Modular compression release device and method for application to a stack of satellites

Abstract

The application relates to a modularized compression release device and method applied to stacked satellites, which comprises a force-bearing base, an off-axis unfolding locking device, a tension spring driving device, a compression cover assembly and a pyrotechnic compression unlocking assembly; the pyrotechnic compression unlocking assemblies are installed on the left and right sides of the upper surface of the force-bearing base, the off-axis unfolding locking devices are installed in front of the two pyrotechnic compression unlocking assemblies on the force-bearing base, the off-axis unfolding locking devices are connected with the pyrotechnic compression unlocking assemblies, the compression cover assemblies are connected with the upper ends of the pyrotechnic compression unlocking assemblies, the tension spring driving devices are connected with the two edge openings of the front end of the force-bearing base, and the other ends of the tension spring driving devices are connected with the compression cover assemblies. The application has the advantages that the modularized compression release device applied to the stacked satellites is convenient for batch production and modularized design and has good interchangeability.

Description

Technical Field

[0001] This invention relates to the field of compression and release technology for stacked satellites, and more specifically, to a modular compression and release device and method for use in stacked satellites. Background Technology

[0002] With the expansion of satellite applications in areas such as space exploration, the widespread adoption of 5G signals, the development of network technology, and low-Earth orbit (LEO) interconnection, the launch missions of multi-satellite LEO satellite constellations have experienced explosive growth.

[0003] Stacked satellites combine multiple identical satellites by stacking them together using support pillars, which can greatly improve the utilization rate of the rocket fairing and save launch costs. This design concept is being used in an increasing number of satellite constellations. For launch modes involving the connection and separation of multiple stacked satellites, modular clamping and release devices are a key technology in this field.

[0004] Traditional inter-satellite locking mainly uses wrap-around or point-type inter-satellite unlocking and separation, with pyrotechnic unlocking and separation being more common. Pyrotechnic separation has problems such as poor safety, large impact load, and the generation of pollutants after detonation. Moreover, given that each satellite is different, the inter-satellite 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 purpose of this invention is to provide a modular compression and release device and method for stacked satellites. This modular compression and release device for stacked satellites is convenient for mass production, modular design, and has good interchangeability.

[0007] This invention provides a modular clamping and releasing device for stacked satellites, comprising a load-bearing base, an off-axis unfolding and locking device, a tension spring driving device, a clamping cover assembly, and a pyrotechnic clamping and unlocking assembly. The pyrotechnic clamping and unlocking assembly is installed on both the left and right sides of the load-bearing base. An off-axis unfolding and locking device is installed on the load-bearing base directly in front of each of the two pyrotechnic clamping and unlocking assemblies, and the off-axis unfolding and locking device is connected to the pyrotechnic clamping and unlocking assembly. The clamping cover assembly is connected to the upper end of the pyrotechnic clamping and unlocking assembly. The tension spring driving device is connected to two openings at the front end of the load-bearing base, and the other end of the tension spring driving device is connected to the clamping cover assembly.

[0008] Furthermore, the pyrotechnic clamping and unlocking assembly includes a lower sleeve, an upper sleeve, a pyrotechnic explosive bolt, an adapter rod, a locking pin, a spring, a baffle, and a rubber pad. The lower sleeve is fixed to the load-bearing base, and the upper sleeve is placed on the lower sleeve. The pyrotechnic explosive bolt is installed inside the lower sleeve, and the adapter rod is installed inside the upper sleeve. The bolt of the pyrotechnic explosive bolt passes through the through holes of the lower sleeve and the upper sleeve and is connected to the adapter rod inside the upper sleeve. Two locking pins and the spring are arranged inside the adapter rod. The baffle is installed at the top of the upper sleeve, and the rubber pad is connected inside the upper sleeve below the baffle.

[0009] Furthermore, the clamping cover assembly includes a tension rod, a clamping cover, a locking nut, and a clamping cover fixing member; one end of the tension rod is connected to the adapter rod inside the upper sleeve, and the other end of the tension rod passes through a through hole on one side of the clamping cover fixing member, and the clamping cover fixing member is fixed to the clamping cover by the locking nut.

[0010] Furthermore, the off-axis unfolding and locking device includes a male hinge, a female hinge, an unfolding shaft, a locking buckle, and a locking assembly; one end of the female hinge is fixed to the support base, and the other end of the female hinge is hinged to the male hinge through the unfolding shaft; the male hinge is connected to an 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 support base directly 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 support base, and the other end of the bracket is connected to two positioning pins; the bracket has a mounting hole, the locking rod is located in the mounting hole, and the locking spring is sleeved on the locking rod to provide force for the locking rod to move outward; when the unfolding and locking device is unfolded into place, the positioning pin is used to limit the unfolding angle, and the locking rod slides into the locking buckle on the male hinge to limit rotation.

[0011] Furthermore, the tension spring drive device includes an extension plate, a lower tension spring bracket, a tension spring, and an upper tension spring bracket; the extension plate is connected to both sides of the front end of the load-bearing base, the lower tension spring bracket is connected to the upper extension plate, the tension spring is connected to the lower tension spring bracket, the other end of the tension spring is connected to the upper tension spring bracket, and the upper tension spring bracket is connected to the tension rod.

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

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

[0014] S1: Unlocking process: The launch vehicle provides the unlocking signal for the pyrotechnics, the explosive bolts detonate simultaneously to unlock, the clamping cap assembly and the adapter rod move upward under the impact of the unlocking of the pyrotechnics, the locking pin inside the adapter rod slides into the locking hole of the upper sleeve to lock, and the preload on the stacked satellite support cylinder is released;

[0015] S2: Movement process: After the explosive bolt is detonated and unlocked, the clamping cover assembly is driven by the tension spring drive device to rotate around the off-axis to open the locking device and finally lock.

[0016] S3: Locking process: After the off-axis locking device is fully deployed, the positioning pin limits the deployment angle, and the locking rod slides into the locking buckle on the male hinge to limit rotation, thus completing the separation.

[0017] The modular clamping and releasing device provided by this invention is suitable for multi-satellite separation schemes of stacked satellites, improving rocket space utilization and reducing launch costs. It adopts a modular design, adapting components such as the load-bearing base, clamping cover, and tensioning rod to accommodate different satellite sizes and stacking heights, making it compatible with various types of stacked satellites. It features advantages such as zero pollution, high load capacity, good separation synchronization, and high reliability. The tensioning rod is locked after deployment to prevent irregular movement after separation from affecting satellite separation. After separation from the rocket, all components of the device are passivated and inserted into orbit with the launch vehicle, with no excess components polluting the space environment. Attached Figure Description

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

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

[0020] Figure 3 for Figure 1 Another schematic diagram of a modular compression release device used in stacked satellites.

[0021] Figure 4 for Figure 1 A disassembled schematic diagram of the pyrotechnic compression unlocking component of a modular compression release device used in stacked satellites.

[0022] Figure 5 for Figure 1 A schematic diagram of the compression cover assembly of a modular compression release device used in stacked satellites.

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

[0024] Figure 7 for Figure 1 A schematic diagram of the locking component of a modular compression release device used in stacked satellites.

[0025] Figure 8 for Figure 1 A schematic diagram of the tension spring drive device used in a modular compression release device for stacked satellites.

[0026] Figure 9 for Figure 1 A schematic diagram of a modular compression and release device used in stacked satellites to compress stacked satellites.

[0027] Figure 10 This is a schematic flowchart of the modular compression and release method provided in an embodiment of the present invention.

[0028] The reference numerals and components involved in the accompanying drawings are shown below:

[0029] 1. Load-bearing base; 2. Offset shaft unfolding and locking device; 201. Male hinge

[0030] 202, Female hinge; 203, Unfolding shaft; 204, Locking buckle

[0031] 210. Locking assembly; 211. Bracket; 212. Locking lever

[0032] 213. Locking spring; 214. Positioning pin; 3. Tension spring drive device

[0033] 301. Extension plate; 302. Lower support bracket of tension spring; 303. Tension spring.

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

[0035] 402. Pressure cap; 403. Locking nut; 404. Pressure cap fixing component.

[0036] 5. Fire-pressurized unlocking assembly 501, lower sleeve 502, upper sleeve

[0037] 503, Explosive bolts for pyrotechnic applications; 504, Adapter rod; 505, Locking pin.

[0038] 506, Spring; 507, Baffle; 508, Rubber Pad Detailed Implementation

[0039] The specific embodiments of the present invention will be described in further detail below with reference to the accompanying drawings and examples. The following examples are for illustrative purposes only and are not intended to limit the scope of the invention.

[0040] The terms "first," "second," "third," "fourth," etc., used in the specification and claims of this invention are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence.

[0041] Example 1

[0042] Figure 1 This is a schematic diagram of the modular compression and release device for stacked satellites provided in an embodiment of the present invention. Figure 2 for Figure 1 A partially enlarged schematic diagram of a modular compression and release device used in stacked satellites. Figure 3 for Figure 1 Another schematic diagram of a modular compression and release device used in stacked satellites. Figure 9 for Figure 1 A schematic diagram of a modular compression and release device used in stacked satellites, illustrating the compression of stacked satellites. Please refer to... Figure 1 , Figure 2 , Figure 3 , Figure 9 The modular clamping and releasing device for stacked satellites provided in this embodiment of the invention includes a load-bearing base 1, an off-axis unfolding and locking device 2, a tension spring driving device 3, a clamping cover assembly 4, and a pyrotechnic clamping and unlocking assembly 5. The pyrotechnic clamping and unlocking assembly 5 is installed on both the left and right sides of the load-bearing base 1. The off-axis unfolding and locking device 2 is installed on the load-bearing base 1 directly in front of each of the two pyrotechnic clamping and unlocking assemblies 5, and the off-axis unfolding and locking device 2 is connected to the pyrotechnic clamping and unlocking assembly 5. The clamping cover assembly 4 is connected to the upper end of the pyrotechnic clamping and unlocking assembly 5. The tension spring driving device 3 is connected to two side 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 clamping cover assembly 4.

[0043] Figure 4 for Figure 1 A disassembled schematic diagram of the pyrotechnic clamping and unlocking assembly of a modular clamping and release device used in stacked satellites. Please refer to... Figure 4The pyrotechnic clamping and unlocking assembly 5 of the present invention includes a lower sleeve 501, an upper sleeve 502, a pyrotechnic explosive bolt 503, an adapter 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. Adapter rod 504; the screw of the explosive bolt 503 passes through the through holes of the lower sleeve 501 and the upper sleeve 502, and is connected to the adapter rod 504 inside the upper sleeve 502; two locking pins 505 and the spring 506 are arranged inside the adapter rod 504; the baffle 507 is installed on the top of the upper sleeve 502; and the rubber pad 508 is connected inside the upper sleeve 502 below the baffle 507.

[0044] Figure 5 for Figure 1 A schematic diagram of the clamping cover assembly of a modular clamping and release device used in stacked satellites. Please refer to... Figure 5 The clamping cover assembly 4 of the present invention includes a tension rod 401, a clamping cover 402, a locking nut 403, and a clamping cover fixing member 404; one end of the tension rod 401 is connected to the adapter rod 504 inside 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 vertically by the locking nut 403.

[0045] It should be noted that during use, the clamping cover 402 clamps the support cylinder of the top stacked satellites, and the clamping preload is applied to the support cylinder of the stacked flat satellites through the tension rod 401 and the clamping cover 402.

[0046] When the launch vehicle sends an unlocking signal to control the release of the explosive bolts, the tension rod 401, the pressure cap assembly 4, and the adapter rod 504 move upward under the impact force of the release of the explosive bolts. The locking pin 505 inside the adapter rod 504 slides into the locking hole of the upper sleeve 502 and locks, releasing the preload on the stacked satellite support cylinder. The baffle 507 is used for limiting the position, and the rubber pad 508 is used for buffering.

[0047] Figure 6 for Figure 1 A schematic diagram of the off-axis deployment locking device of a modular compression release device used in stacked satellites. Figure 7 for Figure 1 A schematic diagram of the locking assembly of a modular clamping and releasing device used in stacked satellites. Please refer to... Figure 6 , Figure 7The off-axis unfolding and locking device 2 of the present invention includes a male hinge 201, a female hinge 202, an unfolding shaft 203, a locking buckle 204, and a locking assembly 210. One end of the female hinge 202 is fixed to the support 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 an extension section on the upper sleeve 502, and the locking buckle 204 is fixedly connected to the upper part of the male hinge 201. The locking assembly 210 is fixedly connected to the support base 1 directly in front of the female hinge 202. The locking assembly 210 includes a bracket 211 and a lock. The bracket 211 comprises a fixed rod 212, a locking spring 213, and a positioning pin 214. One end of the bracket 211 is fixed to the load-bearing base 1, and the other end of the bracket 211 is connected to two positioning pins 214. The bracket 211 has a mounting hole, 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 A schematic diagram of the tension spring drive mechanism used in a modular compression release device for stacked satellites. Please refer to... Figure 8 The tension spring drive device 3 of the present invention includes an extension plate 301, a lower tension spring bracket 302, a tension spring 303, and an upper tension spring bracket 304. The extension plate 301 is connected to both sides of the front end of the load-bearing base 1. The lower tension spring bracket 302 is connected to the upper side of the extension plate 301. The tension spring 303 is connected to the lower tension spring bracket 302. The other end of the tension spring 303 is connected to the upper tension spring bracket 304. The upper tension spring bracket 304 is connected to the tension rod 401.

[0049] It should be noted that after the explosive bolts detonate and unlock, the clamping cover assembly 4, driven by the tension spring drive device 3, rotates around the off-axis to unlock the locking device 2 and finally locks, and then re-enters orbit with the final stage rocket.

[0050] The modular clamping and releasing device of the present invention, applied to stacked satellites, is assembled by first fixing the load-bearing base 1 to the adapter plane of the launch vehicle. According to the position distribution of the load-bearing cylinders of the stacked satellites, the load-bearing base 1 supports the load-bearing cylinders of the stacked satellites. A set of pyrotechnic clamping and unlocking assembly 5, an off-axis unfolding and locking device 2, a clamping cover assembly 4, and a tension spring drive device 3 are installed sequentially on the left and right sides of the load-bearing base 1. After separation, under the force of the tension spring drive device 3, the clamping cover assembly 4 flips downward. When it flips to the end of its stroke, the positioning pin 214 restricts the unfolding angle, and the locking rod 212 slides into the locking buckle 204 on the male hinge 201 to restrict rotation, thus completing the separation.

[0051] Figure 10 This is a schematic flowchart illustrating the modular compression and release method provided in an embodiment of the present invention. Please refer to... Figure 10 The present invention also provides a modular compression release method for stacked satellites, wherein the modular compression release method is applied to the above-mentioned modular compression release device for stacked satellites.

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

[0053] S1: Unlocking process: The launch vehicle provides the unlocking signal for the pyrotechnics, the explosive bolts detonate simultaneously to unlock, the clamping cap assembly 4 and the adapter rod 504 move upward under the impact force of the unlocking of the pyrotechnics, the locking pin 505 inside the adapter rod 504 slides into the locking hole of the upper sleeve 502 to lock, and the preload on the stacked satellite support cylinder is released.

[0054] S2: Movement process: After the explosive bolt is detonated and unlocked, the clamping cover assembly 4 rotates around the off-axis and finally locks under the drive of the tension spring drive device 3;

[0055] S3: Locking process: After the off-axis unfolding locking device 2 is unfolded into place, the positioning pin 214 restricts the unfolding angle, and the locking rod 212 slides into the locking buckle 204 on the male hinge 201 to restrict rotation, and the separation is completed.

[0056] As can be seen from the above description, the advantages of this invention are:

[0057] 1. The modular compression and release device of the present invention, applied to stacked satellites, is suitable for multi-satellite separation schemes of stacked satellites, improving rocket space utilization and reducing launch costs;

[0058] 2. Modular clamping and releasing device for stacked satellites: It adopts a modular design scheme and makes adaptive modifications to parts such as the load-bearing base, clamping cover, and tensioning rod for different satellite sizes and stacking heights, so as to be compatible with different types of stacked satellites.

[0059] 3. The modular compression and release device applied to stacked satellites has the advantages of being pollution-free, having a large load capacity, good separation synchronization, and high reliability;

[0060] 4. A modular clamping and release device applied to stacked satellites, which locks in place after the tension rod is fully extended to prevent irregular movement from affecting satellite separation after separation;

[0061] 5. A modular compression and release device applied to stacked satellites: after separation from the launch vehicle, all components of the device are passivated and inserted into orbit along with the launch vehicle, with no excess parts polluting the space environment.

[0062] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A modular compression and release device for stacked satellites, characterized in that, It includes a load-bearing base (1), an off-axis unfolding and locking device (2), a tension spring drive device (3), a pressure cover assembly (4), and a fire-pressing and unlocking assembly (5). The pyrotechnic pressing and unlocking assembly (5) is installed on both the left and right sides of the support base (1). The off-axis unfolding and locking device (2) is installed on the support base (1) in front of the two pyrotechnic pressing and unlocking assemblies (5). The off-axis unfolding and locking device (2) is connected to the pyrotechnic pressing and unlocking assembly (5). The pressing cover assembly (4) is connected to the upper end of the pyrotechnic pressing and unlocking assembly (5), and the tension spring drive device (3) is connected to both sides of the front end of the bearing base (1). The other end of the tension spring drive device (3) is connected to the pressing cover assembly (4). The pyrotechnic clamping and unlocking assembly (5) includes a lower sleeve (501), an upper sleeve (502), a pyrotechnic explosion bolt (503), an adapter 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 explosive bolt (503) is installed in the lower sleeve (501), and the adapter rod (504) is installed in the upper sleeve (502). The bolt of the explosive bolt (503) passes through the through holes of the lower sleeve (501) and the upper sleeve (502) and is connected to the adapter rod (504) inside the upper sleeve (502). Two locking pins (505) and a spring (506) are arranged inside the adapter rod (504). A baffle (507) is installed on the top of the upper sleeve (502). A rubber pad (508) is connected inside the upper sleeve (502) below the baffle (507).

2. The modular compression and release device for stacked satellites according to claim 1, characterized in that, The clamping cover assembly (4) includes a tensioning rod (401), a clamping cover (402), a locking nut (403), and a clamping cover fastener (404). One end of the tensioning rod (401) is connected to the adapter rod (504) inside the upper sleeve (502), and the other end of the tensioning rod (401) passes through the through hole on one side of the pressure cover fixing member (404), and the pressure cover fixing member (404) and the pressure cover (402) are fixed vertically by the locking nut (403).

3. The modular compression and release device for stacked satellites according to claim 1, characterized in that, The off-axis unfolding locking device (2) includes a male hinge (201), a female hinge (202), an unfolding 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 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 on the upper part of the male hinge (201). The locking assembly (210) is fixedly connected to the load-bearing base (1) in front of the female hinge (202). The locking assembly (210) includes a bracket (211), a locking rod (212), a locking spring (213), and a positioning pin (214). One end of the bracket (211) is fixed to the load-bearing base (1), and the other end of the bracket (211) is connected to two positioning pins (214). The bracket (211) has a mounting hole, the locking rod (212) is located in the mounting hole, and the locking spring (213) is sleeved on the locking rod (212) to provide the locking rod (212) with a force 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 the rotation.

4. The modular compression and release device for stacked satellites according to claim 2, characterized in that, The tension spring drive device (3) includes an extension plate (301), a lower tension spring bracket (302), a tension spring (303), and an upper tension spring bracket (304). The extension plate (301) is connected to both sides of the front end of the load-bearing base (1). The lower tension spring bracket (302) is connected to the upper extension plate (301). The tension spring (303) is connected to the lower tension spring bracket (302). The other end of the tension spring (303) is connected to the upper tension spring bracket (304). The upper tension spring bracket (304) is connected to the tension rod (401).

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