CN-122015587-A - Lever overturning type locking and separating mechanism for rocket stage separation

CN122015587ACN 122015587 ACN122015587 ACN 122015587ACN-122015587-A

Abstract

A lever turnover type locking and separating mechanism for rocket stage separation relates to the technical field of aerospace and aims to solve the problems of high unlocking force, low reliability and poor synchronism of a traditional mechanical locking mechanism. The device comprises an upper-stage compression plate, a lower-stage fixing plate, a frame, a locking assembly, a transmission assembly, a driving assembly and a locking or unlocking driving force, wherein the locking assembly is used for being matched with the upper-stage compression plate of a rocket to realize locking, the transmission assembly is connected between the locking assembly and the driving assembly, the driving assembly is used for providing the locking or unlocking driving force, the locking assembly comprises a threaded pre-tightening seat, the threaded pre-tightening seat is connected with a compression connecting rod through threads and used for adjusting the pre-tightening force of a mechanism, the compression connecting rod is hinged with the frame through a first fixed shaft and is connected with the transmission assembly through a first rotating shaft, and overturning motion is carried out around the first fixed shaft under the driving of the transmission assembly, so that the locking or the separation of the mechanism is realized. The invention provides a more superior interstage connection and separation solution for the next generation carrier rocket through the lever principle and the overturning movement design.

Inventors

YANG FEI
ZHANG HONGJIAN
GUO XIAOFEI
MOU YU
ZHOU TIANSONG
PENG BO
JIA LEI
SUN HAO

Assignees

哈尔滨工业大学
北京宇航系统工程研究所
中国航天科技集团商业火箭有限公司

Dates

Publication Date: 20260512
Application Date: 20260306

Claims (6)

1. A lever turnover type locking separation mechanism for rocket stage separation, comprising an upper stage compression plate (1-1), a lower stage fixing plate (1-2) and a frame (1-3), characterized in that the locking separation mechanism further comprises: The locking component (2) is used for being matched with the upper-stage compression plate (1-1) of the rocket to realize locking; the transmission assembly (3) is connected between the locking assembly (2) and the driving assembly (4); a driving assembly (4) for providing a driving force for locking and unlocking; The locking assembly (2) comprises a threaded pre-tightening seat (2-1), the threaded pre-tightening seat (2-1) is connected with a compression connecting rod (2-2) through threads and used for adjusting the pre-tightening force of the mechanism, the compression connecting rod (2-2) is hinged with the frame (1-3) through a first fixed shaft (2-3), meanwhile, the locking assembly is connected with the transmission assembly (3) through a first rotating shaft (2-4), and the locking assembly is driven by the transmission assembly (3) to do overturning motion around the first fixed shaft (2-3), so that the threaded pre-tightening seat (2-1) at the tail end of the compression connecting rod (2-2) compresses or breaks away from the compression plate (1-1) at the upper stage, and connection or release between two stages is achieved.
2. A lever overturning type locking and separating mechanism for rocket stage separation according to claim 1, wherein the transmission assembly (3) comprises a second rotating shaft (3-1), a transmission connecting rod (3-2), a third rotating shaft (3-3), a second fixed shaft (3-4) and a dead point connecting rod (3-5), the transmission connecting rod (3-2) is hinged with the frame (1-3) through the second fixed shaft (3-4), is connected with the driving assembly (4) through the third rotating shaft (3-3), is hinged with the dead point connecting rod (3-5) through the second rotating shaft (3-1), and the dead point connecting rod (3-5) is hinged with the locking assembly (2) through the first rotating shaft (2-4).
3. A lever overturning type locking and separating mechanism for rocket stage separation according to claim 2, wherein the driving assembly (4) comprises an air driving piston rod (4-1), an air cylinder (4-2) and a third fixed shaft (4-3), the air driving piston rod (4-1) is connected with the transmission connecting rod (3-2) through the third rotating shaft (3-3) to provide locking driving force, and the air cylinder (4-2) is connected with the frame (1-3) through the third fixed shaft (4-3).
4. A lever turnover type locking and separating mechanism for rocket stage separation according to claim 3, characterized in that a tension spring is provided between the pressing connecting rod (2-2) and the second rotating shaft (3-1).
5. A lever overturning type locking and separating mechanism for rocket stage separation as recited in claim 4, wherein a torsion spring is further arranged on the first fixed shaft (2-3), the second fixed shaft (3-4) or the third fixed shaft (4-3).
6. A lever overturning type locking and separating mechanism for rocket stage separation as recited in claim 5, wherein a plurality of mechanisms are uniformly distributed in the circumferential direction between rocket stages to realize synchronous locking or separation.

Description

Lever overturning type locking and separating mechanism for rocket stage separation Technical Field The invention relates to the technical field of aerospace, in particular to a lever overturning type locking and separating mechanism for rocket stage separation. Background Interstage separation of a launch vehicle is a critical motion in flight that is extremely high in reliability requirements and is irreversible. The connecting mechanism must bear huge axial overload, bending moment and complex vibration load in the active section to ensure zero clearance locking of the interstage structure, and after the separation instruction is issued, the synchronous and reliable unlocking of all connecting points is realized within millisecond time, and an initial separation condition without interference is formed, and the performance directly determines the success and failure of the task. In current engineering applications, initiating explosive device driven connecting and separating devices such as explosion bolts, cutting ropes and the like are commonly used for interstage separation. The technology is mature, but the nature of relying on initiating explosive devices brings remarkable inherent defects that firstly, the impact is bad, high-frequency and high-amplitude impact generated by detonation seriously threatens precision equipment on an arrow, secondly, pollution and fragment risks, explosion products possibly pollute an arrow body and generate excessive residues, thirdly, the system cannot be tested repeatedly after final assembly, the single-point verification risk exists, and fourthly, the safety and cost problems are that the production, storage, transportation and operation flow of the initiating explosive devices are complex and strict. In order to overcome the defects of initiating explosive devices and meet the requirements of reusable rockets and high-reliability tasks, the industry is actively exploring mechanical separation schemes which are not initiating explosive devices, low in impact and capable of being repeatedly tested. Among them, various mechanical locking and releasing mechanisms (Marman ring, strap, multipoint lock, etc.) become the focus of research. However, existing mechanical solutions, when applied to large diameter, heavy duty rocket stage connections, still face a core conflict: 1) The contradiction between the load and the unlocking force is that the locking mechanism needs to provide a large pre-tightening force or mechanical interlocking in order to ensure that the disengagement or sliding is not generated under extreme load, which directly leads to a sharp increase of the driving force (such as the output force of the actuator) required for unlocking, and presents a serious challenge to the driving system. 2) The reliability problem is that the unlocking process often involves complex series actions of a plurality of moving parts (such as lock hooks, sliding blocks and connecting rods), and friction, deformation or jamming of any link can cause unlocking failure. The longer the action chain, the lower the reliability. 3) The problem of synchronism is that the multi-point locking mechanism needs to realize synchronous release of all locking points in a very short time. The existing mechanical scheme has the phase difference which is difficult to eliminate when an unlocking instruction and motion are transmitted, so that uneven stress on a separation surface is easily caused, and unexpected attitude disturbance of an arrow body is caused. Therefore, there is a need for a new mechanical locking and disengaging configuration that balances high load reliability with low driving force requirements, while providing simple and direct motion, high synchronization, and robustness. Disclosure of Invention The invention aims to solve the technical problems of high unlocking force, low reliability and poor synchronism of the traditional mechanical locking mechanism, and further provides a lever turnover type locking and separating mechanism for rocket stage separation, which is used for high-strength locking connection and quick separation between an upper stage and a lower stage of a rocket. The lever overturning type locking and separating mechanism provided by the invention fundamentally solves the contradiction through ingenious lever principle and overturning movement design, and provides a more superior interstage connection and separation solution for the next generation of carrier rockets. The technical scheme adopted by the invention for solving the problems is as follows: The invention provides a lever turnover type locking and separating mechanism for rocket stage separation, which comprises an upper stage pressing plate, a lower stage fixing plate, a frame, a locking assembly, a transmission assembly and a driving assembly, wherein the locking assembly is used for being matched with the rocket upper stage pressing plate to realize locking, the transmission assembly is conn