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CN-121990187-A - Electromagnetic unlocking winding type split screw satellite-rocket separation device

CN121990187ACN 121990187 ACN121990187 ACN 121990187ACN-121990187-A

Abstract

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

Inventors

  • RUAN QI
  • DENG YING
  • FU XINFU

Assignees

  • 北京吾天科技有限公司

Dates

Publication Date
20260508
Application Date
20260126

Claims (10)

  1. 1. An electromagnetic unlocking winding type split screw satellite-rocket separating device is characterized by comprising: a load-bearing base (1); The top connecting plate (2), the top connecting plate (2) and the bearing base (1) are arranged in an involution way; The plurality of shear-resistant assemblies (3), each shear-resistant assembly (3) is arranged between the bearing base (1) and the butt joint surface of the top connecting plate (2) and is used for bearing and transmitting shear load acting on the butt joint surface; a separation spring assembly (4), wherein the separation spring assembly (4) is arranged between the bearing base (1) and the top connecting plate (2) and is used for providing a driving force for separating the bearing base (1) from the top connecting plate (2); The split screw assembly (5), the split screw assembly (5) comprises a split screw (51) and a winding spring wire (52), the split screw (51) extends along the separation direction of the top connecting plate (2) and the bearing base (1), two ends of the split screw (51) are respectively connected with the bearing base (1) and the top connecting plate (2), the winding spring wire (52) is wound on a section (511) to be separated of the split screw (51) so as to apply radial constraint force to the split screw (51) to maintain the integral bearing state, and -An electromagnetic triggering unit (6), an action output (611) of the electromagnetic triggering unit (6) being engaged with a releasable end (521) of the wrap spring wire (52) for acting in response to an unlocking command, releasing the radial constraint force, causing the split screw (51) to disengage, thereby allowing the separation spring assembly (4) to drive the top connection plate (2) to separate from the load-bearing base (1).
  2. 2. The electromagnetic unlocking winding type split screw satellite rocket separating device according to claim 1, wherein the electromagnetic triggering unit (6) comprises a pulling pin (61), a permanent magnet (62), an electromagnetic coil (63) and an elastic reset piece (64), in a locking state, the electromagnetic coil (63) is powered off, the magnetic attraction generated by the permanent magnet (62) drives the pulling pin (61) to compress the elastic reset piece (64) and keep an extending position, the action output end (611) of the pulling pin (61) is used for restraining the releasable end (521) of the winding spring wire (52), in an unlocking state, the electromagnetic coil (63) is powered on and generates electromagnetic force opposite to the magnetic field direction of the permanent magnet (62) to offset the magnetic attraction, and the pulling pin (61) is retracted under the action of the restoring force of the elastic reset piece (64), so that the releasable end (521) of the winding spring wire (52) is released.
  3. 3. The electromagnetic unlocking winding split screw satellite-rocket separation device according to claim 2, wherein the electromagnetic triggering unit (6) further comprises a shell (65), a magnetic core (66) and a magnetic conducting ring (67), and the magnetic core (66), the electromagnetic coil (63), the permanent magnet (62) and the magnetic conducting ring (67) are coaxially accommodated in an inner cavity of the shell (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 outside the magnetic core (66) in a surrounding mode, the permanent magnet (62) and the magnetic conducting ring (67) are sequentially sleeved outside the electromagnetic coil (63) along the axial direction of the magnetic core (66), and the permanent magnet (62) is arranged on one side close to the split screw (51); The pulling pin (61) is slidably arranged on the magnetic core (66) in a penetrating mode, one end of the pulling pin (61) is the action output end (611) and extends out of the shell (65), and the other end of the pulling pin is connected with the elastic reset piece (64).
  4. 4. The electromagnetic unlocking winding split screw satellite-rocket separation device according to claim 3, characterized in that one end of the shell (65) close to the split screw (51) is a closed end, and the other end is covered by an end pressing piece (68); -said action output end (611) of said pull pin (61) projecting from said closed end of said housing (65) and engaging a releasable end (521) of said wrap spring wire (52); The other end of the pulling pin (61) passes through the end pressing piece (68), the penetrating end of the pulling pin is fixed with the end pressing piece (68) through a locking piece, and the end pressing piece (68) is used for precompression of the elastic reset piece (64) and setting the extending position of the pulling pin (61) in the locking state.
  5. 5. The electromagnetic unlocking winding type split screw satellite and arrow separation device according to claim 4, wherein the split screw (51) comprises two sections of rod bodies, the ends of the two sections of rod bodies, which are close to each other, are semi-cylindrical, the semi-cylindrical bodies of the two sections of rod bodies are matched in an involution mode to form a cylindrical section (511) to be separated, the winding spring wire (52) is wound on the periphery of the section (511) to be separated so as to relatively fix the two sections of rod bodies, and the action output end (611) of the pulling pin (61) penetrates through the rod body at one end of the section (511) to be separated along the radial direction of the split screw (51) and is connected with the releasable end (521) of the winding spring wire (52) so as to limit the winding spring wire (52).
  6. 6. The electromagnetic unlocking winding split screw satellite-rocket separation device according to claim 1, wherein each shear assembly (3) comprises at least one shear pin (31), and the axial direction of each shear pin (31) is perpendicular to the separation direction of the top connecting plate (2) and the bearing base (1), and penetrates through the matching surfaces arranged on the bearing base (1) and the top connecting plate (2) and is used for bearing and transmitting the shear load.
  7. 7. The electromagnetic unlocking winding split screw satellite and arrow separation device according to claim 6 is characterized in that semi-cylindrical grooves are correspondingly formed in the butt joint surfaces of the bearing base (1) and the top connecting plate (2), when the bearing base (1) is in butt joint with the top connecting plate (2), a pair of semi-cylindrical grooves are butt joint to form cylindrical pin holes, and each shear pin (31) is accommodated in the corresponding pin hole in a matched mode.
  8. 8. The electromagnetic unlocking winding split screw satellite-rocket separation device according to claim 7, characterized in that each shear assembly (3) further comprises a pin baffle (32), wherein the pin baffle (32) is connected to the bearing base (1) or the top connecting plate (2) and is blocked at an axial end opening of the pin hole for preventing the shear pin (31) from axially coming out of the pin hole.
  9. 9. The electromagnetic unlocking winding split screw satellite rocket separating device according to claim 1, wherein the separating spring assembly (4) comprises a separating spring (41) and a spring guide rod (42), the axial direction of the spring guide rod (42) is parallel to the separating direction of the top connecting plate (2) and the bearing base (1), and one end of the spring guide rod (42) is connected to the bearing base (1) or the top connecting plate (2); The separating spring (41) is sleeved on the spring guide rod (42) and is arranged between the bearing base (1) and the top connecting plate (2) in a precompressed state.
  10. 10. The electromagnetic unlocking winding type split screw satellite rocket separating device according to any one of claims 1 to 9, wherein the bearing base (1) is of a rectangular frame structure with an open upper end, the top connecting plate (2) covers the open end of the rectangular frame, and a plurality of separating spring assemblies (4) and a plurality of shearing resistant assemblies (3) are arranged at intervals along the periphery of the rectangular frame.

Description

Electromagnetic unlocking winding type split screw satellite-rocket separation device Technical Field The invention relates to the technical field of aerospace, in particular to an electromagnetic unlocking winding split screw satellite-rocket separating device. Background At present, in the field of aerospace, a carrier rocket is separated from a satellite (or spacecraft) after a transport task is completed, and the separation mainly depends on two main stream connection and separation configurations, namely a multipoint distribution connection configuration and a butt joint frame wrapping belt connection configuration. When the two configurations are finally separated, a fire explosive bolt is used as a power source for unlocking and separating in most cases. The working principle is that the explosive force is generated by igniting the initiating explosive device, and the connecting bolt is directly cut off or released, so that the mechanical unlocking and separation between the satellites and the arrows are realized. However, in the separation mode based on the initiating explosive device, the initiating explosive device can generate extremely intense instant impact at the moment of ignition initiation, and the high-strength impact becomes the main impact source in the satellite and rocket separation process. The impact load is transferred to the satellite platform, which may cause uncontrollable disturbance of the attitude of the satellite at the moment of separation, increasing the burden and risk of the attitude control system. More seriously, the high-frequency and high-amplitude impact is extremely easy to damage or even cause functional failure to precision loads (such as optical instruments, laser communication equipment, precision sensors and the like) which are carried on satellites and are sensitive to the impact, and the task success or failure is directly influenced. Therefore, development and adoption of a non-initiating explosive device and a low-impact power source and a technical approach to replace the traditional initiating explosive device explosion bolt have become important technical directions for reducing the satellite-rocket separation impact and improving the task reliability and the satellite safety. Disclosure of Invention The invention solves the problems of high impact, easy damage to precise load on the satellite and poor separation synchronism and controllability caused by explosive bolts of a fire machine. In order to solve the problems, the invention provides an electromagnetic unlocking winding split screw satellite-rocket separating device, which comprises: A load-bearing base; the top connection plate is arranged in a butt joint way with the bearing base; the shearing assemblies are arranged between the bearing base and the butt joint surface of the top connecting plate and are used for bearing and transmitting shearing loads acting on the butt joint surface; The separation spring assembly is arranged between the bearing base and the top connecting plate and is used for providing driving force for separating the bearing base from the top connecting plate; The split screw assembly comprises a split screw and a winding spring wire, wherein the split screw extends along the separation direction of the top connecting plate and the bearing base, two ends of the split screw are respectively connected with the bearing base and the top connecting plate, the winding spring wire is wound on a section to be separated of the split screw so as to apply radial constraint force to the split screw to maintain the integral bearing state, and And the action output end of the electromagnetic triggering unit is connected with the releasable end of the winding spring wire and is used for responding to an unlocking instruction to act, the radial constraint force is released, the split screw is dissociated, and the separation spring assembly is further allowed to drive the top connecting plate to be separated from the bearing base. Preferably, the electromagnetic triggering unit comprises a pulling pin, a permanent magnet, an electromagnetic coil and an elastic reset piece, wherein in a locking state, the electromagnetic coil is powered off, magnetic attraction generated by the permanent magnet drives the pulling pin to compress the elastic reset piece and keep an extending position, so that the action output end of the pulling pin restrains the releasable end of the winding spring wire, in an unlocking state, the electromagnetic coil is powered on and generates electromagnetic force opposite to the magnetic field direction of the permanent magnet so as to offset the magnetic attraction, and the pulling pin is retracted under the action of the restoring force of the elastic reset piece, so that the releasable end of the winding spring wire is released. Preferably, the electromagnetic triggering unit further comprises a shell, a magnetic core and a magnetic conducting ring, wherein the magne