Space deorbit damper

Abstract

The invention relates to the technical field of space deorbiting, in particular to a space deorbiting damper which comprises a sail film, and the working state of the sail film comprises an unfolded state and a contracted state; when the sail film is in an unfolded state, the sail film is connected end to end to form a circumferentially closed shell with two open ends; a plurality of creases are arranged in the circumferential direction of the sail membrane and divide the sail membrane into a plurality of membrane sheets; when the sail film is in a contraction state, the sail film is folded and contracted to one position in the circumferential direction of the shell through the diaphragm along the folding marks; the guide rail corresponds to the circumferential shape of the shell, and the diaphragm is connected to the guide rail in a sliding mode; and the driver is in driving connection with the diaphragm, and the driver is used for driving the diaphragm to move on the guide rail so as to realize switching of working states of the sail diaphragm. The rail descending function is achieved by switching the working state of the sail membrane, inflation is not needed in the unfolding process of the sail membrane, and the risks such as explosion caused by an inflatable spherical damper are avoided.

Description

Technical Field

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

[0002] As space activities and missions become more frequent, the problem of space debris or failed spacecraft is becoming increasingly serious, posing a certain threat to future space activities. Therefore, in order to mitigate space debris, protect the good space environment, and improve the flexibility of spacecraft missions, the configuration of deorbit sails has become necessary. In order to save fuel costs, the automatically deployed damping deorbit structure is more practical and reduces the dependence on the spacecraft control system.

[0003] At present, the deorbiting devices for space debris are divided into planar structures and inflatable spherical structures. The drag efficiency of the planar deorbiting structure is low, and it is very easy to have the risk of attitude instability when used in orbit. Attitude control is required to adjust the windward surface of the deorbiting device according to the needs of the deorbiting target to achieve effective deorbiting; the inflatable spherical structure needs to load high-pressure gas cylinders, and there is a certain risk of explosion due to the storage and release of high-pressure gas.

[0004] Therefore, there is an urgent need to design a space deorbit damper to avoid the risks of explosion and the like caused by the inflatable spherical damper. Summary of the invention

[0005] In order to overcome the deficiencies of the above-mentioned prior art, the present invention provides a space de-orbit 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, thus 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: A space de-orbit damper: comprising The sail membrane has a working state including 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. A plurality of folds are arranged on the circumference of the sail membrane, and the plurality of 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. A guide rail, the guide rail corresponds to the circumferential shape of the shell, and the diaphragm is slidably connected to the guide rail; The driver is connected to the diaphragm driving device, and is used to drive the diaphragm to move on the guide rail to realize the switching of the working state of the sail membrane.

[0007] Furthermore, in a spatial derailment damper in the present application, each adjacent fold is equally spaced, the adjacent folds are folded in opposite directions, the two ends of the shell are open, and the folds run through the two open ends of the shell. As a preferred embodiment of the present application, based on the above structure, the folds are folded in a Z shape. When the sail membrane is in the unfolded state, there is symmetry between adjacent diaphragms, which helps to evenly distribute pressure and prevent the shell from collapsing due to uneven force.

[0008] Furthermore, a space derailment damper in the present application further includes a pair of top covers, which are respectively covered at two opening ends of the shell; the number of guide rails is 2, and the pair of guide rails are respectively connected to the inner sides of the pair of top covers. As a preferred solution of the present application, the specific top cover is circular, and the top cover is used to connect the derailment target.

[0009] Furthermore, in the present application, a space derailment damper has a circular guide rail and a convex arc fold. As a preferred solution of the present application, based on the above device, the diaphragm is crescent-shaped, and when the sail membrane is in the unfolded state, the shell is spherical as a whole. This can reduce the constraints on the posture during derailment and improve the success rate of the derailment operation.

[0010] Furthermore, a space derailment damper in the present application further comprises a connecting device, which is used to connect the two ends of the shell that are connected in the circumferential direction. As a preferred solution of the present application, the connecting device is used to connect a pair of diaphragms at the two ends of the shell in the circumferential direction.

[0011] Furthermore, in a space derailment damper in the present application, the connection device includes magnetic suction parts, which are arranged in pairs at two ends of the shell that are connected in the circumferential direction. As a preferred embodiment of the present application, when the sail membrane is in the unfolded state, the magnetic suction parts at both ends are magnetically attracted to achieve automatic connection of the head and tail of the sail membrane.

[0012] Furthermore, in the present application, a space de-orbit damper, the driver comprises: A spring, the spring elastically expands and contracts in the circumferential direction of the housing, the spring is connected to the diaphragm, and the spring applies an elastic force to the diaphragm to move toward the expanded state; 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; Unlocking device, the unlocking device is used to make the locking device ineffective. As a preferred solution of the present application, based on the above device, the sail membrane can be controlled to switch from the contracted state to the expanded state. When the sail membrane is in the contracted state, the locking device locks the spring to keep it contracted to store elastic potential energy. When in use, an unlocking command is issued, the unlocking device is activated, the locking device is ineffective, and the spring pushes the diaphragm to move to the expanded state.

[0013] Furthermore, in a spatial off-track damper of the present application, the spring is an arc spring sleeved on the guide rail, the spring is 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 the circumferential uniformity of the diaphragm when in the expanded state.

[0014] 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 rope body from restraining the spring.

[0015] Furthermore, in the space derailment damper of the present application, the rope body is a Dyneema fiber line, and the rope breaking device is a fuse connected to the rope body. As a preferred solution of the present application, the fuse is powered on to heat and melt the rope body to fail and unlock.

[0016] It can be seen from the above technical solution that the present invention has the following beneficial effects: 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 started, 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 decelerate the target and deviate from the original orbit. The fold also plays the role of skeleton support, and the shell is lantern-shaped to enhance the stability of the shell. Therefore, a 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 quality, low production cost, and simple processing process. The posture switching is achieved by spring expansion, the process is simple, the complexity of drive control is reduced, and the reliability is good. At the same time, the spherical structural design avoids additional posture control. In addition, the shell does not require complete sealing, which increases the selectivity of the sail membrane material. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 A schematic diagram of a space de-orbit damper in an embodiment of the present application (the sail membrane is in a retracted state); Figure 2 A schematic diagram of a space de-orbit damper in an embodiment of the present application (the sail membrane is in an unfolded state); Figure 3 A schematic diagram of a space de-orbit damper in an embodiment of the present application (the sail membrane is in the process of being deployed); Figure 4 Schematic diagram of a connecting device in an embodiment of the present application.

[0018] In the figure: 1-sail membrane; 10-shell; 11-fold; 12-diaphragm; 2-guide rail; 3-driver; 31-spring; 4-top cover; 5-magnetic element. DETAILED DESCRIPTION

[0019] Combination Figures 1 to 3 As shown, this embodiment provides a space de-orbit damper, including: The sail membrane 1 has a working state including an unfolded state and a retracted state. When the sail membrane 1 is in the unfolded state, the sail membrane 1 is combined with 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 to a point on the circumference of the shell 10; 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; 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.

[0020] Based on the above structure, a space deorbit damper of the present application is used in the following way: the sail membrane 1 is arranged 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 driver is started, the sail membrane 1 is in an expanded state, and the aerodynamic resistance formed by the thin atmosphere in the low-orbit environment is used to gradually decelerate the target and deviate from the original orbit. The fold 11 also plays the role of skeleton support, and the shell 10 is lantern-shaped to enhance the stability of the shell 10. In this embodiment, the number of diaphragms 12 is 40.

[0021] In this embodiment, each adjacent fold 11 is equally spaced, and the adjacent folds 11 are folded in opposite directions. The shell 10 is open at both ends, and the fold 11 runs through the two open ends of the shell 10. Based on the above structure, the fold 11 is folded in a Z shape. When the sail membrane 1 is in the unfolded state, the adjacent membrane sheets 12 are symmetrical, which helps to evenly distribute the pressure and prevent the shell 10 from collapsing due to uneven force.

[0022] In this embodiment, a pair of top covers 4 are further included, and the pair of top covers 4 are respectively covered at the two opening ends of the housing 10; the number of 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. Specifically, the top covers 4 are circular and are used to connect the lowering target.

[0023] In this embodiment, the guide rail 2 is circular, and the fold 11 is convex and arc-shaped. Based on the above device, the membrane 12 is crescent-shaped, and when the sail membrane 1 is in the unfolded state, the shell 10 is spherical as a whole. This can reduce the constraints on the posture when leaving the track and improve the success rate of the derailment operation.

[0024] Combination Figure 4As shown, in this embodiment, a connecting device is also included, and the connecting device is used to connect the two ends of the shell 10 that are connected circumferentially. 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 suction parts 5, and the magnetic suction parts 5 are arranged in pairs at the two ends of the shell 10 that are connected circumferentially. When the sail membrane 1 is in the unfolded state, the magnetic suction parts 5 at both ends are magnetically attracted to achieve automatic connection between the head and tail of the sail membrane 1. In this embodiment, the magnetic suction parts 5 at both ends are permanent magnets. In other embodiments, the magnetic suction part 5 at one end is a permanent magnet, and the magnetic suction part 5 at the other end is a magnetic metal.

[0025] In this embodiment, the driver includes: a spring 31, which elastically expands and contracts in the circumferential direction of the housing 10, and is connected to the diaphragm 12, and applies an elastic force to the diaphragm 12 to move toward the expanded state; a locking device, which is used to prevent the spring 31 from moving toward the expanded state when the sail membrane 1 is in the contracted state; and an unlocking device, which is used to disable the locking device. Based on the above device, the sail membrane 1 can be controlled to switch from the contracted state to the expanded state. When the sail membrane 1 is in the contracted state, the locking device locks the spring 31 to keep it contracted to store elastic potential energy. When in 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 move to the expanded state.

[0026] In this embodiment, the spring 31 is an arc spring sleeved on the guide rail 2, and the spring 31 is sleeved on the guide rail 2, and the diaphragm 12 is connected one by one with equal intervals to the ring body constituting the spring 31. The diaphragm 12 is connected one by one with equal intervals to the ring body constituting the spring 31 to ensure the circumferential uniformity of the diaphragm 12 when in the unfolded state. In this embodiment, the locking device is a rope body (not shown), 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. Specifically, the rope body is a Dyneema fiber line, and the rope breaking device is a fuse connected to the rope body (not shown). The fuse is powered on and heated to melt the rope body to fail and unlock.

[0027] The technical principles of the present invention are described above in conjunction with specific embodiments. These descriptions are only for explaining the principles of the present invention and cannot be interpreted as limiting the scope of protection of the present invention in any way. Based on the explanations herein, those skilled in the art can associate other specific implementations of the present invention without creative work, and these methods 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 contracted to a point on the circumference of the shell (10) by folding along the folds (11) through the membrane sheets (12); A guide rail (2), the guide rail (2) corresponding to the circumferential shape of the housing (10), and the diaphragm (12) being slidably connected to the guide rail (2); A driver is connected to the diaphragm (12) for driving the diaphragm (12), and is 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).

2. A space de-orbit damper according to claim 1, characterized in that: Adjacent folds (11) are spaced at equal intervals, and adjacent folds (11) are folded in opposite directions; both ends of the shell (10) are open, and the folds (11) penetrate the two open ends of the shell (10).

3. A space de-orbit damper according to claim 2, characterized in that: It also comprises a pair of top covers (4), the pair of top covers (4) respectively covering the two opening 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. A space de-orbit damper according to claim 1, characterized in that: The guide rail (2) is circular, and the fold (11) is convex and arc-shaped.

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

6. A space de-orbit damper according to claim 5, characterized in that: The connecting device comprises magnetic attraction members (5), and the magnetic attraction members (5) are arranged in pairs at two ends of the shell (10) that are connected in the circumferential direction.

7. A space de-orbit damper according to claim 1, characterized in that: The driver comprises: A spring (31), the spring (31) elastically expands and contracts in the circumferential direction of the housing (10), the spring (31) is connected to the diaphragm (12), and the spring (31) applies 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 an expanded state when the sail membrane (1) is in a retracted state; An unlocking device is used to disable the locking device.

8. A space de-orbit damper according to claim 7, characterized in that: The spring (31) is an arc-shaped spring sleeved on the guide rail (2). The spring (31) is sleeved on the guide rail (2), and the diaphragm (12) is connected one by one to the ring body constituting the spring (31) at equal intervals.

9. A space de-orbit damper according to claim 8, characterized in that: 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).

10. A space de-orbit damper according to claim 9, 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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