Elastic expansion type damping device, damping mechanism and spacecraft

Abstract

The invention relates to the technical field of spacecrafts, and discloses a projectile expansion type damping device, a damping mechanism and a spacecraft, and the projectile expansion type damping device comprises a sail film which forms a three-dimensional structure after being expanded; the elastic supporting ring is arranged along the edge of the sail film by a circle, the shape of the elastic supporting ring is matched with that of the edge of the sail film, and the elastic supporting ring has a curled state and an unfolded state; one end of the connecting rope is connected with the elastic supporting ring, and the other end is connected with an object to be deorbited; and the supporting ring locking part is used for locking the elastic supporting ring in the curled state and releasing the elastic supporting ring at a preset time so as to enable the elastic supporting ring to recover to the unfolded state. The sail film of the three-dimensional structure has low requirements on postures, so that the complexity of posture control is obviously reduced. The elastic supporting ring serves as a supporting mechanism in the elastic unfolding type damping device, the sail film can be unfolded by restoring the elastic supporting ring to the unfolding state, and the supporting mechanism is simple in structure, high in safety coefficient and beneficial to improving the efficiency of the damping device and reducing the cost.

Description

Technical Field

[0001] The present disclosure relates to the field of spacecraft technology, for example, to a spring-type damping device, a damping mechanism and a spacecraft. Background Art

[0002] With the continuous increase of space exploration activities, the number of spacecraft launched into Earth orbit has increased dramatically. However, many spacecraft are not equipped with effective deorbit systems after completing their scheduled missions, resulting in these failed spacecraft and debris being stranded in space for a long time. This phenomenon not only increases the risk of collision with other high-value spacecraft, but may also further aggravate the problem of space debris, threatening the safety and sustainability of future space missions.

[0003] In order to meet the deorbiting requirements of spacecraft, the spacecraft in the related technology is equipped with a damping device. The damping devices in the related technology include two types: planar structure and three-dimensional structure. The damping device with a planar structure adopts a sail membrane that unfolds into a planar shape. This damping device has the characteristics of light weight, simple structure and low cost, but it requires attitude control. The planar sail membrane is perpendicular to the speed direction of the spacecraft to effectively increase the resistance area and realize the deorbiting and deorbiting operations of the spacecraft. The damping device with a three-dimensional structure needs to have a supporting mechanism, but the structure of the supporting mechanism in the related technology is relatively complex or has certain dangers. It can be seen that the damping devices in the related technology either rely on complex attitude control or have complex and dangerous supporting mechanisms, resulting in low application efficiency and high cost. Summary of the invention

[0004] In order to provide a basic understanding of some aspects of the disclosed embodiments, a brief summary is given below. The summary is not an extensive review, nor is it intended to identify key / critical components or delineate the scope of protection of these embodiments, but rather serves as a prelude to the detailed description that follows.

[0005] The embodiments of the present disclosure provide an elastic damping device, a damping mechanism and a spacecraft, which can reduce the complexity of attitude control, simplify the complexity of the structure and improve safety.

[0006] According to a first aspect of the present disclosure, there is provided an elastic damping device, the elastic damping device comprising:

[0007] The sail membrane forms a three-dimensional structure after unfolding;

[0008] An elastic support ring is arranged along the edge of the sail membrane, the shape of the elastic support ring matches the edge of the sail membrane, and the elastic support ring has a curled state and an unfolded state;

[0009] A connecting rope, one end of which is connected to the elastic support ring, and the other end is used to connect to the object to be derailed;

[0010] A support ring locking part is used to lock the elastic support ring in a curled state and release the elastic support ring at a preset time so that it returns to an unfolded state.

[0011] In some embodiments, the support ring locking part includes a first rope and a first rope cutter. The rope binds the elastic support ring in a curled state.

[0012] The first rope cutter is arranged on the first rope and is used to cut the first rope at a preset time to release the elastic support ring, so that the elastic support ring returns to an unfolded state.

[0013] In some embodiments, the curled state of the elastic support ring is the state when the elastic support ring is deformed into a parallel double-strand wire and then coiled to form a spiral structure.

[0014] In some embodiments, the head and the outermost coil of the spiral structure are bound to the same first rope, and the tail and the innermost coil of the spiral structure are bound to the same first rope. Each first rope is provided with a first rope cutter.

[0015] In some embodiments, a hollow annular hose conforming to the edge of the sail film is arranged at the edge of the sail film. The shape of the elastic support ring fits the shape of the hollow annular hose, and the elastic support ring is arranged inside the hollow annular hose.

[0016] According to a second aspect of the present disclosure, a damping mechanism is provided. The damping mechanism includes:

[0017] The elastic-expansion damping device provided by the first aspect of the present disclosure;

[0018] An encapsulation box has a closed state and an open state. The encapsulation box in the closed state is used to accommodate the elastic-expansion damping device, and the elastic-expansion damping device is exposed after the encapsulation box becomes the open state. Among them, when the elastic-expansion damping device is located inside the encapsulation box in the closed state, the support ring locking part locks the elastic support ring in a curled state.

[0019] An encapsulation box locking part is used to lock the encapsulation box in the closed state and unlock the encapsulation box at a preset time so that it changes to the open state.

[0020] In some embodiments, the encapsulation box includes a top plate, a bottom plate and a plurality of side plates. One edge of the top plate is hinged to the edge of one side plate, and one edge of each side plate is hinged to one edge of the bottom plate.

[0021] In some embodiments, the damping mechanism further includes an auxiliary unfolding member, and each side plate is provided with an auxiliary unfolding member; the auxiliary unfolding member is used to drive the side plate to rotate relative to the bottom plate when the encapsulation box locking part unlocks the encapsulation box, so that the encapsulation box changes to the open state.

[0022] In some embodiments, the damping mechanism further comprises an ejection member disposed on the bottom plate of the packaging box; the ejection member contacts the elastic damping device in the closed packaging box, and is used to drive the elastic damping device away from the packaging box when the packaging box is changed to an open state.

[0023] In some embodiments, the packaging box locking portion includes a second rope and a second rope breaker, the second rope binds the packaging box in a closed state; the second rope breaker is arranged on the second rope and is used to break the second rope at a preset time to transform the packaging box into an open state.

[0024] According to a third aspect of the present disclosure, a spacecraft is provided, the spacecraft comprising the elastic damping device provided by the first aspect of the present disclosure, or the damping mechanism provided by the second aspect of the present disclosure.

[0025] The elastic damping device provided in the embodiment of the present disclosure can achieve the following technical effects:

[0026] The sail membrane of the elastic damping device forms a three-dimensional structure after being unfolded. The sail membrane of the three-dimensional structure has low requirements for posture, thereby significantly reducing the complexity of posture control. In the initial state of the elastic damping device, the support ring locking part locks the elastic support ring in a curled state, and the sail membrane is folded into a smaller form. When the object to be de-orbited has a need to descend or de-orbit, the support ring locking part releases the elastic support ring to restore it to the unfolded state. The elastic support ring in the unfolded state can open the edge of the sail membrane so that air can enter the sail membrane, so that the sail membrane unfolds and forms a three-dimensional structure. The sail membrane of the three-dimensional structure can generate aerodynamic resistance with the thin atmosphere in the low-orbit environment, so that the object to be de-orbited gradually slows down and leaves the original orbit. The elastic support ring is used as the support mechanism in the elastic damping device. The sail membrane can be opened by restoring the elastic support ring to the unfolded state. This support mechanism has a simple structure and a high safety factor, which helps to improve the efficiency of the damping device and reduce costs.

[0027] The foregoing general description and the following description are exemplary and explanatory only and are not intended to limit the present disclosure. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] One or more embodiments are exemplarily described by corresponding drawings, which do not limit the embodiments. Elements with the same reference numerals in the drawings are shown as similar elements, and the drawings do not constitute a scale limitation, and wherein:

[0029] Figure 1 is a schematic diagram of an elastic damping device in an expanded state provided by an embodiment of the present disclosure;

[0030] Figure 2 The embodiment of the present disclosure provides Figure 1Cross-sectional view of the expandable damping device shown;

[0031] Figure 3 This is provided by an embodiment of the present disclosure Figure 2 Partial enlarged view at position A in;

[0032] Figure 4 Schematic assembly diagram of an elastic support ring and a support ring locking part in a curled state provided by an embodiment of the present disclosure;

[0033] Figure 5 This is provided by an embodiment of the present disclosure Figure 4 Partial enlarged view at position B in;

[0034] Figure 6 Schematic structural diagram of a packaging box in a closed state provided by an embodiment of the present disclosure;

[0035] Figure 7 Schematic structural diagram of a packaging box in an open state provided by an embodiment of the present disclosure;

[0036] Figure 8 Schematic diagram of the process of the expandable damping device expanding after the packaging box provided by the embodiment of the present disclosure is converted to the open state.

[0037] The descriptions of the attached reference numerals are as follows:

[0038] 100 Expandable damping device;

[0039] 1 Sail film, 11 Hollow annular hose;

[0040] 2 Elastic support ring, 3 Connecting rope;

[0041] 4 Support ring locking part, 41 First rope, 42 First rope breaker;

[0042] 200 Packaging box, 5 Top plate, 6 Bottom plate, 7 Side plate;

[0043] 300 Packaging box locking part, 8 Second rope, 9 Second rope breaker;

[0044] 400 Auxiliary expansion part, 500 Ejection part. Detailed implementation manners

[0045] In order to be able to understand the features and technical content of the embodiments of the present disclosure in more detail, the implementation of the embodiments of the present disclosure will be described in detail below with reference to the accompanying drawings. The attached drawings are only for reference and explanation purposes and are not used to limit the embodiments of the present disclosure. In the following technical descriptions, for the sake of explanation, multiple details are provided to provide a full understanding of the disclosed embodiments. However, one or more embodiments can still be implemented without these details. In other cases, well-known structures and devices can be shown in a simplified manner.

[0046] In the description and claims of the embodiments of the present disclosure and the above-mentioned drawings, terms such as "first" and "second" are used to distinguish similar objects and do not necessarily describe a specific order or sequence. It should be understood that the data used in this way can be interchanged under appropriate circumstances so as to implement the embodiments of the present disclosure described herein. In addition, the terms "comprising" and "having" and any variations thereof are intended to cover non-exclusive inclusion.

[0047] Unless otherwise specified, the term "plurality" means two or more.

[0048] In the embodiments of the present disclosure, the character " / " indicates that the objects before and after are in an "or" relationship. For example, A / B means: A or B.

[0049] The term "and / or" is an associative relationship describing an object and indicates that three relationships can exist. For example, A and / or B means: A or B, or, the three relationships of A and B.

[0050] The term "corresponding" may refer to an associative relationship or a binding relationship. A corresponding to B means that there is an associative relationship or a binding relationship between A and B.

[0051] Combined with FIGS. 1 to Figure 5 As shown, the embodiments of the present disclosure provide a telescopic damping device 100, and the telescopic damping device 100 includes a sail film 1, an elastic support ring 2, a connecting rope 3, and a support ring locking portion 4.

[0052] After the sail film 1 is unfolded, a three-dimensional structure is formed, and the shape of this three-dimensional structure can be determined according to actual design requirements. For example, after the sail film 1 is unfolded, it forms an approximately spherical structure with an opening, and the edge of the sail film 1 serves as the edge of the opening. The sail film 1 of the three-dimensional structure has low requirements for attitude, thus significantly reducing the complexity of attitude control.

[0053] The elastic support ring 2 is arranged along the edge of the sail film 1 for one week, and the shape of the elastic support ring 2 fits the edge of the sail film 1. The elastic support ring 2 has a curled state and an unfolded state. Optionally, a hollow annular hose 11 conforming to the shape of the edge of the sail film 1 is arranged at the edge of the sail film 1, the shape of the elastic support ring 2 fits the shape of the hollow annular hose 11, and the elastic support ring 2 is arranged inside the hollow annular hose 11. One end of the connecting rope 3 is connected to the elastic support ring 2, and the other end of the connecting rope 3 is used to connect the object to be deorbited. The support ring locking portion 4 is used to lock the elastic support ring 2 in the curled state and release the elastic support ring 2 at a preset time to restore it to the unfolded state.

[0054] The elastic damping device 100 provided in the embodiment of the present disclosure can be connected to the object to be de-orbited through the connecting rope 3. The object to be de-orbited here can be a normal aircraft that has completed a low-orbit space mission, or it can be a space debris of a spacecraft. In the initial state of the elastic damping device 100, the support ring locking part 4 locks the elastic support ring 2 in a curled state, and the sail membrane 1 is folded into a smaller form. When the object to be de-orbited has a need to descend or de-orbit, the support ring locking part 4 releases the elastic support ring 2 to restore it to the unfolded state. The elastic support ring 2 in the unfolded state can open the edge of the sail membrane 1 so that air can enter the sail membrane 1, so that the sail membrane 1 is unfolded and forms a three-dimensional structure. The sail membrane 1 of the three-dimensional structure can generate aerodynamic resistance with the thin atmosphere in the low-orbit environment, so that the object to be de-orbited gradually slows down and leaves the original orbit. The elastic support ring 2 is used as the support mechanism in the elastic damping device 100, and the sail membrane 1 can be opened by restoring the elastic support ring 2 to the unfolded state. This support mechanism has a simple structure and a high safety factor, which helps to improve the efficiency of the damping device and reduce costs.

[0055] In the embodiment of the present disclosure, Figure 1 As shown, after the sail membrane 1 is unfolded, it forms an approximately spherical structure with an open opening. This sail membrane 1 does not need to be completely closed, which expands the material selection of the sail membrane 1. The way of unfolding the sail membrane 1 is simple and easy, which improves the reliability and impact resistance of the unfolding process.

[0056] In some embodiments, the sail membrane 1 is formed by splicing a plurality of membrane sheets. For example, the sail membrane 1 can be formed by splicing 12 membrane sheets. The material of the sail membrane 1 has high temperature resistance and chemical resistance, for example, the material of the sail membrane 1 can be brown polyimide material.

[0057] In some embodiments, in combination Figure 4 and Figure 5 As shown, the support ring locking part 4 includes a first rope 41 and a first rope breaker 42, and the rope is bound to the elastic support ring 2 in a curled state. The first rope breaker 42 is arranged on the first rope 41, and is used to break the first rope 41 at a preset time to release the elastic support ring 2, so that the elastic support ring 2 returns to the unfolded state.

[0058] The first rope breaker 42 is installed on the first rope 41, and can accurately cut the first rope 41 at a preset operation time, thereby releasing the elastic support ring 2. Once the first rope 41 is cut, the elastic support ring 2 returns to its designed unfolded state, effectively expanding the sail membrane 1 and forming a three-dimensional structure.

[0059] In the disclosed embodiment, the first rope 41 may be made of fiber, and the fiber may be a material such as aramid, ultra-high molecular weight polyethylene, etc. These materials have an extremely high strength-to-weight ratio and can maintain good performance under extreme conditions.

[0060] In the embodiments of the present disclosure, the first rope cutter 42 is configured to cut the first rope 41. The first rope cutter 42 can be a hot knife, a mechanical cutting device, an electromagnetic cutting device, or the like.

[0061] A hot knife refers to a tool that uses the principle of electric heating to heat the blade to a high temperature, thereby being able to melt or cut materials. The hot knife generates heat through an electric current passing through a resistance wire, raising the temperature of the blade to a level sufficient to melt or burn through the first rope 41, thus achieving the cutting of the first rope 41 to release the elastic support ring 2.

[0062] The mechanical cutting device can be a blade - type cutting mechanism, which can act quickly at a predetermined time point through spring loading or other means to cut the first rope 41, thus achieving the cutting of the first rope 41 to release the elastic support ring 2.

[0063] The electromagnetic driving device can use devices such as electromagnets. After being powered on, it generates sufficient force to pull a cutting tool to cut the first rope 41, thus achieving the cutting of the first rope 41 to release the elastic support ring 2.

[0064] In some embodiments, the coiled state of the elastic support ring 2 is the state when the elastic support ring 2 is deformed into a parallel double - strand wire and then coiled to form a helical structure. Since the elastic support ring 2 is initially deformed in the form of a parallel double - strand wire, it ensures a uniform stress distribution during the unfolding process of the elastic support ring 2, thereby increasing the success rate of its restoration to the original state and ensuring that the sail film 1 can be unfolded correctly and completely. The compact helical structure allows the elastic support ring 2 to be compressed into a smaller volume, which not only saves load space but also facilitates the storage and transportation of the elastic support ring 2.

[0065] In some embodiments, in combination Figure 4 and Figure 5 As shown, the elastic expansion damping device 100 includes two support ring locking parts 4, and each support ring locking part 4 includes a first rope 41 and a first rope cutter 42. The head and the outermost coil of the helical structure are bound to the same first rope 41, and the tail and the innermost coil of the helical structure are bound to the same first rope 41. Each first rope 41 is provided with a first rope cutter 42. Support ring locking parts 4 are provided at the head and the tail of the helical structure respectively, ensuring that when the first rope cutter 42 is activated and cuts the first rope 41, the elastic support ring 2 can start to be untied simultaneously from both the head and the tail ends. This can ensure that the entire elastic support ring 2 unfolds in a more uniform and stable manner, avoiding twisting or jamming phenomena caused by one end being untied first.

[0066] The embodiments of the present disclosure provide a damping mechanism. As shown in combination Figures 6 to 8 with, the damping mechanism includes an encapsulation box 200, an encapsulation box locking part 300, and the elastic expansion damping device 100 provided in the above - mentioned embodiments.

[0067] The packaging box 200 has a closed state and an open state. The closed packaging box 200 is used to accommodate the elastic damping device 100. When the packaging box 200 is changed to the open state, the elastic damping device 100 is exposed. When the elastic damping device 100 is located inside the closed packaging box 200, the support ring locking part 4 locks the elastic support ring 2 in the curled state. The packaging box locking part 300 is used to lock the packaging box 200 in the closed state, and unlock the packaging box 200 at a preset time to change it to the open state.

[0068] The packaging box 200 is designed to have two modes, a closed state and an open state, to meet the needs of different stages of the object to be de-orbited. During the launch and initial orbital operation of the object to be de-orbited, the packaging box locking part 300 locks the packaging box 200 in a closed state. At this time, the packaging box 200 acts as a protective shell to safely accommodate the elastic damping device 100. At this time, the support ring locking part 4 of the elastic damping device 100 locks the elastic support ring 2 in a curled state. This closed state not only protects the internal components from vibration and impact during the launch process, but also prevents accidental deployment at inappropriate times. When the object to be de-orbited reaches a predetermined de-orbit or de-orbiting time, the packaging box locking part 300 unlocks the packaging box 200 so that the packaging box 200 is converted from a closed state to an open state through a preset mechanism, thereby exposing the internal elastic damping device 100. Specifically, in a closed state, the support ring locking part 4 firmly locks the elastic support ring 2 in its curled state to ensure its stability and safety. Once the packaging box 200 is transformed into an open state, the support ring locking portion 4 (such as the first rope breaker 42) will be activated at a specified time to release the elastic support ring 2, so that it can quickly return to the pre-designed three-dimensional structure to generate aerodynamic resistance with the thin atmosphere in the low-orbit environment, thereby helping the object to be de-orbited to gradually slow down and leave the original orbit.

[0069] In some embodiments, in combination Figure 6 and Figure 7As shown, the packaging box 200 includes a top plate 5, a bottom plate 6 and a plurality of side plates 7, an edge of the top plate 5 is hinged to an edge of a side plate 7, and an edge of each side plate 7 is hinged to an edge of the bottom plate 6. In a closed state, the top plate 5, the bottom plate 6 and each side plate 7 are tightly combined together to form a complete packaging box 200 to protect the internal elastic damping device 100. In order to maintain the closed state, the packaging box locking part 300 (such as the second rope 8 and the second rope breaker 9) will fix these components together to prevent the packaging box 200 from accidentally opening. When the derailment procedure needs to be initiated when the object to be derailed, the packaging box locking part 300 will be activated at a preset time. At this time, the second rope breaker 9 cuts off the second rope 8 to release the constraints on various parts of the packaging box 200. Once the constraint is released, the top plate 5 and the side plates 7 of the packaging box 200 are flipped based on the hinged position until the top plate 5, the bottom plate 6 and the side plates 7 of the packaging box 200 are fully unfolded, so that the packaging box 200 is transformed into an open state, and the support ring locking part 4 (such as the first rope breaker 42) is activated at a specified time to release the elastic support ring 2, so that it can quickly return to the pre-designed three-dimensional structure, so as to generate aerodynamic resistance with the thin atmosphere in the low-orbit environment, and help the object to be de-orbited to gradually slow down and leave the original orbit.

[0070] In some embodiments, in combination Figure 6 and Figure 7 As shown, the damping mechanism further includes an auxiliary unfolding member 400, and each side plate 7 is provided with an auxiliary unfolding member 400. The auxiliary unfolding member 400 is used to drive the side plate 7 to rotate relative to the bottom plate 6 when the packaging box locking part 300 unlocks the packaging box 200, so that the packaging box 200 is transformed into an open state. The auxiliary unfolding member 400 can be started immediately after the packaging box 200 is unlocked, and the side plate 7 is driven to rotate relative to the bottom plate 6 so that each side plate 7 is unfolded outward in an orderly manner. This ensures that the entire conversion process is smooth and fluent, and avoids any potential mechanical problems or damage risks caused by sudden opening or asymmetric opening.

[0071] In the disclosed embodiment, the auxiliary unfolding member 400 may be an elastic member (such as a spring). One end of the auxiliary unfolding member 400 is fixed to the body of the object to be derailed, and the other end is connected to the corresponding side plate 7. When the packaging box 200 is in a closed state, the auxiliary unfolding member 400 is in an extended state. After the packaging box 200 is unlocked, the auxiliary unfolding member 400 can drive the side plate 7 to rotate relative to the bottom plate 6 under the action of elastic force, so that the packaging box 200 is transformed from a closed state to an open state.

[0072] In some embodiments, in combination Figure 7 and Figure 8As shown, the damping mechanism further includes an ejection member 500, which is disposed on the bottom plate 6 of the packaging box 200. The ejection member 500 contacts the elastic damping device 100 in the closed packaging box 200, and is used to drive the elastic damping device 100 away from the packaging box 200 when the packaging box 200 is transformed into the open state.

[0073] The ejection member 500 can provide a thrust or elastic force at the moment when the packaging box 200 is opened, so as to prompt the elastic damping device 100 to quickly detach from the packaging box 200. By using the ejection member 500 to quickly push the elastic damping device 100 out of the packaging box 200, it is possible to effectively avoid the situation where the sail film 1 or other components are entangled or stuck with the internal structure of the packaging box 200, thereby ensuring that the elastic damping device 100 can be deployed according to the predetermined design.

[0074] In the disclosed embodiment, the ejection member 500 may be an elastic member (such as a spring). One end of the ejection member 500 is fixed to the bottom plate 6, and the other end is in contact with the elastic damping device 100 in the folded state. When the packaging box 200 is in the closed state, the ejection member 500 is in the extended state. The ejection member 500 can drive the elastic damping device 100 away from the packaging box 200 when the packaging box 200 is converted to the open state.

[0075] In some embodiments, the packaging box locking part 300 includes a second rope 8 and a second rope breaker 9. The second rope 8 binds the packaging box 200 in the closed state. The second rope breaker 9 is provided on the second rope 8 and is used to break the second rope 8 at a preset time to transform the packaging box 200 to the open state.

[0076] The second rope breaker 9 is installed on the second rope 8, and can accurately cut the second rope 8 at a preset operation time, thereby releasing the elastic support ring 2. Once the second rope 8 is cut, the elastic support ring 2 returns to its designed unfolded state, effectively stretching the sail membrane 1 and forming a three-dimensional structure.

[0077] In the disclosed embodiment, the second rope 8 may be made of fibers, and the fibers may be materials such as aramid, ultra-high molecular weight polyethylene, etc. These materials have extremely high strength-to-weight ratios and can maintain good performance under extreme conditions.

[0078] In the disclosed embodiment, the second rope breaker 9 has the function of breaking the second rope 8. The second rope breaker 9 can be a hot knife, a mechanical cutting device, an electromagnetic cutting device, or the like.

[0079] A hot knife refers to a tool that uses the principle of electric heating to heat the blade to a high temperature, enabling it to melt or cut materials. The hot knife generates heat by passing an electric current through a resistance wire, raising the temperature of the blade to a level sufficient to melt or burn through the second rope 8, thereby disconnecting the second rope 8 and causing the packaging box 200 to change from a closed state to an open state.

[0080] The mechanical cutting device can be a blade-type cutting mechanism that can act quickly at a predetermined time point through spring loading or other means to cut the second rope 8, thereby disconnecting the second rope 8 and causing the packaging box 200 to change from a closed state to an open state.

[0081] The electromagnetic drive device can use devices such as electromagnets to generate sufficient force after being energized to pull the cutting tool to cut the second rope 8, thereby disconnecting the second rope and causing the packaging box 200 to change from a closed state to an open state.

[0082] The embodiments of the present disclosure provide a spacecraft that includes the damping mechanism provided in the above embodiments. When the expandable damping device 100 is disposed inside the packaging box 200 in a closed state, one end of the connecting rope 3 of the expandable damping device 100 is connected to the elastic support ring 2, and the other end of the connecting rope 3 can pass through the packaging box 200 and be connected to the object to be deorbited. Optionally, the packaging box 200 is provided with a through hole, for example, a through hole is provided in the bottom plate 6, and the end of the connecting rope 3 passes through the through hole and is connected to the spacecraft. Optionally, there is a gap between two adjacent plate members of the packaging box 200 (such as the bottom plate 6 and a side plate 7), and the end of the connecting rope 3 passes through the gap and is connected to the spacecraft.

[0083] In some embodiments, the expandable damping device further includes a control module (not shown in the figure), and the control module can control the drive mechanism to drive a plurality of capture actuators to capture the target. The control module includes a processor and a memory. Optionally, the control module may further include a communication interface and a bus. Among them, the processor, the communication interface, and the memory can complete mutual communication through the bus. The communication interface can be used for information transmission. The processor can call the logical instructions in the memory to control the support ring locking portion to release the elastic support ring at a preset time to restore it to the expanded state, and control the packaging box locking portion to unlock the packaging box at a preset time to cause it to change to an open state.

[0084] In addition, when the logic instructions in the above-mentioned memory are implemented in the form of software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. As a computer-readable storage medium, the memory can be used to store software programs and computer-executable programs, such as the program instructions / modules corresponding to the methods in the embodiments of the present disclosure. By running the program instructions / modules stored in the memory, the processor executes functional applications and data processing, that is, controls the elastic support ring locking part to release the elastic support ring at a preset time so that it returns to the unfolded state, and controls the packaging box locking part to unlock the packaging box at a preset time so that it changes to the open state.

[0085] The memory may include a program storage area and a data storage area. Among them, the program storage area may store an operating system and application programs required for at least one function; the data storage area may store data created according to the use of the terminal device, etc. In addition, the memory may include high-speed random access memory and may also include non-volatile memory.

[0086] The device embodiments described above are merely illustrative. For example, the division of the units may be only a logical function division. In actual implementation, there may be other division methods. For example, multiple units or components may be combined or integrated into another system, or some features may be ignored or not executed. In addition, the displayed or discussed mutual coupling, direct coupling, or communication connection may be through some interfaces. The indirect coupling or communication connection of the devices or units may be in electrical, mechanical, or other forms. The units described as separate components may or may not be physically separated. The components displayed as units may or may not be physical units, that is, they may be located in one place or distributed to multiple network units. Some or all of the units can be selected according to actual needs to implement this embodiment. In addition, in the embodiments of the present disclosure, the functional units may be integrated in one processing unit, or each unit may exist physically alone, or two or more units may be integrated in one unit.

Claims

1. A spring-type damping device, characterized in that: include: The sail membrane forms a three-dimensional structure after unfolding; An elastic support ring is arranged along the edge of the sail membrane, the shape of the elastic support ring matches the edge of the sail membrane, and the elastic support ring has a curled state and an unfolded state; A connecting rope, one end of which is connected to the elastic support ring, and the other end is used to connect to the object to be derailed; The support ring locking portion is used to lock the elastic support ring in a curled state and release the elastic support ring at a preset time to restore it to an unfolded state.

2. The elastic damping device according to claim 1, characterized in that: The support ring locking part includes a first rope and a first rope breaker, and the rope is bound to the elastic support ring in a curled state; The first rope breaker is arranged on the first rope, and is used for breaking the first rope at a preset time to release the elastic support ring, so that the elastic support ring returns to the unfolded state.

3. The elastic damping device according to claim 2, characterized in that: The curled state of the elastic support ring is the state when the elastic support ring is deformed into a parallel double-stranded wire and then coiled to form a spiral structure.

4. The elastic damping device according to claim 3, characterized in that: The head and the outermost coil of the spiral structure are bound to the same first rope, and the tail and the innermost coil of the spiral structure are bound to the same first rope. Each first rope is provided with a first rope breaker.

5. The elastic damping device according to claim 1, characterized in that: The edge of the sail membrane is provided with a hollow annular hose conforming to the shape of the sail membrane. The shape of the elastic support ring matches the shape of the hollow annular hose. The elastic support ring is arranged inside the hollow annular hose.

6. A damping mechanism, characterized in that: include: The elastic damping device according to any one of claims 1 to 5; The packaging box has a closed state and an open state. The closed state packaging box is used to accommodate the elastic damping device. When the packaging box is changed to the open state, the elastic damping device is exposed. When the elastic damping device is located inside the closed state packaging box, the support ring locking part locks the elastic support ring in a curled state. The packaging box locking part is used to lock the packaging box in a closed state and unlock the packaging box at a preset time to change it to an open state.

7. The damping mechanism according to claim 6, characterized in that: The packaging box comprises a top plate, a bottom plate and a plurality of side plates, one edge of the top plate is hinged to an edge of a side plate, and one edge of each side plate is hinged to an edge of the bottom plate.

8. The damping mechanism according to claim 7, characterized in that: It also includes an auxiliary deployment piece, and each side panel is provided with an auxiliary deployment piece; The auxiliary unfolding member is used for driving the side plate to rotate relative to the bottom plate when the packaging box locking unit unlocks the packaging box, so that the packaging box is transformed into an open state.

9. The damping mechanism according to claim 7, characterized in that: It also includes an ejection member, which is arranged on the bottom plate of the packaging box; The ejection member contacts the elastic damping device in the closed packaging box, and is used to drive the elastic damping device away from the packaging box when the packaging box is changed to the open state.

10. The damping mechanism according to claim 6, characterized in that: The packaging box locking part includes a second rope and a second rope breaker, and the second rope binds the packaging box in a closed state; The second rope breaker is arranged on the second rope and is used for breaking the second rope at a preset time to change the packaging box to an open state.

11. A spacecraft, characterized in that: It comprises the elastic damping device as described in any one of claims 1 to 5, or the damping mechanism as described in any one of claims 6 to 10.

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