A layout structure of a lightweight bicycle-integrated short-range missile air defense system

Abstract

The present invention relates to a layout structure of a short-range missile air defense system integrated with a light bicycle, including a 4X4 light wheeled chassis, a weapon unit, a detection unit, a control unit, a power supply unit, and a missile tail flame protection device. The Y-shaped launch rack and the space conjugate drive structure of the heteromorphic quadrilateral mechanism are adopted to realize the miniaturization and light weight of the short-range missile air defense system structure, and achieve the system integration structure design on the 4X4 light chassis; through the high-rigidity composite structure of the missile pitch drive mechanism and the arc-shaped slide rail support assembly, the overall rigidity of the weapon unit in the vertical and lateral directions is ensured, and the heavy multi-vehicle separated structure of the existing short-range missile air defense system is optimized into a light bicycle integrated structure form. The entire system has a simple structure and a small volume, which is convenient for structural layout; the mechanism has high reliability and low cost, and the short-range missile air defense system can be used more conveniently when the conventional transportation capacity, financial resources, and personnel requirements are small.

Description

Technical Field

[0001] The invention belongs to the field of electronic machinery and relates to the structural design of a short-range missile air defense system, and in particular to a layout structure of a short-range missile air defense system integrated with a light single vehicle. Background Art

[0002] Based on the degree of air threat defense from large to small and the air defense range from far to near, missile air defense systems can generally be divided into terminal missile air defense systems, long-range missile air defense systems, medium-range missile air defense systems and short-range missile air defense systems.

[0003] As a typical representative of the existing short-range missile air defense system, China's HQ-6A can be regarded as a relatively advanced short-range missile weapon system. Taking HQ-6A as an example, the existing short-range missile air defense system usually adopts the form of missile launch vehicles and guidance radar vehicles, which requires a large number of chassis, resulting in the entire missile air defense system occupying a large space and requiring a large number of operators, bringing reliability technical difficulties and cost and other economic bottlenecks to the entire missile air defense system; moreover, most of the existing short-range missile air defense systems use large chassis such as 6X6 medium-sized trucks, and the single vehicle is large in size and heavy in weight, which has strict requirements on transportability and roadbed bearing capacity. The existing short-range missile air defense system has the characteristics of low structural integration, high personnel requirements, large size and heavy weight, making it difficult to quickly adapt to the new needs of modern government, military and other important personnel accompanying air defense. Summary of the invention

[0004] Technical issues to be solved

[0005] How to provide a light single-vehicle integrated short-range missile air defense system layout structure through the structural integration design of the mechanism in the system, so as to overcome the technical difficulties in system reliability and cost bottlenecks brought about by the existing short-range missile air defense weapon system, which occupies a large space, has a large single-vehicle volume and heavy weight, and is not conducive to the system structure layout.

[0006] Technical Solution

[0007] A layout structure of a short-range missile air defense system integrated with a light single vehicle adopts a single vehicle integrated overall structural design, and integrates a short-range missile air defense system with a single vehicle on a light 4X4 wheeled chassis, including a 4X4 light wheeled chassis, a weapon unit, a detection unit, a control unit, a power supply unit, and a missile tail flame protection device. Among them, the weapon unit and the detection unit are integrated on the turret, which is installed in the chassis axle near the rear axle area; the control unit is integrated on the instrument panel in front of the co-pilot seat of the chassis; the power supply unit is installed in the axle area close to the rear of the cockpit, and the missile tail flame protection device is installed on the top.

[0008] Further, the weapon unit includes a turret base, a turret turntable, a Y-shaped launcher, a missile pitch drive mechanism, an arc-shaped slide rail support assembly, a missile twin-mounted rack, a box-type short-range air defense missile combination (4 rounds, hereinafter referred to as the box missile combination), nitrogen pipes (2 pieces), a turret azimuth drive mechanism, and a missile firing control combination. The turret is the support platform for the entire weapon system; the box missile combination and nitrogen pipes are installed on both sides of the Y-shaped launcher through the missile twin-mounted rack; the bottom end of the Y-shaped launcher is fixed on the turret turntable and rotates around the axis, and the top end makes a pitching motion; the missile pitch drive mechanism realizes precise movement in the pitch dimension of the missile, and together with the arc-shaped slide rail support assembly, ensures the overall rigidity of the light weapon unit in the vertical and lateral directions; the azimuth drive mechanism and the missile firing control combination are installed inside the turntable.

[0009] Further, the Y-shaped launcher adopts a Y-shaped topological structure design. To enhance its overall rigidity, criss-crossing structural ribs are designed therein, and the interval of the structural ribs is not greater than 100 mm; the Y-shaped launcher is integrally cast from a high-strength and low-density aviation aluminum alloy lightweight metal material.

[0010] Further, the high-rigidity composite structure of the missile pitch drive mechanism and the arc-shaped slide rail support assembly ensures the rigidity of the weapon unit in the vertical and lateral directions.

[0011] Further, the detection unit includes an optoelectronic module and a search radar module. The optoelectronic module includes an optoelectronic detection mirror body, an optoelectronic pitch drive mechanism, and a mirror body locking combination; the optoelectronic module is installed on the left missile twin-mounted rack. The search radar module includes a radar front end, a radar azimuth drive mechanism, a special-shaped quadrilateral radar lifting support mechanism, and a lifting mechanism stabilizing strut combination; the search radar module is integrated in the rear half area of the turntable.

[0012] Further, for the special-shaped quadrilateral radar lifting support mechanism, the support rod structure is integrally forged from high-strength steel.

[0013] Further, when the vehicle is in the transportation state, the included angle between the support rod in the radar lifting support mechanism and the horizontal is 20°.

[0014] Further, the special-shaped quadrilateral structure of the radar support lifting mechanism and the Y-shaped launcher of the weapon unit are designed into a hierarchical space conjugate structure in terms of structure, and this structure is the key to the structural design for the entire system to achieve miniaturization and lightweight.

[0015] Further, in the missile twin-mounted rack, the horizontal distance between the box missile combinations is 220 mm to ensure the movement dimension of the rear support rod in the conjugate space of the special-shaped quadrilateral mechanism; the horizontal distance between the left missile twin-mounted rack and the right missile twin-mounted rack is 320 mm to ensure the movement dimension of the front support rod in the interval of the special-shaped quadrilateral mechanism;

[0016] Furthermore, the portable terminal in the control system is detachably installed on the terminal support frame in front of the co-pilot seat, and the terminal support frame is made of lightweight carbon fiber material.

[0017] Furthermore, the power system includes a power station and its starting battery; a missile tail flame protection device is installed on the top, which can effectively prevent the impact of the missile tail flame and the erosion of rainwater.

[0018] Beneficial effects

[0019] The layout structure of a short-range missile air defense system integrated with a light bicycle provided by the present invention, compared with the problems of large occupied space, large single-vehicle volume and weight, and low system reliability and high cost of the existing short-range missile air defense system, the present invention adopts a Y-shaped launch rack and a space conjugate drive structure with a hierarchical heterotrophic quadrilateral mechanism to realize the miniaturization and lightweight of the short-range missile air defense system structure, and achieve the system integration structure design on a 4X4 light chassis; through the high-rigidity composite structure of the missile pitch drive mechanism and the arc-shaped slide rail support assembly, the overall rigidity of the weapon unit in the vertical and lateral directions is ensured, and the heavy multi-vehicle separated structure of the existing short-range missile air defense system is optimized into a light single-vehicle integrated structure form. The whole system has a simple structure and a small volume, which is convenient for structural layout; the mechanism has high reliability and low cost, and the short-range missile air defense system can be used more conveniently when the conventional transportation force, financial resources, and personnel requirements are small, and the equipment has strong market competitiveness. Brief description of the drawings

[0020] The drawings are only for the purpose of showing specific embodiments, and are not considered to be a limitation of the present invention. Throughout the drawings, the same reference signs represent the same components.

[0021] Figure 1 It is a schematic diagram of the whole vehicle composition of the present invention;

[0022] Figure 2 It is a schematic diagram of the turret composition of the present invention;

[0023] Figure 3 It is a schematic diagram of the control terminal of the present invention;

[0024] Figure 4 It is a schematic diagram of the whole vehicle in the transportation state;

[0025] Figure 5 It is a schematic diagram of the whole vehicle in the working state.

[0026] 1 - Chassis, power station 2, 3 - Turret turntable, 4 - Mirror body locking combination, 5 - Optoelectronic detection mirror body, 6 - Optoelectronic pitch drive mechanism, 7 - Missile left combined mounting rack, 8 - Rear support rod, 9 - Radar front end, 10 - Radar azimuth drive mechanism, 11 - Front support rod, 12 - Shortwave communication antenna, 13 - Missile right combined mounting rack, 14 - Nitrogen pipe, 15 - Box and missile combination, 16 - Shortwave antenna support, 17 - Y-shaped launch rack, 18 - Launch rack shaft, 19 - Missile pitch drive mechanism, 20 - Pitch stability component support seat, 21 - Pitch stability component support rod, 22 - Pitch stability component slide rail, 23 - Turret azimuth drive mechanism, 24 - Turret base, 25 - Pitch stability component pulley, 26 - Radar lifting mechanism stable support column combination, 27 - Radar lifting mechanism positioning combination, 28 - Radar lifting drive mechanism, 29 - Terminal support frame, 30 - Portable terminal, 31 - Missile tail flame protection device. Detailed implementation mode

[0027] In order to make the objectives, technical solutions and advantages of the present invention clearer and more understandable, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0028] This embodiment provides a layout structure of a light single-vehicle integrated short-range missile air defense system, and the technical composition is as Figure 1 、 Figure 2 and Figure 3 shown, including a 4X4 light wheeled chassis 1 (hereinafter referred to as chassis 1), power station 2, turret turntable 3, mirror body locking combination 4, optoelectronic detection mirror body 5, optoelectronic pitch drive mechanism 6, missile left combined mounting rack 7, rear support rod 8 (2 pieces), radar front end 9, radar azimuth drive mechanism 10, front support rod 11, shortwave communication antenna 12, missile right combined mounting rack 13, nitrogen pipe 14, box and missile combination 15 (4 pieces), shortwave antenna support 16, Y-shaped launch rack 17, launch rack shaft 18, missile pitch drive mechanism 19, pitch stability component support seat 20, pitch stability component support rod 21, pitch stability component slide rail 22, turret azimuth drive mechanism 23, turret base 24, pitch stability component pulley 25, radar lifting mechanism stable support column combination 26, radar lifting mechanism positioning combination 27, radar lifting drive mechanism 28, terminal support frame 29, portable terminal 30 and missile tail flame protection device 31.

[0029] Figure 4 、 Figure 5 are respectively the schematic diagram of the transportation state and the working state of the system.

[0030] The connection relationships of each part are as follows: The chassis 1 is the foundation of the whole system, on which a turret (including a weapon unit and a detection unit), a control unit, a power supply unit, and a tail flame protection device are respectively installed. As Figure 1 , Figure 2 and Figure 3 shown: In the weapon unit, the turret is fixedly connected to the chassis 1 through the turret base 24; the turret turntable 3 is connected to the turret base 24 through the azimuth bearing in the turret azimuth drive mechanism 23. Driven by the turret azimuth drive mechanism 23, the turret turntable 3 can rotate 360° in azimuth relative to the turret base 24; the rear end of the Y-shaped launch rack 17 is connected to the upper support of the turret turntable 3 through a positioning shaft, and the front part is connected to the end of the missile pitch drive mechanism 19; the bottom of the missile pitch drive mechanism 19 is connected to the support of the turret turntable 3; the Y-shaped launch rack 17, driven by the missile pitch drive mechanism 19, realizes the pitch movement of it and the above components; the missile left multi-pack hanging rack 7 and the missile right multi-pack hanging rack 13 are respectively hung on both sides of the Y-shaped launch rack 17, and the box missile combination 15 is connected through the slide rails on the missile multi-pack hanging racks (7 and 13); the nitrogen pipe 14 is fixedly connected to the missile multi-pack hanging rack; the pitch stability component support 20 is fixedly connected to the turret turntable 3, the pitch stability component slide rail 22 is positioned and installed outside the pitch stability component support 20, the pitch stability component support rod 21 is positioned and installed on both sides of the launch rack 17, and the pitch stability component pulley 25 is installed in the pitch stability component support rod 21 through a fixed shaft and fits the pitch stability component slide rail 22. The whole stability component (20, 21, 22, and 25) can improve the vertical and horizontal overall structural rigidity of the weapon unit when the Y-shaped launch rack 17 makes a pitch movement; the missile firing control combination adopts a standard ATR chassis structure and is installed inside the turret turntable 3. In the detection unit, the optoelectronic module is installed outside the missile left multi-pack hanging rack 7; the base of the optoelectronic pitch drive mechanism 6 is fixedly connected to the missile left multi-pack hanging rack 7, the optoelectronic detection mirror body 5 is connected to the upper adapter plate of the optoelectronic pitch drive mechanism 6, and the mirror body locking combination 4 is connected to the rear of the optoelectronic detection mirror body 5.

[0031] Working process:

[0032] First, complete the setup of the entire system from the transportation state to the working state, which are, in sequence, powering on the portable terminal 30, powering the power station 2, setting up the radar module and the optoelectronic module, and setting up the weapon unit. Powering on the portable terminal 30 and powering the power station 2 can be carried out simultaneously. The setup of the radar module and the optoelectronic module can be carried out simultaneously: When setting up the radar module, the radar lifting drive mechanism 28 drives the front support rod 11 into the vertical working direction, thereby driving the radar azimuth drive mechanism 10 and the rear support rod 8 to the working positions. With the help of the non-isosceles parallelogram mechanism, the radar front end 9 is pushed to the working position, the working lock in the radar lifting mechanism stabilizer combination 26 is locked, and the azimuth lock in the radar azimuth drive mechanism 10 is unlocked; thus, the setup of the radar module is completed. When setting up the optoelectronic module, unlock the lens body locking combination 4, and the optoelectronic detection lens body 5 can perform precise pitching motion independently; the setup of the optoelectronic module is completed. When setting up the weapon unit, the missile pitching drive mechanism 19 drives the launch rack 17 and its components and combinations thereon to the initial working position, and unlocks the azimuth lock in the radar azimuth drive mechanism 10; the setup of the weapon unit is completed. The rapid setup of the entire system is completed.

[0033] Secondly, each subsystem and unit in the system work in coordination. In the azimuth dimension: The turret azimuth drive mechanism 23 drives the weapon system, the radar module, and the optoelectronic module to move rapidly in the azimuth dimension; the radar module can, under the drive of the radar azimuth drive mechanism 10, perform precise independent movement in the azimuth dimension in superposition. In the pitching dimension: The missile pitching drive mechanism 19 drives the weapon unit and the optoelectronic module to perform precise movement in the pitching dimension; the optoelectronic module can, under the drive of the optoelectronic pitching drive mechanism 6, perform precise movement independently in superposition; the radar pitching dimension is in a fixed-angle mode, and the phased array mode is adopted to achieve autonomous target seeking in the pitching dimension. The movements in the azimuth and pitching dimensions can be carried out independently of each other without interference, realizing the precise spatial orientation and pointing of the entire system.

[0034] Finally, complete the retraction of the entire system. First, retract the weapon unit: The turret azimuth drive mechanism 23 drives the weapon unit to retract to the zero position in the azimuth dimension, lock the azimuth lock in the mechanism, and the missile pitching drive mechanism 19 drives the weapon unit to reach the zero position in the pitching dimension. The optoelectronic module and the radar module are retracted simultaneously: The optoelectronic pitching drive mechanism 6 drives the optoelectronic detection lens body 5 to the zero position, and the lens body locking combination 4 is locked; the radar front end 9 reaches the zero position under the drive of the radar azimuth drive mechanism 10, the azimuth lock is locked, the working lock in the radar lifting mechanism stabilizer combination 26 is released, and the radar lifting drive mechanism 28 drives the radar lifting mechanism to drive the radar front end 9 to the transportation position. Powering off the power station 2 and powering off the portable terminal 30 are carried out simultaneously. Thus, the rapid retraction of the entire system from the working state to the transportation state is completed.

[0035] As described above, it is only the specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention can easily think of various equivalent modifications or substitutions, and these modifications or substitutions should all be covered within the protection scope of the present invention.

Claims

1. A layout structure of a lightweight vehicle-integrated short-range missile air defense system, which adopts an overall structure design of vehicle integration, and integrates a short-range missile air defense system on a lightweight 4X4 wheeled chassis. It is characterized in that It includes a 4X4 light wheeled chassis, a weapon unit, a detection unit, a control unit, a power supply unit and a missile tail flame protection device; wherein the weapon unit and the detection unit are integrated on the turret, and the turret is installed in the area of ​​the chassis axle close to the rear axle; the control unit is integrated on the instrument panel in front of the co-pilot seat of the chassis; the power supply unit is installed in the area of ​​the axle close to the rear of the cockpit, and the missile tail flame protection device is installed on the top; the weapon unit includes a turret base, a turret turntable, a Y-shaped launcher, a missile pitch drive mechanism and an arc-shaped slide rail support assembly, a missile joint mounting bracket, a box-type short-range air defense missile combination, a nitrogen pipe, a turret azimuth drive mechanism and a missile launch control combination; the turret is the support platform of the entire weapon system; the box-type short-range air defense missile combination , nitrogen pipes are installed on the left and right sides of the Y-shaped launcher through missile mounting brackets; the bottom end of the Y-shaped launcher is fixed on the turret turntable and rotates around the axis, and the top end performs pitch movement; the missile pitch drive mechanism realizes precise pitch movement of the missile, and cooperates with the arc-shaped slide rail support assembly to ensure the overall vertical and lateral rigidity of the light weapon unit; the azimuth drive mechanism and the missile launch control assembly are installed inside the turntable; the Y-shaped launcher adopts a Y-shaped topological structure design; in order to enhance its overall rigidity, criss-cross structural ribs are designed, and the spacing between the structural ribs is not more than 100mm; the Y-shaped launcher is made of high-strength and low-density aviation aluminum alloy lightweight metal material cast in one piece; the detection unit includes an optoelectronic module and a search radar module, the optical The electrical module includes an optoelectronic detection mirror, an optoelectronic pitch drive mechanism and a mirror locking combination; the optoelectronic module is installed on the left mounting bracket of the missile; the search radar module includes a radar front end, a radar azimuth drive mechanism, an anisotropic quadrilateral radar lifting support mechanism and a lifting mechanism stabilizing support column combination; the search radar module is integrated in the rear half of the turntable; the anisotropic quadrilateral radar lifting support mechanism adopts an anisotropic parallelogram structure, and the support rod is forged from high-strength steel in one piece; the support rod in the anisotropic quadrilateral radar lifting support mechanism is at an angle of 20° to the horizontal when the whole vehicle is transported; the anisotropic quadrilateral structure of the anisotropic quadrilateral radar lifting support mechanism and the Y-shaped launcher of the weapon unit are structurally designed to form a hierarchical space The conjugate structure is the key to the structural design of the entire system structure to achieve miniaturization and lightweight; in the missile mounting bracket, the horizontal distance between the box-missile combination is 220mm to ensure the movement size of the rear support rod in the heterosexual quadrilateral mechanism in the conjugate space; the horizontal distance between the left missile mounting bracket and the right missile mounting bracket is 320mm to ensure the movement size of the front support rod in the heterosexual quadrilateral mechanism in the interval; the portable terminal in the control unit is detachably installed on the terminal support frame in front of the co-pilot seat, and the terminal support frame is made of lightweight carbon fiber material; the power supply unit includes a power station and its starting battery; a missile tail flame protection device is installed on the top to effectively prevent the impact of the missile tail flame and rain erosion.

2. A working method of the layout structure of the short-range missile air defense system integrated with a light bicycle as described in claim 1, characterized in that, include: First, complete the setup of the entire system from the transportation state to the working state, which is carried out in sequence as follows: power on the portable terminal, supply power from the power station, set up the radar module and the optoelectronic module, and set up the weapon unit; powering on the portable terminal and supplying power from the power station can be carried out simultaneously; setting up the radar module and the optoelectronic module can be carried out simultaneously: when setting up the radar module, the radar lifting drive mechanism drives the front support rod into the vertical working direction, thereby driving the radar azimuth drive mechanism and the rear support rod to the working position, and using the anisotropic parallelogram mechanism to push the front end of the radar to the working position, lock the working lock in the stable strut combination of the radar lifting mechanism, and unlock the azimuth lock in the radar azimuth drive mechanism; At this point, the setup of the radar module is completed; When setting up the optoelectronic module, unlock the mirror body locking combination, and the optoelectronic detection mirror body can perform precise pitching motion independently; Complete the setup of the optoelectronic module; when setting up the weapon unit, the missile pitching drive mechanism drives the launch rack and its components and combinations to the initial working position, and unlocks the azimuth lock in the radar azimuth drive mechanism; complete the setup of the weapon unit; the rapid setup of the entire system is completed; Secondly, each subsystem and unit in the system work together; in the azimuth dimension: the turret azimuth drive mechanism drives the weapon system, the radar module, and the optoelectronic module to move rapidly in the azimuth dimension; The radar module can perform precise independent motion in the azimuth dimension under the drive of the radar azimuth drive mechanism; in the pitching dimension: the missile pitching drive mechanism drives the weapon unit and the optoelectronic module to perform precise motion in the pitching dimension; The optoelectronic module can perform precise independent motion under the drive of the optoelectronic pitching drive mechanism; The radar pitching dimension is in a fixed-angle mode, and the phased array mode is used to achieve autonomous homing in the pitching dimension; the motions in the azimuth and pitching dimensions can be carried out independently of each other without interference, realizing the spatial precise orientation and pointing of the entire system; Finally, complete the retraction of the entire system; first, retract the weapon unit: the turret azimuth drive mechanism drives the weapon unit to retract to the zero position in the azimuth dimension, lock the azimuth lock in the mechanism, and the missile pitching drive mechanism drives the weapon unit to reach the zero position in the pitching dimension; the optoelectronic module and the radar module are retracted simultaneously: the optoelectronic pitching drive mechanism drives the optoelectronic detection mirror body to the zero position, and the mirror body locking combination is locked; The front end of the radar reaches the zero position under the drive of the radar azimuth drive mechanism, the azimuth lock is locked, the working lock in the stable strut combination of the radar lifting mechanism is released, and the radar lifting drive mechanism drives the radar lifting mechanism to drive the front end of the radar to the transportation position; power off the power station and shut down the portable terminal simultaneously; at this point, the rapid retraction of the entire system from the working state to the transportation state is completed.

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