Thermal unlocking structure for spaceflight satellite

Abstract

The invention discloses a thermal unlocking structure for a spaceflight satellite. The thermal unlocking structure comprises a first structural part, a second structural part, a thermal unlocking assembly, a winding assembly and a restraint strap. After the restraint strap is fused by the hot knife, the knife holder retreats under the action of the spring, and the stop pin synchronously unlocks the limiting piece on the winding roller; the winding roller is driven by the pre-tightening torsion spring to rotate rapidly, and the fused restraint strap is completely rewound into the closed cavity in the shell through the guide wire. According to the design, it is ensured that restraint strap residues generated in the separation process are actively stored and restrained, and the risk that the restraint strap residues freely drift away to become space junk or interfere with a satellite body and an unfolding mechanism is fundamentally eliminated. The whole recovery process does not need extra energy, only depends on elastic potential energy pre-stored by the mechanism for driving, has the advantages of high reliability, low impact and no secondary pollution, and remarkably improves the safety and cleanliness of an on-orbit unlocking and releasing task of the spacecraft.

Description

Technical Field

[0001] This invention relates to the field of spacecraft unlocking technology, specifically a thermal unlocking structure for space satellites. Background Technology

[0002] In the field of spacecraft technology, to ensure the mechanical safety of satellites and their payloads during launch, many components must be locked during launch and unlocked and deployed after entering orbit. The reliability of this unlocking and release function is directly related to the success or failure of the on-orbit mission. Traditionally, pyrotechnic unlocking devices are used, which achieve separation by generating instantaneous explosive force, but these have inherent limitations such as high impact and high pollution risk. To adapt to the increasingly demanding requirements of clean and low-impact environments for precision spacecraft platforms, non-pyrotechnic thermal cutting unlocking devices have emerged. This device mainly consists of a high-strength constraint band that withstands pre-tension and a matching thermal blade. Upon receiving the unlocking command in orbit, the thermal blade is energized and heats up, instantly melting the constraint band it contacts, thereby releasing the mechanical constraint on the connected components and enabling satellite separation into orbit and the deployment of mechanisms such as solar panels and antennas. Due to its advantages such as minimal impact and no pollution, this technology has become an important development direction for modern spacecraft unlocking mechanisms. However, the currently widely used thermal cutting unlocking technology generally has a common defect: it only completes the melting and unlocking function, and lacks an effective on-orbit disposal design for the remaining segment of the constraint band in a free state after melting. These remnants may be directly ejected into orbit, becoming potential space debris; or they may remain near the spacecraft, drifting freely and easily becoming entangled or hooked during subsequent attitude adjustments or mechanism deployments, posing serious safety hazards and interference risks to the normal operation of the spacecraft. This unresolved "space debris" problem restricts the further application of thermal cutting unlocking technology in high-reliability, high-cleanliness space missions. Summary of the Invention

[0003] Therefore, in order to solve the above problems, the object of the present invention is to provide a thermal unlocking structure for aerospace satellites, comprising: A first structural component, the first structural component including a first mating surface, the first mating surface being provided with a positioning protrusion; The second structural component includes a second mating surface, and a positioning recess is provided on the second mating surface; A thermal unlocking assembly is installed on a second structural member and includes a thermal blade, a blade holder, and a blade holder spring. The thermal blade is installed on the blade holder, and a stop pin is provided on the side of the blade holder facing away from the thermal blade. The blade holder spring is disposed between the second structural member and the blade holder. A winding assembly is installed on the side of the second structural member facing away from the thermal unlocking assembly. It includes a housing, a winding roller, and a torsion spring. The housing is connected to the second structural member. The winding roller and the torsion spring are disposed inside the housing. The two ends of the torsion spring are respectively connected to the winding roller and the housing. A guide wire is connected to the winding roller. The end of the guide wire protrudes out of the housing. A limit member is fixed on the side of the winding roller. A constraint band is connected to the guide wire and its inner edge abuts against the hot knife. The constraint band is used to pre-tighten the first structural member and the second structural member.

[0004] The stop pin extends into the housing and abuts against the limiting member.

[0005] Preferably, the limiting element is a cam, and the lower end of the stop pin is arc-shaped and cooperates with the cam.

[0006] Preferably, the side of the housing is provided with a torsion spring tensioning mechanism, which includes a ratchet and a drive wheel arranged coaxially. The ratchet is arranged facing the inside of the housing, and the drive wheel is arranged facing the outside of the housing. One end of the torsion spring is fixed to the ratchet. The housing is provided with a stop pawl that cooperates with the ratchet. The drive wheel is provided with a drive groove facing away from the ratchet.

[0007] Preferably, the tool holder includes a first base plate and a second base plate connected to each other, the hot knife is mounted on the first base plate, there is an adjustment gap between the first base plate and the second base plate, the second structural member has a guide post on the side facing the tool holder, the spring is sleeved on the outer edge of the guide post, the guide post has a bolt hole in the middle, an adjusting bolt is provided in the bolt hole, and the nut of the adjusting bolt is engaged in the adjustment gap.

[0008] Preferably, the housing has a wire passage groove on the side away from the second structural member, one end of the guide wire passes through the wire passage groove and is connected to the constraint band, and protective covers are provided on both sides of the wire passage groove. When the protective covers are closed, a sealed space is formed inside the housing.

[0009] Preferably, the two sides of the second structural member are symmetrically provided with guide plates, and the guide plates include guide grooves through which the restraint belt can pass.

[0010] Preferably, the tool holder includes a tool groove, in which at least two parallel hot tools are installed, and the end of the hot tool that abuts against the constraint band has a chamfer.

[0011] Preferably, the second structural member has symmetrical mounting plates on the side near the winding assembly, the mounting plates are rotatably connected to the second structural member, the outer edge of the housing has a mounting bevel that fits with the mounting plate, and the mounting bevel and the mounting plate have coaxial bolt holes.

[0012] Preferably, the housing further includes a release port, wherein the release port is provided with a detachable cover plate; A disassembly / assembly channel through which the take-up roller passes; An axial channel is provided for mounting a take-up roller. A first elastic element and a second elastic element are provided on the side of the axial channel facing away from the cam. The first elastic element is axially arranged to push the take-up roller to move toward the cam, and the second elastic element is circumferentially arranged to restrict the axial movement of the first elastic element.

[0013] The take-up roller has protruding edges at both ends. The protruding edge facing away from the cam is engaged with the second elastic element, and the protruding edge facing the cam is provided with a spline. The side of the cam facing the take-up roller is provided with a keyway that is engaged with the spline.

[0014] Preferably, the first elastic element and the second elastic element are specifically elastic metal sheets.

[0015] The beneficial effects of this invention are: By incorporating a torsion spring-driven winding assembly within the component and linking it with the hot-blade unlocking mechanism, immediate, automatic, and reliable recovery of the constraint tape after it melts is achieved. Specifically, after the hot blade melts the constraint tape, the blade holder retracts under the action of the spring, and its stop pin simultaneously releases the lock on the upper limit of the winding roller. Driven by the pre-tensioned torsion spring, the winding roller rotates rapidly, winding the melted constraint tape back into the sealed cavity inside the shell via the guide wire. This design ensures that the constraint tape residue generated during the separation process is actively collected and restrained, fundamentally eliminating the risk of it freely dispersing into space debris or interfering with the satellite body and deployment mechanism. The entire recovery process requires no additional energy, relying solely on the pre-stored elastic potential energy of the mechanism, and has the advantages of high reliability, low impact, and no secondary pollution, significantly improving the safety and cleanliness of spacecraft on-orbit unlocking and release missions. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of the structure of the present invention; Figure 2 This is a schematic diagram of the hot-unlocking component; Figure 3 This is a cross-sectional structural diagram of the present invention; Figure 4 This is a schematic diagram of the winding assembly. Figure 5 This is a schematic diagram of the internal structure of the winding assembly; Figure 6 This is a structural diagram of the internal structure of the winding assembly from another perspective. Figure 7 for Figure 5 A schematic diagram of the structure at point A; Figure 8 This is a cross-sectional structural diagram of the winding assembly; Figure 9 for Figure 8 A schematic diagram of the structure at point B; Figure 10 A structural schematic diagram of the winding assembly from another perspective; Figure 11 This is a schematic diagram of the wire channel structure; Reference numerals: 0100, First structural component; 0101, First mating surface; 0102, Positioning convex surface; 0200, Second structural component; 0201, Second mating surface; 0202, Positioning concave surface; 0203, Mounting plate; 0204, Guide post; 0205, Adjusting bolt; 0206, Guide guard plate; 0207, Guide groove; 0300, Thermal unlocking assembly; 0301, Hot knife; 0302, Knife holder; 0303, Knife groove; 0304, First base plate; 0305, Second base plate; 0306, Adjusting gap; 0307, ​​Knife holder spring; 0308, Stop pin; 0400, Rewinding assembly; 0400 1. Housing; 0402. Mounting ramp; 0403. Release port; 0404. Cover plate; 0405. Disassembly / assembly channel; 0406. Axial channel; 0407. Wire guide groove; 0408. Take-up roller; 0409. Guide wire; 0410. Raised edge; 0411. Spline; 0412. Torsion spring; 0413. Cam; 0414. Keyway; 0415. Rotating shaft; 0416. First elastic element; 0417. Second elastic element; 0418. Torsion spring tensioning mechanism; 0419. Ratchet; 0420. Drive wheel; 0421. Drive groove; 0422. Stop pawl; 0423. Protective cover; 0500. Restraint strap.

[0018] The realization of the objective, functional features and advantages of the present invention will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0019] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.

[0020] In the description of this application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0021] Unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to the internal connection between two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0022] Example 1: Figures 1-11 This invention illustrates a thermal unlocking structure for a spacecraft, comprising a first structural component 0100, a second structural component 0200, a thermal unlocking assembly 0300, a winding assembly 0400, and a restraint strap 0500. The first structural component 0100 and the second structural component 0200 are respectively connected to two independent parts on the spacecraft that require fixation. During launch, the restraint strap 0500 secures them together to form a single structure to withstand mechanical loads. After orbiting, the thermal unlocking assembly 0300 melts the restraint strap 0500, allowing the first structural component 0100 and the second structural component 0200 to separate.

[0023] The first structural component 0100 has a first mating surface 0101 with a positioning convex surface 0102, and the second structural component 0200 has a second mating surface 0201 with a positioning concave surface 0202. The positioning convex surface 0102 and the positioning concave surface 0202 cooperate to ensure precise positioning accuracy when the two structural components are mated, providing a basis for the reliable operation of the thermal unlocking assembly 0300. The thermal unlocking assembly 0300 is installed on the second structural component 0200 and includes a hot blade 0301, a blade holder 0302, and a blade holder spring 0307. The hot blade 0301 is fixed to the blade holder 0302, and a stop pin 0308 is provided on the side of the blade holder 0302 facing away from the hot blade 0301. The blade holder spring 0307 is pre-tensioned and installed between the second structural component 0200 and the blade holder 0302 to provide the blade holder 0302 with an elastic restoring force to move it away from the second structural component 0200. The constraint strap 0500 wraps around and tightens the first and second structural members 0200, fixing them together. A take-up assembly 0400 is installed on the side of the second structural member 0200 facing away from the thermal unlocking assembly 0300, used to retrieve the melted constraint strap 0500. It includes a housing 0401, a take-up roller 0408, and a torsion spring 0412. The housing 0401 is connected to the second structural member 0200, and the take-up roller 0408 and torsion spring 0412 are housed within the housing 0401. One end of the torsion spring 0412 is connected to the take-up roller 0408, and the other end is connected to the housing 0401, providing rotational torque to the take-up roller 0408. A guide wire 0409 is wound around the take-up roller 0408, its end extending out of the housing 0401 and connecting to the constraint strap 0500. A limiting member is fixed to the side of the take-up roller 0408, and the stop pin 0308 of the thermal unlocking assembly 0300 extends into the housing 0401, with its end abutting against the limiting member. During initial assembly, the torsion spring 0412 is preloaded to store elastic potential energy. Then, the blade holder 0302 is pressed down, causing the stop pin 0308 to abut against the limiting member, preventing the take-up roller 0408 from rotating under the action of the torsion spring 0412. Finally, the constraint band 0500 is installed and tensioned. The constraint band 0500 generates a clamping force on the hot blade 0301. This clamping force is transmitted to the stop pin 0308 through the blade holder 0302, and is ultimately converted into a locking force on the limiting member, balancing the preload torque of the torsion spring 0412 and keeping the system in a stable locked state. When the hot knife 0301 is energized and melts the constraint band 0500, the tension of the constraint band 0500 disappears. Under the action of the knife holder spring 0307, ​​the cutter holder 0302 drives the stop pin 0308 to retract, releasing the mechanical constraint on the limiting component. The torsion spring 0412 then releases its stored elastic potential energy, driving the take-up roller 0408 to rotate. Through the guide line 0409, the melted constraint band 0500 is quickly and completely rewound and stored inside the housing 0401, completing the waste recycling.

[0024] In this embodiment, the limiting component is designed as a cam 0413. The lower end of the stop pin 0308 is machined into an arc surface to match the contour surface of the cam 0413. This configuration allows the stop pin 0308 to form effective line contact or surface contact with the protruding part of the cam 0413 within a certain assembly tolerance range, achieving reliable locking. A rotating shaft 0415 is provided at the axis of the cam 0413, which is rotatably fixed to the cam 0413 and can be sleeved by a torsion spring 0412.

[0025] The housing 0401 integrates a torsion spring tensioning mechanism 0418 on its side, used to apply and adjust the preload of the torsion spring 0412 during later assembly or maintenance. This mechanism includes a ratchet 0419 and a drive wheel 0420 coaxially arranged. The ratchet 0419 is rotatably connected to a rotating shaft 0415, and both the ratchet 0419 and the drive wheel 0420 are rotatably connected to the housing 0401. The ratchet 0419 faces inwards from the housing 0401, and one end of the torsion spring 0412 is fixed to it. The drive wheel 0420 faces outwards from the housing 0401, and its end face has a drive groove 0421 for engaging with external tools. The housing 0401 contains a stop pawl 0422 that meshes with the ratchet 0419. When the drive wheel 0420 is turned by an external tool, the ratchet 0419 rotates in the same direction, applying and increasing the preload torque to the torsion spring 0412. The stop pawl 0422 prevents the ratchet 0419 from reversing, thereby maintaining the set preload force.

[0026] To prevent the hot knife 0301 from contacting the first structural member 0100 due to excessive movement caused by inertia or spring force after melting the constraint band 0500, a travel limit mechanism for the hot knife 0301 is provided. Specifically, the tool holder 0302 is composed of a first base plate 0304 and a second base plate 0305 connected together. The hot knife 0301 is mounted on the first base plate 0304, and an adjustment gap 0306 is left between the two base plates. The second structural member 0200 is provided with a guide post 0204, and the tool holder spring 0307 is sleeved around the guide post 0204. The guide post 0204 has a threaded hole in its center, and an adjusting bolt 0205 is built in it. The head of the bolt is located within the aforementioned adjustment gap 0306. Rotating the adjusting bolt 0205 can change the height of its head relative to the second structural member 0200. When the constraint band 0500 melts and the tool holder 0302 retracts under the action of the spring, the second seat plate 0305 will abut against the head of the adjusting bolt 0205, thereby limiting the maximum retraction stroke of the tool holder 0302 and protecting the surrounding equipment.

[0027] A wire-passing groove 0407 is opened on the side of the housing 0401 away from the second structural component 0200, through which the guide wire 0409 exits. Protective covers 0423 are hinged to both sides of the wire-passing groove 0407. When the restraint strap 0500 is completely retracted, the spring force installed inside the housing 0401 pushes the two protective covers 0423 to close, forming a sealed cavity inside the housing 0401, effectively preventing the reclaimed material from accidentally falling out and shielding it from the influence of the external environment.

[0028] The second structural component 0200 has guide plates 0206 symmetrically installed on its two sides, with guide grooves 0207 on the plates. The constraint belt 0500 passes through the two guide grooves 0207, and its winding movement path is constrained and guided by the guide grooves 0207, which can effectively prevent it from hooking or interfering with other components of the spacecraft during the winding process, ensuring smooth and reliable recovery.

[0029] The tool holder 0302 has a tool groove 0303, within which two hot blades 0301 are installed side-by-side. These two hot blades 0301 are electrically independent. If one fails due to an open circuit, material defect, or installation error, the other can still be independently powered and heated, ensuring that the restraint band 0500 is reliably melted. This redundant design enhances the reliability of thermal unlocking. The cutting edge of the hot blade 0301 that contacts the restraint band 0500 is chamfered. This chamfer eliminates sharp edges, preventing unintended cutting wear on the restraint band 0500 during tensioning and spacecraft vibration, ensuring that it is only melted when the hot blade 0301 is powered on and heated.

[0030] Working principle: In the initial state before launch, the pre-tightened constraint band 0500 generates tension, which is transmitted to the cutter holder 0302 through the hot knife 0301, forcing the stop pin 0308 to press against the cam 0413 on the take-up roller 0408, thereby resisting the torque of the torsion spring 0412, keeping the entire system in a stable lock, and ensuring that the first and second structural components 0200 are fixed together.

[0031] Upon receiving an unlocking command, the current drives the hot knife 0301. The redundant design of the dual hot knives 0301 ensures that the constraint band 0500 is reliably melted. At the moment the constraint band 0500 melts, the clamping force applied to the knife holder 0302 disappears, and the mechanical balance within the device is broken. Driven by the knife holder spring 0307, ​​the knife holder 0302 causes the stop pin 0308 to quickly retract, disengaging from contact with the cam 0413. The rotational constraint of the take-up roller 0408 is thus released.

[0032] Driven by the elastic potential energy stored in the pre-tensioned torsion spring 0412, the take-up roller 0408 rotates at high speed, quickly and neatly rewinding the broken restraint strap 0500 back onto the take-up roller 0408 inside the shell 0401 via the guide wire 0409, completing the active collection of space waste. Finally, as the restraint strap 0500 is fully retracted, the protective cover 0423 at the outlet of the shell 0401 automatically closes under the action of the internal spring, permanently restraining the recovered material within the sealed cavity and completely eliminating any potential interference risk to the spacecraft's on-orbit operation. The entire process is automatically triggered by a fusible link, requiring no external secondary commands, and is completed solely by the spring potential energy stored within the mechanism.

[0033] It should also be noted that the constraint strap 0500 is in a relaxed state in the attached drawing, but in actual application it is in a tied and tightened state. The constraint strap 0500 in the attached drawing is only used to illustrate the structural position.

[0034] Example 2: Figures 1-11 This invention illustrates a thermal unlocking structure for aerospace satellites. The difference between this embodiment and Embodiment 1 is that the drive groove 0421 is cross-shaped and fits into a screwdriver. This embodiment is designed for testing. Operators can increase the preload of the torsion spring 0412 by turning the drive wheel 0420 with a screwdriver to confirm the specific value of the torsion spring 0412 preload setting. This ensures that during subsequent mass production, the rotational force applied by the torsion spring 0412 can cause the take-up roller 0408 to rotate a sufficient number of revolutions to fully retract the constraint band 0500 into the housing 0401.

[0035] Example 3: Figures 1-11 This invention provides a thermal unlocking structure for aerospace satellites. The difference between this embodiment and Embodiment 1 is that the winding assembly 0400 in this embodiment is designed to be detachable, so that the winding assembly 0400 can be disassembled after the second structural component 0200 is recovered for subsequent testing and analysis.

[0036] To facilitate assembly and maintenance, a mounting plate 0203 is symmetrically arranged on the side of the second structural component 0200 adjacent to the winding assembly 0400. This mounting plate 0203 is rotatably connected to the second structural component 0200. The outer edge of the housing 0401 is designed with a matching mounting ramp 0402, and coaxial bolt holes are provided on both the ramp and the mounting plate 0203. During assembly, the winding assembly 0400 is initially positioned, then the mounting plate 0203 is rotated to align its bolt holes with the bolt holes on the ramp of the housing 0401, and finally the fastening bolts are inserted, thus achieving a reliable and quick connection between the winding assembly 0400 and the second structural component 0200.

[0037] The housing 0401 structure is further optimized, integrating maintenance and assembly guidance functions. Specifically, the housing 0401 is provided with a release port 0403, which is closed by a removable cover plate 0404. The housing 0401 internally has a connecting disassembly / assembly channel 0405 and an axial channel 0406. The disassembly / assembly channel 0405 allows the entire take-up roller 0408 to pass through; the axial channel 0406 is used to ultimately accommodate and support the take-up roller 0408, and its end facing away from the cam 0413 is provided with a first elastic element 0416 and a second elastic element 0417. In this embodiment, the first elastic element 0416 includes a spring and a locking block connected to the spring, and the second elastic element 0417 is specifically a resilient metal tab. The first elastic element 0416 is arranged axially to apply a spring force to the take-up roller 0408, causing it to move towards the cam 0413; the second elastic element 0417 is arranged circumferentially to limit the axial displacement of the first elastic element 0416 during the initial installation phase. The take-up roller 0408 has radial protrusions 0410 at both ends. The protrusions 0410 facing away from the cam 0413 are used to cooperate with the second elastic element 0417, while the end face of the protrusions 0410 facing the cam 0413 is machined with splines 0411. The end face of the cam 0413 facing the take-up roller 0408 is provided with a keyway 0414 that cooperates with it.

[0038] During installation, the operator opens the release port 0403 cover 0404 and places the take-up roller 0408 assembly into the housing 0401 along the disassembly / removal channel 0405. When the protruding edge 0410 at one end of the take-up roller 0408 moves to contact the second elastic element 0417, it pushes the protruding edge 0410 and causes it to undergo radial elastic deformation until the protruding edge 0410 is embedded in the housing 0401. At this time, the first elastic element 0416 is released, and its axial elastic force pushes the entire take-up roller 0408 towards the cam 0413. If the spline 0411 of the take-up roller 0408 is exactly aligned with the keyway 0414 of the cam 0413, the spline 0411 automatically engages with the keyway 0414, achieving axial rotational linkage. If misalignment occurs, the drive wheel 0420 can be turned with an external tool. The torque of the drive wheel 0420 is transmitted to the torsion spring 0412 via the ratchet 0419, which further drives the cam 0413, which is fixed to the torsion spring 0412, to rotate slightly until the keyway 0414 rotates to the position aligned with the spline 0411. Under the continuous pushing of the first elastic element 0416, the spline 0411 is then fully engaged with the keyway 0414. At this point, the take-up roller 0408 and the cam 0413 are reliably connected, completing the assembly of the core transmission component.

[0039] When disassembling the take-up roller 0408, first open the release port 0403 cover plate 0404. Use a tool to clamp or hold the radial protrusion 0410 of the take-up roller 0408 on the side opposite to the cam 0413, and apply axial force to pull the take-up roller 0408, causing it to overcome the elastic force of the first elastic element 0416 and move away from the cam 0413. This axial displacement will cause the spline 0411 at the end of the take-up roller 0408 to disengage from the keyway 0414 of the cam 0413. Then, the take-up roller 0408 assembly can be completely removed from the housing 0401 along the disassembly channel 0405, completing the disassembly operation.

[0040] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the implementation of the present invention. Those skilled in the art will be able to make various obvious changes, readjustments, and substitutions without departing from the scope of protection of the present invention. It is neither necessary nor possible to exhaustively describe all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the claims of the present invention.

Claims

1. A thermal unlocking structure for aerospace satellites, characterized in that, include: The first structural component (0100) includes a first mating surface (0101) and a positioning protrusion (0102) is provided on the first mating surface (0101). The second structural component (0200) includes a second mating surface (0201) and a positioning recess (0202) is provided on the second mating surface (0201). A thermal unlocking assembly (0300) is installed on a second structural member (0200) and includes a thermal blade (0301), a blade holder (0302), and a blade holder spring (0307). The thermal blade (0301) is installed on the blade holder (0302). A stop pin (0308) is provided on the side of the blade holder (0302) facing away from the thermal blade (0301). The blade holder spring (0307) is disposed between the second structural member (0200) and the blade holder (0302). A winding assembly (0400) is installed on the side of the second structural member (0200) facing away from the thermal unlocking assembly (0300). The winding assembly (0400) includes a housing (0401), a winding roller (0408), and a torsion spring (0412). The housing (0401) is connected to the second structural member (0200). The winding roller (0408) and the torsion spring (0412) are disposed inside the housing (0401). The two ends of the torsion spring (0412) are respectively connected to the winding roller (0408) and the housing (0401). A guide line (0409) is connected to the winding roller (0408). The end of the guide line (0409) protrudes from the housing (0401). A limiter is fixed on the side of the winding roller (0408). A constraint band (0500) is connected to a guide wire (0409) and its inner edge abuts against a hot knife (0301). The constraint band (0500) is used to pre-tighten the first structural member (0100) and the second structural member (0200). The stop pin (0308) extends into the housing (0401) and abuts against the limiting member.

2. The thermal unlocking structure for aerospace satellites according to claim 1, characterized in that, The limiting component is a cam (0413), and the lower end of the stop pin (0308) is arc-shaped and cooperates with the cam (0413).

3. The thermal unlocking structure for aerospace satellites according to claim 1, characterized in that, The housing (0401) has a torsion spring tensioning mechanism (0418) on its side. The torsion spring tensioning mechanism (0418) includes a ratchet (0419) and a drive wheel (0420) arranged coaxially. The ratchet (0419) is arranged facing the inside of the housing (0401), and the drive wheel (0420) is arranged facing the outside of the housing (0401). One end of the torsion spring (0412) is fixed to the ratchet (0419). The housing (0401) has a stop pawl (0422) that cooperates with the ratchet (0419). The drive wheel (0420) has a drive groove (0421) facing away from the ratchet (0419).

4. The thermal unlocking structure for aerospace satellites according to claim 1, characterized in that, The tool holder (0302) includes a first base plate (0304) and a second base plate (0305) connected to each other. A hot knife (0301) is installed on the first base plate (0304). There is an adjustment gap (0306) between the first base plate (0304) and the second base plate (0305). The second structural member (0200) has a guide post (0204) on the side facing the tool holder (0302). The spring is sleeved on the outer edge of the guide post (0204). The guide post (0204) has a bolt hole in the middle. An adjusting bolt (0205) is provided in the bolt hole. The nut of the adjusting bolt (0205) is engaged in the adjustment gap (0306).

5. The thermal unlocking structure for aerospace satellites according to claim 1, characterized in that, The housing (0401) has a wire groove (0407) on the side away from the second structural member (0200). One end of the guide wire (0409) passes through the wire groove (0407) and is connected to the constraint band (0500). Protective covers (0423) are provided on both sides of the wire groove (0407). When the protective covers (0423) are closed, a sealed space is formed inside the housing (0401).

6. The thermal unlocking structure for aerospace satellites according to claim 1, characterized in that, The second structural member (0200) has guide plates (0206) symmetrically arranged on two sides. The guide plates (0206) include guide grooves (0207) through which the restraint belt (0500) can pass.

7. The thermal unlocking structure for aerospace satellites according to claim 1, characterized in that, The tool holder (0302) includes a tool groove (0303), in which at least two parallel hot blades (0301) are installed, and the end of the hot blade (0301) that abuts against the constraint band (0500) has a chamfer.

8. The thermal unlocking structure for aerospace satellites according to claim 1, characterized in that, The second structural component (0200) has a mounting plate (0203) symmetrically provided on the side near the winding assembly (0400). The mounting plate (0203) is rotatably connected to the second structural component (0200). The outer edge of the housing (0401) has a mounting inclined surface (0402) that cooperates with the mounting plate (0203). The mounting inclined surface (0402) and the mounting plate (0203) have coaxial bolt holes.

9. The thermal unlocking structure for aerospace satellites according to claim 1, characterized in that, The housing (0401) also includes: Release port (0403), wherein a detachable cover plate (0404) is provided at the release port (0403). Disassembly and assembly channel (0405), through which take-up roller (0408) passes; An axial channel (0406) is provided for mounting a take-up roller (0408). A first elastic element (0416) and a second elastic element (0417) are provided on the side of the axial channel (0406) facing away from the cam (0413). The first elastic element (0416) is axially arranged to push the take-up roller (0408) towards the cam (0413). The second elastic element (0417) is circumferentially arranged to restrict the axial movement of the first elastic element (0416). The take-up roller (0408) has protruding edges (0410) at both ends. The protruding edge (0410) facing away from the cam (0413) is engaged with the second elastic element (0417). The protruding edge (0410) facing the cam (0413) is provided with a spline (0411). The side of the cam (0413) facing the take-up roller (0408) is provided with a keyway (0414) which is engaged with the spline (0411).

10. The thermal unlocking structure for aerospace satellites according to claim 9, characterized in that, The first elastic element (0416) and the second elastic element (0417) are specifically elastic metal bent sheets.

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