Foldable three-channel movable vane two-dimensional correction fuse

Abstract

The application relates to a two-dimensional correction fuze of a foldable three-channel movable rudder, wherein a near-blast module is fixedly arranged in a wind cap; a security module, a thermal battery and a penetration body are sequentially arranged in the rear section of a fuze body; a relative-rotation fuze seat is arranged at the rear end of the rear section of the fuze body; a transmission explosion module is screwed into the fuze seat; a rudder engine module and a navigation and guidance control module are arranged in the front section of the fuze body; the rudder engine module is a four-axle three-channel foldable rudder wing electric rudder engine, which comprises an X-shaped layout rudder wing, a servo mechanism, a shell and a torsional spring; the rudder wing is driven by the servo mechanism and is composed of a pair of differential rudders and a pair of steering rudders. The rudder blade of the fuze is in a folded state when being discharged from a barrel, thereby increasing the stability of a projectile; the correction angle of the correction fuze is variable; the steering rudders and the differential rudders can provide correction forces in the range lateral direction, correction efficiency is increased, and the defect that the correction capacity is not fully utilized when the fixed rudder assembly is corrected is effectively avoided.

Description

Technical Field

[0001] This invention relates to the field of two-dimensional ballistic correction fuse technology, and particularly to a foldable three-channel movable rudder two-dimensional correction fuse. Background Technology

[0002] Two-dimensional ballistic correction technology is an effective way to improve the precision strike capability of conventional unguided munitions and has received widespread attention in recent years. It can significantly improve firing accuracy by adding a precision guidance component without changing the original projectile. However, due to the requirements of low cost and reliability of munitions, designing a simple, reliable, and miniaturized precision guidance component has become an urgent problem to solve. Some projectiles have low stability margins upon exiting the muzzle, and the outward extension of the rudder blades can easily cause projectile instability. Furthermore, fixed rudder correction components, due to their fixed rudder deflection angle, suffer from insufficient or over-correction capabilities. Summary of the Invention

[0003] This invention provides a foldable three-channel movable rudder two-dimensional correction fuze. The rudder blades of this fuze are folded when leaving the muzzle, increasing projectile stability. The rudder deflection angle of the correction fuze is variable, and both the control rudder and the differential rudder can provide correction force in the lateral deflection direction of the range, increasing correction efficiency and effectively avoiding the drawback of insufficient use of correction capability when using fixed rudder components. At the same time, the increased correction efficiency enables ballistic correction independent of weather conditions, improving the robustness of ballistic correction. Furthermore, the structure is simple, compact, and reliable, providing a low-cost and miniaturized solution for precision guidance components in the field of two-dimensional ballistic correction.

[0004] To achieve the above objectives, the present invention provides the following technical solution:

[0005] A foldable three-channel movable rudder two-dimensional correction fuze, the fuze includes a fuze body, fuze seat, wind cap, proximity module, antenna module, navigation guidance and control module, thermal battery, detonation module, security module, penetrator and servo module;

[0006] The fuse body consists of a fixedly connected front section and a rear section; the wind cap is located at the very front of the fuse and is fixedly connected to the front end of the front section; the proximity module for detecting and identifying targets is fixedly installed inside the wind cap; the antenna module is fixedly installed in the antenna slot of the front section; a wiring port cover is fixedly connected to the outer periphery of the front section; the security module, the thermal battery, and the penetrator are sequentially installed in the rear section; a rotatable fuse seat is installed at the rear end of the rear section; the detonation transmission module is screwed into the fuse seat; the servo module and the navigation guidance control module are installed inside the front section of the fuse body.

[0007] The servo module is a four-axis, three-channel folding rudder servo motor, comprising an X-shaped rudder wing, a servo mechanism, a housing, and a torsion spring. The rudder wing is driven by the servo mechanism and consists of a pair of differential rudders and a pair of control rudders. The differential rudders are used to generate steering torque and provide correction force in the lateral deflection direction. The control rudders are used to provide correction force in the lateral deflection direction. The servo mechanism is used to receive control commands from the navigation, guidance, and control integrated machine and respond accordingly.

[0008] When the navigation guidance control module receives the rudder deployment signal, the rudder wing pops out from inside the front section of the fuse body under the action of the torsion spring.

[0009] Furthermore, it also includes a rotation-isolating device disposed between the fuze body and the fuze seat;

[0010] The rotation isolation device allows the fuse body and the fuse seat to rotate relative to each other, causing the antenna mounted on the fuse body to rotate relative to the ground, thereby obtaining information such as the attitude of the projectile and the rotation speed of the fuse body.

[0011] Furthermore, the anti-spin device consists of a bearing installed in the rear section of the fuze body and a wave spring installed between the bearing and the fuze seat, so that the fuze body separates from the fuze seat after being subjected to high overload, thereby realizing the ballistic correction function.

[0012] Furthermore, the wind cap is threadedly connected to the front section of the fuse body, and the shoulder inside the front section of the fuse body provides axial restraint to the housing, thereby preventing axial movement of the servo module.

[0013] Furthermore, both the navigation guidance control module and the front section of the fuze body are provided with pin holes;

[0014] The navigation guidance control module achieves circumferential positioning of the front section of the fuze body through a pin installed in the pin hole.

[0015] Furthermore, the navigation and guidance control module includes a servo controller and a navigation and guidance control integrated unit.

[0016] Furthermore, the outer peripheral surface of the housing is provided with receiving grooves corresponding to the rudder wings, and the rudder wings are folded into the receiving grooves before they extend out of the front section of the fuse body;

[0017] The front section of the fuse body is provided with slots that correspond one-to-one with the rudder wings, which are used to pop out the rudder wings.

[0018] Furthermore, the servo module also includes positioning cone sleeves that correspond one-to-one with each rudder wing; the positioning cone sleeves are used to achieve positioning after the corresponding rudder wing is deployed;

[0019] The torsion spring is installed on the positioning cone sleeve to provide the elastic force for the rudder to extend;

[0020] The rudder has a positioning groove on one side edge and is fixed in the receiving groove through the positioning groove.

[0021] Furthermore, the proximity module is fixed inside the wind cap by the threads of a bracket that is threadedly connected to the wind cap.

[0022] Furthermore, the servo mechanism includes a DC motor, a reducer, an angle sensor, and a servo control system;

[0023] The penetrator is threadedly connected to the rear section of the fuse and is located before the security module and the thermal battery, to protect the security module for reliable operation at the detonation point.

[0024] Compared with the prior art, the present invention has the following beneficial effects:

[0025] This invention relates to a three-channel movable rudder two-dimensional correction fuze employing a four-axis, three-channel folding rudder electric servo motor. The X-shaped rudder is driven by a servo mechanism and consists of a pair of differential rudders and a pair of control rudders. The differential rudders generate a guiding torque and simultaneously provide a correction force in the range lateral deflection direction. The control rudders provide a correction force in the range lateral deflection direction. The servo mechanism receives and responds to control commands from the navigation, guidance, and control integrated machine. The rudders of this fuze are folded during launch, increasing projectile stability. The control rudders have variable deflection angles, and the differential rudders can also provide a correction force in the range lateral deflection direction. The increased correction force in the deflection direction enhances correction efficiency, effectively avoiding the drawback of insufficient correction capability when using fixed rudder components. Simultaneously, the increased correction efficiency enables trajectory correction independent of weather conditions, improving the robustness of trajectory correction. The fuze body and fuze seat are fixed to the projectile body, rotating relative to each other. An inertial sensor can be installed inside the fuze body for more accurate trajectory measurement. Furthermore, the aforementioned fuze structure is simple, compact, and reliable, providing a low-cost, miniaturized solution for precision guidance components in the field of two-dimensional trajectory correction.

[0026] The three-channel movable rudder two-dimensional correction fuse of this invention can be widely used in the upgrade and modification of conventional mortars. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the structure of the foldable three-channel movable rudder two-dimensional correction fuze of the present invention;

[0028] Figure 2 This is a schematic diagram of the servo module.

[0029] Figure 3 This is a schematic diagram illustrating the working principle of the fuze of the present invention;

[0030] Figure 4 This is a schematic diagram of the rudder deployment structure.

[0031] Figure 5 This is a schematic diagram of the rudder folding structure.

[0032] Among them, 1-wind cap, 2-proximity module, 3-bracket, 4-front section of fuse body, 5-antenna module, 6-connection port cover, 7-navigation guidance control module, 8-bearing, 9-wave spring, 10-thermal battery, 11-rear section of fuse body, 12-fuze seat, 13-detonation transmission module, 14-security module, 15-penetrating body, 16-servo module, 17-rudder wing, 18-control rudder, 19-servo mechanism, 20-differential rudder, 21-positioning slot, 22-shell, 23-torsion spring, 24-positioning cone sleeve. Detailed Implementation

[0033] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0034] This invention provides a foldable three-channel movable rudder two-dimensional correction fuze for satellite attitude measurement, such as... Figure 1 As shown in the structure, the fuze includes a wind cap 1, a proximity module 2, a bracket 3, a front section of the fuze body 4, an antenna module 5, a wiring port cover 6, a navigation and guidance control module 7, a bearing 8, a wave spring 9, a thermal battery 10, a rear section of the fuze body 11, a fuze seat 12, a detonation transmission module 13, a security module 14, a penetrator 15, a servo module 16, a rudder wing 17, a control rudder 18, a servo mechanism 19, a differential rudder 20, a positioning slot 21, a housing 22, a torsion spring 23, and a positioning cone sleeve 24; wherein:

[0035] The wind cap 1 is located at the very front of the fuse and is fixedly connected to the front end of the fuse body front section 4; the proximity module 2 is fixed inside the wind cap 1 by the thread of the bracket 3; the fuse body front section 4 is one of the fuse bodies, and has a shoulder inside to fix the axial position of the servo module 16; the wind cap 1 and the fuse body front section 4 can be connected by threads to prevent the servo module 16 from moving axially; the rudder 17 is installed on the servo module 16 by pins; the antenna module 5 is installed in the antenna slot of the fuse body front section 4 by screws; the wiring port cover 6 is connected to the fuse body front section 4 by screws to facilitate the testing and maintenance of the internal control module; a wiring port is provided inside the wiring port cover 6 to facilitate wiring and circuit debugging; the navigation and guidance control module 7 includes control modules such as the servo controller and the navigation and guidance control integrated machine, which are installed inside the fuse body and are axially fixed by the shoulders of the fuse body front section 4 and rear section; the navigation and guidance control module 7 and the fuse body front section 4 are provided with pin holes to achieve circumferential fixation of the navigation and guidance control module 7;

[0036] The security module 14, thermal battery 10, and penetrator 15 are sequentially installed into the rear section 11 of the fuse body. The rear section 11 has an internal shoulder to prevent circumferential movement of the parts. The penetrator 15 is threaded to the rear section 11 and is secured to the thermal battery 10 from the side via a pin. The penetrator 15 is threaded to the rear section 11 and positioned before the security module 14 and thermal battery 10 to ensure reliable operation of the security module 14 at the detonation point. After assembling the internal parts of the front section 4 and rear section 11 of the fuse body, the front and rear sections are connected by screws. The bearing 8 is placed within the fuse body and... Between the fuze seat 12 and the front bearing 8, a wave spring 9 is installed to buffer vibration and resist high overload. The bearing 8 and the wave spring 9 form a rotation isolation device, allowing the fuze body and the fuze seat 12 to rotate relative to each other. This causes the antenna mounted on the fuze body to rotate relative to the ground, thereby acquiring information such as the projectile's attitude and the fuze body's rotation speed. It also allows the fuze body to separate from the fuze seat 12 after being subjected to high overload, realizing the ballistic correction function. The fuze body and the fuze seat 12 are fixed to the projectile body. With the relative rotation of the fuze body and the fuze seat 12, an inertial sensor can be installed inside the fuze body to achieve more accurate ballistic measurement. The detonation module 13 is screwed into the fuze seat 12 from the rear of the fuze. The overall structure is compact and has a high space utilization rate.

[0037] like Figure 2As shown in the structure, the servo module 16 is a four-axis, three-channel folding servo 17 electric servo, mainly composed of servo 17, servo mechanism 19 and housing 22. The servo 17 is driven by servo mechanism 19 and adopts an X-shaped layout, consisting of a pair of differential rudders 20 and a pair of control rudders 18. The differential rudders 20 generate steering torque and provide correction force in the lateral deflection direction of the range. The control rudders 18 provide correction force in the lateral deflection direction of the range. The servo mechanism 19 includes a reducer, DC motor, angle sensor and servo control system, which receives control commands from the navigation, guidance and control integrated machine and responds accordingly. The housing 22 is the outer shell of the servo module 16, providing positioning and support for the servo module 16. The outer peripheral surface of the housing 22 is provided with receiving grooves corresponding to the rudder wings 17, and the rudder wings 17 are folded into the receiving grooves before the fuse body front section 4 is ejected; the fuse body front section 4 is provided with slots corresponding to the rudder wings 17, for the rudder wings 17 to be ejected; the fuse body front section 4 may also be provided with rudder wing mounting holes, so that the rudder wings can be replaced in time during the experimental stage; the servo module 16 also includes positioning cone sleeves 24 corresponding to the rudder wings 17; the positioning cone sleeves 24 are used to achieve positioning after the corresponding rudder wings 17 are ejected; the torsion spring 23 is installed on the positioning cone sleeves 24 to provide the elastic force for the rudder wings 17 to be ejected; a positioning groove 21 is provided on one side edge of the rudder wing 17, and it is fixed in the receiving groove through the positioning groove.

[0038] like Figure 3 As shown, before launch, the data is set via the setting coil. During flight, the thermal battery 10 supplies power to the entire system. The rudder 17 is folded to maintain projectile stability when exiting the muzzle. When the static stability margin exceeds the threshold, a rudder extension signal is issued, and the rudder 17 is ejected to the positioning cone sleeve 24 under the action of the torsion spring 23. The differential rudder 20 deflects at a certain angle, causing the front section 4 and rear section of the fuze to be in a micro-rotation state. The antenna module 5 receives satellite signals and calculates the current position and velocity information of the projectile. The navigation, guidance and control module 7 receives the projectile position and velocity information and calculates and generates control commands. The servo module 16 controls the deflection of the control rudder 18 and the differential rudder 20 to generate equivalent control force and control torque, guiding the projectile to the vicinity of the target point. The proximity module 2 detects and identifies the target and issues a signal. The security system is deactivated and an initiation signal is issued. During the approach to the target, the penetrator 15 protects the security system from damage after the fuze is impacted, and the ammunition detonates successfully.

[0039] Figure 4 This is a schematic diagram of the structure when the rudder 17 is deployed. Figure 5 This is a schematic diagram of the structure of the rudder 17 when it is folded. The rudder blade is fixed inside the front section 4 of the fuse body through the positioning groove 21. When the navigation guidance control module 7 receives the rudder deployment signal, the rudder 17 is ejected to the positioning cone sleeve 24 under the action of the torsion spring 23.

[0040] The aforementioned three-channel movable rudder two-dimensional correction fuze employs a four-axis, three-channel folding rudder electric servo motor. The X-shaped rudder is driven by a servo mechanism and consists of a pair of differential rudders and a pair of control rudders. The differential rudders generate the steering torque and provide correction force in the range lateral deflection direction. The control rudders provide correction force in the range lateral deflection direction. The servo mechanism receives and responds to control commands from the navigation, guidance, and control integrated machine. The rudders of this fuze are folded during launch, increasing projectile stability. The control rudders have variable deflection angles, and the differential rudders can also provide correction force in the range lateral deflection direction. The increased correction force in the deflection direction enhances correction efficiency, effectively avoiding the drawback of insufficient correction capability when using fixed rudder components. Simultaneously, the increased correction efficiency enables trajectory correction independent of weather conditions, improving the robustness of trajectory correction. The fuze body and fuze seat are fixed to the projectile body, rotating relative to each other. An inertial sensor can be installed inside the fuze body for more accurate trajectory measurement. Furthermore, the aforementioned fuze structure is simple, compact, and reliable, providing a low-cost, miniaturized solution for precision guidance components in the field of two-dimensional trajectory correction.

[0041] Obviously, those skilled in the art can make various modifications and variations to the embodiments of the present invention without departing from the spirit and scope of the invention. Therefore, if these modifications and variations fall within the scope of the claims of the present invention and their equivalents, the present invention also intends to include these modifications and variations.

Claims

1. A foldable three-channel movable rudder two-dimensional correction fuze, characterized in that, It includes a fuse body, fuse holder, wind cap, proximity module, antenna module, navigation guidance and control module, thermal battery, detonation transmission module, security module, penetrator, and servo motor module; The fuse body consists of a fixedly connected front section and a rear section; the wind cap is located at the very front of the fuse and is fixedly connected to the front end of the front section; the proximity module for detecting and identifying targets is fixedly installed inside the wind cap; the antenna module is fixedly installed in the antenna slot of the front section; a wiring port cover is fixedly connected to the outer periphery of the front section; the security module, the thermal battery, and the penetrator are sequentially installed in the rear section; a rotatable fuse seat is installed at the rear end of the rear section; the detonation transmission module is screwed into the fuse seat; the servo module and the navigation guidance control module are installed inside the front section of the fuse body. The servo module is a four-axis, three-channel folding rudder electric servo, including an X-shaped rudder, a servo mechanism, a housing, and a torsion spring; the rudder is driven by the servo mechanism and consists of a pair of differential rudders and a pair of control rudders; the differential rudders are used to generate steering torque and provide correction force in the lateral deflection direction of the range. The control rudder is used to provide a corrective force in the lateral deflection direction of the firing range; The servo mechanism is used to receive control commands from the navigation, guidance and control integrated machine and respond accordingly. When the navigation guidance control module receives the rudder deployment signal, the rudder wing pops out from inside the front section of the fuse body under the action of the torsion spring; It also includes a rotation-isolating device disposed between the fuze body and the fuze seat; The rotation isolation device allows the fuse body and the fuse seat to rotate relative to each other; The anti-spin device consists of a bearing installed in the rear section of the fuze body and a wave spring installed between the bearing and the fuze seat, so that the fuze body separates from the fuze seat after being subjected to high overload, thereby realizing the ballistic correction function.

2. The fuse according to claim 1, characterized in that, The wind cap is threadedly connected to the front section of the fuse body, and the shoulder inside the front section of the fuse body provides axial restraint to the housing, thereby preventing axial movement of the servo module.

3. The fuze according to claim 1, characterized in that, Both the navigation guidance control module and the front section of the fuse body are provided with pin holes; The navigation guidance control module achieves circumferential positioning of the front section of the fuze body through a pin installed in the pin hole.

4. The fuse according to claim 1, characterized in that, The navigation and guidance control module includes a servo controller and an integrated navigation and guidance control unit.

5. The fuze according to claim 1, characterized in that, The outer peripheral surface of the housing is provided with receiving grooves corresponding to the rudder wings, and the rudder wings are folded into the receiving grooves before they extend out of the front section of the fuse body; The front section of the fuse body is provided with slots that correspond one-to-one with the rudder wings, which are used to pop out the rudder wings.

6. The fuze according to claim 5, characterized in that, The servo module also includes a positioning cone sleeve corresponding to each rudder wing; the positioning cone sleeve is used to achieve positioning after the corresponding rudder wing is deployed. The torsion spring is installed on the positioning cone sleeve to provide the elastic force for the rudder to extend; The rudder has a positioning groove on one side edge and is fixed in the receiving groove through the positioning groove.

7. The fuze according to claim 1, characterized in that, The proximity module is fixed inside the wind cap by a bracket that is threadedly connected to the wind cap.

8. The fuse according to any one of claims 1-7, characterized in that, The servo mechanism includes a DC motor, a reducer, an angle sensor, and a servo control system; The penetrator is threadedly connected to the rear section of the fuse and is located before the security module and the thermal battery, to protect the security module for reliable operation at the detonation point.

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