Modularized pressing and releasing device and method applied to stacked satellites

Abstract

The invention relates to a modularized pressing and releasing device and method applied to stacked satellites. The modularized pressing and releasing device comprises a force bearing base, an off-axis unfolding and locking device, a tension spring driving device, a pressing cover assembly and a hot work pressing and unlocking assembly. The initiating explosive pressing and unlocking assemblies are installed on the left side and the right side of the upper face of the force bearing base correspondingly, the off-axis unfolding and locking devices are installed on the portions, located right in front of the two initiating explosive pressing and unlocking assemblies, of the force bearing base correspondingly, and the off-axis unfolding and locking devices are connected with the initiating explosive pressing and unlocking assemblies; the upper end of the fire work pressing unlocking assembly is connected with the pressing cover assembly, the two edge openings of the front end of the force bearing base are both connected with the tension spring driving devices, and the other ends of the tension spring driving devices are connected with the pressing cover assembly. The modularized pressing and releasing device applied to the stacked satellites has the advantages that batch production is facilitated, modularized design is achieved, and good interchangeability is achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of compression and release of stacked satellites, and more specifically, to a modular compression and release device and method for stacked satellites. Background Art

[0002] With the expansion of satellite application fields such as space exploration, popularization of 5G signals, development of network technology and low-orbit interconnection, the launch missions of low-orbit satellite constellations with multi-satellite networking have grown explosively.

[0003] Stacked satellites are multiple identical satellites stacked together through load-bearing columns, which can greatly improve the utilization rate of rocket fairings and save launch costs. This design concept is being used by more and more networked satellite constellations. For the launch mode of multi-satellite stacking connection and separation, the modular compression release device is a key technology in this field.

[0004] Traditional intersatellite locking is mainly composed of belt-type and point-type intersatellite unlocking and separation, and pyrotechnic unlocking and separation are mostly adopted. Pyrotechnic separation has problems such as poor safety, large impact load, and pollutant generation after detonation. In addition, given the differences in satellites launched each time, the intersatellite locking and unlocking device needs to be redesigned for each launch, which takes a lot of time and effort.

[0005] The preceding description is intended to provide general background information and does not necessarily constitute prior art. Summary of the invention

[0006] The object of the present invention is to provide a modular compression and release device and method for stacking satellites. The modular compression and release device for stacking satellites is convenient for mass production, modular design, and has good interchangeability.

[0007] The present invention provides a modular compression and release device for stacking satellites, comprising a load-bearing base, an eccentric expansion locking device, a tension spring driving device, a compression cover assembly and a pyrotechnic compression and unlocking assembly; the pyrotechnic compression and unlocking assemblies are installed on the left and right sides of the load-bearing base, the eccentric expansion locking device is installed on the load-bearing base directly in front of the two pyrotechnic compression and unlocking assemblies, and the eccentric expansion locking device is connected to the pyrotechnic compression and unlocking assembly; the compression cover assembly is connected to the upper end of the pyrotechnic compression and unlocking assembly, the tension spring driving device is connected to the two edge openings at the front end of the load-bearing base, and the other end of the tension spring driving device is connected to the compression cover assembly.

[0008] Furthermore, the pyrotechnic compression and unlocking assembly includes a lower sleeve, an upper sleeve, a pyrotechnic explosive bolt, a transfer rod, a locking pin, a spring, a baffle and a rubber pad; the lower sleeve is fixed on the load-bearing base, the upper sleeve is placed on the lower sleeve, the pyrotechnic explosive bolt is installed in the lower sleeve, and the transfer rod is installed in the upper sleeve; the screw rod of the pyrotechnic explosive bolt passes through the through holes of the lower sleeve and the upper sleeve, and is connected to the transfer rod in the upper sleeve; two locking pins and the spring are arranged in the transfer rod, the baffle is installed on the top of the upper sleeve, and the rubber pad is connected to the lower part of the baffle in the upper sleeve.

[0009] Furthermore, the clamping cover assembly includes a tensioning rod, a clamping cover, a locking nut and a clamping cover fixing piece; one end of the tensioning rod is connected to the transfer rod in the upper sleeve, and the other end of the tensioning rod passes through a through hole on one side of the clamping cover fixing piece, and the clamping cover fixing piece is fixed to the clamping cover up and down by the locking nut.

[0010] Furthermore, the eccentric deployment locking device includes a male hinge, a female hinge, an deployment axis, a locking buckle and a locking assembly; one end of the female hinge is fixed on the load-bearing base, and the other end of the female hinge is hinged to the male hinge through the deployment axis; the male hinge is connected to the extension section on the upper sleeve, and the locking buckle is fixedly connected to the top of the male hinge; the locking assembly is fixedly connected to the load-bearing base just in front of the female hinge, and the locking assembly includes a bracket, a locking rod, a locking spring and a positioning pin; one end of the bracket is fixed to the load-bearing base, and the other end of the bracket is connected to two of the positioning pins; a mounting hole is provided on the bracket, the locking rod is located in the mounting hole, and the locking spring is sleeved on the locking rod to provide a force for the locking rod to move outward; when the deployment locking device is deployed in place, the positioning pin is used to limit the deployment angle, and the locking rod slides into the locking buckle on the male hinge to limit rotation.

[0011] Furthermore, the tension spring driving device includes an extension plate, a tension spring lower bracket, a tension spring and a tension spring upper bracket; the extension plate is connected to the two edge edges at the front end of the load-bearing base, the tension spring lower bracket is connected to the top of the extension plate, the tension spring is connected to the tension spring lower bracket, the other end of the tension spring is connected to the tension spring upper bracket, and the tension spring upper bracket is connected to the tension rod.

[0012] The present invention also provides a modular compression and release method applied to stacked satellites, and the modular compression and release method is applied to the above-mentioned modular compression and release device applied to stacked satellites.

[0013] Furthermore, the modular compression and release method comprises the following steps:

[0014] S1: Unlocking process: The launch vehicle provides an unlocking signal for the pyrotechnics, the explosive bolts are detonated and unlocked at the same time, the compression cover assembly and the transfer rod move upward under the impact force of the pyrotechnics unlocking, the locking pin in the transfer rod slides into the locking hole of the upper sleeve and locks, and the preload force on the stacked satellite bearing cylinder is released;

[0015] S2: Movement process: After the explosive bolt is detonated and unlocked, the compression cover assembly is driven by the tension spring drive device to rotate around the eccentric axis and finally lock;

[0016] S3: Locking process: After the eccentric deployment locking device is deployed in place, the positioning pin limits the deployment angle, the locking rod slides into the locking buckle on the male hinge to limit the rotation, and the separation is completed.

[0017] The modular clamping and releasing device for stacked satellites provided by the present invention is suitable for stacked satellite multi-satellite separation solutions, which improves the space utilization rate of the rocket and reduces the launch cost; a modular design solution is adopted to adaptively modify the load-bearing base, clamping cover, tensioning rod and other parts according to different satellite sizes and stacking heights, so as to be adaptable to different types of stacked satellites; the device has the advantages of being pollution-free, large load-bearing capacity, good separation synchronization and high reliability; the tensioning rod is locked after being deployed into place to prevent irregular movement after separation from affecting satellite separation; after the separation of the satellite and the rocket, all parts of the device are passivated and put into orbit with the carrier, and no excess parts pollute the space environment. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 A schematic structural diagram of a modular compression and release device for stacking satellites provided in an embodiment of the present invention.

[0019] Figure 2 for Figure 1 A partially enlarged schematic diagram of the modular compression and release device used for stacking satellites.

[0020] Figure 3 for Figure 1 Another structural schematic diagram of the modular compression and release device used for stacking satellites.

[0021] Figure 4 for Figure 1 Schematic diagram of the disassembly of the pyrotechnic clamping and unlocking components of the modular clamping and releasing device used for stacking satellites.

[0022] Figure 5 for Figure 1 Schematic diagram of the structure of the clamping cover assembly of the modular clamping release device used in stacked satellites.

[0023] Figure 6 for Figure 1Schematic diagram of the structure of the off-axis deployment locking device of the modular compression release device used in stacked satellites.

[0024] Figure 7 for Figure 1 Schematic diagram of the structure of the locking assembly of the modular clamping and releasing device used for stacking satellites.

[0025] Figure 8 for Figure 1 Schematic diagram of the structure of the tension spring drive device of the modular clamping and releasing device used in stacked satellites.

[0026] Fig. 9 for Figure 1 Schematic diagram of a compacted stacked satellite with a modular compaction and release device for use with stacked satellites.

[0027] Fig.10 A schematic flow chart of a modular compression and release method provided in an embodiment of the present invention.

[0028] The reference numerals and components involved in the drawings are as follows:

[0029] 1. Load-bearing base 2. Eccentric expansion locking device 201. Male hinge

[0030] 202, mother hinge 203, unfolding axis 204, locking buckle

[0031] 210, locking assembly 211, bracket 212, locking rod

[0032] 213, locking spring 214, positioning pin 3, tension spring driving device

[0033] 301, extension plate 302, tension spring lower bracket 303, tension spring

[0034] 304, tension spring upper bracket 4, pressing cover assembly 401, tension rod

[0035] 402, compression cover 403, locking nut 404, compression cover fixing piece

[0036] 5. Pyrotechnics pressing and unlocking assembly 501, lower sleeve 502, upper sleeve

[0037] 503, pyrotechnic explosive bolt 504, adapter rod 505, locking pin

[0038] 506, spring 507, baffle 508, rubber pad DETAILED DESCRIPTION

[0039] The specific implementation of the present invention is further described in detail below in conjunction with the accompanying drawings and examples. The following examples are used to illustrate the present invention, but are not intended to limit the scope of the present invention.

[0040] The terms "first", "second", "third", "fourth" and the like in the description and claims of the present invention are used to distinguish similar objects and are not necessarily used to describe a particular order or sequence.

[0041] Example 1

[0042] Figure 1 A schematic diagram of the structure of a modular compression and release device for stacking satellites provided in an embodiment of the present invention. Figure 2 for Figure 1 A partial enlarged schematic diagram of the modular compression and release device used for stacking satellites. Figure 3 for Figure 1 Another structural schematic diagram of a modular compression and release device for stacking satellites, Fig. 9 for Figure 1 Schematic diagram of the stacked satellites with modular hold-down release devices for stacked satellites. Figure 1 , Figure 2 , Figure 3 , Fig. 9 The modular compression and release device for stacking satellites provided in an embodiment of the present invention comprises a load-bearing base 1, an eccentric expansion locking device 2, a tension spring driving device 3, a compression cover assembly 4 and a pyrotechnic compression and unlocking assembly 5; the pyrotechnic compression and unlocking assemblies 5 are installed on the left and right sides of the load-bearing base 1, and the eccentric expansion locking device 2 is installed on the load-bearing base 1 directly in front of the two pyrotechnic compression and unlocking assemblies 5, and the eccentric expansion locking device 2 is connected to the pyrotechnic compression and unlocking assembly 5; the compression cover assembly 4 is connected to the upper end of the pyrotechnic compression and unlocking assembly 5, and the tension spring driving device 3 is connected to the two edge openings at the front end of the load-bearing base 1, and the other end of the tension spring driving device 3 is connected to the compression cover assembly 4.

[0043] Figure 4 for Figure 1 Schematic diagram of the disassembly of the pyrotechnic hold-down and release assembly of the modular hold-down and release device used for stacking satellites. Figure 4The pyrotechnic pressing and unlocking assembly 5 of the present invention comprises a lower sleeve 501, an upper sleeve 502, a pyrotechnic explosive bolt 503, a transfer rod 504, a locking pin 505, a spring 506, a baffle 507 and a rubber pad 508; the lower sleeve 501 is fixed on the load-bearing base 1, the upper sleeve 502 is placed on the lower sleeve 501, the pyrotechnic explosive bolt 503 is installed in the lower sleeve 501, and the upper sleeve 502 is installed in the upper sleeve 502. The transfer rod 504; the screw rod of the pyrotechnic explosive bolt 503 passes through the through holes of the lower sleeve 501 and the upper sleeve 502, and is connected to the transfer rod 504 in the upper sleeve 502; two locking pins 505 and the spring 506 are arranged in the transfer rod 504, the baffle plate 507 is installed on the top of the upper sleeve 502, and the rubber pad 508 is connected to the lower part of the baffle plate 507 in the upper sleeve 502.

[0044] Figure 5 for Figure 1 Schematic diagram of the structure of the clamping cover assembly of the modular clamping release device used for stacking satellites. Figure 5 The clamping cover assembly 4 of the present invention includes a tensioning rod 401, a clamping cover 402, a locking nut 403 and a clamping cover fixing piece 404; one end of the tensioning rod 401 is connected to the transfer rod 504 in the upper sleeve 502, and the other end of the tensioning rod 401 passes through a through hole on one side of the clamping cover fixing piece 404, and the clamping cover fixing piece 404 is fixed to the clamping cover 402 up and down by the locking nut 403.

[0045] It should be noted that, when in use, the compression cover 402 compresses the load-bearing cylinder of the uppermost stacked satellite, and applies a compression pre-tightening force to the load-bearing cylinder of the stacked flat-panel satellite through the tension rod 401 and the compression cover 402 .

[0046] When the carrier's last-stage rocket sends an unlocking signal to control the explosive bolt to unlock, the tension rod 401, the clamping cover assembly 4 and the adapter rod 504 move upward under the impact force of the explosive bolt unlocking, and the locking pin 505 in the adapter rod 504 slides into the locking hole of the upper sleeve 502 to lock, and the preload force on the stacked satellite bearing cylinder is released; the baffle 507 is used for limiting, and the rubber pad 508 is used for buffering.

[0047] Figure 6 for Figure 1 A schematic diagram of the structure of the off-axis deployment locking device of the modular compression release device used for stacked satellites, Figure 7 for Figure 1 Schematic diagram of the locking assembly of the modular hold-down release device used for stacked satellites. Figure 6 , Figure 7The eccentric deployment locking device 2 of the present invention comprises a male hinge 201, a female hinge 202, an deployment shaft 203, a locking buckle 204 and a locking assembly 210; one end of the female hinge 202 is fixed on the load-bearing base 1, and the other end of the female hinge 202 is hinged to the male hinge 201 through the deployment shaft 203; the male hinge 201 is connected to the extension section on the upper sleeve 502, and the locking buckle 204 is fixedly connected to the male hinge 201; the locking assembly 210 is fixedly connected to the load-bearing base 1 just in front of the female hinge 202, and the locking assembly 210 comprises a bracket 211, a lock A fixed rod 212, a locking spring 213 and a positioning pin 214; one end of the bracket 211 is fixed on the load-bearing base 1, and the other end of the bracket 211 is connected to two positioning pins 214; a mounting hole is provided on the bracket 211, and the locking rod 212 is located in the mounting hole, and the locking spring 213 is sleeved on the locking rod 212 to provide a force for the locking rod 212 to move outward; when the unfolding locking device 2 is unfolded into place, the positioning pin 214 is used to limit the unfolding angle, and the locking rod 212 slides into the locking buckle 204 on the male hinge 201 to limit rotation.

[0048] Figure 8 for Figure 1 Schematic diagram of the structure of the tension spring drive device of the modular compression release device used in stacked satellites. Figure 8 The tension spring driving device 3 of the present invention comprises an extension plate 301, a tension spring lower bracket 302, a tension spring 303 and a tension spring upper bracket 304; the extension plate 301 is connected to the two edges of the front end of the load-bearing base 1, the tension spring lower bracket 302 is connected to the top of the extension plate 301, the tension spring lower bracket 302 is connected to the tension spring 303, the other end of the tension spring 303 is connected to the tension spring upper bracket 304, and the tension spring upper bracket 304 is connected to the tension rod 401.

[0049] It should be noted that after the explosive bolt is detonated and unlocked, the clamping cover assembly 4 is driven by the tension spring drive device 3 to rotate around the eccentric axis deployment locking device 2 and finally lock, and re-enter the orbit with the final stage rocket.

[0050] The modular clamping and releasing device for stacking satellites of the present invention is assembled by first fixing the load-bearing base 1 to the adapter plane of the launch vehicle, and supporting the load-bearing cylinder of the stacked satellite according to the position distribution of the load-bearing cylinder of the stacked satellite; a set of pyrotechnic clamping and unlocking components 5, eccentric expansion locking devices 2, clamping cover components 4 and tension spring driving devices 3 are respectively installed on the left and right sides of the load-bearing base 1; after separation, the clamping cover components 4 are flipped downward by the force of the tension spring driving device 3, and when flipped to the end of the stroke, the positioning pin 214 limits the expansion angle, and the locking rod 212 slides into the locking buckle 204 on the male hinge 201 to limit the rotation, and the separation is completed.

[0051] Fig.10 This is a flow chart of a modular compression and release method provided by an embodiment of the present invention. Fig.10 The present invention also provides a modular compression and release method applied to stacked satellites, and the modular compression and release method is applied to the above-mentioned modular compression and release device applied to stacked satellites.

[0052] Specifically, the modular compression and release method comprises the following steps:

[0053] S1: Unlocking process: The launch vehicle provides an unlocking signal for the pyrotechnics, the explosive bolts are simultaneously detonated and unlocked, the pressing cover assembly 4 and the transfer rod 504 move upward under the impact force of the pyrotechnics unlocking, the locking pin 505 in the transfer rod 504 slides into the locking hole of the upper sleeve 502 and locks, and the preload force on the stacked satellite bearing cylinder is released;

[0054] S2: Movement process: After the explosive bolt is detonated and unlocked, the compression cover assembly 4 is driven by the tension spring driving device 3 to rotate around the eccentric expansion locking device 2 and finally locked;

[0055] S3: Locking process: After the eccentric deployment locking device 2 is deployed in place, the positioning pin 214 limits the deployment angle, and the locking rod 212 slides into the locking buckle 204 on the male hinge 201 to limit the rotation, and the separation is completed.

[0056] Based on the above description, it can be seen that the advantages of the present invention are:

[0057] 1. The modular compression and release device for stacked satellites of the present invention is suitable for stacked satellite multi-satellite separation scheme, which improves rocket space utilization and reduces launch costs;

[0058] 2. The modular compression and release device used for stacked satellites adopts a modular design scheme. According to different satellite sizes and stacking heights, the load-bearing base, compression cover, tension rod and other parts are adaptively modified to adapt to different types of stacked satellites;

[0059] 3. The modular compression and release device used for stacked satellites has the advantages of no pollution, large load, good separation synchronization and high reliability;

[0060] 4. Modular compression and release device for stacked satellites. The tension rod is locked after being deployed to prevent irregular movement after separation from affecting satellite separation.

[0061] 5. The modular compression and release device used for stacked satellites. After the satellite and rocket are separated, all parts of the device are passivated and put into orbit with the carrier, and no extra parts pollute the space environment.

[0062] The above is only a specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art can easily think of changes or substitutions within the technical scope disclosed by the present invention, which should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. A modular compression and release device for stacking satellites, characterized in that: It comprises a load-bearing base (1), an eccentric expansion locking device (2), a tension spring driving device (3), a pressing cover assembly (4) and a pyrotechnic pressing and unlocking assembly (5); The pyrotechnic compression and unlocking components (5) are installed on both left and right sides of the load-bearing base (1), and the eccentric expansion locking device (2) is installed on the load-bearing base (1) directly in front of the two pyrotechnic compression and unlocking components (5), and the eccentric expansion locking device (2) is connected to the pyrotechnic compression and unlocking components (5); The upper end of the pyrotechnic clamping and unlocking assembly (5) is connected to the clamping cover assembly (4), and the two edges of the front end of the load-bearing base (1) are connected to the tension spring drive device (3), and the other end of the tension spring drive device (3) is connected to the clamping cover assembly (4).

2. The modular compression and release device for stacking satellites according to claim 1, characterized in that: The pyrotechnic pressing and unlocking assembly (5) comprises a lower sleeve (501), an upper sleeve (502), a pyrotechnic explosive bolt (503), a transfer rod (504), a locking pin (505), a spring (506), a baffle (507) and a rubber pad (508); The lower sleeve (501) is fixed on the load-bearing base (1), the upper sleeve (502) is placed on the lower sleeve (501), the pyrotechnic explosive bolt (503) is installed in the lower sleeve (501), and the transfer rod (504) is installed in the upper sleeve (502); The screw rod of the explosive bolt (503) of the pyrotechnics passes through the through holes of the lower sleeve (501) and the upper sleeve (502), and is connected to the transfer rod (504) in the upper sleeve (502); The two locking pins (505) and the spring (506) are arranged in the transfer rod (504), the baffle (507) is installed on the top of the upper sleeve (502), and the rubber pad (508) is connected below the baffle (507) in the upper sleeve (502).

3. The modular compression and release device for stacking satellites according to claim 2, characterized in that: The compression cover assembly (4) comprises a tension rod (401), a compression cover (402), a locking nut (403) and a compression cover fixing member (404); One end of the tension rod (401) is connected to the transfer rod (504) in the upper sleeve (502), and the other end of the tension rod (401) passes through a through hole on one side of the clamping cover fixing member (404), and the clamping cover fixing member (404) and the clamping cover (402) are fixed up and down by the locking nut (403).

4. The modular compression and release device for stacking satellites according to claim 2, characterized in that: The off-axis deployment locking device (2) comprises a male hinge (201), a female hinge (202), a deployment shaft (203), a locking buckle (204) and a locking assembly (210); One end of the female hinge (202) is fixed on the load-bearing base (1), and the other end of the female hinge (202) is hinged to the male hinge (201) via the unfolding shaft (203); the male hinge (201) is connected to the extension section on the upper sleeve (502), and the locking buckle (204) is fixedly connected to the upper surface of the male hinge (201); The locking assembly (210) is fixedly connected to the load-bearing base (1) directly in front of the mother hinge (202), and the locking assembly (210) comprises a bracket (211), a locking rod (212), a locking spring (213) and a positioning pin (214); One end of the bracket (211) is fixed on the load-bearing base (1), and the other end of the bracket (211) is connected to two positioning pins (214); A mounting hole is provided on the bracket (211), the locking rod (212) is located in the mounting hole, and the locking spring (213) is sleeved on the locking rod (212) to provide a force for the locking rod (212) to move outward; When the deployment locking device (2) is deployed in place, the positioning pin (214) is used to limit the deployment angle, and the locking rod (212) slides into the locking buckle (204) on the male hinge (201) to limit rotation.

5. The modular compression and release device for stacking satellites according to claim 3, characterized in that: The tension spring driving device (3) comprises an extension plate (301), a tension spring lower bracket (302), a tension spring (303) and a tension spring upper bracket (304); The extension plate (301) is connected to the two edges of the front end of the load-bearing base (1), the tension spring lower bracket (302) is connected to the top of the extension plate (301), the tension spring (303) is connected to the tension spring lower bracket (302), the other end of the tension spring (303) is connected to the tension spring upper bracket (304), and the tension spring upper bracket (304) is connected to the tension rod (401).

6. A modular compression and release method for stacking satellites, characterized in that: The modular compression and release method is applied to the modular compression and release device for stacking satellites as described in any one of claims 1-5.

7. The modular compression and release method for stacking satellites according to claim 6, characterized in that: The modular compression and release method comprises the following steps: S1: Unlocking process: The launch vehicle provides an unlocking signal for the pyrotechnics, the explosive bolts are simultaneously detonated and unlocked, the pressing cover assembly (4) and the transfer rod (504) move upward under the impact force of the pyrotechnics unlocking, the locking pin (505) in the transfer rod (504) slides into the locking hole of the upper sleeve (502) and locks, and the pre-tightening force on the stacked satellite bearing cylinder is released; S2: Movement process: After the explosive bolt is detonated and unlocked, the compression cover assembly (4) is driven by the tension spring drive device (3) to rotate around the eccentric expansion locking device (2) and finally lock; S3: Locking process: After the eccentric deployment locking device (2) is deployed in place, the positioning pin (214) limits the deployment angle, and the locking rod (212) slides into the locking buckle (204) on the male hinge (201) to limit rotation, and the separation is completed.

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