A space deorbit damper

Abstract

The present invention relates to the field of space deorbit technology, and specifically to a space deorbit damper, comprising: a sail membrane, wherein the working states of the sail membrane include an expanded state and a contracted state; when the sail membrane is in the expanded state, the sail membrane is connected end to end to form a circumferentially closed shell with openings at both ends; a plurality of folds are provided on the circumference of the sail membrane, and the plurality of folds separate the sail membrane into a plurality of diaphragms; when the sail membrane is in the contracted state, the sail membrane is contracted to a point on the circumference of the shell by folding the diaphragms along the folds; a guide rail, wherein the guide rail corresponds to the circumferential shape of the shell, and the diaphragms are slidably connected to the guide rail; and a driver, which is connected to the diaphragm driving and is used to drive the diaphragm to move on the guide rail to realize switching of the working state of the sail membrane. By switching the working state of the sail membrane, the function of lowering the orbit is realized, and no inflation is required during the deployment of the sail membrane, thereby avoiding the risks of explosion and the like caused by the inflated ball-shaped damper.

Description

Technical Field

[0001] The present invention relates to the technical field of active space deorbiting, and in particular to a space spherical deorbiting damper. Background Art

[0002] As space activities and missions become more frequent, the problem of space debris and failed spacecraft is becoming increasingly serious, posing a threat to future space activities. Therefore, to mitigate space debris, protect the space environment, and enhance spacecraft mission flexibility, the deployment of deorbit sails has become necessary. To save fuel costs, automatically deploying damped deorbit structures is more practical and reduces reliance on spacecraft control systems.

[0003] Currently, space debris deorbiting devices are divided into two types: planar and inflatable spherical. Planar deorbiting devices have low drag efficiency and are prone to attitude instability when used on-orbit. Attitude control is required to adjust the windward surface of the deorbiting device according to the deorbit target to achieve effective deorbiting. Inflatable spherical devices require the use of high-pressure gas cylinders, which, due to the storage and release of high-pressure gas, carry a certain explosion risk.

[0004] Therefore, there is an urgent need to design a space deorbit damper to avoid the risks of explosion and other risks caused by the inflatable ball-shaped damper. Summary of the Invention

[0005] In order to overcome the deficiencies of the above-mentioned prior art, the present invention provides a space deorbit damper, which realizes the function of lowering the orbit by switching the working state of the sail membrane. The sail membrane does not need to be inflated during the deployment process, avoiding the risks of explosion and the like caused by the inflated spherical damper.

[0006] In order to achieve the above object, the present invention is implemented through the following technical solutions:

[0007] A space deorbit damper: comprising

[0008] The sail membrane has two working states: an expanded state and a contracted state. When the sail membrane is in the expanded state, the sail membrane is connected end to end to form a circumferentially closed shell. The sail membrane is provided with a plurality of folds on the circumference, and the folds separate the sail membrane into a plurality of membrane sheets. When the sail membrane is in the contracted state, the sail membrane is contracted to a point on the circumference of the shell by folding the membrane sheets along the folds.

[0009] A guide rail, the guide rail corresponds to the circumferential shape of the shell, and the diaphragm is slidably connected to the guide rail;

[0010] The driver is connected to the diaphragm driving device and is used to drive the diaphragm to move on the guide rail to achieve the switching of the sail membrane working state.

[0011] Furthermore, the present application discloses a spatial derailment damper in which adjacent folds are equally spaced and fold in opposite directions. The shell is open at both ends, and the folds extend through both ends. As a preferred embodiment of the present application, based on the above-mentioned structure, the folds are folded in a Z-shape. When the sail membrane is in the expanded state, adjacent membrane sheets are symmetrical, which helps evenly distribute pressure and prevents the shell from collapsing due to uneven force.

[0012] Furthermore, the space derailment damper of the present application further includes a pair of top covers, one of which covers covers the two open ends of the housing; and two guide rails, one of which is connected to the inner side of the pair of top covers. As a preferred embodiment of the present application, the top covers are circular and are used to connect to the derailment target.

[0013] Furthermore, the present application proposes a space derailment damper with a circular guide rail and an outwardly convex arc-shaped fold. As a preferred embodiment of the present application, based on the above-mentioned device, the diaphragm is crescent-shaped, and when the sail membrane is deployed, the overall shell is spherical. This can reduce posture constraints during derailment and improve the success rate of derailment operations.

[0014] Furthermore, the space derailment damper in the present application further includes a connecting device for connecting the two circumferential ends of the shell. As a preferred embodiment of the present application, the connecting device is used to connect a pair of diaphragms at the two circumferential ends of the shell.

[0015] Furthermore, in a space derailment damper disclosed herein, the connection device includes magnetic elements, which are arranged in pairs at the circumferentially connected ends of the housing. As a preferred embodiment of the present invention, when the sail membrane is deployed, the magnetic elements at both ends engage magnetically, automatically connecting the ends of the sail membrane.

[0016] Furthermore, in the present application, a space deorbit damper driver includes:

[0017] A spring, the spring elastically expands and contracts in the circumferential direction of the housing, the spring being connected to the diaphragm, and applying an elastic force to the diaphragm to move toward the expanded state;

[0018] A locking device, the locking device is used to prevent the spring from moving toward the expanded state when the sail membrane is in the retracted state;

[0019] An unlocking device is used to disable the locking device. As a preferred embodiment of this application, the above-mentioned device can be used to control the sail membrane from a retracted state to an extended state. When the sail membrane is in the retracted state, the locking device locks the spring to keep it retracted, thereby storing elastic potential energy. During use, an unlocking command is issued, the unlocking device is activated, the locking device is disabled, and the spring pushes the diaphragm to the extended state.

[0020] Furthermore, in a spatial derailment damper disclosed herein, the spring is an arc-shaped spring sleeved on a guide rail, the spring sleeved on the guide rail, and the diaphragm is connected to the ring body constituting the spring at equal intervals. As a preferred embodiment of the present application, the diaphragm is connected to the ring body constituting the spring at equal intervals to ensure circumferential uniformity of the diaphragm when in the deployed state.

[0021] Furthermore, in a space derailment damper in the present application, the locking device is a rope body, which restrains the movable end of the spring when locked; the unlocking device is a rope-breaking device, which is used to destroy the rope body to release the restraint of the rope body on the spring.

[0022] Furthermore, in the present application, a space derailment damper has a rope body made of Dyneema fiber and a rope-breaking device made of a fuse connected to the rope body. As a preferred embodiment of the present application, the fuse is electrically heated to melt the rope body to unlock the device.

[0023] It can be seen from the above technical solution that the present invention has the following beneficial effects:

[0024] The present invention provides a space deorbit damper, and the method of using the damper is as follows: the damper is arranged on the surface of a spacecraft or a space target to be deorbited with a sail membrane in a retracted state; once the mission is completed or a deorbit signal is issued, the driver is activated, the sail membrane is in an expanded state, and the aerodynamic resistance formed by the thin atmosphere in the low-orbit environment is used to gradually slow down the target and deviate from the original orbit. The folds also serve as a skeleton support, and the shell is lantern-shaped to enhance the stability of the shell. Therefore, the space deorbit damper in the present application draws on the structure of an origami lantern, does not rely on metal skeleton support, and has the advantages of light structure, low production cost, and simple processing. Attitude switching is achieved by spring expansion, which is a simple process, reduces the complexity of drive control, and has good reliability. At the same time, the spherical structural design avoids additional attitude control. In addition, the shell does not require complete sealing, which increases the selectivity of the sail membrane material. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 A schematic diagram of a space deorbit damper according to an embodiment of the present application (the sail membrane is in a retracted state);

[0026] Figure 2 A schematic diagram of a space deorbit damper according to an embodiment of the present application (the sail membrane is in an expanded state);

[0027] Figure 3 A schematic diagram of a space deorbit damper in an embodiment of the present application (the sail membrane is in the process of being deployed);

[0028] Figure 4 Schematic diagram of the connection device in an embodiment of the present application.

[0029] In the figure: 1-sail membrane; 10-housing; 11-fold; 12-diaphragm; 2-guide rail; 3-driver; 31-spring; 4-top cover; 5-magnetic element. DETAILED DESCRIPTION

[0030] Combine Figures 1 to 3 As shown, this embodiment provides a space deorbit damper, comprising:

[0031] The sail membrane 1 has two working states: an expanded state and a contracted state. When the sail membrane 1 is in the expanded state, the sail membrane 1 Figure 2 As shown, the sail membrane 1 is connected end to end to form a circumferentially closed shell 10; the sail membrane 1 is provided with a plurality of folds 11 on the circumference, and the plurality of folds 11 separate the sail membrane 1 into a plurality of membrane sheets 12; when the sail membrane 1 is in a contracted state, the combined Figure 1 As shown, the sail membrane 1 is folded and contracted along the fold 11 by the membrane sheet 12 at a point on the circumference of the shell 10;

[0032] The guide rail 2 corresponds to the circumferential shape of the housing 10, and the diaphragm 12 is slidably connected to the guide rail 2;

[0033] The driver is connected to the diaphragm 12 and is used to drive the diaphragm 12 to move on the guide rail 2 to achieve the switching of the working state of the sail membrane 1.

[0034] Based on the above structure, the present application discloses a space deorbit damper, wherein the damper is deployed on the surface of a spacecraft or a space target to be deorbited, with the sail membrane 1 in a retracted state. Once the mission is completed or a deorbit signal is issued, the actuator is activated, and the sail membrane 1 is deployed. The aerodynamic drag formed by the thin atmosphere in the low-orbit environment is utilized to gradually decelerate the target and derail it. The fold 11 also serves as a skeletal support, and the shell 10 is lantern-shaped to enhance its stability. In this embodiment, the number of diaphragms 12 is 40.

[0035] In this embodiment, adjacent folds 11 are spaced evenly apart and fold in opposite directions. The housing 10 is open at both ends, and the folds 11 extend through both ends. Based on this structure, the folds 11 form a Z-shaped fold. When the sail membrane 1 is deployed, adjacent membrane sheets 12 are symmetrical, which helps evenly distribute pressure and prevents the housing 10 from collapsing due to uneven force.

[0036] In this embodiment, a pair of top covers 4 are further included, each covering the two open ends of the housing 10. Two guide rails 2 are respectively connected to the inner sides of the pair of top covers 4. The top covers 4 are circular and are used to connect to the lowering target.

[0037] In this embodiment, the guide rail 2 is circular, and the fold 11 is convex and arc-shaped. Based on the above arrangement, the membrane 12 is crescent-shaped, and when the sail membrane 1 is deployed, the shell 10 is spherical. This reduces posture constraints during derailment and improves the success rate of derailment operations.

[0038] Combine Figure 4 As shown, in this embodiment, a connecting device is further included, and the connecting device is used to connect the two ends of the shell 10 that are connected in the circumferential direction. That is, the connecting device is used to connect a pair of diaphragms 12 at the two ends of the shell 10 in the circumferential direction. In this embodiment, the connecting device includes magnetic parts 5, and the magnetic parts 5 are arranged in pairs at the two ends of the shell 10 that are connected in the circumferential direction. When the sail membrane 1 is in the unfolded state, the magnetic parts 5 at both ends are magnetically attracted to achieve automatic connection of the head and tail of the sail membrane 1. In this embodiment, the magnetic parts 5 at both ends are permanent magnets. In other embodiments, the magnetic part 5 at one end is a permanent magnet, and the magnetic part 5 at the other end is magnetic metal.

[0039] In this embodiment, the actuator includes: a spring 31 that elastically expands and contracts in the circumferential direction of the housing 10. The spring 31 is connected to the diaphragm 12 and applies an elastic force toward the expanded state; a locking device that prevents the spring 31 from moving toward the expanded state when the sail 1 is in the retracted state; and an unlocking device that disables the locking device. Based on this device, the sail 1 can be controlled to switch from the retracted state to the expanded state. When the sail 1 is in the retracted state, the locking device locks the spring 31 to keep it retracted, thereby storing elastic potential energy. During use, an unlocking command is issued, the unlocking device is activated, the locking device is disabled, and the spring 31 pushes the diaphragm 12 to the expanded state.

[0040] In this embodiment, the spring 31 is an arc-shaped spring that is sleeved onto the guide rail 2. The diaphragm 12 is evenly spaced, one-on-one, and connected to the rings that comprise the spring 31. This evenly spaced, one-on-one connection ensures circumferential uniformity of the diaphragm 12 when deployed. In this embodiment, the locking device is a rope (not shown) that restrains the movable end of the spring 31 when locked. The unlocking device is a rope-breaking device that breaks the rope to release the restraint on the spring 31. Specifically, the rope is made of Dyneema fiber, and the rope-breaking device is a fuse (not shown) connected to the rope. The fuse heats the rope upon application of electricity, melting it and releasing the lock.

[0041] The technical principles of the present invention have been described above in conjunction with specific embodiments. These descriptions are intended solely to illustrate the principles of the present invention and are not to be construed in any way as limiting the scope of protection of the present invention. Based on the explanations herein, those skilled in the art will be able to conceive of other specific embodiments of the present invention without inventive effort, and such embodiments will fall within the scope of protection of the present invention.

Claims

1. A space de-orbit damper, characterized in that: include: A sail membrane (1), wherein the working state of the sail membrane (1) includes an expanded state and a contracted state; when the sail membrane (1) is in the expanded state, the sail membrane (1) is connected end to end to form a circumferentially closed shell (10); a plurality of folds (11) are provided on the circumference of the sail membrane (1), and the plurality of folds (11) separate the sail membrane (1) into a plurality of membrane sheets (12); when the sail membrane (1) is in the contracted state, the sail membrane (1) is folded and contracted to a point on the circumference of the shell (10) through the membrane sheets (12); A guide rail (2), the guide rail (2) corresponds to the circumferential shape of the housing (10), and the diaphragm (12) is slidably connected to the guide rail (2); A driver, the driver being in driving connection with the diaphragm (12), the driver being used to drive the diaphragm (12) to move on the guide rail (2) to achieve switching of the working state of the sail membrane (1); The driver includes: a spring (31), the spring (31) elastically expanding and contracting in the circumferential direction of the housing (10), the spring (31) being connected to the diaphragm (12), and the spring (31) applying an elastic force to the diaphragm (12) to move toward the expanded state; A locking device, the locking device being used to prevent the spring (31) from moving toward the expanded state when the sail membrane (1) is in the retracted state; an unlocking device, the unlocking device being used to disable the locking device; The spring (31) is an arc-shaped spring sleeved on the guide rail (2). The spring (31) is sleeved on the guide rail (2). The diaphragm (12) and the ring body constituting the spring (31) are connected one by one at equal intervals. The locking device is a rope body, which restrains the movable end of the spring (31) when locked; the unlocking device is a rope-breaking device, which is used to destroy the rope body to release the rope body from restraining the spring (31).

2. A space deorbit damper according to claim 1, characterized in that: Adjacent folds (11) are spaced at equal intervals, and the folds (11) are folded in opposite directions. Both ends of the shell (10) are open, and the folds (11) pass through the two open ends of the shell (10).

3. The space deorbit damper according to claim 2, characterized in that: It also includes a pair of top covers (4), which are respectively covered on the two open ends of the shell (10); the number of the guide rails (2) is 2, and the pair of guide rails (2) are respectively connected to the inner sides of the pair of top covers (4).

4. The space deorbit damper according to claim 1, characterized in that: The guide rail (2) is circular, and the fold (11) is convex and arc-shaped.

5. The space deorbit damper according to claim 1, characterized in that: It also includes a connecting device, which is used to connect the two ends of the shell (10) that are connected in the circumferential direction.

6. The space deorbit damper according to claim 5, characterized in that: The connecting device comprises magnetic members (5), which are arranged in pairs at two circumferentially connected ends of the housing (10).

7. The space deorbit damper according to claim 1, characterized in that: The rope body is a Dyneema fiber line, and the rope breaking device is a fuse connected to the rope body.

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