Electromagnetic drive type super-large bearing locking and separating mechanism for stage separation of carrier rocket
The electromagnetically driven, ultra-high load-bearing locking and separation mechanism solves the problems of non-reusability and undetectability of traditional rocket locking and separation mechanisms, achieving high reliability and low impact locking and separation, meeting the reusability requirements of rockets, and improving mission success rate and mechanism rigidity.
Patent Information
- Application Number
- CN202511354386.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-09-22
- Publication Date
- 2025-11-21
AI Technical Summary
Traditional rocket locking and separation mechanisms are driven by pyrotechnic energy, which has problems such as non-reusability, undetectability, excessive impact, and explosion pollution, making it difficult to meet the reusability and high reliability requirements of future rockets.
An electromagnetically driven, ultra-high load-bearing locking and separating mechanism is adopted. It uses electromagnets and a six-bar linkage to unlock non-pyrotechnic components. The locking claws arranged symmetrically cooperate with the hemispherical grooves of the locked parts to achieve reliable constraints on the three degrees of freedom of X, Y, and Z. Multiple sets of parallel and segmented transmission components are used to enhance the rigidity and load distribution of the mechanism.
It enables non-pyrotechnic unlocking, eliminates the risk of severe impact and explosion pollution, improves locking reliability and positioning accuracy, reduces the total life cycle cost, significantly improves mission success rate and mechanism rigidity, and can withstand thrust and torque in the millions of Newtons.
Smart Images
Figure CN120991669A_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present application relates to an electromagnetic drive type super large bearing locking separation mechanism, belonging to the technical field of space launch vehicle structure. BACKGROUND
[0002] At present, the launch vehicle is the main means for human beings to enter space. During the flight of the launch vehicle, multiple separation actions including boost separation, fairing separation, interstage separation and satellite-rocket separation need to be completed. The reliability and accuracy of the locking separation mechanism directly affect the success or failure of the rocket flight.
[0003] The locking separation mechanism of the launch vehicle has the characteristics of large size of the separated body, long interstage separation stroke, and large locking load. At the same time, it needs to adapt to complex flight environments such as high impact, strong vibration, and wide temperature range. The traditional rocket locking separation mechanism mostly uses separation technology based on pyrotechnic energy drive (such as explosive bolts, cutters, and expansion tubes). Although this type of separation mechanism has the advantages of strong bearing capacity and reliable unlocking, it has the disadvantages of non-reusable, non-detectable, excessive impact, and explosion pollution. Therefore, a non-pyrotechnic separation mechanism with large bearing capacity, reliable unlocking, strong impact resistance, and reusability is needed to effectively meet the future reusable development needs of the launch vehicle. SUMMARY
[0004] The present application is to solve the problem that the traditional rocket locking separation mechanism mostly uses separation technology based on pyrotechnic energy drive. Although this type of separation mechanism has the advantages of strong bearing capacity and reliable unlocking, it has the problems of non-reusable, non-detectable, excessive impact, and explosion pollution. Therefore, an electromagnetic drive type super large bearing locking separation mechanism for interstage separation of the launch vehicle is proposed.
[0005] The technical solution adopted by the present application to solve the above problems is as follows: the present application comprises a rack, a jaw assembly is arranged in the middle of the rack, the jaw assembly is used to lock the locked part, an electromagnetic assembly is arranged at the upper and lower parts of the rack, the electromagnetic assembly is used to drive a transmission assembly, each electromagnetic assembly is connected with the jaw assembly through a transmission assembly, the transmission assembly is used to transmit the driving force of the electromagnetic assembly to the jaw assembly, and the locked part is clamped in the jaw assembly.
[0006] Further, the jaw assembly comprises a jaw seat arranged in the middle of the rack, two hinge shafts are installed on the jaw seat, a locking jaw is installed on each hinge shaft, and the two locking jaws can lock the locked part when closed.
[0007] Further, the inner surface of the locking jaw is provided with a clamping groove, and the clamping groove is used to clamp the locked part.
[0008] Further, the electromagnetic assembly comprises a bracket installed on the upper and lower parts of the rack, an electromagnet is installed on the bracket, and the bracket is connected with the jaw assembly through the transmission assembly.
[0009] Further, the transmission assembly comprises a connecting rod L1, one end of the connecting rod L1 is connected with the rack through a first shaft, the other end of the connecting rod L1 is connected with the attracted piece and one end of a connecting rod L2, the other end of the connecting rod L2 is connected with one end of an upper supporting rod and one end of a connecting rod L3, the other end of the upper supporting rod is connected with the rack through a second shaft, the other end of the connecting rod L3 is connected with one end of a lower supporting rod and one end of a connecting rod L4, the other end of the lower supporting rod is connected with the rack through a third shaft, the other end of the connecting rod L4 is connected with one end of a connecting rod L5 and one end of a connecting rod, the other end of the connecting rod L5 is connected with the locking jaw through a fourth shaft, the other end of the connecting rod is provided with a supporting frame, and the supporting frame is connected with the support through two fifth shafts.
[0010] The beneficial effects of the present application are: 1. The present application adopts an electromagnet driving cooperation six-connecting-rod transmission mechanism, realizes non-explosive product unlocking (power-on locking and power-off unlocking), eliminates the violent impact, fragment pollution and electromagnetic interference risk caused by the explosion of traditional explosives, and meets the development trend of future rockets towards low impact and high reliability; 2. The present application can be tested for locking-unlocking cycle on the ground for multiple times, verifies the function reliability and service life, eliminates the risk of single-point failure of explosives and undetectable, significantly improves the mission success rate and reduces the whole life cycle cost; 3. The present application realizes reliable constraint of X, Y and Z three degrees of freedom through the cooperation of the three locking ends on the locked piece and the symmetrically arranged locking jaw and the semispherical groove formed by the closure of the locking jaw; the present application optimizes the load distribution, significantly reduces the local stress of the locking contact area, improves the locking reliability, and also greatly improves the positioning accuracy of the locked piece and the rigidity of the mechanism in the whole locking state; 4. The transmission assembly of the present application adopts a multi-group parallel and segmented design in the key parts, which greatly increases the effective support section number and bending section modulus of the key shafts, can reliably bear and transmit the thrust, bending moment and shear force of the order of magnitude of millions of newtons of the interstage separation surface of the heavy launch vehicle, and meets the needs of the heavy launch vehicle. BRIEF DESCRIPTION OF DRAWINGS
[0011] Figure 1 is a schematic diagram of the overall structure of the present application; Figure 2 is a sectional view of the present application; Figure 3 is a schematic diagram of the position of the transmission assembly in the locking state; Figure 4 is a schematic diagram of the position of the transmission assembly in the separation state; Figures 1 to 41-1-Electromagnet, 1-2-Bracket, 1-3-Claw seat, 1-4-Frame, 1-5-Locking claw, 1-6-Hinge shaft, 1-7-Locked part, 2-Transmission assembly, 2-1-Connecting rod L1, 2-2-First shaft, 2-3-Attracted part, 2-4-Connecting rod L2, 2-5-Upper support rod, 2-6-Second shaft, 2-7-Connecting rod L3, 2-8-Lower support rod, 2-9-Third shaft, 2-10-Connecting rod L4, 2-11-Connecting rod L5, 2-12-Fourth shaft, 2-13-Connecting rod, 2-14-Support frame, 2-15-Fifth shaft. Detailed Implementation
[0012] Specific implementation method one: as follows Figure 1 As shown, an electromagnetically driven, ultra-large load-bearing locking and separation mechanism for interstage separation of a launch vehicle includes a frame 1-4. A claw assembly is provided in the middle of the frame 1-4 for locking the locked component 1-7. An electromagnetic assembly is provided at the upper and lower parts of the frame 1-4 for driving a transmission assembly. Each electromagnetic assembly is connected to the claw assembly through a transmission assembly. The transmission assembly is used to transmit the driving force of the electromagnetic assembly to the claw assembly. The locked component 1-7 is clamped in the claw assembly.
[0013] Specific implementation method two: such as Figure 2 As shown, the mechanism, arranged on both sides of the interstage frame annular support, mainly consists of electromagnet 1-1, support 1-2, claw seat 1-3, frame 1-4, locking claw 1-5, hinge shaft 1-6, and transmission assembly 2. Electromagnet 1-1 is rigidly fixed to frame 1-4 via support 1-2. Frame 1-4, as the core load-bearing base of the entire mechanism, is fixed to the rocket interstage frame via high-strength bolts. Its function is to integrate all functional components, provide an installation reference for the locking mechanism, and evenly transmit the mega-Newton-level locking preload and flight load to the main structure. Locking claw 1-5 is a key component at the actuator end of the mechanism, symmetrically arranged on claw seat 1-3, and the two are connected to frame 1-4 via hinge shaft 1-6. In the locked state, locking claw 1-5 is completely in contact with the load-bearing surface. Under the action of transmission component 2, locking claw 1-5 rotates around hinge shaft 1-6 and unfolds outward, realizing the separation of the mechanism from the locked component, i.e., the lower stage rocket connecting frame 1-7, with a maximum opening angle of 70°. The locked component 1-7 has three locking ends, which can cooperate with the hemispherical locking groove formed by the closing of locking claw 1-5 to achieve reliable constraint of the locked component 1-7 in the X, Y, and Z degrees of freedom and reliable transmission of mega-Newton level loads. Compared with a single locking end, this structure can optimize the load distribution on the locked component 1-7, reduce local stress, improve the reliability of locking, and at the same time completely restrict the degrees of freedom of the locked component 1-7, improving the positioning accuracy of the locked component 1-7 and the overall rigidity of the mechanism.
[0014] Specific implementation method three: such asFigure 3 and Figure 4 As shown in the figure, the transmission assembly 2 is a six-link mechanism, mainly including connecting rod L12-1, shaft 12-2, attracted piece 2-3, connecting rod L22-4, upper support rod 2-5, shaft 22-6, connecting rod L32-7, lower support rod 2-8, shaft 32-9, connecting rod L42-10, connecting rod L52-11, shaft 42-12, connecting rod 2-13, support frame 2-14 and shaft 52-15. The shaft 12-2, the shaft 22-6, the shaft 32-9, the support frame 2-14 and the shaft 52-15 are fixedly connected with the rack 1-4, and their positions remain unchanged when the mechanism moves. The attracted piece 2-3 is made of ferromagnetic material, and when the electromagnet 1-1 is powered off and demagnetized, the attracted piece 2-3 is immediately separated from the electromagnet 1-1, driving the connecting rod L12-1 to move. The connecting rod L12-1 is connected with the connecting rod L22-4, the connecting rod L22-4 is connected with the connecting rod L32-7, the connecting rod L32-7 is connected with the connecting rod L42-10, and the connecting rod L42-10 is connected with the connecting rod L52-11 through shafts. The upper support rod 2-5 is connected with the connecting rod L22-4 and the connecting rod L32-7 through a shaft, the lower support rod 2-8 is connected with the connecting rod L32-7 and the connecting rod L42-12 through a shaft, and the connecting rod 2-13 is connected with the connecting rod L42-10 and the connecting rod L52-11 through a shaft. The upper support rod 2-5, the lower support rod 2-8 and the connecting rod 2-13 limit the degrees of freedom of the mechanism, and at the same time, by increasing the number of shaft cross sections, the maximum bending moment in a single span is reduced, and the risk of bending deformation or even fracture of the shaft is reduced.
[0015] To cope with the intense vibration, high-temperature gas scouring and huge separation overload caused by the ignition of the upper stage engine during the interstage thermal separation, all the key rotating shafts of the transmission assembly 2 are designed with multi-section redundant parallel support. Specifically, the connecting rod L52-11 connected between the end of the transmission assembly 2 and the locking jaw 1-5 is provided with three groups of five parallel connecting rod units, which are connected to the shaft 42-12 together, thereby significantly increasing the effective support section number of the shaft 42-12, which is 53. Similarly, the connecting rod 2-13 is also designed with multi-group parallel design and divided into three groups of five units, so that the connecting rod 2-13, the connecting rod L42-10 and the connecting rod L52-11 connected to the rotating shaft obtain more equivalent support section numbers, which is 59. In addition, the connecting rod L22-4, the connecting rod L32-7, the lower support rod 2-8 and the connecting rod L42-10 are designed in a segmented manner and divided into two segments, and the connecting rod L12-1 and the upper support rod 2-5 are designed in an integral manner, which greatly improves the bending strength of each rotating shaft node and the rigidity of the whole mechanism. The equivalent support section numbers obtained by each node are as follows: the connecting rod L12-1, the connecting rod L22-4 connected to the rotating shaft of the attracted member 2-3, the connecting rod L22-4, the upper support rod 2-5 and the connecting rod L32-7 connected to the rotating shaft, and the connecting rod L32-7, the lower support rod 2-8 and the connecting rod L42-10 connected to the rotating shaft, which are 11, 11, 11 and 9 respectively, which is enough to resist deformation and failure under extreme load.
[0016] Working principle Locking process: Before the rocket is launched and during the active stage flight, the electromagnet 1-1 is continuously energized and magnetized to reliably attract the attracted member 2-3, so that the six-link transmission assembly 2 overcomes its inertia and external load and maintains the locking position. This action drives the locking jaws 1-5 on both sides to rotate inward around the hinge shaft 1-6 to the completely closed state. After the locking jaw 1-5 is closed, the semispherical groove formed by the locking jaw 1-5 tightly holds the three locking ends on the locked member 1-7, completing the locking action.
[0017] Separation process: When the rocket flies to the interstage separation point, the onboard computer issues a separation command. The electromagnet 1-1 is instantaneously de-energized and demagnetized according to the command. The attracted member 2-3 separates from the electromagnet 1-1 quickly under the action of inertia, drives the connecting rod L12-1 to rotate, and drives the locking jaw 1-5 to rotate outward around the hinge shaft 1-6 to an opening angle of 70°, completely releasing the constraint on the locked member 1-7. After the constraint is released, the lower stage rocket body completes the separation action under the thrust of the upper stage rocket engine jet.
[0018] The above merely describes preferred embodiments of the present application, and is not intended to limit the present application in any form. Although the present application has been disclosed with preferred embodiments as above, it is not intended to limit the present application. Any person skilled in the art, without departing from the technical solution of the present application, can make some changes or modifications to the above disclosed technical content to obtain equivalent embodiments with equivalent changes. However, as long as it does not deviate from the technical solution of the present application, and is within the spirit and principles of the present application, any simple modification, equivalent replacement and improvement of the above embodiments are still within the protection scope of the technical solution of the present application.
Claims
1. An electromagnetically driven, ultra-large load-bearing locking and separation mechanism for interstage separation of a launch vehicle, characterized in that, The device includes a frame (1-4), with a claw assembly in the middle of the frame (1-4) for locking the locked part (1-7). An electromagnetic assembly is provided at the top and bottom of the frame (1-4) for driving the transmission assembly. Each electronic assembly is connected to the claw assembly through a transmission assembly. The transmission assembly is used to transmit the driving force of the electromagnetic assembly to the claw assembly. The locked part (1-7) is clamped in the claw assembly.
2. The electromagnetically driven ultra-large load-bearing locking and separation mechanism for interstage separation of a launch vehicle according to claim 1, characterized in that, The jaw assembly includes a jaw seat (1-3) located in the middle of the frame (1-4). Two hinge shafts (1-6) are mounted on the jaw seat (1-3), and a locking jaw (1-5) is mounted on each hinge shaft (1-6). When the two locking jaws (1-5) are closed, they can lock the locking member (1-7).
3. The electromagnetically driven ultra-large load-bearing locking and separation mechanism for interstage separation of a launch vehicle according to claim 2, characterized in that, The inner surface of the locking claw (1-5) is provided with a groove, which is used to clamp the locked part (1-7).
4. The electromagnetically driven ultra-large load-bearing locking and separation mechanism for interstage separation of a launch vehicle according to claim 1, characterized in that, The electromagnetic assembly includes a bracket (1-2) installed on the upper and lower parts of the frame (1-4), an electromagnet (1-1) is installed on the bracket (1-2), and the bracket (1-2) is connected to the claw assembly through a transmission assembly (2).
5. An electromagnetically driven, ultra-large load-bearing locking and separation mechanism for interstage separation of a launch vehicle, as described in claim 1, 2, or 4, characterized in that, The transmission assembly (2) includes a connecting rod L1 (2-1). One end of the connecting rod L1 (2-1) is connected to the frame (1-4) via a first shaft (2-2). The other end of the connecting rod L1 (2-1) is connected to the suction object (2-3) and one end of the connecting rod L2 (2-4). The other end of the connecting rod L2 (2-4) is connected to one end of the upper support rod (2-5) and one end of the connecting rod L3 (2-7). The other end of the upper support rod (2-5) is connected to the frame (1-4) via a second shaft (2-6). The other end of the connecting rod L3 (2-7) is connected to one end of the lower support rod (2-8). One end of the connecting rod L4 (2-10) and the other end of the lower support rod (2-8) are connected to the frame (1-4) via the third shaft (2-9). The other end of the connecting rod L4 (2-10) is connected to one end of the connecting rod L5 (2-11) and one end of the connecting rod (2-13). The other end of the connecting rod L5 (2-11) is connected to the locking claw (1-5) via the fourth shaft (2-12). The other end of the connecting rod (2-13) is equipped with a support frame (2-14). The support frame (2-14) is connected to the bracket (1-4) via two fifth shafts (2-15).