Push rod linkage-based throwing device for spacecraft landing impact test

Abstract

The invention relates to the technical field of spacecraft ground test equipment, in particular to a launching device for a spacecraft landing impact test based on push rod linkage, and is characterized in that one end of a sling is connected with a lower hanging ring, the lower hanging ring is arranged at the bottom of a shell, a driving mechanism is mounted in an upper cavity, and a releasing mechanism is mounted in a lower cavity; the output end of the driving mechanism penetrates through the partition plate to be in transmission connection with the releasing mechanism, the positioning disc is clamped to the bottom of the releasing mechanism, the spacecraft is connected to the bottom of the positioning disc, the lower hanging ring is hinged to the positioning disc, the upper hanging ring is installed on the top of the shell, and the other end of the hanging belt is connected with the upper hanging ring. The releasing operation is more convenient, it is ensured that the releasing device can be repeatedly used, meanwhile, the symmetrical structural design is adopted, the mass center is arranged in the center of the shell, and the unstable conditions such as overturning, shaking or rotating in the releasing process of the spacecraft are avoided.

Description

Technical Field

[0001] The present invention relates to the technical field of spacecraft ground test equipment, and particularly to a spacecraft landing impact test delivery device based on push rod linkage. Background Art

[0002] In order to ensure that a spacecraft can withstand various forces during launch, operation, and return, and maintain structural integrity and normal functions, mechanical tests are carried out after each subsystem is assembled into a complete spacecraft. These tests include landing impact tests and vibration tests, etc. In order to verify the structural strength of the spacecraft, test the effectiveness of shock absorption devices and buffer materials, and evaluate the impact on electrical and electronic equipment during the landing impact process, the spacecraft conducts a landing impact simulation test on the ground after completing the whole spacecraft vibration, noise tests, and impact unlocking tests.

[0003] The landing impact simulation test requires transporting the spacecraft to the landing impact test site. Through the landing impact test sling, the spacecraft is lifted to a specified height and adjusted to the initial delivery attitude for testing. In order to achieve the goals of this test, the test equipment must have the following functions: 1) Hoisting function: being able to safely lift the spacecraft and fix it in an appropriate position; 2) Release function: being able to release the spacecraft smoothly and reliably in an extremely short instant; 3) Limiting function: ensuring that the test equipment does not touch the ground after releasing the spacecraft, thereby avoiding interfering with the test results; 4) Buffer function: after the spacecraft lands, the sling connected to the spacecraft still needs to fall a certain distance, and the sling needs to decelerate smoothly to a stop before colliding with the spacecraft to protect the spacecraft. Because during the process of the sling and the cabin body falling together until the cabin body lands, the sling and the cabin body fall freely, the influence of the sling on the connection of the cabin body during this process can be ignored. Until the cabin body lands, the cabin body is in a free fall state, which can ensure the accuracy and reliability of data collection. In order to achieve these functions and complete the landing impact test task, the delivery device needs to solve the following technical difficulties: 1) Quick unlocking and release: ensuring that the spacecraft can be vertically released instantaneously during the test; 2) Attitude stability: ensuring that the spacecraft does not shake or deviate during the hoisting process; 3) Maintaining a safe distance from the protrusions on the spacecraft cabin surface: avoiding unnecessary contact or interference between the sling and related components and the spacecraft; 4) Energy buffering: being able to absorb energy and decelerate the speed of the sling itself after unlocking; 5) Reusability: the unlocking device needs to be reusable. Through these measures, the actual landing situation can be simulated to the greatest extent, ensuring the effectiveness and reliability of the test results.

[0004] In the existing spacecraft landing impact tests, the sling installed on it often falls freely together with the spacecraft. This test method not only causes deviations in the test results, but also causes the sling fixed on the spacecraft to damage the spacecraft, making the test device unable to be reused.

[0005] Therefore, how to quickly release the spacecraft and avoid the sling from damaging the landed spacecraft, and how to provide a reusable impact test launching device have become technical problems that need to be solved urgently by those skilled in the art. Summary of the Invention

[0006] The present invention provides a launching device for a spacecraft landing impact test based on push rod linkage, aiming at the problems of how to quickly release the spacecraft, avoid the sling from damaging the landed spacecraft, and how to provide a reusable impact test launching device.

[0007] The present invention provides a launching device for a spacecraft landing impact test based on push rod linkage, including: Sling; Lower suspension ring, one end of the sling is connected to the lower suspension ring; Shell, the lower suspension ring is arranged at the bottom of the shell; the internal space of the shell is divided into an upper chamber and a lower chamber by a horizontally installed partition; Driving mechanism, installed in the upper chamber; Release mechanism, installed in the lower chamber, and the output end of the driving mechanism passes through the partition and is in transmission connection with the release mechanism; Positioning disk, clamped at the bottom of the release mechanism, the spacecraft is connected to the bottom of the positioning disk, and the lower suspension ring is hinged to the positioning disk; Upper suspension ring, installed at the top of the shell, and the other end of the sling is connected to the upper suspension ring.

[0008] In some embodiments, the driving mechanism includes: Motor, installed inside the upper chamber, and the output end of the motor passes through the partition and extends into the inside of the lower chamber; Threaded lead screw, installed inside the lower chamber, and the top is connected to the end of the motor extending into the inside of the lower chamber; Nut, threadedly connected to the threaded lead screw; Movable disk, fixedly installed at the bottom of the nut, and slidably connected to the inner wall of the shell.

[0009] In some embodiments, a vertically distributed chute is opened on the inner wall of the shell in the lower chamber, and a slider adapted to the chute is installed on the edge of the movable disk, and the slider is slidably connected to the chute.

[0010] In some embodiments, the release mechanism includes: Sliding tube, slidably connected to the inner wall of the lower chamber, and the top of the sliding tube abuts against the bottom surface of the movable disk; Sleeve, slidably sleeved on the end of the threaded lead screw away from the motor, and the sleeve is located above the positioning disk; Spring, one end is connected to the sleeve; One end of the clamp is rotatably connected to the bottom of the shell, and the other end is in contact with the sliding pipe. The other end of the spring is connected to the clamp.

[0011] In some embodiments, the cross section of the sliding tube is trapezoidal, and the side where the long side of the sliding tube is located abuts against the bottom surface of the movable disk, and the side where the short side of the sliding tube is located abuts against the clamp.

[0012] In some embodiments, the abutting end between the clamp and the sliding tube is an arc-shaped structure, and the spring is connected to an end close to the arc-shaped structure.

[0013] In some embodiments, multiple groups of clamps are provided, and the multiple groups of clamps are evenly arranged circumferentially with the threaded screw as the center.

[0014] In some embodiments, a groove is formed at one end of the clamp away from the sliding tube, and the positioning plate is engaged with the clamp through the groove.

[0015] In some embodiments, a fixing plate is installed on the inner bottom of the shell, a through hole is formed on the fixing plate, and an end of the clamp away from the positioning plate passes through the through hole and abuts against the sliding tube.

[0016] In some embodiments, the bottom of the sleeve is connected to the upper surface of the fixing plate.

[0017] The beneficial effects of the present invention are as follows: A launch device for a spacecraft landing impact test based on a push rod linkage of the present invention connects the spacecraft to a positioning plate, and the positioning plate is clamped in the grooves of multiple sets of clamps and maintained horizontally and stably. When the impact test is to be carried out, the motor is started, the motor drives the screw to rotate, and the nut is fixedly installed on the movable plate. The movable plate can only move in the vertical direction and cannot rotate. Therefore, the nut and the movable plate will move downward in the vertical direction together, causing the slide tube to slide downward synchronously and abut against the clamp to rotate the clamp, compressing the spring and opening the bottom until the positioning plate is completely out of the groove, achieving an instant release effect. At this time, the positioning plate drives the spacecraft to fall freely. When it falls to the ground, the lower hanging ring is still in free fall. In the technical solution of the present invention, the lower hanging ring is constrained by the sling to prevent it from falling to the ground, so the lower hanging ring will not cause damage to the spacecraft. After a single experiment is completed, the positioning plate and the spacecraft can be recovered. It is only necessary to reverse the motor and re-clamp the positioning plate in the groove. The present invention has the following advantages: 1) The release mechanism of the present invention has an automatic reset function, which not only makes the release operation more convenient, but also ensures that it can be reused, greatly improving the practicality and economic benefits of the device.

[0018] 2) In terms of structural design, the delivery device of the present invention has been optimized and simplified, thereby further enhancing safety and reliability. By streamlining complex mechanical components and processes, the safety and controllability of operation have been effectively improved.

[0019] 3) The present invention adopts a symmetrical structural design and locates the center of mass at the center of the housing. This innovative design not only helps prevent the spacecraft from tipping, shaking, or rotating during the release process, but also greatly saves human and material resources. This optimization makes the entire device operate more efficiently and reliably. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 is a schematic structural view of one perspective of a delivery device for a spacecraft landing impact test based on push rod linkage of the present invention; Figure 2 is Figure 1 a cross-sectional view of a delivery device for a spacecraft landing impact test based on push rod linkage as shown; In the drawings, 1, suspension strap; 2, lower suspension ring; 3, motor; 4, threaded lead screw; 5, nut; 6, movable disk; 7, sliding tube; 8, spring; 9, fixture; 10, positioning disk; 11, upper suspension ring; 12, fixing plate. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0021] The technical solutions of the present invention will be clearly and completely described below in conjunction with the embodiments. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0022] As described in the background, to complete landing impact tests, a launch device must address the following technical challenges: 1) Rapid unlocking and release: ensuring instant vertical release of the spacecraft during the test; 2) Stable attitude: ensuring the spacecraft does not sway or deflect during the lift; 3) Maintaining a safe distance from protruding surfaces on the spacecraft's cabin: preventing unnecessary contact or interference between the lifter and related components and the spacecraft; 4) Energy buffering: absorbing energy and slowing the lifter's own speed after unlocking; and 5) Reusability: the unlocking device must be reusable. These measures maximize the simulation of actual landing conditions and ensure the validity and reliability of the test results. Conventional spacecraft landing impact tests often involve the lifter being free-falling with the spacecraft. This experimental method not only leads to distorted test results but can also damage the spacecraft from the lifter, making the experimental device unreusable. Therefore, how to quickly release the spacecraft, prevent lifter damage after landing, and how to provide a reusable launch device for impact tests have become urgent technical challenges for those skilled in the art.

[0023] To solve the above problems, refer to Figure 1 and Figure 2 The present invention provides a launching device for spacecraft landing impact test based on push rod linkage, including a sling 1, a lower sling ring 2, a shell, a driving mechanism, a releasing mechanism, a positioning plate 10 and an upper sling ring 11. One end of the sling 1 is connected to the lower sling ring 2, and the lower sling ring 2 is arranged at the bottom of the shell; the interior of the shell is divided into an upper chamber and a lower chamber by a horizontally installed partition, the driving mechanism is installed in the upper chamber, the releasing mechanism is installed in the lower chamber, and the output end of the driving mechanism is connected to the releasing mechanism through the partition, the positioning plate 10 is clamped at the bottom of the releasing mechanism, the spacecraft is connected to the bottom of the positioning plate 10, the lower sling ring 2 is hinged to the positioning plate 10, the upper sling ring 11 is installed on the top of the shell, and the other end of the sling 1 is connected to the upper sling ring 11.

[0024] Specifically, when the device of the present invention is actually used, the length of the sling 1 needs to be selected with reference to the height of the free fall to ensure that the spacecraft can freely fall to the ground, and the lower ring 2 will perform free fall motion synchronously with the spacecraft. After the spacecraft falls to the ground, due to the limiting effect of the sling 1, the lower ring 2 will "hang" above the positioning plate 10 and will not fall to the ground to damage the spacecraft, thereby achieving the purpose of reusing the spacecraft.

[0025] Furthermore, the lower hoist ring 2 and the upper hoist ring 11 are used to lift the spacecraft to a specified height to ensure that the initial conditions required for the landing impact test are met. By precisely controlling the lifting process, the spacecraft can be released at a predetermined height.

[0026] Preferably, the driving mechanism includes: a motor 3, a threaded lead screw 4, a nut 5, and a movable disk 6. The motor 3 is installed inside the upper chamber, and the output end of the motor 3 passes through the partition and extends into the lower chamber. The threaded lead screw 4 is installed inside the lower chamber, and its top is connected to the end of the motor 3 extending into the lower chamber. The nut 5 is threadedly connected to the threaded lead screw 4, and the movable disk 6 is fixedly installed at the bottom of the nut 5 and is slidably connected to the inner wall of the housing.

[0027] Specifically, the cooperation of the motor 3 with the threaded lead screw 4 and the nut 5 enables the movable disk 6 to move vertically along the inner wall of the housing, thereby opening the release mechanism, causing the positioning disk 10 to drive the spacecraft to "instantly" break away from the release mechanism and start to free fall. As a result, the device of the present invention can achieve rapid unlocking and release, and the positioning disk 10 is in a stable state. There is no connection relationship of any form between the housing of the device of the present invention and other components and the positioning disk 10. The positioning disk 10 is only clamped on the release mechanism. Therefore, whether it is lifting or releasing, the positioning disk 10 will not shake or be eccentric.

[0028] Preferably, a vertically distributed chute is provided on the inner wall of the housing in the lower chamber. A slider adapted to the chute is installed on the edge of the movable disk 6, and the slider is slidably connected to the chute.

[0029] Specifically, the vertically moving movable disk 6 only exerts a vertical force on the sliding tube 7, avoiding the rotation of the sliding tube 7 caused by oblique or horizontal forces, which in turn causes the fixture 9 to shift, resulting in the eccentricity of the positioning disk 10 when it is released. In the device of the present invention, the fixture 9 can only rotate around the connection point with the housing as the center, without generating offset, avoiding the eccentricity of the positioning disk 10.

[0030] Preferably, the release mechanism includes: a sliding tube 7, a sleeve, a spring 8, and a fixture 9. The sliding tube 7 is slidably connected to the inner wall of the lower chamber, and the top of the sliding tube 7 abuts against the bottom surface of the movable disk 6. The sleeve is slidably sleeved on the end of the threaded lead screw 4 away from the motor 3, and the sleeve is located above the positioning disk 10. One end of the spring 8 is connected to the sleeve, one end of the fixture 9 is rotatably connected to the bottom of the housing, and the other end abuts against the sliding tube 7. The other end of the spring 8 is connected to the fixture 9.

[0031] Specifically, when releasing the positioning disk 10, multiple groups of fixtures 9 open synchronously, and are limited by springs with the same specifications, so that the fixtures 9 open and close synchronously under the action of the driving mechanism, and the opening angles of the fixtures 9 are the same at any moment.

[0032] Furthermore, the release mechanism can accurately release the positioning plate 10 and the lifting appliance at a specified height. The release mechanism includes a clamp 9, which can be automatically opened and closed by the forward and reverse rotation of the driving mechanism, thus ensuring that the equipment can be reused and meet the requirements of instantaneous release.

[0033] Preferably, the cross-section of the sliding tube 7 is trapezoidal, and the side where the long side of the sliding tube 7 is located abuts against the bottom surface of the movable plate 6, and the side where the short side is located abuts against the clamp 9.

[0034] Specifically, the side of the sliding tube 7 where the long side is located is the top surface of the sliding tube 7, and the top surface has a larger area and abuts against the movable plate 6. The larger contact area can make the force more balanced and more stable, enabling the device of the present invention to release the positioning plate 10 for simulating a spacecraft smoothly and reliably in an extremely short moment.

[0035] Preferably, the abutting end of the clamp 9 and the sliding tube 7 is an arc structure, and the spring 8 is connected to one end close to the arc structure.

[0036] Specifically, the setting of the arc structure can make the force on the clamp 9 more linear and gentle, without jamming, so as not to cause the deviation of a certain group of clamps, and can also improve the reliability of the device of the present invention.

[0037] Preferably, multiple groups of clamps 9 are provided, and the multiple groups of clamps are circumferentially and evenly arranged with the threaded lead screw 4 as the center.

[0038] Specifically, the setting of multiple groups of clamps 9 can perform circumferential clamping on the positioning plate 10 to keep its initial state horizontal. In the technical solution of the present invention, the number of clamps 9 is not less than three groups.

[0039] Preferably, a groove is provided at one end of the clamp 9 away from the sliding tube 7, and the positioning plate 10 is clamped with the clamp 9 through the groove.

[0040] Specifically, the clamping groove in the present invention forms a support at the bottom of the positioning plate 10 when it is not released, and no support is provided at the top. Such a design enables the clamp 9 on the upper side of the positioning plate 10 to rotate towards the center of the circle when the positioning plate 10 is released, while the clamp 9 on the lower side rotates away from the center of the circle, avoiding the situation of jamming the positioning plate 10 during the release process, and thus enabling the positioning plate 10 in the present invention to be quickly and accurately released instantaneously.

[0041] Preferably, a fixing plate 12 is installed at the inner bottom of the housing, and through holes are provided on the fixing plate 12. One end of the clamp 9 away from the positioning plate 10 passes through the through hole and abuts against the sliding tube 7.

[0042] Specifically, the through-holes in the present invention are all elongated holes. The length should be greater than the horizontal displacement of the fixture 9 during rotation, and the width should be the same as the thickness of the fixture 9 to limit it and prevent it from shifting during rotation, causing the positioning disk 10 to jam.

[0043] Preferably, the bottom of the sleeve is connected to the upper surface of the fixed plate 12.

[0044] A spacecraft landing impact test launching device based on push rod linkage proposed by the present invention has the following advantages: 1) Lifting function: The launching device is connected to the hoisting tool through the lower lifting ring 2 and the upper lifting ring 11, and can realize the function of safely lifting the spacecraft to a specified height. This ensures that the spacecraft meets the required initial conditions before the landing impact test.

[0045] 2) Precise release mechanism: When the initial conditions are set and confirmed to be correct, the release mechanism can instantaneously release the spacecraft, allowing it to simulate the actual landing process in a free-fall manner. Among them, the motor 3 realizes the opening and closing of the fixture 9 through forward and reverse operations, thus ensuring that the device can be reused.

[0046] 3) Safety limit protection: The sling 1 for limit protection is connected between the lower lifting ring 2 and the upper lifting ring 11 of the release mechanism. After the fixture 9 of the release mechanism is opened, the positioning disk 10, the lower lifting ring 2 and the spacecraft jointly perform free-fall motion. When the spacecraft touches the ground, the positioning disk 10 and the lower lifting ring 2 will descend a certain distance further to ensure that the sling 1 is tightened, thereby preventing the positioning disk 10 and the lower lifting ring 2 from causing further damage to the spacecraft.

[0047] 4) Structural design advantages: The overall structure of the launching device is symmetrical and simple, so its center of mass is located in the middle, avoiding the shaking problem caused by eccentricity, which may affect the test results. This optimized design significantly improves the efficiency of the spacecraft landing impact test and effectively eliminates potential product failure hazards caused by shaking.

[0048] 5) Wide applicability: The launching device can be connected to the hoisting tools corresponding to different models of spacecraft through the lifting rings, and can adapt to various types of spacecraft ground landing impact launching tests; at the same time, by changing the length of the sling 1, the hoisting tool and the spacecraft cabin can be released at any specified height, increasing the flexibility of the experimental operation.

[0049] In summary, the present invention not only improves the safety and reliability of the spacecraft landing impact test, but also greatly improves the experimental efficiency and reusability.

[0050] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation on the present invention.

[0051] In addition, the terms "first" and "second" are only used for descriptive purposes and should not be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one of such features. In the description of the present invention, the meaning of "a plurality" is at least two, such as two, three, etc., unless otherwise specifically defined.

[0052] In the present invention, unless otherwise clearly defined and limited, the terms "mounted", "connected", "coupled", "fixed", etc. should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or integrated; it may be a mechanical connection, an electrical connection, or communicable with each other; it may be directly connected, or indirectly connected through an intermediate medium, and may be the internal communication of two elements or the interaction relationship between two elements, unless otherwise clearly limited. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0053] In the present invention, the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples", etc. mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic descriptions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in a suitable manner in any one or more embodiments or examples. In addition, without contradiction, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.

[0054] Although the embodiments of the present invention have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as a limitation on the present invention. Those of ordinary skill in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present invention.

Claims

1. A dropping device for spacecraft landing impact test based on push rod linkage, characterized in that Comprising: A suspension strap (1); A lower suspension ring (2), one end of the suspension strap (1) being connected to the lower suspension ring (2); A housing, the lower suspension ring (2) being provided at the bottom of the housing; the internal space of the housing is divided into an upper chamber and a lower chamber by a horizontally installed partition; A driving mechanism, installed in the upper chamber; A release mechanism, installed in the lower chamber, and the output end of the driving mechanism passes through the partition and is in transmission connection with the release mechanism; A positioning disc (10), snap-fitted to the bottom of the release mechanism, a spacecraft being connected to the bottom of the positioning disc (10), and the lower suspension ring (2) being hinged to the positioning disc (10); An upper suspension ring (11), installed at the top of the housing, and the other end of the suspension strap (1) being connected to the upper suspension ring (11).

2. The dropping device for spacecraft landing impact test based on push rod linkage according to claim 1, characterized in that, The driving mechanism includes: A motor (3), installed inside the upper chamber, and the output end of the motor (3) passes through the partition and extends into the inside of the lower chamber; A threaded lead screw (4), installed inside the lower chamber, the top of which is connected to one end of the motor (3) extending into the inside of the lower chamber; A nut (5), threadedly connected to the threaded lead screw (4); A movable disc (6), fixedly installed at the bottom of the nut (5), and slidably connected to the inner wall of the housing.

3. The dropping device for spacecraft landing impact test based on push rod linkage according to claim 2, characterized in that, A chute distributed in the vertical direction is provided on the inner wall of the housing in the lower chamber, and a slider adapted to the chute is installed at the edge of the movable disc (6), and the slider is slidably connected to the chute.

4. A launching device for a spacecraft landing impact test based on push rod linkage according to claim 2, characterized in that, The release mechanism includes: A sliding tube (7), slidably connected to the inner wall of the lower chamber, and the top of the sliding tube (7) abuts against the bottom surface of the movable disc (6); A sleeve, slidably sleeved on one end of the threaded lead screw (4) away from the motor (3), and the sleeve is located above the positioning disc (10); A spring (8), one end of which is connected to the sleeve; A clamp (9), one end of which is rotatably connected to the bottom of the housing, the other end of which abuts against the sliding tube (7), and the other end of the spring (8) is connected to the clamp (9).

5. The dropping device for spacecraft landing impact test based on push rod linkage according to claim 4, characterized in that, The cross-section of the sliding tube (7) is trapezoidal, and the side where the long side of the sliding tube (7) is located abuts against the bottom surface of the movable disc (6), and the side where the short side is located abuts against the clamp (9).

6. The dropping device for spacecraft landing impact test based on push rod linkage according to claim 4, wherein, The abutting end of the clamp (9) and the sliding tube (7) is an arc structure, and the spring (8) is connected to one end close to the arc structure.

7. A dropping device for spacecraft landing impact test based on push rod linkage according to claim 4, characterized in that, Multiple groups of the clamps (9) are provided, and the multiple groups of the clamps are circumferentially and evenly arranged with the threaded lead screw (4) as the center.

8. The dropping device for spacecraft landing impact test based on push rod linkage according to claim 4, characterized in that A groove is provided at one end of the clamp (9) away from the sliding tube (7), and the positioning disc (10) is snap-fitted to the clamp (9) through the groove.

9. The launch device for spacecraft landing impact test based on push rod linkage according to claim 4, characterized in that: A fixing plate (12) is installed at the inner bottom of the housing, a through hole is provided on the fixing plate (12), and one end of the clamp (9) away from the positioning disc (10) passes through the through hole and abuts against the sliding tube (7).

10. The launch device for spacecraft landing impact test based on push rod linkage according to claim 9, characterized in that: The bottom of the sleeve is connected to the upper surface of the fixing plate (12).

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