A spacecraft extravehicular assembly throw-off test system and method

Abstract

This invention relates to a spacecraft extravehicular component ejection and separation test system and method, comprising: a ejected component, a cabin, a raised platform, and a deceleration and recovery system; the ejected component is mounted on the cabin, which is placed on a raised platform to ensure sufficient descent distance and operational space for the ejected component during the test; the ejected component is connected to the deceleration and recovery system; after unlocking and separation, the ejected component undergoes horizontal ejection motion, subject only to gravity, with the motion path denoted as process A, during which the deceleration and recovery system exerts no force on the ejected component; after a certain point, it enters deceleration phase B, where the deceleration is controlled by the length of the ropes in the deceleration and recovery system, and the deceleration is achieved through the traction between multiple ropes in the deceleration and recovery system until it comes to a stationary hovering position in the air. This invention solves the verification problem of actively ejecting parts of extravehicular components during spacecraft operation based on mission requirements or abnormal situations.

Description

Technical Field

[0001] This invention relates to a test system and method for verifying the launch function of spacecraft extravehicular components in the space environment, belonging to the field of spacecraft test technology. Background Technology

[0002] During operation, a lunar lander needs to perform specific tasks on the lunar surface. These tasks require the lander to actively jettison some external modules based on mission requirements or abnormal situations. During this jettisoning process, the reliability and safety of the system must be ensured to prevent any accidents or malfunctions. Simultaneously, collisions between the jettisoned external modules and the lunar module must be prevented to ensure normal system operation and successful mission completion. Therefore, ground tests must rigorously verify the jettisoning process to ensure the system's reliability and safety in practical applications. Secondly, the jettisoned components must not be damaged during the test. This not only increases the difficulty of ground testing but also requires additional protection measures in the test design and implementation to ensure that their future reuse or other uses are not affected. Therefore, there is an urgent need for a ground testing method that can effectively verify the jettisoning function of external modules while ensuring product safety.

[0003] Currently, most experimental methods for simulating spacecraft missions on the lunar or Martian surface rely on microgravity simulation technology. Relatively mature microgravity simulation methods include suspension, air levitation, and magnetic levitation. However, these methods all have the following shortcomings:

[0004] 1) The suspension method requires complex motor and rope coordination control, which makes the test system complex and large. When faced with a complex test object, the test device is difficult to adapt. In addition, the dynamic tracking of the suspension system is poor. If the test object moves too fast, the suspension system cannot react in time, which will affect the test process and cause interference.

[0005] 2) The air-float method can generally only adapt to two-dimensional motion and is difficult to meet the requirements of three-dimensional motion; and the test objects for the lunar lander's external component launch test are large in weight and size, and the air-float platform cannot support the lander system to complete the launch test.

[0006] 3) The magnetic levitation method also requires a complex control system to maintain the stable levitation of the test object, which requires high costs and a sufficiently large test space. At the same time, considering the size and weight of the test object, there is a problem that exceeds the load-bearing capacity of the magnetic levitation method.

[0007] The lunar lander's external module separation test has its unique characteristics: the separated components separate rapidly and are heavy; the entire module needs to participate in the test, and the test site conditions cannot be too harsh; the component loading space environment is complex, and external tooling is not easily connected to the separated components; furthermore, the separated components will continue to undergo various tests, requiring the product to remain undamaged while simultaneously verifying the separation function. To address these issues, it is necessary to design a new testing method that can circumvent the limitations of test tooling requirements and test site conditions, and simultaneously verify the lunar surface separation function of the external modules while protecting the product. Summary of the Invention

[0008] The technical problem solved by the present invention is to overcome the shortcomings of the prior art and provide a spacecraft extravehicular component ejection test system and method, which solves the verification problem of actively ejecting some extravehicular components during spacecraft operation according to mission requirements or abnormal situations.

[0009] The technical solution of this invention is:

[0010] A spacecraft extravehicular component ejection test system, characterized in that it includes: the ejected component, the cabin, the platform, and the deceleration and recovery system;

[0011] The ejected component is installed on the cabin. Before the test, the cabin is placed on a high platform to ensure that the ejected component has sufficient falling distance and operating space during the test to avoid collisions. The ejected component is connected to the deceleration and recovery system.

[0012] After being unlocked and separated, the component being thrown performs a horizontal throwing motion and is only subject to gravity. The motion path is denoted as process A. The attitude and trajectory during the free fall process are captured by a high-speed camera. During process A, the deceleration and recovery system exerts no force on the component being thrown.

[0013] After moving to a certain point, it enters deceleration phase B. The position where deceleration takes effect is controlled by the length of the rope in the deceleration and recovery system. The traction between multiple ropes in the deceleration and recovery system provides tension to decelerate until the thrown component comes to a standstill and hangs in the air.

[0014] Furthermore, the multi-cable recovery system includes a horizontal deceleration cable assembly, a vertical deceleration cable assembly, and an anti-sway cable assembly;

[0015] Both the horizontal deceleration cable assembly and the vertical deceleration cable assembly include elastic elements, anti-reverse mechanisms, and ropes; the anti-sway cable assembly includes a drive unit, an anti-reverse mechanism, and ropes.

[0016] All ropes are connected to the thrown component. The elastic element converts the kinetic energy and gravitational potential energy of the thrown component into elastic potential energy in one direction. At the same time, the anti-reverse mechanism prevents the elastic potential energy from being converted into kinetic energy. The drive unit actively contracts the rope of the anti-swing cable assembly to keep it taut.

[0017] Furthermore, the ropes of the horizontal deceleration cable assembly and the anti-swing cable assembly are connected to both sides of the thrown component, while the rope of the vertical deceleration cable assembly is connected to the top of the thrown component.

[0018] Furthermore, during the entire deceleration process, i.e., deceleration phase B, the resultant force of the rope passes through the center of mass of the thrown component, thus avoiding the generation of overturning moment.

[0019] Furthermore, the horizontal deceleration cable assembly and the vertical deceleration cable assembly have the same structure, and their elastic elements are parallel elastic ropes; the anti-reverse mechanism includes: a one-way slider and an anti-reverse pawl; the rope is a deceleration wire rope;

[0020] One end of the deceleration wire rope is connected to the thrown component, and the other end is connected to the parallel elastic rope after passing through the anti-reverse mechanism. The parallel elastic rope gradually decelerates the component, eventually suspending it in the air. The anti-reverse mechanism is used to limit and prevent the thrown component from rebounding. The one-way slider and the anti-reverse pawl are both installed on the frame structure of the anti-reverse mechanism. The one-way slider limits the maximum deformation of the parallel elastic rope, and the anti-reverse pawl ensures that the deceleration wire rope can only move in one direction.

[0021] Furthermore, in the anti-sway cable assembly, the rope is the anti-sway wire rope;

[0022] The anti-sway wire rope is connected to the throwing assembly and needs to be connected to the drive unit through the anti-reverse mechanism. The anti-reverse mechanism maintains unidirectional movement, that is, the anti-sway wire rope can only be shortened and cannot be extended. During the throwing and deceleration recovery process, the drive unit actively contracts the anti-sway wire rope to maintain tension.

[0023] Furthermore, after the test, the kinetic energy and gravitational potential energy of the thrown component are converted into the elastic potential energy of the rope, which is calculated as follows. Here, the rope refers to the parallel elastic rope in the horizontal deceleration cable assembly and the vertical deceleration cable assembly.

[0024]

[0025] In the formula, k is the stiffness of the parallel elastic rope, m is the mass of the thrown component, g is the gravitational acceleration, h is the vertical free fall distance of the thrown component, x is the horizontal movement distance, and v is the separation velocity. For different thrown components, the stiffness of the parallel elastic rope is designed according to the mass of the thrown component, the separation velocity, and the safe distance allowed for throwing in the test.

[0026] Secondly, the present invention also proposes a method for launching and testing spacecraft extravehicular components, including: an experimental design stage, an experimental preparation stage, an experimental implementation stage, and an experimental withdrawal stage;

[0027] Experimental design phase:

[0028] (1) First, confirm the mass characteristics, external dimensions and available interfaces of the thrown component. Design a hanger for the thrown component. The hanger is connected to the external support of the load chamber. The hanger is equipped with horizontal deceleration cable rings and vertical deceleration cable rings. The horizontal deceleration cable rings also serve as anti-sway cable rings. The mass deviation and center of gravity deviation between the load chamber and the hanger assembly and the load chamber do not exceed 5%.

[0029] (2) Confirm the load-bearing capacity of the interface, and combine the horizontal or vertical distance that allows the thrown component to move freely, as well as the horizontal and vertical distance that allows the thrown component to decelerate, to confirm the length and stiffness of the rope;

[0030] (3) Design a simulated component of the thrown component to simulate the outer envelope and mass characteristics of the thrown component;

[0031] (4) Design a simulated ejection system, and adopt a spring separation mechanism at the separation interface between the ejected component and the simulated test specimen to achieve the separation effect of simulating the explosion of pyrotechnics;

[0032] (5) Design a simulation chamber that only simulates the installation interface with the component to be launched and the shape and size of the component to be launched;

[0033] (6) Place the simulation chamber in the test site, connect the simulated component to the simulation chamber, debug the test system, and verify the spring thrust through the pre-test;

[0034] Experiment preparation phase:

[0035] (1) Confirm interface compatibility after assembly;

[0036] (2) Check the status of the test product to confirm that the thrown components do not interfere with or hook up with the cabin;

[0037] (3) Check and confirm the status of the pyrotechnics and separation device to ensure that the separation action can be completed during the test;

[0038] Experimental implementation phase:

[0039] (1) Level the spacecraft to ensure that the cabin levelness meets the requirements;

[0040] (2) The spacecraft is placed on a high platform to expand the movement space of the thrown components and avoid collisions between the thrown components and the ground or the cabin; the high platform is achieved by using a vertical parking bracket.

[0041] (3) Transport the spacecraft and its parking support assembly to the inside of the tower. A deceleration and recovery system is installed on the tower. Vertical deceleration cable rings, horizontal deceleration cable rings and anti-sway cable rings are installed on the gantry. The deceleration and recovery system is connected to the thrown sub-component through the rings.

[0042] (4) Pull the rope directly connected to the thrown component away from the cabin to prevent the rope from getting caught on the cabin.

[0043] (5) After the cabin position is set, a high-speed photogrammetry system is deployed and a target is attached to the projectile component;

[0044] (6) Set the vertical deceleration cable to be relaxed in the initial state, with its elastic element located at the top of the tower; set the horizontal deceleration cable to be relaxed in the initial state, with its elastic element located at the rear of the tower; set the anti-sway cable to be stretched in the initial state, apply a stretching force of 10N, and set the anti-sway cable to be located at the front of the tower.

[0045] (7) Issue a separation command, and the thrown component is thrown freely for a distance, then decelerates and finally hovers in the air;

[0046] Trial withdrawal phase:

[0047] (1) Inspect the appearance of the ejected components and the cabin, and take photos to confirm that there is no damage;

[0048] (2) The tooling for parking the thrown components is transported to the test site and parked in a suitable position;

[0049] (3) Adjust the rope to slowly lower the thrown component to the ground sponge pad and separate the rope from the hanger;

[0050] (4) Remove the hanger and place the thrown component at its parking fixture location;

[0051] (5) The cabin was removed from under the test tower and placed in the designated location;

[0052] (6) Organize other equipment and products at the test site, and finally interpret the measurement data, confirm the validity of the measurement data, and complete the test.

[0053] The advantages of this invention compared to the prior art are:

[0054] (1) The test method of the present invention can be easily adjusted according to different components to be thrown, and can complete the throwing test of different components. It can meet the needs of multiple component throwing tests of lunar landers and is a relatively universal technical means.

[0055] (2) The test method of the present invention does not require a harsh test site environment. The test tooling is simple and can adapt to the complex loading space of the components, solving the problem of limited separation space and easy collision.

[0056] (3) The test method of the present invention can meet the special requirements of the lunar lander's external component throwing test, can protect the safety of the thrown product, and can achieve the purpose of serious component throwing function. Attached Figure Description

[0057] Figure 1 A schematic diagram of the workflow for the component scattering test method;

[0058] Figure 2 This is a schematic diagram of the working principle of a multi-rope deceleration and recovery system.

[0059] Figure 3 A schematic diagram of a vertical (horizontal) deceleration cable;

[0060] Figure 4 Diagram of the stop-motion oscillator;

[0061] Figure 5 This is a schematic diagram of the motion process of the component being thrown during the experiment;

[0062] Figure 6 A schematic diagram of the assembly of the thrown component and the tooling hanger; Detailed Implementation

[0063] The specific embodiments of the present invention will now be described in further detail with reference to the accompanying drawings.

[0064] This invention provides a method for launching and separating extravehicular components of a spacecraft. By launching the components directly under ground gravity, compared with the lunar surface conditions, the horizontal separation speed of the components is unaffected, while the vertical descent speed is faster. The safe distance between the launched component and the products located below it on the spacecraft during the separation process will decrease. Thus, if the ground test is passed, the separation safety of the launched component can be considered verified. However, the safe distance between the launched component and the products located above it on the spacecraft during the separation process will increase. At this time, the simulation model can be modified based on the ground test measurement results to obtain the dynamic characteristics of lunar surface launch.

[0065] The component throwing test system is attached. Figure 1 The system includes: a thrown component 1, a cabin 4, a raised platform 5, and a deceleration and recovery system. The thrown component 1 is installed on the cabin 4. Before the test, the cabin 4 is placed on a raised platform 5 to ensure that the thrown component 1 has sufficient falling distance and operating space during the test to avoid collisions. The thrown component 1 is connected to the deceleration and recovery system. After unlocking and separating, the thrown component 1 undergoes a horizontal throwing motion and is only subject to gravity. The motion path is denoted as process A. The attitude and trajectory during free fall are captured by a high-speed camera. During process A, the deceleration and recovery system exerts no force on the thrown component. After moving to a certain point, it enters the deceleration phase B. The position where deceleration takes effect is controlled by the length of the ropes in the deceleration and recovery system. The traction between multiple ropes in the deceleration and recovery system provides tension to decelerate the component until it comes to a standstill and hangs in the air.

[0066] The most important experimental device during the test was the device for decelerating and recovering the projectile, called the deceleration and recovery system. The working principle of the deceleration and recovery system is detailed in the appendix. Figure 2 According to functional requirements, the deceleration and recovery system needs to be equipped with a horizontal deceleration cable assembly 6, a vertical deceleration cable assembly 7, and an anti-sway cable assembly 8. Both the horizontal deceleration cable assembly 6 and the vertical deceleration cable assembly 7 include an elastic element, a reverse-blocking mechanism, and a rope. The anti-sway cable assembly 8 includes a drive unit, a reverse-blocking mechanism, and a rope. All ropes are connected to the thrown component 1. The elastic element unidirectionally converts the kinetic energy and gravitational potential energy of the thrown component into elastic potential energy, while the reverse-blocking mechanism prevents the conversion of elastic potential energy into kinetic energy. The drive unit actively contracts the rope of the anti-sway cable assembly 8 to keep it taut. The ropes of the horizontal deceleration cable assembly 6 and the anti-sway cable assembly 8 are connected to both sides of the thrown component, while the rope of the vertical deceleration cable assembly 7 is connected to the top of the thrown component.

[0067] During the entire deceleration process, i.e. deceleration phase B, the resultant force of the rope passes through the center of mass of the thrown component to avoid generating an overturning moment.

[0068] like Figure 3 As shown, the horizontal deceleration cable assembly 6 and the vertical deceleration cable assembly 7 have the same structure, and their elastic elements are parallel elastic ropes 62; the anti-reverse mechanism 63 includes: a one-way slider 65 and an anti-reverse pawl 66; the rope is the deceleration wire rope 64.

[0069] One end of the deceleration wire rope 64 is connected to the thrown component, and the other end is connected to the parallel elastic rope 62 after passing through the anti-reverse mechanism 63. The parallel elastic rope 62 plays a role in gradually decelerating the component, eventually suspending it in the air. The anti-reverse mechanism 63 is used to limit and prevent the thrown component from rebounding. The one-way slider 65 and the anti-reverse pawl 66 are both installed on the frame structure of the anti-reverse mechanism 63. The one-way slider 65 plays a role in limiting the maximum deformation of the parallel elastic rope 62, and the anti-reverse pawl ensures that the deceleration wire rope 64 can only move in one direction.

[0070] The parallel elastic rope has a lower moment of inertia compared to the spring. At the moment the deceleration cable is tensioned 0.5 seconds after the projectile's flight, the inertial impact of the deceleration cable on the projectile is relatively small. The design concepts of the horizontal and vertical deceleration cable systems are the same, the differences being: the stiffness parameters of the parallel elastic rope and the unidirectional slider stroke.

[0071] like Figure 4 As shown, in the anti-sway cable assembly 8, the rope is the anti-sway wire rope 83; the anti-sway wire rope 83 is connected to the throwing assembly and needs to be connected to the drive unit 81 through the anti-reverse mechanism 63. The anti-reverse mechanism 63 maintains unidirectional movement, that is, the anti-sway wire rope 83 can only be shortened and cannot be extended; during the throwing and deceleration recovery process, the drive unit 81 actively contracts the anti-sway wire rope 83 to keep it taut.

[0072] The motion process of the thrown component during the experiment is shown in the appendix. Figure 5 Initially, the thrown component 1 is at position 2, and the suspension rope is slack. At the moment of separation, the thrown component 1 falls freely to position 3, where the rope generates tension, and the thrown component 1 begins to decelerate. The allowed vertical free fall distance is h, and the horizontal movement distance is x, eventually reaching position 4, at which point the component's velocity in all directions must be reduced to 0. Figure 5 Points I and II are the fixing points of the vertical and horizontal suspension cables, respectively, and point III is the fixing point of the pendulum cable. After the test, the kinetic energy and gravitational potential energy of the thrown component are converted into the elastic potential energy of the rope, as shown in the following calculation formula. Here, the rope refers to the parallel elastic rope in the horizontal deceleration cable assembly (6) and the vertical deceleration cable assembly (7):

[0073]

[0074] In the formula, k is the stiffness of the parallel elastic rope, m is the mass of the thrown component, g is the gravitational acceleration, h is the vertical free fall distance of the thrown component, x is the horizontal movement distance, and v is the separation velocity. For different thrown components, the stiffness of the parallel elastic rope is designed according to the mass of the thrown component, the separation velocity, and the safe distance allowed for throwing in the test.

[0075] Example:

[0076] This embodiment provides a method for launching and testing spacecraft external components, including: test design stage, test preparation stage, test implementation stage, and test withdrawal stage.

[0077] 1. Experimental Design Stage

[0078] 1) First, confirm the mass characteristics, external dimensions, and available interfaces of the component to be thrown, such as... Figure 6 As shown, a hanger 11 is designed for the thrown component. The hanger 11 is connected to the external support 13 of the load chamber. The hanger 11 is equipped with a horizontal deceleration cable ring 14 and a vertical deceleration cable ring 12. The horizontal deceleration cable ring 14 also serves as an anti-swing cable ring. The mass deviation and center of gravity deviation between the load chamber and the hanger assembly and the load chamber do not exceed 5% to ensure the stability of the test process and the authenticity of the test results.

[0079] 2) Confirm the load-bearing capacity of the interface, and determine the length and stiffness of the rope by combining the horizontal or vertical distance that allows the launched component to move freely, as well as the horizontal and vertical distance that allows the launched component to decelerate; finally, confirm the test status of the products on the launched component, and restore the real state of the lunar launch component as much as possible while protecting the real product.

[0080] 3) Design a simulated component to be thrown, simulate the outer envelope and mass characteristics of the component to be thrown, and participate in the system debugging and pre-test before the formal test;

[0081] 4) Design a simulated ejection system, adopting a scheme of setting a spring separation mechanism at the separation interface between the ejected component and the simulated test specimen to achieve the separation effect of simulating the explosion of pyrotechnics;

[0082] 5) Design a simulation chamber that only simulates the installation interface with the component being launched, as well as the shape and dimensions of the vicinity of the component being launched;

[0083] 6) Place the simulation chamber in the test site, connect the simulation component to the simulation chamber, debug the test system, and verify the spring thrust through pre-test.

[0084] 2. Experimental Preparation Stage

[0085] 1) The test fixture needs to be tested with the actual component to be thrown in advance to confirm the interface compatibility. If mismatch occurs, the connectors are allowed to be repaired.

[0086] 2) Check the condition of the test product to confirm that the thrown components do not interfere with or snag on the chamber;

[0087] 3) Check and confirm the status of the pyrotechnics and separation device to ensure that the separation action can be completed during the test.

[0088] 3. Trial Implementation Phase

[0089] 1) Level spacecraft 4 to ensure that the levelness of cabin 4 meets the requirements;

[0090] 2) The spacecraft 4 is placed on the vertical parking bracket 5 as a whole. This can expand the movement space of the components, avoid collision between the thrown components 1 and the ground or cabin, and improve the safety and flexibility of the test.

[0091] 3) Transport the spacecraft and the vertical parking support assembly into the tower. The tower is equipped with a deceleration and recovery system. The gantry is equipped with vertical deceleration cable rings, horizontal deceleration cable rings, and anti-sway cable rings. The deceleration and recovery system is connected to the thrown sub-components through the rings.

[0092] 4) Pull the rope directly connected to the component being thrown away from the hull to the side away from the hull to prevent the rope from getting caught on the hull;

[0093] 5) After the cabin position is set, deploy the high-speed photogrammetry system and attach the target to the projectile component;

[0094] 6) Set the vertical deceleration cable to be slack in the initial state, with its elastic element located at the top of the tower; set the horizontal deceleration cable to be slack in the initial state, with its elastic element located at the rear of the tower; set the anti-sway cable to be taut in the initial state, apply a 10N taut force, and set the anti-sway cable to be located at the front of the tower.

[0095] 7) After issuing the separation command, the thrown component is thrown freely for a certain distance, then decelerates and finally hovers in the air.

[0096] 4. Trial withdrawal phase

[0097] 1) Inspect the appearance of the ejected components and the hull, and take photos to confirm that there is no damage;

[0098] 2) The component to be thrown is transported to the test site and placed in a suitable location;

[0099] 3) Adjust the rope to slowly lower the component to the ground foam pad and then separate the rope from the hanger;

[0100] 4) Remove the hanger and place the thrown component at its designated parking fixture location;

[0101] 5) The test chamber was removed from under the test tower and placed in the designated location;

[0102] 6) Organize other equipment and products at the test site, and finally interpret and confirm the measurement data to complete the test.

[0103] The parts of this invention not described in detail are common knowledge to those skilled in the art.

Claims

1. A spacecraft external component launch test system, characterized in that, include: The thrown component (1), the cabin (4), the platform (5), and the deceleration and recovery system; The thrown component (1) is installed on the cabin (4). Before the test, the cabin (4) is placed on a high platform (5) to ensure that the thrown component (1) has enough falling distance and operating space during the test to avoid collision. The thrown component (1) is connected to the deceleration and recovery system. After being unlocked and separated, the thrown component (1) performs a horizontal throwing motion and is only subject to gravity. The motion path is denoted as process A. The attitude and trajectory during the free fall process are captured by a high-speed camera. During process A, the deceleration and recovery system has no force on the thrown component. After moving to a certain point, it enters deceleration phase B. The position where deceleration takes effect is controlled by the length of the rope in the deceleration and recovery system. The traction between multiple ropes in the deceleration and recovery system provides tension to decelerate until the thrown component comes to a standstill and hangs in the air.

2. The spacecraft extravehicular component launch test system according to claim 1, characterized in that: The multi-cable recovery system includes a horizontal deceleration cable assembly (6), a vertical deceleration cable assembly (7), and a sway-stopping cable assembly (8); Both the horizontal deceleration cable assembly (6) and the vertical deceleration cable assembly (7) include an elastic element, a reverse-stopping mechanism, and a rope; the anti-sway cable assembly (8) includes a drive unit, a reverse-stopping mechanism, and a rope. All ropes are connected to the thrown component (1). The elastic element converts the kinetic energy and gravitational potential energy of the thrown component into elastic potential energy in one direction. At the same time, the anti-reverse mechanism prevents the elastic potential energy from being converted into kinetic energy. The drive unit actively contracts the rope of the anti-swing cable component (8) to keep it taut.

3. The spacecraft extravehicular component launch test system according to claim 2, characterized in that: The ropes of the horizontal deceleration cable assembly (6) and the anti-swing cable assembly (8) are connected to both sides of the thrown component, and the rope of the vertical deceleration cable assembly (7) is connected to the top of the thrown component.

4. A spacecraft extravehicular component launch test system according to claim 2 or 3, characterized in that: During the entire deceleration process, i.e. deceleration phase B, the resultant force of the rope passes through the center of mass of the thrown component to avoid generating an overturning moment.

5. The spacecraft extravehicular component launch test system according to claim 3, characterized in that: The horizontal deceleration cable assembly (6) and the vertical deceleration cable assembly (7) have the same structure, and their elastic elements are parallel elastic ropes (62); the anti-reverse mechanism (63) includes: a one-way slider (65) and an anti-reverse pawl (66); the rope is a deceleration wire rope (64); One end of the deceleration wire rope (64) is connected to the thrown component, and the other end is connected to the parallel elastic rope (62) after passing through the anti-reverse mechanism (63). The parallel elastic rope (62) gradually decelerates the component, eventually suspending it in the air. The anti-reverse mechanism (63) is used to limit and prevent the thrown component from rebounding. The one-way slider (65) and the anti-reverse pawl (66) are both installed on the frame structure of the anti-reverse mechanism (63). The one-way slider (65) limits the maximum deformation of the parallel elastic rope (62), and the anti-reverse pawl allows the deceleration wire rope (64) to move only in one direction.

6. The spacecraft extravehicular component launch test system according to claim 3, characterized in that: In the anti-swing cable assembly (8), the rope is the anti-swing wire rope (83); The anti-sway wire rope (83) is connected to the throwing assembly and is connected to the drive unit (81) through the anti-reverse mechanism (63). The anti-reverse mechanism (63) maintains unidirectional movement, that is, the anti-sway wire rope (83) can only be shortened and cannot be extended. During the throwing and deceleration recovery process, the drive unit (81) actively contracts the anti-sway wire rope (83) to keep it taut.

7. The spacecraft extravehicular component launch test system according to claim 3, characterized in that: After the test, the kinetic energy and gravitational potential energy of the thrown component are converted into the elastic potential energy of the rope, and the following calculation formula is given. Here, the rope refers to the parallel elastic rope in the horizontal deceleration rope assembly (6) and the vertical deceleration rope assembly (7). In the formula, k is the stiffness of the parallel elastic rope, m is the mass of the thrown component, g is the gravitational acceleration, h is the vertical free fall distance of the thrown component, x is the horizontal movement distance, and v is the separation velocity. For different thrown components, the stiffness of the parallel elastic rope is designed according to the mass of the thrown component, the separation velocity, and the safe distance allowed for throwing in the test.

8. A method for launching and testing spacecraft external components based on the spacecraft external component launch and testing system described in claim 1, characterized in that, include: The test consists of three phases: test design, test preparation, test implementation, and test withdrawal. Experimental design phase: (1) First, confirm the mass characteristics, external dimensions and available interfaces of the component to be thrown. Design a hanger (11) for the component to be thrown. The hanger (11) is connected to the external support (13) of the load chamber. The hanger (11) is equipped with horizontal deceleration cable rings (14) and vertical deceleration cable rings (12). The horizontal deceleration cable rings (14) also serve as anti-sway cable rings. The mass deviation and center of gravity deviation between the load chamber and the hanger assembly and the load chamber do not exceed 5%. (2) Confirm the load-bearing capacity of the interface, and combine the horizontal or vertical distance that allows the thrown component to move freely, as well as the horizontal and vertical distance that allows the thrown component to decelerate, to confirm the length and stiffness of the rope; (3) Design a simulated component of the thrown component to simulate the outer envelope and mass characteristics of the thrown component; (4) Design a simulated ejection system, and adopt a spring separation mechanism at the separation interface between the ejected component and the simulated test specimen to achieve the separation effect of simulating the explosion of pyrotechnics; (5) Design a simulation chamber that only simulates the installation interface with the component to be launched and the shape and size of the component to be launched; (6) Place the simulation chamber in the test site, connect the simulated component to the simulation chamber, debug the test system, and verify the spring thrust through the pre-test; Experiment preparation phase: (1) Confirm interface compatibility after assembly; (2) Check the status of the test product to confirm that the thrown components do not interfere with or hook up with the cabin; (3) Check and confirm the status of the pyrotechnics and separation device to ensure that the separation action can be completed during the test; Experimental implementation phase: (1) Level the spacecraft to ensure that the cabin levelness meets the requirements; (2) Place the entire spacecraft on a high platform to expand the movement space of the thrown components and avoid collisions between the thrown components and the ground or the cabin. The elevated platform is achieved using vertically mounted support frames. (3) Transport the spacecraft and vertical parking support assembly to the inside of the tower. A deceleration and recovery system is installed on the tower. Vertical deceleration cable rings, horizontal deceleration cable rings and anti-sway cable rings are installed on the gantry. The deceleration and recovery system is connected to the thrown sub-component through the rings. (4) Pull the rope directly connected to the thrown component away from the cabin to prevent the rope from getting caught on the cabin. (5) After the cabin position is set, a high-speed photogrammetry system is deployed and a target is attached to the projectile component; (6) Set the vertical deceleration cable to be relaxed in the initial state, with its elastic element located at the top of the tower; set the horizontal deceleration cable to be relaxed in the initial state, with its elastic element located at the rear of the tower; set the anti-sway cable to be stretched in the initial state, apply a stretching force of 10N, and set the anti-sway cable to be located at the front of the tower. (7) Issue a separation command, and the thrown component is thrown freely for a distance, then decelerates and finally hovers in the air; Trial withdrawal phase: (1) Inspect the appearance of the ejected components and the cabin, and take photos to confirm that there is no damage; (2) The tooling for parking the thrown components is transported to the test site and parked in a suitable position; (3) Adjust the rope to slowly lower the thrown component to the ground sponge pad and separate the rope from the hanger; (4) Remove the hanger and place the thrown component at its parking fixture location; (5) The cabin was removed from under the test tower and placed in the designated location; (6) Organize other equipment and products at the test site, and finally interpret the measurement data, confirm the validity of the measurement data, and complete the test.

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