Buffer device for spacecraft landing impact test

Abstract

A buffering device for a spacecraft landing impact test comprises a lifting appliance, a releasing device, an electric throwing assembly, a limiting protection device and a buffering energy absorption device, and the lifting appliance is a tool for lifting a spacecraft and is used for hanging the spacecraft; the upper end of the release device is hung on the crown block hook, and the lower end is connected with the hanger to lift the hanger and the spacecraft; the electrical releasing assembly is connected with the releasing device and supplies power to the releasing device, so that the releasing device releases the lifting appliance when electrified; the buffering energy-absorbing device is used for limiting and protecting the spacecraft after the spacecraft is released, the two ends of the buffering energy-absorbing device are connected with the limiting protection devices respectively, the limiting protection device at one end is connected with the crown block hook, and the limiting protection device at the other end is connected with the upper end of the lifting appliance. Linear speed reduction is provided for falling of the lifting appliance, instant braking of the lifting appliance is converted into slow stop motion, impact energy in the free falling process of the lifting appliance can be effectively absorbed, the lifting appliance can stably move in the landing impact test process, and a spacecraft and a crane are protected.

Description

Technical Field

[0001] The present invention relates to a buffer device for spacecraft landing impact tests, belonging to the field of landing tests. Background Art

[0002] When a spacecraft conducts a landing impact test, a sling is used to lift the spacecraft to a specified height and release it in a horizontal attitude at the specified height. After release, there is a limit protection device to avoid adverse effects on the test due to the interaction between the sling and the spacecraft. During the free fall of the spacecraft and the sling, there is a large impact when the sling stops instantaneously under the action of the limit protection device. Currently, most shock tests use the method of spring damping. The reaction force during the damping process is large, resulting in severe shaking of the sling and the crane, posing potential risks of damaging the spacecraft and the overhead crane / crane. Summary of the Invention

[0003] The technical problem to be solved by the present invention is: overcoming the deficiencies of the prior art, providing a buffer device for spacecraft landing impact tests. The device can provide a constant reaction force throughout the buffer stroke, provide linear deceleration for the falling sling, convert the instantaneous braking of the sling into a slow stop motion, effectively absorb the impact energy during the free fall of the sling, making the sling move smoothly during the landing impact test and protecting the spacecraft and the crane.

[0004] The technical solution of the present invention is: a buffer device for spacecraft landing impact tests, including: a sling, a release device, an electrical release component, a limit protection device, and a buffer energy absorption device, where:

[0005] The sling is a tool for hoisting the spacecraft and is used to hang the spacecraft;

[0006] The upper end of the release device is hung on the overhead crane hook, and the lower end is connected to the sling to realize the lifting of the sling and the spacecraft;

[0007] The electrical release component is connected to the release device and supplies power to it, enabling the release device to release the sling when powered on;

[0008] The buffer energy absorption device is used to limit and protect the spacecraft after its release. Both ends of the buffer energy absorption device are respectively connected to the limit protection device. One end of the limit protection device is simultaneously connected to the overhead crane hook, and the other end of the limit protection device is simultaneously connected to the upper end of the sling.

[0009] Preferably, the limit protection device is a sling with a load-bearing capacity greater than 1 ton.

[0010] Preferably, the sling selects any one of the following according to the lifting interface of the spacecraft:

[0011] Cross-folded sling, one-beam sling, sling.

[0012] Preferably, the release device includes a lifting ring, a bomb hook fixing member, a bomb hook, a connecting bolt nut gasket, a lifting lug, a first shackle, and a second shackle; specifically:

[0013] One end of the first shackle is connected to the lifting ring, and the other end passes through a through hole at the upper end of the bomb hook fixing member and is connected to the bomb hook fixing member; the main structure of the bomb hook fixing member is a groove with an opening downward, and the bomb hook is embedded in the groove of the bomb hook fixing member and fixed by a connecting bolt nut gasket;

[0014] A locking device is provided on the bomb hook, and a hook is provided on the locking device; the hook is connected to the lifting lug, and the second shackle is connected to the lifting lug;

[0015] The locking device on the bomb hook is connected to the electrical release assembly. When not powered on, the hook tightly grasps the lifting lug to lift the sling and the spacecraft. When powered on, the locking device automatically unlocks, the hook opens, and the sling and the spacecraft are released.

[0016] Preferably, the buffer energy absorption device includes a buffer, an upper lifting lug, a lower lifting lug, four first support rods, four second support rods, a bottom plate, a load-bearing plate, and a guide tube; among them:

[0017] The upper ends of the four first support rods are respectively connected to the four corners of the lower surface of the upper lifting lug, and the lower ends are respectively connected to the four corners of the upper surface of the bottom plate; one end of the buffer is fixed to the lower end of the upper lifting lug, and the other end is fixed above the bottom plate;

[0018] A through hole is provided at the center of the load-bearing plate, which is sleeved and fixed on the upper section of the buffer; four notches are provided at the edge of the load-bearing plate to avoid the four first support rods and play a guiding role at the same time; the guide tube is sleeved on the buffer, and one end is fixedly connected to the lower surface of the load-bearing plate;

[0019] The lower lifting lug is parallel to the upper lifting lug and is located below the bottom plate after rotating 45° horizontally relative to the upper lifting lug; one end of the four second support rods is respectively fixedly connected to the four corners of the upper surface of the lower lifting lug, and the other end is connected to the lower surface of the load-bearing plate.

[0020] Preferably, the buffer is an adjustable buffer, and a throttle valve is adopted inside, which can change the damping value to adapt to different load conditions.

[0021] Preferably, the electrical release assembly includes a power cable, a momentary switch, and a DC power supply; the power cable is connected to the bomb hook, and the momentary switch and the DC power supply are located on the ground, and the test personnel operate on the ground at the experimental site to unlock the bomb hook.

[0022] The present invention has the following advantages compared with the prior art:

[0023] (1) According to different loads, the present invention can select corresponding damping values for the buffer to absorb impact energy, provide a constant reaction force, and provide better protection for the overhead crane and the sling.

[0024] (2) The damping of the present invention is adjustable and can be applied to landing impact tests with multiple loads, and the application scenarios are more extensive. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 is a schematic diagram of the composition of the present invention;

[0026] Figure 2 is a schematic diagram of the sling structure of the present invention;

[0027] Figure 3 is a schematic diagram of the release device structure of the present invention;

[0028] Figure 4 is a schematic diagram of the connection of the electrical release assembly of the present invention;

[0029] Figure 5 is a schematic diagram of the buffer energy absorption device structure of the present invention. DETAILED DESCRIPTION OF THE INVENTION

[0030] The present invention provides a buffer device for spacecraft landing impact tests. By installing a buffer energy absorption device on the limit protection device, the impact energy during the impact test can be effectively absorbed, and the instantaneous braking of the sling is transformed into a slow stop motion, so that the sling moves smoothly during the landing impact test and can well protect the spacecraft and the crane.

[0031] The landing impact test buffer system consists of a sling, a release device, an electrical release assembly, a limit protection device, and a buffer energy absorption device. The sling is used to lift the spacecraft to a specified height, the release device is used for the release of the spacecraft, the limit protection device is used for the limit protection after the release of the spacecraft to avoid adverse effects on the test due to the interaction between the sling and the spacecraft, and the buffer energy absorption device is installed on the limit protection device to absorb the impact energy during the release of the sling and protect the spacecraft and the overhead crane.

[0032] The sling can be a beam-type sling, a cross-folded sling or a simple sling, and is used for hoisting the spacecraft and hoisting the spacecraft to a specified height.

[0033] The release device is used to connect the overhead crane and the sling, and the electrical release assembly is used to release the sling and the spacecraft. The release device consists of a lifting ring, a bomb hook, a bomb hook fixing piece, a connecting bolt and nut gasket, a lifting lug and a shackle, etc.; the electrical release assembly includes a power cable, a momentary switch, and a DC power supply, and is used for experimenters to operate and unlock the release hook assembly on the spot on the ground.

[0034] The limit protection device includes a sling and is used for the limit protection after the release of the spacecraft.

[0035] The buffer energy absorption device consists of a lifting lug, a spring, a damper, a guide cylinder, etc. The damping of the buffer energy absorption device is adjustable, and the damping value can be adjusted according to the size of the load of the spacecraft sling, so as to obtain the optimal damping ratio and absorb the impact energy during the test to the greatest extent.

[0036] The present invention will be described in detail below with reference to the accompanying drawings and by way of examples:

[0037] As Figure 1 shown, a buffer system for spacecraft landing impact tests mainly includes a sling 100, a release device 200, an electrical release assembly 300, a limit protection device 400, and a buffer energy absorption device 500, where:

[0038] The sling 100 is a tool for hoisting a spacecraft and is used to hang the spacecraft;

[0039] The upper end of the release device 200 is hung on the crane hook, and the lower end is connected to the sling 100 to realize the lifting of the sling and the spacecraft;

[0040] The electrical release assembly 300 is connected to the release device 200 and supplies power to it, so that the release device 200 releases the sling when powered on;

[0041] The buffer energy absorption device 500 is used to limit and protect the spacecraft after its release. Both ends of the buffer energy absorption device 500 are respectively connected to the limit protection device 400. One end of the limit protection device 400 is connected to the crane hook, and the other end of the limit protection device 400 is connected to the upper end of the sling 100.

[0042] As Figure 2 shown, the sling 100 is a tool for hoisting a spacecraft. It can be selected according to the hoisting interface of the spacecraft. It can be the cross-folded sling shown in the figure, or the one-beam sling, or a sling, etc. The upper part of the sling shown in the figure is connected to the release device 200 and the limit protection device 400 through the main lifting ring 101, and the lower part is connected to the spacecraft to be tested through the sling point connector.

[0043] As Figure 3As shown in the figure, the release device 200 mainly consists of a lifting ring 201, a bomb hook fixing member 202, a bomb hook 203, a connecting bolt nut gasket 204, a lifting lug 205, a first shackle 206, and a second shackle 207. Among them, the lifting ring 201 is connected to the hook of the overhead crane at the test site to realize the lifting of the lifting tool and the spacecraft; the bomb hook fixing member 202 is connected and fixed to the bomb hook 203 through the connecting bolt nut gasket 204. Specifically: the main structure of the bomb hook fixing member 202 is a groove with an opening downward, and the bomb hook 203 is embedded in the groove of the bomb hook fixing member 202 and fixed through the connecting bolt nut gasket 204; the lifting ring 201 and the bomb hook fixing member 202, and the lifting lug 205 and the main lifting ring 101 of the lifting tool are all connected through the first shackle 206. Specifically: one end of the first shackle 206 is connected to the lifting ring 201, and the other end passes through the through hole at the upper end of the bomb hook fixing member 202 and is connected to the bomb hook fixing member 202; the main structure of the bomb hook fixing member 202 is a groove with an opening downward, and the bomb hook 203 is embedded in the groove of the bomb hook fixing member 202 and fixed through the connecting bolt nut gasket 204. The bomb hook 203 is an important part for realizing the landing impact test. A locking device is provided on the bomb hook 203, and a hook is provided on the locking device; the hook is connected to the lifting lug 205, and the second shackle 207 is connected to the lifting lug 205; the locking device on the bomb hook 203 is powered by the power cable of the electrical release assembly 300. During use, the lifting lug 205 is placed on the hook of the locking device of the bomb hook 203, the locking device is tightened, and the hook is locked; during release, the bomb hook 203 is powered on, the locking device is automatically unlocked, and the hook is opened to realize the release function.

[0044] As Figure 4 shown, the electrical release assembly 300 includes a power cable 301, a momentary switch 302, and a DC power supply 303. Since the bomb hook of the release device is at a certain height from the ground at the test site, it is relatively difficult to operate the unlocking and releasing action of the bomb hook mechanically in the air. Therefore, the function of the electrical release assembly is to facilitate the on-site test personnel to operate and unlock the bomb hook on the ground at the test site. Because the coil power supply of the electromagnetic release mechanism of the bomb hook is 20V / 6A DC, the DC power supply of the electrical release assembly converts AC 220V into 20V / 6A DC, and a momentary switch is connected to the power cable connected between the bomb hook and the DC power supply as the electrical operation button for unlocking the bomb hook.

[0045] The limit protection device 400 is a sling, and its load-bearing capacity is greater than 1 ton;

[0046] As Figure 5As shown in the figure, the 500 buffer energy absorption device consists of a buffer 501, an upper lifting lug 502, a lower lifting lug 503, four first support rods 504, four second support rods 505, a bottom plate 506, a load-bearing plate 507, and a guide cylinder 508. The lower buffer 501 is fixed on the bottom plate 506 and connected to the upper lifting lug 502 through the first support rods 504 and fastened with nuts. The load-bearing plate 507 is fixed on the upper section of the buffer and connected to the lower lifting lug 503 through the second support rods 2 and fastened with nuts. The upper lifting lug 502 and the lower lifting lug 503 are connected to the overhead crane hook and the main sling ring of the lifting appliance through a sling. Specifically, the upper ends of the four first support rods 504 are respectively connected to the four corners of the lower surface of the upper lifting lug 502, and the lower ends are respectively connected to the four corners of the upper surface of the bottom plate 506. One end of the buffer 501 is fixed to the lower end of the upper lifting lug 502, and the other end is fixed above the bottom plate 506.

[0047] A through hole is provided at the center of the load-bearing plate 507, which is sleeved and fixed on the upper section of the buffer. Four notches are provided at the edge of the load-bearing plate 507 to avoid the four first support rods 504 and play a guiding role at the same time. The guide cylinder 508 is sleeved on the buffer, and one end is fixedly connected to the lower surface of the load-bearing plate 507.

[0048] The lower lifting lug 503 is parallel to the upper lifting lug 502 and rotates 45° relative to the upper lifting lug 502 and is located below the bottom plate 506. One ends of the four second support rods 505 are respectively fixedly connected to the four corners of the upper surface of the lower lifting lug 503, and the other ends are connected to the lower surface of the load-bearing plate 507.

[0049] The buffer 501 is an adjustable buffer, and a throttle valve is adopted inside, which can change the damping size to adapt to different load conditions.

[0050] Although the present invention has been described in detail with general descriptions and specific embodiments above, based on the present invention, some modifications or improvements can be made, which are obvious to those skilled in the art. Therefore, these modifications or improvements made without departing from the spirit of the present invention all fall within the scope of protection required by the present invention.

[0051] The content not described in detail in the specification of the present invention belongs to the prior art well-known to those skilled in the art.

Claims

1. A buffer device for spacecraft landing impact tests, characterized in that Comprising: A lifting appliance (100), a release device (200), an electrical release assembly (300), a limit protection device (400), and a buffer energy absorption device (500), where: The lifting appliance (100) is a tool for hoisting a spacecraft and is used to suspend the spacecraft; The upper end of the release device (200) is hung on the overhead crane hook, and the lower end is connected to the lifting appliance (100) to achieve the lifting of the lifting appliance and the spacecraft; The electrical release assembly (300) is connected to the release device (200) and supplies power to it, enabling the release device (200) to release the lifting appliance when powered on; The buffer energy absorption device (500) is used to provide limit protection for the spacecraft after its release. The two ends of the buffer energy absorption device (500) are respectively connected to the limit protection device (400), and one end of the limit protection device (400) is simultaneously connected to the overhead crane hook, and the other end of the limit protection device (400) is simultaneously connected to the upper end of the lifting appliance (100).

2. The buffer device for spacecraft landing impact test according to claim 1, wherein: The limit protection device (400) is a sling, and its load-bearing capacity is greater than 1 ton.

3. A buffer device for a spacecraft landing impact test according to claim 1, characterized in that: The lifting appliance (100) selects any one of the following according to the hoisting interface of the spacecraft: Cross-folded lifting appliance, one-beam lifting appliance, sling.

4. A buffer device for spacecraft landing impact tests according to claim 1, characterized in that: The release device (200) includes a lifting ring (201), a bomb hanger fixing part (202), a bomb hanger (203), connecting bolt nut washers (204), a lifting lug (205), a first shackle (206), and a second shackle (207); specifically: One end of the first shackle (206) is connected to the lifting ring (201), and the other end passes through the through hole at the upper end of the bomb hanger fixing part (202) and is connected to the bomb hanger fixing part (202); the main structure of the bomb hanger fixing part (202) is a groove with an opening downward, and the bomb hanger (203) is embedded in the groove of the bomb hanger fixing part (202) and fixed by the connecting bolt nut washers (204); A locking device is provided on the bomb hanger (203), and a hook is provided on the locking device; the hook is connected to the lifting lug (205), and the second shackle (207) is connected to the lifting lug (205); The locking device on the bomb hanger (203) is connected to the electrical release assembly (300). When not powered on, the hook tightly grips the lifting lug (205) to lift the lifting appliance and the spacecraft. When powered on, the locking device automatically unlocks, the hook opens, and the lifting appliance and the spacecraft are released.

5. A buffer device for a spacecraft landing impact test according to claim 1, characterized in that: The buffer energy absorption device (500) includes a buffer (501), an upper lifting lug (502), a lower lifting lug (503), four first support rods (504), four second support rods (505), a bottom plate (506), a load-bearing plate (507), and a guide cylinder (508); where: The upper ends of the four first support rods (504) are respectively connected to the four corners of the lower surface of the upper lifting lug (502), and the lower ends are respectively connected to the four corners of the upper surface of the bottom plate (506); one end of the buffer (501) is fixed to the lower end of the upper lifting lug (502), and the other end is fixed above the bottom plate (506); A through hole is provided at the center of the load-bearing plate (507), which is sleeved and fixed on the upper section of the buffer; four notches are provided at the edge of the load-bearing plate (507) to avoid the four first support rods (504), and at the same time play a guiding role; the guiding cylinder (508) is sleeved on the buffer, and one end is fixedly connected to the lower surface of the load-bearing plate (507). The lower lifting lug (503) is parallel to the upper lifting lug (502), and is located below the bottom plate (506) after horizontally rotating 45° relative to the upper lifting lug (502); one end of the four second support rods (505) is fixedly connected to the four corners of the upper surface of the lower lifting lug (503), and the other end is connected to the lower surface of the load-bearing plate (507).

6. A buffer device for a spacecraft landing impact test according to claim 1, characterized in that: The buffer (501) is an adjustable buffer, and a throttle valve is adopted inside, which can change the damping size to adapt to different load conditions.

7. A buffer device for a spacecraft landing impact test according to claim 4, characterized in that: The electric release assembly (300) includes a power cable (301), a momentary switch (302), and a DC power supply (303); among them, the power cable (301) is connected to the bomb hook (203), and the momentary switch (302) and the DC power supply (303) are located on the ground, and the test personnel operate on the ground at the experimental site to unlock the bomb hook (203).

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