors 81 may be disposed correspondingly.

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

[0056] In this embodiment, the above-mentioned loading member 72 is arranged in the form of a horizontal frame, which can not only enable the missile to be placed horizontally, but also enable the position of the moving part 5 and the control rack 94 to be accurately observed through its central hollow area, thereby making the loading position more accurate.

[0057] In this embodiment, a plurality of placement bars 73 are disposed on one side of the loading member 72 close to the first support portion 61. The placement bars 73 may preferably be V-shaped or U-shaped to enhance the placement stability of the missile to be tested (or the missile to be unloaded).

[0058] In this embodiment, the setting position of the above-mentioned feeding member 72 is matched with the setting position of the above-mentioned vibration test platform, that is, the above-mentioned feeding member 72 and the above-mentioned vibration test platform are both located in the length direction of the clamped missile.

[0059] The above are only preferred embodiments of this specification and are not intended to limit this specification. For those skilled in the art, this specification may have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of this specification shall be included in the protection scope 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: Including test components and feeding components; The test assembly includes a plurality of vibration test benches and a clamping mechanism, wherein a test wall of the vibration test bench abuts against a side wall of the missile along its length direction, and the clamping mechanism is arranged on a side of the vibration test bench close 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 where the test wall of the vibration test bench is located. The lifting mechanism can be lowered to the position where the test wall of the vibration test bench is located so that the side wall of the missile to be tested along its length direction abuts against the test wall.

2. The missile full-projectile dual-stage parallel excitation reliability test device based on comprehensive stress according to claim 1 is characterized in that: The test assembly includes a first vibration test bench and a second vibration test bench, wherein the first vibration test bench and the second vibration test bench are spaced apart along the length direction of the missile, and the test walls of the first vibration test bench and the second vibration test bench are respectively abutted against two ends of the missile along the length direction thereof.

3. The missile full-projectile dual-stage parallel excitation reliability test device based on comprehensive stress according to claim 2 is characterized in that: The vibration test bench is symmetrically provided with two curved bars at one end close to the missile, and the two curved bars cooperate to clamp the missile, and a rotating shaft is provided at one end of the curved bar away from the missile, and the rotating shaft penetrates the vibration test bench along the length direction of the missile, and the two ends of the rotating shaft are respectively connected to the fixed ends of the curved bar located on both sides of the vibration test bench; A transmission rod, a clamping gear and a control gear are arranged between the two vibration test benches. The clamping gear is sleeved on the outside of the transmission rod, and the clamping gear is engaged with the control size. The two ends of the transmission rod are respectively connected to the opposite ends of the rotating shafts arranged on 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.

4. The missile full-projectile dual-stage parallel excitation reliability test device based on comprehensive stress according to claim 3 is characterized in that: A limiting column is arranged on the rotation path of the curved strip away from the missile.

5. The missile full-projectile dual-stage parallel excitation reliability test device based on comprehensive stress according to claim 3 is characterized in that: The movable part includes a first supporting part, a second supporting part and a movable part. The setting direction of the first supporting part is consistent with the length direction of the missile. The two ends of the second supporting part are respectively connected to the first supporting part and the movable part. The movable part can reciprocate linearly along the length direction of the missile. The second supporting part can reciprocate linearly under the action of the movable part.

6. The missile full-projectile dual-stage parallel excitation reliability test device based on comprehensive stress according to claim 5 is characterized in that: The lifting mechanism includes a lifting frame, the first supporting part 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 piece, a control rack is provided on the side of the loading piece away from the first supporting part, the control rack can engage with the control gear when the loading piece moves between the two vibration test tables, the lifting frame drives the control rack to descend to the side away from the missile, and the control rack drives the control gear to rotate under the descending action of the lifting frame to drive the bent bar to clamp the missile to be tested.

7. The missile full-projectile dual-stage parallel excitation reliability test device based on comprehensive stress according to claim 6 is characterized in that: The lifting frame comprises a vertical portion and a horizontal portion, one end of the vertical portion is connected to the horizontal portion, and the other end of the vertical portion passes through the lifting through hole and is connected to the loading member.

8. The missile full-projectile dual-stage parallel excitation reliability test device based on comprehensive stress according to claim 7 is characterized in that: The first supporting part is provided with a driving motor, the vertical part is provided with a lifting rack, the lifting rack is meshed with the driving gear of the driving motor, and the vertical part moves up and down along the height direction of the vibration test table under the meshing action of the driving motor and the lifting rack.

9. The missile full-projectile dual-stage parallel excitation reliability test device based on comprehensive stress according to claim 3 is characterized in that: The loading piece is in the shape of a horizontal frame, and the central hollow area of ​​the loading piece can correspond to the position of the clamping gear.

10. The missile full-projectile dual-stage parallel excitation reliability test device based on comprehensive stress according to claim 1 is characterized in that: It also includes a test box, in which the test assembly and the feeding assembly are arranged, and the vibration test bench is fixed to the side wall of the test box on a side away from the missile. A temperature control unit and a humidity control unit are also arranged in the test box, and the temperature control unit and the humidity control unit can respectively control the temperature and humidity in the test box.

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