Electromagnetic unlocking winding type split screw satellite-rocket separation device

Abstract

The invention relates to the technical field of aerospace, in particular to an electromagnetic unlocking winding type split screw satellite-rocket separation device which comprises a bearing base, a top connecting plate, a plurality of anti-shear assemblies, a separation spring assembly, a split screw assembly and an electromagnetic trigger unit. The anti-shearing assembly is used for bearing and transmitting a shearing load acting on the involution surface; the separation spring assembly is used for providing driving force for separating the bearing base from the top connecting plate; the winding spring wire is wound on a to-be-separated section of the sectioning screw rod so as to apply radial constraint force to the sectioning screw rod, so that the sectioning screw rod is kept in an overall force bearing state; and the action output end of the electromagnetic trigger unit is jointed with the releasable end of the winding spring wire and is used for responding to an unlocking instruction to act, release the radial constraint force and dissociate the split screw rod, so that the separation spring assembly is allowed to drive the top connecting plate to be separated from the bearing base. On the premise of ensuring that a satellite-rocket connection interface has rigidity and bearing capacity, ultralow impact, high synchronism and high reliability in the separation process are realized.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and more specifically, to an electromagnetically unlocked, wound-type split-screw star-rocket separation device. Background Technology

[0002] Currently, in the aerospace field, the separation of launch vehicles and satellites (or spacecraft) after completing their missions primarily relies on two main connection and separation configurations: a multi-point distributed connection configuration and a docking frame-encased connection configuration. In most cases, both configurations utilize pyrotechnic explosive bolts as the power source for unlocking and separation during final separation. Their working principle involves igniting pyrotechnics to generate explosive force, directly cutting or releasing the connecting bolts, thereby achieving mechanical unlocking and separation between the launch vehicle and the satellite.

[0003] However, this pyrotechnic-based separation method generates an extremely violent instantaneous impact at the moment of ignition and detonation of the pyrotechnic components. This high-intensity impact has become the primary source of impact during satellite-rocket separation. This impact load is transmitted to the satellite platform, potentially causing uncontrollable attitude disturbances at the moment of separation, increasing the burden and risk on the attitude control system. More seriously, this high-frequency, high-amplitude impact can easily damage or even cause functional failure of impact-sensitive precision payloads on the satellite (such as optical instruments, laser communication equipment, and precision sensors), directly affecting the success or failure of the mission. Therefore, developing and adopting non-pyrotechnic, low-impact power sources and technologies to replace traditional pyrotechnic explosive bolts has become an important technological direction for reducing the impact of satellite-rocket separation and improving mission reliability and satellite safety. Summary of the Invention

[0004] This invention addresses the problems of high impact from pyrotechnic explosive bolts, which can easily damage precision loads on spacecraft, and poor separation synchronization and controllability.

[0005] To solve the above problems, the present invention provides an electromagnetic unlocking winding type split screw star-rocket separation device, comprising: Support base; A top connecting plate, wherein the top connecting plate is configured to mate with the supporting base; Multiple shear-resistant components, each of which is disposed between the mating surfaces of the bearing base and the top connecting plate, for bearing and transmitting shear loads acting on the mating surfaces; A separation spring assembly is disposed between the support base and the top connecting plate, and is used to provide a driving force to separate the support base from the top connecting plate; The segmented screw assembly includes a segmented screw and a wound spring wire. The segmented screw extends along the separation direction between the top connecting plate and the bearing base, and both ends of the segmented screw are connected to the bearing base and the top connecting plate, respectively. The wound spring wire is wound around the segmented screw in the section to be separated to apply a radial constraint force to the segmented screw and maintain its overall load-bearing state. An electromagnetic trigger unit, the actuation output end of which engages with the releasable end of the wound spring wire, is used to act in response to an unlocking command to release the radial constraint force, thereby disengaging the split screw and allowing the separation spring assembly to drive the top connecting plate to separate from the support base.

[0006] Preferably, the electromagnetic triggering unit includes a pull pin, a permanent magnet, an electromagnetic coil, and an elastic reset member. In the locked state, the electromagnetic coil is de-energized, and the magnetic attraction force generated by the permanent magnet drives the pull pin to compress the elastic reset member and maintain its extended position, so that the action output end of the pull pin constrains the releasable end of the wound spring wire. In the unlocked state, the electromagnetic coil is energized and generates an electromagnetic force opposite to the magnetic field direction of the permanent magnet to counteract the magnetic attraction force, causing the pull pin to retract under the restoring force of the elastic reset member, thereby releasing the releasable end of the wound spring wire.

[0007] Preferably, the electromagnetic triggering unit further includes a housing, a magnetic core, and a magnetic ring, wherein the magnetic core, the electromagnetic coil, the permanent magnet, and the magnetic ring are coaxially housed within the inner cavity of the housing; The magnetic core is sleeve-shaped and arranged along the axial direction of the pull pin. The electromagnetic coil is arranged around the magnetic core. The permanent magnet and the magnetic ring are sequentially sleeved around the electromagnetic coil along the axial direction of the magnetic core, and the permanent magnet is arranged on the side close to the split screw. The pull pin is slidably inserted through the magnetic core. One end of the pull pin is the action output end and extends out of the housing, while the other end is connected to the elastic reset member.

[0008] Preferably, one end of the housing near the split screw is a closed end, and the other end is covered by an end clamping plate; The actuated output end of the pull pin extends from the closed end of the housing and engages with the releasable end of the wound spring wire; The other end of the pull pin passes through the end pressure plate, and its protruding end is fixed to the end pressure plate by a locking member. The end pressure plate is used to pre-compress the elastic reset member and set the protruding position of the pull pin in the locked state.

[0009] Preferably, the split screw includes two rod sections, the adjacent ends of which are semi-cylinders, and the semi-cylinders of the two rod sections are matched to form a cylindrical section to be separated; the winding spring wire is wound around the outer periphery of the section to be separated to fix the two rod sections relative to each other; the actuated output end of the pull pin passes radially through the rod located at one end of the section to be separated along the split screw and engages with the releasable end of the winding spring wire to limit the winding spring wire.

[0010] Preferably, each of the shear-resistant components includes at least one shear-resistant pin, the axis of which is perpendicular to the separation direction of the top connecting plate and the bearing base, and is disposed through the mating surface of the bearing base and the top connecting plate, for bearing and transmitting the shear load.

[0011] Preferably, the bearing base and the top connecting plate have corresponding semi-cylindrical grooves on their mating surfaces; when the bearing base and the top connecting plate are mated, a pair of semi-cylindrical grooves mate to form a cylindrical pin hole; each shear pin is fitted into the corresponding pin hole.

[0012] Preferably, each of the shear-resistant components further includes a pin stop plate, which is connected to the bearing base or the top connecting plate and blocks the axial end opening of the pin hole to prevent the shear-resistant pin from axially dislodging from the pin hole.

[0013] Preferably, the separation spring assembly includes a separation spring and a spring guide rod, the axial direction of the spring guide rod being parallel to the separation direction between the top connecting plate and the bearing base, and one end of the spring guide rod being connected to the bearing base or the top connecting plate; The separation spring is sleeved on the spring guide rod and is positioned in a pre-compressed state between the bearing base and the top connecting plate.

[0014] Preferably, the supporting base is a rectangular frame structure with an open top; the top connecting plate covers the open end of the rectangular frame, and a plurality of the separation spring assemblies and a plurality of the anti-shear assemblies are arranged at intervals along the periphery of the rectangular frame.

[0015] The intended technical effects of this invention are as follows: This invention provides an electromagnetically unlocked, wound-wound, segmented screw satellite-rocket separation device. The device integrates a support base, a top connecting plate, and an electromagnetic triggering unit. Its core load-bearing and separation functions are achieved by the segmented screw assembly. The segmented screw serves as the main load-bearing path, directly connecting the satellite and rocket structures via the support base and top connecting plate. A radial clamping force is applied to the section to be separated using wound spring wires to maintain integrity, thus providing high connection stiffness and load-bearing capacity during launch. Simultaneously, the unlocking action is not directly applied to the main load-bearing component but is controlled by the electromagnetic triggering unit to release the constraint of the wound spring wires. The output end of the electromagnetic triggering unit engages with the release end of the wound spring wires, responding to the unlocking command to release the radial constraint force, causing the segmented screw to disengage. This allows the separation spring assembly to drive the top connecting plate to separate from the support base. This process completely eliminates the instantaneous high-frequency, high-amplitude impact of the gunpowder explosion, ensuring a smooth and controllable force. This guarantees low-impact separation from the source, effectively protecting the precision payload on the satellite and ensuring stable separation attitude. Meanwhile, the shear-resistant component is specifically responsible for bearing the shear load between the mating surfaces of the bearing base and the top connecting plate, complementing the split screw that bears the axial tensile force, together forming a rigid multi-dimensional load-bearing system; while the pre-compressed separation spring assembly provides a constant and reliable initial separation driving force after the main constraint is released, ensuring a thorough separation action.

[0016] In summary, this invention achieves low-impact unlocking through electromagnetic triggering, integrates load-bearing and unlocking through a wound-type segmented screw design, and achieves high synchronization through electrical signal control. Furthermore, the combination of the shear-resistant component 3 and the separation spring component ensures reliable connection and decisive separation. Ultimately, while ensuring extremely high rigidity and load-bearing capacity at the spacecraft-rocket connection interface, it achieves synchronous low-impact unlocking of the multi-point locking mechanism. This meets the stringent comprehensive requirements for high load-bearing rigidity, extremely high unlocking reliability, an absolutely clean environment, excellent synchronization, and controllable low impact during spacecraft-rocket separation. It represents an advanced separation device for modern spacecraft, especially satellites carrying high-value, highly sensitive payloads, addressing future spaceflight needs. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the structure of an electromagnetic unlocking wound-type split screw star-rocket separation device according to one embodiment of the present invention; Figure 2 This is another axial side view of an electromagnetic unlocking wound-type split screw star-rocket separation device according to one embodiment of the present invention; Figure 3 This is a schematic diagram of the electromagnetic unlocking wound type split screw star-rocket separation device of the present invention with the top connecting plate removed; Figure 4 for Figure 3 A cross-sectional diagram; Figure 5 This is a schematic diagram of the structure of the segmented screw assembly in one embodiment of the present invention; Figure 6 This is a cross-sectional schematic diagram of an electromagnetic triggering unit in one embodiment of the present invention.

[0018] Explanation of reference numerals in the attached figures: 1-Bearing base; 2-Top connecting plate; 3-Anti-shear assembly; 31-Anti-shear pin; 32-Pin stop plate; 4-Separation spring assembly; 41-Separation spring; 42-Spring guide rod; 5-Split screw assembly; 51-Split screw; 511-Separation section; 52-Winding spring wire; 521-Releasable end; 6-Electromagnetic trigger unit; 61-Pull pin; 611-Action output end; 62-Permanent magnet; 63-Electromagnetic coil; 64-Elastic reset component; 65-Housing; 66-Magnetic core; 67-Magnetic ring; 68-End pressure plate. Detailed Implementation

[0019] To make the above-mentioned objects, features, and advantages of the present invention more apparent and understandable, specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. Although some embodiments of the present invention are shown in the drawings, it should be understood that the present invention can be implemented in various forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided to provide a more thorough and complete understanding of the present invention. It should be understood that the accompanying drawings and embodiments of the present invention are for illustrative purposes only and are not intended to limit the scope of protection of the present invention.

[0020] The term "comprising" and its variations as used herein are open-ended, meaning "including but not limited to"; the term "based on" means "at least partially based on"; the term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one additional embodiment"; the term "some embodiments" means "at least some embodiments"; and the term "optionally" means "optional embodiments". Definitions of other terms will be given in the following description. It should be noted that the concepts of "first," "second," etc., mentioned in this invention are used only to distinguish different devices, modules, or units, and are not intended to limit the order of functions performed by these devices, modules, or units or their interdependencies.

[0021] It should be noted that the terms "a" and "a plurality of" used in this invention are illustrative rather than restrictive. Those skilled in the art should understand that, unless otherwise expressly indicated in the context, they should be understood as "one or more".

[0022] To address the problems existing in the aforementioned related technologies, embodiments of the present invention provide an electromagnetically unlocked winding-type split screw star-rocket separation device.

[0023] like Figures 1 to 4As shown, an embodiment of the present invention discloses an electromagnetic unlocking winding type split screw star-rod separation device, comprising a support base 1, a top connecting plate 2, multiple shear-resistant components 3, a separation spring assembly 4, a split screw assembly 5, and an electromagnetic triggering unit 6. The top connecting plate 2 is mated to the support base 1; each shear-resistant component 3 is disposed between the mating surfaces of the support base 1 and the top connecting plate 2, for bearing and transmitting shear loads acting on the mating surfaces; the separation spring assembly 4 is disposed between the support base 1 and the top connecting plate 2, for providing the driving force to separate the support base 1 from the top connecting plate 2. The split screw assembly 5 includes a split screw 51 and a wound spring wire 52. The split screw 51 extends along the separation direction between the top connecting plate 2 and the support base 1, and both ends of the split screw 51 are connected to the support base 1 and the top connecting plate 2, respectively. The wound spring wire 52 is wound around the section 511 of the split screw 51 to be separated, so as to apply a radial constraint force to the split screw 51 to maintain its overall load-bearing state. The action output end 611 of the electromagnetic trigger unit 6 is engaged with the release end 521 of the wound spring wire 52, and is used to act in response to the unlocking command to release the radial constraint force, so as to release the split screw 51 and allow the separation spring assembly 4 to drive the top connecting plate 2 to separate from the support base 1.

[0024] It should be noted that the support base 1 and the top connecting plate 2 form a connecting support mechanism. The support base 1 can be connected to the rocket, and the top connecting plate 2 can be reliably connected to the satellite. The connecting support mechanism and the electromagnetic triggering unit 6 are designed as a single unit. Its core support and separation functions are realized by the split screw assembly 5. The split screw 51 serves as the main load-bearing path and consists of two separable parts. The section to be separated, 511, is the overlapping part of the two separable parts. The integrity of the split screw 51 can be maintained by applying a radial clamping force to the section to be separated, 511, through the winding spring wire 52, thereby providing high connection stiffness and load-bearing capacity during the launch phase. At the same time, the unlocking action is not directly applied to the main load-bearing component, but is controlled by the electromagnetic triggering unit 6 to release the constraint of the winding spring wire 52. The actuation output terminal 611 of the electromagnetic trigger unit 6 engages with the release terminal 521 of the wound spring wire 52, and is activated in response to an unlocking command to release the radial constraint force, causing the split screw 51 to disengage. This allows the separation spring assembly 4 to drive the top connecting plate 2 to separate from the support base 1. This process completely eliminates the instantaneous high-frequency, high-amplitude impact caused by the gunpowder explosion, and its force is smooth and controllable, ensuring low-impact characteristics of separation from the source, effectively protecting the precision payload on the satellite and ensuring the stability of the separation attitude. In addition, the electrical signal triggering mechanism enables multiple separation nodes distributed in different locations to achieve precise synchronous action at the millisecond level, overcoming the separation asynchrony problem caused by the discreteness of the action time of the pyrotechnics, and further ensuring the precise controllability of the separation attitude.

[0025] The shear-resistant component 3 is specifically responsible for bearing the shear load between the mating surfaces of the bearing base 1 and the top connecting plate 2. It complements the split screw 51, which bears the axial tensile force, and together they form a rigid multi-dimensional load-bearing system. The pre-compressed separation spring component 4 provides a constant and reliable initial separation driving force after the main constraint is released, ensuring the completeness of the separation action.

[0026] In summary, the electromagnetic unlocking wound-type segmented screw satellite-rocket separation device of the present invention achieves low-impact unlocking through electromagnetic triggering, integrates load-bearing and unlocking through the wound-type segmented screw design, achieves high synchronization through electrical signal control, and ensures reliable connection and decisive separation by combining the shear-resistant component 3 and the separation spring component 4. Ultimately, while ensuring that the satellite-rocket connection interface has extremely high rigidity and load-bearing capacity, it achieves ultra-low impact, high synchronization, high reliability and complete controllability in the separation process, providing a superior separation technology approach for modern spacecraft, especially satellites carrying high-value and highly sensitive payloads.

[0027] like Figure 5 and Figure 6 As shown, in one embodiment of the present invention, the electromagnetic triggering unit 6 includes a pull pin 61, a permanent magnet 62, an electromagnetic coil 63, and an elastic reset member 64. In the locked state, the electromagnetic coil 63 is de-energized, and the magnetic attraction force generated by the permanent magnet 62 drives the pull pin 61 to compress the elastic reset member 64 and maintain its extended position, so that the action output end 611 of the pull pin 61 constrains the releasable end 521 of the wound spring wire 52. In the unlocked state, the electromagnetic coil 63 is energized and generates an electromagnetic force opposite to the magnetic field direction of the permanent magnet 62 to counteract the magnetic attraction force, so that the pull pin 61 retracts under the action of the restoring force of the elastic reset member 64, thereby releasing the releasable end 521 of the wound spring wire 52.

[0028] It should be noted that the electromagnetic triggering unit 6, through the permanent magnet holding of the permanent magnet 62, the electromagnetic cancellation of the electromagnetic coil 63, and the elastic drive of the elastic reset component 64, fundamentally eliminates the violent mechanical impact and detonation wave generated during the detonation of traditional pyrotechnics (such as explosive bolts). The unlocking process relies on the smooth conversion between the electromagnetic force generated by the controllable current and the pre-stored spring force, resulting in a smooth force curve without abrupt changes, thereby reducing the impact load transmitted to the satellite platform at the moment of separation. This effectively protects the highly impact-sensitive precision instruments and payloads on board, ensuring the stability of the separation attitude. Secondly, the unlocking action is directly triggered and controlled by an electrical signal, resulting in a fast response speed and extremely high timing accuracy. Through a unified control circuit, multiple separation nodes arranged circumferentially on the spacecraft can achieve millisecond-level synchronous action, overcoming the separation asynchrony problem caused by the discrete properties of pyrotechnic agents, thus avoiding harmful torques generated by asymmetric unlocking, making the separation process more controllable and the attitude more precise. Furthermore, the electromagnetic trigger unit 6 does not contain any one-time, irreversible components such as gunpowder; its locking and unlocking state transitions depend solely on changes in the magnetic circuit and mechanical state. Therefore, repeated power-on tests and functional verifications can be performed during the ground assembly and testing phase, improving the mission's success rate and safety.

[0029] In addition, the core components of the electromagnetic triggering unit 6, namely the pull pin 61, permanent magnet 62, electromagnetic coil 63 and elastic reset component 64, are much less sensitive to temperature than pyrotechnics. This allows it to adapt to the wide temperature environment experienced by spacecraft without the need for an additional complex thermal control system, thus enhancing the system's environmental adaptability.

[0030] In one embodiment of the present invention, the electromagnetic triggering unit 6 further includes a housing 65, a magnetic core 66, and a magnetic ring 67. The magnetic core 66, the electromagnetic coil 63, the permanent magnet 62, and the magnetic ring 67 are coaxially housed in the inner cavity of the housing 65. The magnetic core 66 is sleeve-shaped and is arranged along the axial direction of the pull pin 61. The electromagnetic coil 63 is arranged around the magnetic core 66. The permanent magnet 62 and the magnetic ring 67 are sequentially sleeved around the electromagnetic coil 63 along the axial direction of the magnetic core 66, and the permanent magnet 62 is arranged on the side close to the split screw 51. The pull pin 61 is slidably inserted through the magnetic core 66. One end of the pull pin 61 is an action output end 611 and extends out of the housing 65, and the other end is connected to the elastic reset member 64.

[0031] It should be noted that the electromagnetic trigger unit 6, by designing the magnetic core 66 as a sleeve-like structure and allowing the pull pin 61 to slide through it, provides precise guidance and support for the axial movement of the pull pin 61, preventing deviation or jamming during operation, and ensuring the linearity and reliability of the force applied by the action output end 611 to the release end 521 of the wound spring wire 52. The electromagnetic coil 63 is wrapped around the magnetic core 66, and the permanent magnet 62 and the magnetic ring 67 are coaxially sleeved on the outside of the electromagnetic coil 63, with the permanent magnet 62 positioned on the side closer to the split screw 51, thus constructing an efficient and controllable electromagnetic power system. When not powered on, the magnetic holding force provided by the permanent magnet 62 reliably keeps the pin 61 in the locked position, giving the device inherent anti-interference capability and power-off self-locking safety. When unlocking is required, a pulse current in a specific direction is applied to the electromagnetic coil 63. The electromagnetic field generated interacts with the magnetic field of the permanent magnet, which can accurately and quickly cancel the magnetic holding force and form an electromagnetic force in the magnetic core 66 to drive the pin 61 to slide, thereby achieving millisecond-level fast response and triggering. The entire electromagnetic triggering unit 6 is highly integrated, with all components coaxially housed in the cavity of the housing 65. The compact structure and optimized magnetic field path not only improve electromagnetic efficiency and reduce power consumption, but also enhance the overall mechanical robustness and environmental adaptability. In addition, the elastic reset member 64 connected to the end of the pin 61 allows the pin 61 to automatically return to its original position under the action of the elastic reset member 64 after the triggering action is completed or during ground testing, further enhancing its superior repeatability. Therefore, the electromagnetic trigger unit 6 has multiple performance advantages such as high reliability, fast response, low power consumption, anti-interference and easy testing, thus ensuring the accurate and reliable execution of the core unlocking action.

[0032] In one embodiment of the present invention, one end of the housing 65 near the split screw 51 is a closed end, and the other end is covered by an end pressure plate 68; the actuation output end 611 of the pull pin 61 extends from the closed end of the housing 65 and engages with the releasable end 521 of the wound spring wire 52; the other end of the pull pin 61 connecting elastic reset member 64 passes through the end pressure plate 68, and its protruding end is fixed to the end pressure plate 68 by a locking member. The end pressure plate 68 is used to pre-compress the elastic reset member 64 and set the extension position of the pull pin 61 in the locked state.

[0033] It should be noted that designing the end of the housing 65 near the split screw 51 as a closed end not only provides a sealed protective space for the internal electromagnetic components (magnetic core 66, electromagnetic coil 63, permanent magnet 62, and magnetic ring 67), effectively preventing the intrusion of external dust and impurities from affecting motion accuracy or magnetic circuit performance, but more importantly, this closed end structure, as a rigid axial reference surface, combined with the design of the action output end 611 of the pull pin 61 extending from this point, ensures that the motion axis of the pull pin 61 is always perpendicular to the separation interface between the support base 1 and the top connecting plate 2. This makes the force direction of the pull pin 61 on the release end 511 of the wound spring wire 51 precise and stable, avoiding friction, jamming, or incomplete release caused by lateral force, thus ensuring the certainty and consistency of the unlocking action. The other end of the housing 65, covered by the end pressure plate 68, forms a conveniently openable debugging and maintenance window. One end of the pull pin 61, which connects to the elastic reset member 64, passes through the end pressure plate 68 and is fixed to the end pressure plate 68 by a locking member, thus enabling adjustable pre-compression of the elastic reset member 64. By tightening or loosening the locking member, the extension position of the pull pin 61 in the locked state can be precisely set, thereby fine-tuning its engagement depth and pre-tightening force with the wound spring wire 52; at the same time, this pre-compression structure also provides the pull pin 61 with a precise and reproducible reset stroke and force value after triggering. The entire assembly relationship makes the electromagnetic trigger unit 6 a highly modular and self-contained independent component: when locked, it can remain stable against harsh mechanical environments through the rigid support of the closed end and the housing 65, as well as the cooperation of the internal magnetic circuit and pre-compression; when triggered, the pull pin 61 can move precisely along a predetermined axis; during reset or testing, detection and parameter fine-tuning can be conveniently performed through the covering structure of the end pressure plate 68. By integrating core electromagnetic drive, precise mechanical guidance, adjustable preload settings, and easy-to-maintain structure, the electromagnetic trigger unit 6 not only boasts superior performance but is also easy to assemble, test, and calibrate.

[0034] In one embodiment of the present invention, the split screw 51 includes two rod sections, the ends of which are close to each other are semi-cylindrical, and the semi-cylindrical sections of the two rod sections are matched to form a cylindrical section to be separated 511; a winding spring wire 52 is wound around the outer periphery of the section to be separated 511 to fix the two rod sections relative to each other; the actuation output end 611 of the pull pin 61 passes radially through the rod section located at one end of the section to be separated 511 along the split screw 51 and engages with the releasable end 521 of the winding spring wire 52 to limit the winding spring wire 52.

[0035] Furthermore, the other end of the wound spring wire 52, opposite to the releasable end 521, is connected to the split screw 51 via a fixing pin. The two semi-cylinders of the section to be separated 511 have an axial mating surface structure with interlocking teeth. This allows the shear component of the axial load to be transmitted between the two semi-cylinders not only through friction but also through direct meshing of the teeth after radial clamping force is applied to the wound spring wire 52. This enhances the overall shear resistance and load-bearing stiffness of the split screw 51 in the locked state, while providing a precise assembly positioning reference for the two parts and reducing the dependence on the winding preload, thereby comprehensively improving the reliability of the separation device and the certainty of the unlocking action.

[0036] It should be noted that the section 511 to be separated by the split screw 51 can be two semi-cylinders separated along an axial plane. This makes the separation plane a single axial plane, easily ensuring the machining accuracy and alignment consistency of the two semi-cylinders, reducing manufacturing and assembly difficulty. When the winding spring wire 52 applies a radial constraint force, this force acts perpendicularly to the flat separation plane, most effectively pressing the two semi-cylinders into a single cylinder. The resulting contact surface is large and the pressure distribution is uniform, ensuring no relative slippage or misalignment between the two semi-cylinders under enormous axial loads. The winding spring wire 52 is wound around the outer circumference of the section 511 to be separated, and its constraint force action perfectly matches the aforementioned structure. The circumferential clamping force generated by the winding is directly converted into normal pressure acting on the separation plane of the two semi-cylinders. This constraint mechanism allows a relatively light and simple winding action to generate the enormous clamping force required to maintain the structural integrity, achieving the goal of obtaining maximum load-bearing capacity with minimal added mass and volume.

[0037] The actuation output end 611 of the pull pin 61 passes radially through the split screw 51 below the section to be separated 511 and engages with the release end 521 of the winding spring wire 52, ensuring the certainty of the unlocking action. By setting the point of action of the pull pin 61 radially and below the section to be separated 511, the pull pin 61 limits the winding spring wire 52 through a latching or blocking mechanism, rather than directly resisting the winding force, requiring less unlocking force. Simultaneously, the position of the pull pin 61 below the section to be separated 511 ensures that the pull pin 61 itself does not pass through the main load-bearing section (the section to be separated 511), avoiding weakening the main load-bearing structure. This engagement method directly controls the winding end; once the pull pin 61 is radially pulled out, the release end 521 of the winding spring wire 52 immediately loses its constraint, and the pre-tightened winding spring wire 52 quickly loosens under its own elasticity, allowing the winding constraint to be released instantly.

[0038] In one embodiment of the present invention, each shear-resistant component includes at least one shear-resistant pin 31, the axial direction of each shear-resistant pin 31 being perpendicular to the separation direction of the top connecting plate 2 and the bearing base 1, and being disposed through the mating surface of the bearing base 1 and the top connecting plate 2, for bearing and transmitting shear loads.

[0039] It should be noted that during spacecraft launch and flight, the spacecraft-rocket interface is subjected to complex lateral loads, torsional moments, and vibrations, all of which generate significant shear stress on the separation surface. This invention addresses this by incorporating independent shear pins 31, allowing the shear load to be borne by the specially optimized shear pins 31, while the axial tensile load is borne by the segmented screw assembly 51. This division of labor enables each component to maximize its effectiveness in its most advantageous stress direction (shear pins 31 resist shear, segmented screw 51 resists tension), optimizing the load transfer path of the structure and improving overall load-bearing efficiency and safety.

[0040] Specifically, the segmented screw assembly 5 is the core of the unlocking function. If it were simultaneously subjected to enormous shear force, the complex stress could cause deformation, fretting wear, or localized stress concentration, thus interfering with the uniformity of the winding constraint or affecting the smooth release of the separation plane. By isolating the shear force, the segmented screw 51 is ensured to always be in a relatively pure axial tensile state, fundamentally guaranteeing the reliability of its unlocking function. At the same time, multiple anti-shear pins 31 are distributed circumferentially along the mating surface, effectively suppressing any relative lateral displacement or rotational tendency between the bearing base 1 and the top connecting plate 2. This enhances the overall stiffness and connection stiffness of the separation surface in the locked state, enabling the entire device to better resist the dynamic environment and providing a more stable and reliable installation platform for the spacecraft load.

[0041] In one embodiment of the present invention, a semi-cylindrical groove is provided on the mating surface of the bearing base 1 and the top connecting plate 2; when the bearing base 1 and the top connecting plate 2 are mated, a pair of semi-cylindrical grooves are mated to form a cylindrical pin hole; each shear pin 31 is fitted into the corresponding pin hole.

[0042] It should be noted that machining semi-cylindrical grooves on the mating surfaces of the supporting base 1 and the top connecting plate 2 significantly improves the feasibility of manufacturing and assembly. Compared to machining a complete deep hole with high coaxiality requirements on two independent components, machining open semi-cylindrical grooves is simpler and more precise in terms of tooling, dimensional inspection, and tolerance control. When the two are mated, a pair of precisely machined semi-cylindrical grooves align to form a cylindrical pin hole. This is an automatic, visually verifiable precision alignment process that ensures the axial position accuracy of the shear pin hole, providing a foundation for the insertion and positioning of the shear pin 31. The formed pin hole provides uniform circumferential envelope and support for the shear pin 31. When the shear pin 31 is subjected to shear loads, its load transfer surface is the entire cylindrical surface, resulting in uniform stress distribution and avoiding local stress concentration. This maximizes the shear resistance of the material and improves fatigue resistance.

[0043] More importantly, this design inherently provides a complete and rigid support environment for the anti-shear pin 31 in the locked state, allowing it to reliably transmit shear force. When the separation command is triggered and the supporting base 1 and the top connecting plate 2 begin to move relative to each other under spring drive, the pin hole formed by the two mating parts immediately and automatically disengages into two independent semi-open slots. The anti-shear pin 31 then automatically and smoothly disengages without any additional unlocking action or overcoming separation resistance. This process achieves the rigidity of the anti-shear function during locking and its automatic disappearance during separation, meeting the stringent requirements of instantaneous disengagement in star-rocket separation. Furthermore, as an independent standard part, the anti-shear pin 31 can be easily inserted or removed from the mating surface, facilitating installation, inspection, or replacement.

[0044] In one embodiment of the present invention, each shear-resistant component further includes a pin stop 32, which is connected to the bearing base 1 or the top connecting plate 2 and is positioned at the axial end opening of the pin hole to prevent the shear-resistant pin 31 from axially dislodging from the pin hole.

[0045] It should be noted that the anti-shear pin 31 has potential failure modes in complex dynamic environments. Although the anti-shear pin 31 is tightly enclosed by the pin hole in the radial direction, it is a free part in the open pin hole in its own axial direction. Under the extreme vibration, impact, and possible micro-deformation environment experienced by the launching section, there is a probability risk that the anti-shear pin 31 may gradually fall off from the end opening of the pin hole due to inertia or fretting. Once this happens, it will not only lead to the complete loss of the anti-shear function at that point, causing the load to be abnormally transferred to the core split screw 51, but the detached pin may also become a destructive foreign object, getting stuck in other moving parts. The pin stop 32, as a rigid mechanical barrier, is directly blocked at the axial end opening of the pin hole, forming a reliable axial displacement constraint on the anti-shear pin 31, ensuring that the anti-shear pin 31 is firmly restricted to its designed working position under any dynamic environment. Meanwhile, the design and installation method of the pin retainer 32 ensures that while fulfilling axial constraints, it does not affect the core function of radial load bearing of the shear pin 31, nor does it hinder the predetermined actions of the pin hole mating surfaces separating and the shear pin 31 automatically falling off during separation. Its presence is non-interfering with both load bearing and separation states.

[0046] In one embodiment of the present invention, the separation spring assembly 4 includes a separation spring 41 and a spring guide rod 42. The axial direction of the spring guide rod 42 is parallel to the separation direction between the top connecting plate 2 and the bearing base 1. One end of the spring guide rod 42 is connected to the bearing base 1 or the top connecting plate 2. The separation spring 41 is sleeved on the spring guide rod 42 and is disposed between the bearing base 1 and the top connecting plate 2 in a pre-compressed state.

[0047] It should be noted that the axial direction of the spring guide rod 42 is set parallel to the separation direction, and one end of it is fixed to the bearing base 1 or the top connecting plate 2, establishing a rigid reference axis for the entire separation action. The elastic potential energy stored in the separation spring 41, which is sleeved on it, in the pre-compression state, is forcibly constrained in its release direction by the spring guide rod 42, and can only be converted into kinetic energy to separate the top connecting plate 2 from the bearing base 1 along this specific axis. This fundamentally eliminates the risk of off-center loading, jamming, or asynchronous movement that may occur during the separation process, ensuring that the two separation components separate smoothly and steadily along a straight line. At the same time, the separation spring 41 is in a pre-compression state, which means that the energy required for separation has been pre-stored when the device is locked, and there is almost no delay between unlocking (disengagement of the split screw 51) and power release. More importantly, by precisely designing and controlling the stiffness coefficient, pre-compression amount, and stroke determined by the spring guide rod 42 of the separation spring 41, the thrust that can be provided at the moment of separation can be accurately calculated, so that the separation process is no longer a vague spring-like opening, but a controlled dynamic event that can be accurately simulated, predicted, and verified.

[0048] In one embodiment of the present invention, the support base 1 is a rectangular frame structure with an open top; the top connecting plate 2 covers the open end of the rectangular frame, and multiple separation spring assemblies 4 and multiple anti-shear assemblies 3 are arranged at intervals along the periphery of the rectangular frame.

[0049] It should be noted that the support base 1 is designed as a rectangular frame structure with an open top, and the segmented screw assembly 5 is located inside the rectangular frame structure of the support base 1. Since the rectangular frame structure itself has excellent bending and torsional stiffness, it can provide a stable installation foundation for the entire separation device and the satellite payload connected above. The top connecting plate 2 acts as a cover plate sealing the open end of the rectangular frame structure, together forming a closed, highly integrated box-type support structure. More importantly, multiple separation spring assemblies 4 and multiple shear-resistant assemblies 3 are arranged at intervals along the periphery of this rectangular frame structure, with the separation springs 41 evenly distributed along the periphery. This ensures that at the moment of unlocking, the thrust driving the top connecting plate 2 to separate is uniform and centrally symmetrical on the plane of action, thereby avoiding separation jamming, tilting, or additional torque that may be caused by eccentric driving force, ensuring smooth separation movement and stable attitude. Similarly, multiple shear-resistant components 3 are spaced apart along the perimeter, which can most effectively transfer shear loads from all directions, transmitted from the top connecting plate 2, to the bearing base 1 nearby, forming a short and direct force flow path, maximizing the overall structural resistance to complex shear and torsional loads. The placement of components such as the separation spring 41 and the shear-resistant pin 31, which require a certain linear space or installation interface, fully utilizes the side wall height and internal corner space of the rectangular frame structure, minimizing the height of the device in the separation direction. This achieves a compact and low-profile design for the entire separation device, providing ample and undisturbed space for the core components located in the central area of ​​the separation device, namely the split screw assembly 5 and its electromagnetic trigger unit 6. This allows the core bearing and unlocking components to be placed in a protected position at the center of the structure, and further optimizes the transmission of axial forces.

[0050] While the present invention has been disclosed above, its scope of protection is not limited thereto. Those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention, and all such changes and modifications will fall within the scope of protection of the present invention.

Claims

1. An electromagnetically unlocked, wound-type split-screw star-rocket separation device, characterized in that, include: Support base (1); Top connecting plate (2), which is configured to mate with the support base (1); Multiple shear-resistant components (3), each of the shear-resistant components (3) is disposed between the mating surfaces of the bearing base (1) and the top connecting plate (2), for bearing and transmitting shear loads acting on the mating surfaces; Separation spring assembly (4), which is disposed between the support base (1) and the top connecting plate (2), is used to provide a driving force to separate the support base (1) from the top connecting plate (2); The split screw assembly (5) includes a split screw (51) and a wound spring wire (52). The split screw (51) extends along the separation direction between the top connecting plate (2) and the bearing base (1), and both ends of the split screw (51) are connected to the bearing base (1) and the top connecting plate (2) respectively. The wound spring wire (52) is wound around the section (511) of the split screw (51) to be separated, so as to apply a radial constraint force to the split screw (51) to maintain its overall load-bearing state. The electromagnetic trigger unit (6) has its action output end (611) engaged with the release end (521) of the wound spring wire (52) to respond to the unlocking command and release the radial constraint force, thereby allowing the split screw (51) to disengage and allowing the separation spring assembly (4) to drive the top connecting plate (2) to separate from the support base (1).

2. The electromagnetic unlocking wound-type split screw star-rocket separation device according to claim 1, characterized in that, The electromagnetic triggering unit (6) includes a pull pin (61), a permanent magnet (62), an electromagnetic coil (63), and an elastic reset member (64). In the locked state, the electromagnetic coil (63) is de-energized, and the magnetic attraction force generated by the permanent magnet (62) drives the pull pin (61) to compress the elastic reset member (64) and keep it in the extended position, so that the action output end (611) of the pull pin (61) constrains the releasable end (521) of the wound spring wire (52). In the unlocked state, the electromagnetic coil (63) is energized and generates an electromagnetic force opposite to the magnetic field direction of the permanent magnet (62) to counteract the magnetic attraction force, so that the pull pin (61) retracts under the action of the restoring force of the elastic reset member (64), thereby releasing the releasable end (521) of the wound spring wire (52).

3. The electromagnetic unlocking winding type split screw star-rocket separation device according to claim 2, characterized in that, The electromagnetic triggering unit (6) further includes a housing (65), a magnetic core (66), and a magnetic ring (67). The magnetic core (66), the electromagnetic coil (63), the permanent magnet (62), and the magnetic ring (67) are coaxially housed in the inner cavity of the housing (65). The magnetic core (66) is sleeve-shaped and is arranged along the axial direction of the pull pin (61). The electromagnetic coil (63) is arranged around the magnetic core (66). The permanent magnet (62) and the magnetic ring (67) are sequentially sleeved around the electromagnetic coil (63) along the axial direction of the magnetic core (66). The permanent magnet (62) is arranged on the side close to the split screw (51). The pull pin (61) is slidably inserted through the magnetic core (66). One end of the pull pin (61) is the action output end (611) and extends out of the housing (65), while the other end is connected to the elastic reset member (64).

4. The electromagnetic unlocking wound-type split screw star-rocket separation device according to claim 3, characterized in that, The end of the housing (65) near the split screw (51) is a closed end, and the other end is covered by an end pressure plate (68); The actuation output end (611) of the pull pin (61) extends from the closed end of the housing (65) and engages with the releasable end (521) of the wound spring wire (52). The other end of the pull pin (61) passes through the end pressure plate (68), and its protruding end is fixed to the end pressure plate (68) by a locking member. The end pressure plate (68) is used to pre-compress the elastic reset member (64) and set the protruding position of the pull pin (61) in the locked state.

5. The electromagnetic unlocking wound-type split screw star-rocket separation device according to claim 4, characterized in that, The split screw (51) includes two rod sections, the ends of which are close to each other are semi-cylindrical, and the semi-cylindrical sections of the two rod sections are matched to form a cylindrical section to be separated (511); the winding spring wire (52) is wound around the outer periphery of the section to be separated (511) to fix the two rod sections relative to each other; the action output end (611) of the pull pin (61) passes radially through the rod section located at one end of the section to be separated (511) along the split screw (51) and engages with the release end (521) of the winding spring wire (52) to limit the winding spring wire (52).

6. The electromagnetic unlocking wound-type split screw star-rocket separation device according to claim 1, characterized in that, Each of the shear-resistant components (3) includes at least one shear-resistant pin (31), the axis of which is perpendicular to the separation direction of the top connecting plate (2) and the bearing base (1), and is disposed through the mating surface of the bearing base (1) and the top connecting plate (2) for bearing and transmitting the shear load.

7. The electromagnetic unlocking wound-type split screw star-rocket separation device according to claim 6, characterized in that, The bearing base (1) and the top connecting plate (2) have corresponding semi-cylindrical grooves on their mating surfaces; when the bearing base (1) and the top connecting plate (2) are mated, a pair of semi-cylindrical grooves are mated to form a cylindrical pin hole; each shear pin (31) is fitted into the corresponding pin hole.

8. The electromagnetic unlocking wound-type split screw star-rocket separation device according to claim 7, characterized in that, Each of the shear-resistant components (3) further includes a pin stop (32), which is connected to the bearing base (1) or the top connecting plate (2) and is positioned at the axial end opening of the pin hole to prevent the shear-resistant pin (31) from axially dislodging from the pin hole.

9. The electromagnetic unlocking wound-type split screw star-rocket separation device according to claim 1, characterized in that, The separation spring assembly (4) includes a separation spring (41) and a spring guide rod (42). The axial direction of the spring guide rod (42) is parallel to the separation direction of the top connecting plate (2) and the bearing base (1). One end of the spring guide rod (42) is connected to the bearing base (1) or the top connecting plate (2). The separation spring (41) is sleeved on the spring guide rod (42) and is positioned in a pre-compressed state between the bearing base (1) and the top connecting plate (2).

10. The electromagnetic unlocking wound-type split screw star-rocket separation device according to any one of claims 1-9, characterized in that, The supporting base (1) is a rectangular frame structure with an open top; the top connecting plate (2) covers the open end of the rectangular frame, and multiple separation spring assemblies (4) and multiple shear-resistant assemblies (3) are arranged at intervals along the periphery of the rectangular frame.

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