A three-dimensional derailment device based on a multi-stage deployment structure

Abstract

The present invention belongs to the technical field of spacecraft deorbiting, and specifically relates to a three-dimensional deorbiting device based on a multi-stage deployment structure. It comprises an outer tube, a launch assembly, and a telescopic rod, a drag-increasing film, an upper flat sail, a lower flat sail, and a strapping assembly arranged inside the outer tube; an upper flat sail and a lower flat sail are respectively provided at both ends of the telescopic rod, and the flat sail deploys the flat film inside the sail by means of a mast driven by a volute spring, and the four masts of the flat sail are respectively connected to the four corners of the flat film, and the drag-increasing film is arranged in a ring shape on the outer periphery of the telescopic rod, and the two ends of the drag-increasing film are clearly fixed to the four corners of the flat film of the flat sail. After deployment, the drag-increasing film and the upper and lower flat sails together form a cube; the launch assembly is used to unlock the strapping assembly to form a three-dimensional deorbiting sail. The present invention realizes the separation of the three-dimensional deorbiting device and the deployment of the multi-stage telescopic rod by pyrotechnic launch and delayed ignition, thereby increasing the deorbiting efficiency and deorbiting stability of the deorbiting device.

Description

Technical Field

[0001] The present invention belongs to the technical field of spacecraft deorbiting, and in particular relates to a three-dimensional deorbiting device based on a multi-stage deployment structure. Background Art

[0002] As nations accelerate their exploration of space resources, the number of satellites in orbit continues to grow year by year. However, due to satellite breakups, collisions, and operational debris, the amount of debris in space is rapidly increasing, posing a serious threat to the safety of spacecraft in orbit. Therefore, effective measures must be taken to remove deorbited space debris, curb the growing debris population, and protect the safety of orbiting spacecraft.

[0003] Currently, space debris deorbiting methods include dragging, electric tether deorbiting, deorbiting sails, chemical propulsion deorbiting, and solar sails. Deorbiting sails significantly increase the surface area of ​​the deorbiting target in its orbit, thereby increasing frictional resistance between the target and Earth's upper atmosphere. This resistance accelerates the target's orbital decay, ultimately causing it to descend and be destroyed in the atmosphere. Planar deorbiting sails have low drag efficiency and are highly susceptible to attitude instability when used in orbit. Summary of the Invention

[0004] The purpose of the present invention is to provide a three-dimensional deorbiting device based on a multi-stage deployment structure, which solves the problems of low efficiency and insufficient stability of the current planar deorbiting sail during deorbiting. The separation of the three-dimensional deorbiting device and the deployment of the multi-stage telescopic rods are achieved through pyrotechnic launch and delayed ignition, greatly improving the deorbiting efficiency and deorbiting stability of the deorbiting device.

[0005] The technical solution for achieving the purpose of the present invention is as follows: a three-dimensional deorbiting device based on a multi-stage deployment structure, comprising an outer cylinder with one end completely open and the other end provided with a perforated end cap, a telescopic rod, a drag-enhancing film, an upper flat sail, a lower flat sail, and a lashing assembly arranged inside the outer cylinder, and a launching assembly connected to the bottom of the outer cylinder;

[0006] An upper flat sail and a lower flat sail are provided at both ends of the telescopic rod. The upper flat sail and the lower flat sail have the same structure, including a mast, a scroll spring and a flat film. The flat film inside the sail is unfolded by driving the mast through the scroll spring. The four masts of the flat sail are respectively connected to the four corners of the flat film. The drag-increasing film is arranged in a ring shape on the outer periphery of the telescopic rod. The two ends of the drag-increasing film are clearly fixed to the four corners of the flat film of the flat sail. After folding, it is placed between the upper flat sail and the lower flat sail. After unfolding, the drag-increasing film, the upper flat sail and the lower flat sail together form a cube.

[0007] The bundling assembly is used to bundle the telescopic rod, the drag-increasing film, the upper flat sail, and the lower flat sail in a folded state and place them in the outer cylinder;

[0008] The launching assembly is used to unlock the bundling assembly and launch the telescopic rod, the drag-increasing film, the upper plane sail, the lower plane sail and the bundling assembly arranged in the outer cylinder out of the outer cylinder to form a three-dimensional off-orbit sail.

[0009] Furthermore, the firing assembly includes a delay charge, a firing tube, a firing pin chamber, a firing pin, a retaining ring, a claw piston, a blocking cover, a firing pin spring, a stop rod and an igniter;

[0010] The launch tube is fixedly connected to the end cover at the bottom of the outer tube, the lower end of the launch tube is fixedly connected to the baffle, the middle of the baffle is provided with an igniter, the claw piston is provided at the lower end of the launch tube, the upper end of the launch tube is fixedly connected to the firing pin chamber, the upper part of the firing pin chamber is provided with a delay charge, the lower part of the firing pin chamber is provided with a firing pin, and the firing pin is a cavity type rotating body structure;

[0011] The claw piston includes a plurality of evenly distributed claws, a limit rod is arranged in the middle of the claw piston, a firing pin spring is mounted on the limit rod, the upper part of the limit rod on which the firing pin spring is mounted is arranged inside the firing pin, and the fixing ring is an annular structure, which is connected to the firing pin chamber by a thread and is used to limit the claw. A trapezoidal groove is arranged on the outside of the firing pin to cooperate with the claw of the claw piston and be fixed by the claw.

[0012] Furthermore, the launch tube is cylindrical with a flange, and the flange of the launch tube is connected to the end cover at the bottom of the outer tube by bolts; the bottom end of the cylindrical body of the launch tube is connected to the blocking cover by threads; and an annular step for clamping the firing pin chamber is provided inside the launch tube.

[0013] Furthermore, a threaded through hole is provided in the middle of the blocking cover, and the igniter is arranged in the threaded through hole;

[0014] An annular groove is provided on the side wall of the claw piston body, and a piston sealing ring is provided in the annular groove; a threaded hole is provided in the middle of the claw piston body, and one end of the limit rod is threadedly connected to the claw piston through the threaded hole.

[0015] Furthermore, the telescopic rod includes a multi-stage rod nested with each other, a plug connected to the inner wall of the innermost tube, a piston connected to the inner wall of the outermost tube, and an air chamber arranged at the rear end of the piston; the rear ends of the tubes other than the outermost tube are abutted against the end of the piston; a lower flat sail is provided on the outer periphery of the bottom of the outermost tube of the telescopic rod, and an upper flat sail is movably sleeved on the outer end of the telescopic rod, and the upper flat sail is fixedly connected to the plug;

[0016] The gas chamber is a rotating structure with two air passages in the middle. The gunpowder gas pushes the piston to move through the air passages; the piston movement pushes the other stage tubes forward and expands.

[0017] Furthermore, the plug is a rotating body structure, and the multi-stage rod includes a first stage rod, a second stage rod, a third stage rod, a fourth stage rod, a fifth stage rod, a sixth stage rod, a seventh stage rod and an eighth stage rod;

[0018] The plug is connected to one end of the eighth rod, the other end of the eighth rod is a gradually expanding section, and the second rod (303), the third rod, the fourth rod, the fifth rod, the sixth rod and the seventh rod all have one end with a gradually expanding section and the other end with a gradually contracting section;

[0019] One end of the first-stage rod is fixedly connected to the air chamber, and the other end is a tapered section; the first-stage rod, second-stage rod, third-stage rod, fourth-stage rod, fifth-stage rod, sixth-stage rod, seventh-stage rod and eighth-stage rod are all thin-walled aluminum tubes, which are nested in sequence and fixed in place by binding ropes before unfolding.

[0020] Furthermore, the strapping assembly is symmetrically arranged about the central axis of the telescopic rod, and the strapping assembly includes a strapping rope, a sleeve, a shear pin, a connecting ring and a shear piston;

[0021] Both sleeves are hollow structures. The sleeve is connected to the air chamber through the external thread on the outside of one end, and a vertical hole is opened at the other end of the sleeve to place the shear pin; a connecting ring is provided at the end of the tying rope, the shear pin passes through the connecting ring, and a shear piston is provided in the sleeve; after the delay column is delayed, the gunpowder is ignited and the two shear pistons are pushed to move backwards at the same time, and the tying rope is released after the shear pin is cut off.

[0022] Furthermore, a sealing ring is provided on the circumference of the shearing piston through an annular groove.

[0023] Furthermore, a rope cutter is provided at the outer end of the upper plane sail. One end of the derailment connecting rope passes through the rope cutter and is connected to the plug of the telescopic rod, and the other end is connected to the derailment target.

[0024] Furthermore, the three-dimensional deorbiting device is connected to the satellite platform, and the number of three-dimensional deorbiting devices installed on orbit is optional.

[0025] Compared with the prior art, the present invention has the following significant advantages:

[0026] The present invention is based on a three-dimensional deorbiting device with a multi-stage deployment structure. The three-dimensional deorbiting device is smoothly separated from the satellite platform by pyrotechnic launch, and the safe deployment of the deorbiting device after leaving the platform is achieved by delaying the cutting of the binding rope. The three-dimensional deorbiting device has no requirements for the deorbiting posture and still has the deorbiting capability in the deflection or spinning state. The three-dimensional deorbiting device adopts the design principle of double-sided redundancy. Even if one side of the sail or the drag-enhancing film fails due to damage, the overall drag-enhancing area will not be reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 Schematic diagram of the overall three-dimensional derailment device of the present invention; (a) is a three-dimensional schematic diagram, and (b) is a cross-sectional view.

[0028] Figure 2 Schematic diagram of the launch component.

[0029] Figure 3 Schematic diagram of the telescopic rod.

[0030] Figure 4 Schematic diagram of the resistance-enhancing film.

[0031] Figure 5 Schematic diagram of the launch tube.

[0032] Figure 6 Schematic diagram of a flat sail.

[0033] Figure 7 Schematic diagram of bundling method.

[0034] Figure 8 Schematic diagram of the strapping assembly.

[0035] Figure 9 Expanded view of the three-dimensional deorbit device.

[0036] Description of reference numerals:

[0037] 1-De-orbit connecting rope, 2-Launching assembly, 3-Telescopic rod, 4-Drag-increasing film, 5-Outer cylinder, 6-Upper plane sail, 7-Lower plane sail, 8-Rope cutter, 9-Bundling assembly, 201-Delay charge, 202-Launching tube, 203-Firing pin chamber, 204-Firing pin, 205-Retaining ring, 206-Claw piston, 207-Block cover, 208-Firing pin spring, 209-Limiting rod, 210-Piston sealing ring, 211 -Igniter, 301-plug, 302-first stage rod, 303-second stage rod, 304-third stage rod, 305-fourth stage rod, 306-fifth stage rod, 307-sixth stage rod, 308-seventh stage rod, 309-eighth stage rod, 310-piston, 311-air chamber, 901-binding rope, 902-sleeve, 903-connecting ring, 904-shear pin, 905-shear piston, 906-sealing ring. DETAILED DESCRIPTION

[0038] The present invention is further described in detail below with reference to the accompanying drawings.

[0039] like Figure 1-9As shown, a three-dimensional deorbiting device based on a multi-stage deployment structure includes a deorbiting connecting rope 1, a firing assembly 2, a telescopic rod 3, a drag-enhancing film 4, an outer tube 5, an upper flat sail 6, a lower flat sail 7, a rope cutter 8, and a lashing assembly 9. The three-dimensional deorbiting device is cylindrical in shape, and the number of on-orbit installations can be customized according to actual needs. The firing assembly 2 is mounted at the lower end of the outer tube 5. The firing tube 202 in the firing assembly 2 is connected to the outer tube 5 by bolts evenly spaced around the circumference. The firing tube 202 is a rotating body with internal threads on the inner wall of the lower end, which is connected to the cover 207. The cover 207 has a threaded hole in the middle for accommodating an igniter 211. Three claws are evenly spaced above the claw piston 206, with the middle threaded hole connected to the stop rod 209. The claw piston 206 has two annular grooves for accommodating the piston seal 210. The fixing ring 205 is an annular structure with three evenly spaced rectangular holes. It is threadedly connected to the firing pin chamber 203 and is positioned above the claw piston. The firing pin spring 208 is positioned outside the stop rod 209. The firing pin 204, a hollow rotating body, is mounted outside the firing pin spring 208. A trapezoidal groove is provided on the outside of the firing pin 204 to engage the latch piston 206 and is secured therein. A delay charge 201 is located above the firing pin chamber 203 and is triggered by the firing pin 204.

[0040] Above the firing assembly 2 is the strapping assembly 9, which primarily consists of a strapping rope 901, a sleeve 902, a connecting pin 904, a connecting ring 903, a shear piston 905, and a sealing ring 906. The strapping assembly 9 is symmetrically arranged. The sleeve 902 is a hollow structure, with external threads on one end connecting to the air chamber 311 and arranged symmetrically. A small hole is provided at the other end of the sleeve 902 for the connecting pin 904. The connecting pin 904 passes through the annular connecting ring 903 within the sleeve 902. The strapping rope 901 is attached to the connecting ring. After a certain delay, the delay charge 201 ignites the gunpowder and simultaneously pushes the two shear pistons 905 in opposite directions, simultaneously severing the shear pin 904 and releasing the strapping rope 901.

[0041] Above the strapping assembly 9 is a telescopic rod 3, with an upper flat sail 6 and a lower flat sail 7 secured to each end. Both sails deploy using scroll springs to drive masts, with the four masts connecting the four corners of the film. The film's center is securely connected to the center of the sails. The drag-enhancing film 4 is an annular film, with its ends securely connected to the film's four corners. After folding, it's placed between the upper and lower sails 6 and 7. When deployed, the film, along with the two sails, forms a cube.

[0042] The telescopic rod 3 mainly consists of a plug 301 , a first-stage rod 302 , a second-stage rod 303 , a third-stage rod 304 , a fourth-stage rod 305 , a fifth-stage rod 306 , a sixth-stage rod 307 , a seventh-stage rod 308 , an eighth-stage rod 309 , a piston 310 and an air chamber 311 .

[0043] The plug 301 is a rotating body structure, and one end of the eighth rod 309 is placed thereon. The other end of the eighth rod 309 is a gradually expanding section.

[0044] The second-stage rod 303, third-stage rod 304, fourth-stage rod 305, fifth-stage rod 306, sixth-stage rod 307, and seventh-stage rod 308 all have a gradually expanding section at one end and a gradually converging section at the other. The first-stage rod 302 is fixedly connected to the air chamber 311 at one end and has a gradually converging section at the other end. The air chamber 311 is a rotating structure with two air passages in the center. The propellant gas passes through these air passages to push the piston 310. The piston 310 is positioned below the second-stage rod 303 and the eighth-stage rod 309.

[0045] The first rod 302 , the second rod 303 , the third rod 304 , the fourth rod 305 , the fifth rod 306 , the sixth rod 307 , the seventh rod 308 , and the eighth rod 309 are all thin-walled aluminum tubes, which are nested in sequence and are fixed in position by binding ropes 901 before being unfolded.

[0046] When the piston 310 moves, it pushes the second-stage rod 303 to the eighth-stage rod 309 to move forward. When they move to the specified position, the tapered section of the first-stage rod 302 will clamp the gradually expanding section of the second-stage rod 303 and the piston. The tapered section of the second-stage rod 303 limits the gradually expanding section of the third-stage rod 304. The remaining rods continue to move under the action of inertia and are limited in sequence until they are all deployed.

[0047] When the telescopic rod 3 is extended, the two flat sails are unfolded simultaneously, and finally a three-dimensional derailment device is formed.

[0048] One end of the derailing connecting rope 1 passes through the rope cutter 8 and is connected to the plug of the telescopic rod 3, and the other end is connected to the derailed object.

[0049] When an accident occurs during ignition and launch, the rope cutter 8 can be used for emergency cutting to ensure the safety of the satellite platform.

Claims

1. A three-dimensional derailment device based on a multi-stage deployment structure, characterized in that: The invention comprises an outer cylinder (5) with one end completely open and the other end provided with an end cap with a hole, a telescopic rod (3), a drag-enhancing film (4), an upper flat sail (6), a lower flat sail (7) and a tying assembly (9) arranged inside the outer cylinder (5), and a launching assembly (2) connected to the bottom of the outer cylinder (5); An upper plane sail (6) and a lower plane sail (7) are respectively provided at both ends of the telescopic rod (3). The upper plane sail (6) and the lower plane sail (7) have the same structure, both comprising a mast, a scroll spring and a plane film. The plane film in the sail is unfolded by driving the mast through the scroll spring. The four masts of the plane sail are respectively connected to the four corners of the plane film. The resistance-increasing film (4) is arranged in an annular shape on the outer periphery of the telescopic rod (3). The two ends of the resistance-increasing film (4) are respectively fixed to the four corners of the plane film of the plane sail. After being folded, the resistance-increasing film (4) is placed between the upper plane sail (6) and the lower plane sail (7). After being unfolded, the resistance-increasing film (4) forms a cube together with the upper plane sail (6) and the lower plane sail (7). The bundling assembly (9) is used to bundle the telescopic rod (3), the resistance-enhancing film (4), the upper flat sail (6), and the lower flat sail (7) in a folded state and arrange them inside the outer cylinder (5); The launching assembly (2) is used to unlock the tying assembly (9) and launch the telescopic rod (3), the drag-enhancing film (4), the upper plane sail (6), the lower plane sail (7) and the tying assembly (9) arranged in the outer cylinder (5) out of the outer cylinder (5) to form a three-dimensional off-orbit sail; The firing assembly (2) comprises a delayed charge (201), a firing tube (202), a firing pin chamber (203), a firing pin (204), a fixing ring (205), a claw piston (206), a blocking cover (207), a firing pin spring (208), a limiting rod (209) and an igniter (211); The launch tube (202) is fixedly connected to the end cover at the bottom of the outer tube (5); the lower end of the launch tube (202) is fixedly connected to the blocking cover (207); the middle of the blocking cover (207) is provided with an igniter (211); the claw piston (206) is provided at the lower end of the launch tube (202); the upper end of the launch tube is fixedly connected to the firing pin chamber (203); the upper part of the firing pin chamber (203) is provided with a delay charge (201); the lower part of the firing pin chamber (203) is provided with a firing pin (204); the firing pin (204) is a cavity type rotary body structure; The claw piston (206) includes a plurality of evenly distributed claws. A limiting rod (209) is provided in the middle of the claw piston (206). A firing pin spring (208) is sleeved on the limiting rod (209). The upper portion of the limiting rod (209) sleeved with the firing pin spring (208) is provided inside the firing pin (204). The fixing ring (205) is an annular structure and is connected to the firing pin chamber (203) through a thread for limiting the claw. A trapezoidal groove is provided on the outer side of the firing pin (204) to cooperate with the claw of the claw piston (206) and be fixed by the claw.

2. The three-dimensional derailment device according to claim 1, characterized in that: The launch tube (202) is cylindrical with a flange, and the flange of the launch tube is connected to the end cover at the bottom of the outer tube (5) through bolts; the bottom end of the cylindrical body of the launch tube is connected to the blocking cover (207) through a thread; and an annular step for clamping the firing pin chamber (203) is provided in the launch tube (202).

3. The three-dimensional derailment device according to claim 2, characterized in that: A threaded through hole is provided in the middle of the blocking cover (207), and the igniter (211) is arranged in the threaded through hole; The side wall of the claw piston (206) body is provided with an annular groove, and a piston sealing ring (210) is provided in the annular groove; a threaded hole is provided in the middle of the claw piston (206) body, and one end of the limiting rod (209) is threadedly connected to the claw piston (206) through the threaded hole.

4. The three-dimensional derailment device according to claim 3, characterized in that: The telescopic rod (3) comprises a multi-stage rod nested with each other, a plug (301) connected to the inner wall of the innermost tube, a piston (310) connected to the inner wall of the outermost tube, and an air chamber (311) arranged at the rear end of the piston (310); the rear ends of the other tubes except the outermost tube are abutted against the end of the piston (310); a lower plane sail (7) is provided on the outer periphery of the bottom of the outermost tube of the telescopic rod (3); an upper plane sail (6) is movably sleeved on the outer end of the upper end of the telescopic rod (3); and the upper plane sail (6) is fixedly connected to the plug (301); The air chamber (311) is a rotating body structure with two air passages in the middle. The gunpowder gas pushes the piston (310) to move through the air passages; the movement of the piston (310) pushes the other stage pipes to move forward and expand.

5. The three-dimensional derailment device according to claim 4, characterized in that: The plug (301) is a rotating body structure, and the multi-stage rod includes a first stage rod (302), a second stage rod (303), a third stage rod (304), a fourth stage rod (305), a fifth stage rod (306), a sixth stage rod (307), a seventh stage rod (308) and an eighth stage rod (309); The plug (301) is connected to one end of the eighth rod (309), the other end of the eighth rod (309) is a gradually expanding section, and the second rod (303), the third rod (304), the fourth rod (305), the fifth rod (306), the sixth rod (307) and the seventh rod (308) all have one end with a gradually expanding section and the other end with a gradually contracting section. One end of the first-stage rod (302) is fixedly connected to the air chamber (311), and the other end is a tapered section; the first-stage rod (302), the second-stage rod (303), the third-stage rod (304), the fourth-stage rod (305), the fifth-stage rod (306), the sixth-stage rod (307), the seventh-stage rod (308) and the eighth-stage rod (309) are all thin-walled aluminum tubes, which are nested in sequence and are fixed by a tying rope (901) before being unfolded.

6. The three-dimensional derailment device according to claim 5, characterized in that: The tying assembly (9) is symmetrically arranged about the central axis of the telescopic rod (3), and the tying assembly (9) includes a tying rope (901), a sleeve (902), a shear pin (904), a connecting ring (903) and a shear piston (905); The two sleeves (902) are both hollow structures. The sleeves (902) are connected to the air chamber (311) through an external thread on the outer side of one end. The other end of the sleeve (902) is provided with a vertical small hole for placing a shear pin (904). The end of the tying rope (901) is provided with a connecting ring (903), the shear pin (904) passes through the connecting ring (903), and a shear piston (905) is provided in the sleeve (902). After the delay charge (201) is delayed, the gunpowder is ignited and the two shear pistons (905) are pushed to move in opposite directions, and the shear pin (904) is cut off at the same time, and the tying rope (901) is released.

7. The three-dimensional derailment device according to claim 6, characterized in that: A sealing ring (906) is provided on the circumference of the shearing piston (905) through an annular groove.

8. The three-dimensional derailing device according to claim 7, characterized in that: A rope cutter (8) is provided at the outer end of the upper plane sail (6); one end of the derailing connecting rope (1) passes through the rope cutter (8) and is connected to the plug of the telescopic rod (3); and the other end is connected to the derailed target.

9. The three-dimensional derailing device according to claim 8, characterized in that: The three-dimensional deorbit device is connected to the satellite platform, and the number of three-dimensional deorbit devices installed on orbit is optional.

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