Shearing gas vane mechanism
By designing a shearable gas rudder mechanism, the gas rudder wings are sheared and separated before the missile is launched, which solves the problem of gas rudder thrust loss to the engine, and achieves the improvement of the missile's maximum range and the normal provision of control torque.
Patent Information
- Application Number
- CN202511148415.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-08-17
- Publication Date
- 2025-09-26
AI Technical Summary
The existing gas rudder causes thrust loss to the engine when the missile attacks long-range targets, affecting the missile's maximum range performance.
A shearable gas rudder mechanism is designed. By executing the shear command before the missile is launched, the gas generator generates high-pressure gas to shear the shear pin, so that the gas rudder wings are separated before launch to avoid thrust loss; it can still work normally and provide control force when hitting short-range targets.
Without affecting other combat performance, the maximum range performance of the missile is improved and the impact on vehicle-mounted equipment and following infantry is reduced.
Smart Images
Figure CN120702278A_ABST
Abstract
Description
Technical Field
[0001] The invention belongs to the technical field of gas rudder design, and in particular relates to a shearable gas rudder mechanism. Background Art
[0002] After exiting the tube, vertically launched missiles are required to achieve significant attitude angle changes in a short period of time. However, at this point, the missile's speed is low, and air rudder control efficiency is low, often making it difficult to provide the required control force and torque. Currently, missiles generally use gas rudder technology to achieve rapid turns. However, the presence of gas rudders results in a certain thrust loss on the engine, limiting the missile's maximum range.
[0003] Since the missile needs to make rapid turns in the initial stage of flight when attacking medium and short-range targets, and adopts a high-throw trajectory when attacking long-range targets, which does not require rapid turns, gas rudders are not needed to provide control force when attacking long-range targets. Summary of the Invention
[0004] (1) Technical issues to be solved
[0005] The technical problem to be solved by the present invention is: how to reduce the thrust loss caused by the gas rudder to the engine when the missile attacks a long-range target.
[0006] (2) Technical solution
[0007] In order to solve the above technical problems, the present invention provides a shearable gas rudder mechanism, comprising a drive shaft, a piston, a transmission shaft, a connecting rod, a shear pin, a gas rudder wing, a fireproof seat, a gas shell, and a gas generating device;
[0008] The left end of the drive shaft is connected to the motor drive device and is used to rotate under the drive of the motor drive device; the right end of the drive shaft is fixedly connected to the flange at the left end of the gas shell, and the right end of the gas shell is fixedly connected to the left end of the drive shaft. A stepped hole is provided inside the drive shaft; the connecting rod is disposed in the stepped hole inside the drive shaft, and the two are connected by a key for transmitting rotational torque; the right end of the connecting rod passes through the stepped hole inside the drive shaft and is inserted into the shaft hole of the gas rudder wing; the connecting rod and the gas rudder wing are also connected by a key for transmitting rotational torque;
[0009] The piston is arranged inside the gas shell, and the right end of the piston is fixedly connected to the left end of the connecting rod; a shear pin is provided between the side wall of the connecting rod and the axial hole of the gas rudder wing; the gas generating device is arranged on the side wall of the gas shell, and when ignited, it is used to provide high-pressure gas to the piston to move to the left.
[0010] Among them, when in the long-range attack mode, the gas rudder shear command is executed before the missile is fired. After receiving the command, the gas generator generates high-pressure gas to put pressure on the piston and cut the shear pin. The piston drives the connecting rod to move, and the connecting rod exits the gas rudder wing shaft hole. The gas rudder wing naturally separates under the action of gravity, and the gas rudder wing is ejected out of the tube with the missile and thrown away from the launch platform.
[0011] Among them, when in the medium and short range attack mode, the missile does not execute the gas rudder shear instruction, the missile is ejected from the tube normally and ignited, and the motor driving torque is transmitted to the gas rudder through the drive shaft, gas casing, transmission shaft, and connecting rod, driving the gas rudder to deflect and generate vector thrust.
[0012] The gas generating device is installed on the side of the gas shell by means of threaded connection.
[0013] The present invention also provides a missile using the shearable gas rudder mechanism.
[0014] (3) Beneficial effects
[0015] Compared with existing technologies, the present invention offers the following advantages: When attacking long-range targets, the gas rudder is sheared and separated before launch, eliminating thrust loss caused by the gas rudder and thereby improving the missile's maximum range performance. The sheared gas rudder is ejected from the launch tube holder at a low velocity and low mass, thus minimizing impact on onboard equipment and accompanying infantry. When attacking medium- and short-range targets, the gas rudder shear command is not executed, allowing the gas rudder to continue functioning normally to provide initial control. This effectively improves the maximum range performance of vertically launched missiles while minimizing impact on other operational performance indicators. BRIEF DESCRIPTION OF THE DRAWINGS
[0016] Figure 1 This is a schematic diagram of the shearable gas rudder mechanism.
[0017] Figure 2 This is a schematic diagram of the shearable gas rudder mechanism.
[0018] Figure 3 This is a schematic diagram of the shearable gas rudder mechanism after shearing.
[0019] Figure 4 Schematic diagram of the piston and connecting rod structure. DETAILED DESCRIPTION
[0020] In order to make the purpose, content, and advantages of the present invention more clear, the specific implementation methods of the present invention are further described in detail below with reference to the accompanying drawings and examples.
[0021] like Figure 1As shown, this embodiment mainly includes a drive shaft 1, a piston 2, a transmission shaft 3, a connecting rod 4, a shear pin 5, a gas rudder 6, a fireproof seat 7, a gas shell 8, a bearing 9, a gas generating device 10, etc.
[0022] The drive shaft 1 is connected to the motor drive unit and rotates under its drive. The drive shaft 1 is connected to the gas casing 8 via four flange screws. The gas casing 8 is connected to the drive shaft 3 via three radial screws. The drive shaft 3 is connected to the connecting rod 4, and the connecting rod 4 is connected to the gas rudder 6 via keyways. The piston 2 is connected to the connecting rod 4 via a steel pin, which transmits axial force. The connecting rod 4 is connected to the gas rudder 6 via a shear pin 5 made of tungsten-copper-infiltrated material. It shears and breaks when subjected to a certain axial force. The gas generator 10 is threadedly mounted to the side of the gas casing 8.
[0023] When the shear instruction is not executed, the motor drives the drive shaft 1 to rotate, and the driving torque is transmitted to the gas rudder wing 6 through the drive shaft 1, the gas shell 8, the transmission shaft 3, and the connecting rod 4, and overcomes the hinge torque on the gas rudder wing 6 to drive the gas rudder wing 6 to rotate, completing the vector thrust function of the gas rudder.
[0024] When the shear command is executed, the gas generator 10 ignites to generate high-pressure gas. This pressure exerts pressure on the piston 2, which is then transmitted to the shear pin 5 via the connecting rod 4. By rationally designing the maximum shear force of the shear pin 5, the gas pressure ensures that the shear pin 5 reliably shears. After the shear pin 5 breaks, the piston 2, under pressure, drives the connecting rod 4 outward, allowing it to withdraw from the keyway of the gas rudder 6. The gas rudder 6 then naturally falls under the action of gravity, completing the gas rudder shear separation function.
[0025] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the technical principles of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.
Claims
1. A shearable gas rudder mechanism, characterized in that: It comprises a drive shaft (1), a piston (2), a transmission shaft (3), a connecting rod (4), a shear pin (5), a gas rudder (6), a fireproof seat (7), a gas casing (8), and a gas generating device (10); The left end of the drive shaft (1) is connected to the motor drive device and is used to rotate under the drive of the motor drive device; the right end of the drive shaft (1) is fixedly connected to the flange of the left end of the gas shell (8), the right end of the gas shell (8) is fixedly connected to the left end of the transmission shaft (3), and a step hole is provided inside the transmission shaft (3); the connecting rod (4) is arranged in the step hole inside the transmission shaft (3), and the two are connected by a key for transmitting rotational torque; the right end of the connecting rod (4) passes through the step hole inside the transmission shaft (3) and is inserted into the shaft hole of the gas rudder wing (6); the connecting rod and the gas rudder wing are also connected by a key for transmitting rotational torque; The piston (2) is arranged inside the gas housing (8), and the right end of the piston (2) is fixedly connected to the left end of the connecting rod (4); a shear pin (5) is provided between the side wall of the connecting rod (4) and the axial hole of the gas rudder wing (6); and a gas generating device (10) is provided on the side wall of the gas housing (8) and is used to provide high-pressure gas to the piston (2) to move leftward when ignited.
2. The shearable gas rudder mechanism according to claim 1, characterized in that: When in the long-range attack mode, the gas rudder shear command is executed before the missile is fired. After receiving the command, the gas generator generates high-pressure gas to put pressure on the piston and shear the shear pin. The piston drives the connecting rod to move, and the connecting rod exits the gas rudder wing shaft hole. The gas rudder wing naturally separates under the action of gravity, and the gas rudder wing is ejected out of the tube with the missile and thrown away from the launch platform.
3. The shearable gas rudder mechanism according to claim 1, characterized in that: When in the medium and short range attack mode, the missile does not execute the gas rudder shear instruction. The missile is ejected from the tube and ignited normally. The motor driving torque is transmitted to the gas rudder through the drive shaft, gas casing, transmission shaft, and connecting rod, driving the gas rudder to deflect and generate vector thrust.
4. The shearable gas rudder mechanism according to claim 1, characterized in that: The gas generating device is installed on the side of the gas shell through threaded connection.
5. A missile using a shearable gas rudder mechanism.