Self-adaptive multi-mode intelligent cold launching tactical system

Abstract

The utility model relates to the technical field of aircraft launching, in particular to a self-adaptive multi-mode intelligent cold launching tactical system which comprises a vehicle body and multiple sets of launching cabins, the multiple sets of launching cabins are arranged on the top of the vehicle body side by side, and unmanned aerial vehicle bodies are arranged in the middles of the multiple sets of launching cabins. An ejection frame for supporting the unmanned aerial vehicle body is arranged in the launching cabin, and two sets of push cylinders for ejecting the unmanned aerial vehicle body upwards are transversely and symmetrically arranged in the middle of the ejection frame. Compared with a traditional heat emission system, the system does not need to consume initiating explosive devices, so that the long-term use cost and the daily maintenance cost are remarkably reduced; according to the design, a pulley rope structure is adopted, the large-stroke launching requirement is met in a small space, adaptation can be correspondingly carried out according to different launching requirements, the initial speed launching requirement of 0-100 m / s is met, and therefore the efficient launching performance is achieved in the limited space.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of the navigation vehicle launching technology field, concretely relates to a self -adaptation multimode intelligent cold launching tactical system. BACKGROUND

[0002] Traditional military unmanned plane launching mode is divided into small unmanned plane hand throws and takes off and large unmanned plane slide run and takes off, and the unmanned plane of hand throw launching is usually small or micro unmanned plane. Because the strength of manpower throws is limited, it is difficult to successfully launch the large and heavy unmanned plane, which limits the load capacity and endurance capacity of the unmanned plane. The slide run and take off needs the runway with the proper length and mass, and the runway length is determined according to the type and take-off weight of the unmanned plane, and generally, the unmanned plane above the medium type needs the longer runway, and the length can be several hundred meters to one thousand meters, and is easily affected by the environment weather. With the increasing demand of modern war on unmanned plane system, the traditional launching mode cannot meet the demand of rapid deployment and mobile operation. Therefore, the utility model aims at providing a novel navigation vehicle launching technology to solve the problems in the prior art. SUMMARY

[0003] The utility model aims at providing a self -adaptation multimode intelligent cold launching tactical system to solve the above -mentioned problems, realizes the cold launching of the aircraft through the preparation and transmission of high pressure gas, has the characteristics of rapid deployment, low use cost and high mobility, and details are described below.

[0004] To achieve the above object, the utility model provides the following technical scheme:

[0005] The utility model provides a self -adaptation multimode intelligent cold launching tactical system, including the car body and multiple sets of launching cabin, multiple sets of the launching cabin are arranged in parallel on the top of the car body, and the middle part of multiple sets of launching cabin is provided with unmanned plane body, the inside of the launching cabin is provided with the ejection frame of supporting unmanned plane body, the middle part of the ejection frame is provided with two groups of push cylinder that ejects unmanned plane body upwards in the horizontal symmetry, and the outside of the car body is provided with the energy storage system that supplies the launching air pressure to the push cylinder,

[0006] The bottom of the ejection frame is vertically slidably provided with the push clamping plate that supports the unmanned plane body, and the outside of two groups of push cylinder is provided with the ejection cable that supports the upward movement of the push clamping plate, and the inside top of the ejection frame is provided with the deceleration cable on the front and back sides, and the two ends of the deceleration cable are connected with the deceleration device fixed to the inside of the ejection frame.

[0007] The adaptive multi-modal intelligent cold launch tactical system is used for preparing high-pressure gas by using a designed gas compressor and an energy storage system, a working pressure range is 0.1MPa-100MPa, high-pressure compressed gas is delivered to the energy storage system through a pipe by a cylinder-piston combination structure. Before launching, the high-pressure gas source is rapidly transmitted to the cylinder-piston of the launching device through the pipeline, the movable pulley is pushed up by the launching steel cable, the launching steel cable is pulled up by the movable pulley and the impact pulley, the push clamp plate is rapidly moved up, the pressure energy is converted into mechanical energy, the push clamp plate pushes the UAV body to move up, the launched aircraft is ejected from the cabin, the deceleration hook on the push clamp plate hooks the deceleration rope, the movable plate is pulled up by the deceleration rope to compress the spring to realize the first deceleration, when the deceleration hook continues to move up to the impact pulley position, the deceleration hook contacts the impact pulley to realize the second deceleration, and then the push clamp plate is slowed down and falls back to reset under the spring support.

[0008] As preferred, the top of the launching cabin is provided with two sets of split covers, the inside of the launching frame is provided with rotating seats for supporting rotation of the impact pulleys, and the bottom of the launching frame is provided with the fixed pulleys.

[0009] As preferred, the telescopic end of the push cylinder is provided with a pulley frame, the inside of the pulley frame is provided with a movable pulley, one end of the launching steel cable is fixed to the launching frame, the other end of the launching steel cable extends downward along the movable pulley to the fixed pulley, the launching steel cable extends upward to bypass the impact pulley and is connected downward to the push clamp plate.

[0010] As preferred, the push clamp plate includes a base and a guide block vertically sliding with the launching frame, the top of the base is provided with two sets of clamping mechanisms horizontally symmetrically arranged and supporting the UAV body, and the front and rear sides of the base are provided with two sets of deceleration hooks with upward openings corresponding to the deceleration ropes.

[0011] As preferred, the inside of the launching frame between the two sets of deceleration devices is provided with a guide pulley and a limiting pulley, and the deceleration rope extends along the top side of the guide pulley to the bottom side of the limiting pulley.

[0012] As preferred, the deceleration device includes a fixed plate fixed to the inside of the launching frame, the bottom side of the fixed plate is provided with a sleeve vertically telescopic, and the bottom end of the sleeve is fixed with a movable plate.

[0013] As preferred, the outside of the sleeve is provided with a spring, the two ends of the spring are respectively abutted against the fixed plate and the movable plate, and the end of the deceleration rope penetrates through the fixed plate and is fixed to the top side of the movable plate downward.

[0014] As preferred, the top side of the vehicle body is provided with a folding arm crane, which is a two-joint folding three-stage telescopic mechanism.

[0015] The beneficial effects are: 1. The utility model converts gas pressure energy into mechanical kinetic energy to realize launching operation. The launching energy mainly comes from the atmosphere, compared with the traditional thermal launching system, the system does not need to consume the initiating explosive, therefore the long-term use cost and daily maintenance cost are significantly reduced;

[0016] 2. The design adopts a pulley rope structure to realize the launching requirement of large stroke in a small space, can be adapted according to different launching requirements, meets the initial speed launching requirement of 0 to 100 m / s, so that the efficient launching performance is realized in the limited space;

[0017] 3. In order to meet the multi-scene and multi-carrier use requirement of the ejection system part, the patent designs a self-adaptive multi-modal intelligent cold launching tactical system, which can make relevant adaptive structure according to the requirements of different carriers at the installation interface end, has compatibility and universality, can replace the vehicle body with the corresponding carrier, and meets the use of equipment on different types of carriers such as large ships, aircrafts and ground special vehicles;

[0018] 4. The push-clamping plate clamping carrier is more flexible in selection, can adaptively replace the unmanned aerial vehicle body according to the requirements, can meet the clamping ability of fixed-wing unmanned aerial vehicles, variable unmanned aerial vehicles, compound-wing unmanned aerial vehicles and small and medium-sized cannon shells, so that the application scenarios of the design are more abundant. BRIEF DESCRIPTION OF DRAWINGS

[0019] In order to more clearly illustrate the technical scheme in the embodiments of the utility model or the prior art, the following will briefly introduce the drawings needed to be used in the embodiment or the prior art description, obviously, the drawings in the following description are only some embodiments of the utility model, and for those skilled in the art, other drawings can also be obtained according to these drawings without creating labor.

[0020] Figure 1 It is the front view structure diagram of the utility model;

[0021] Figure 2 It is the three-dimensional structure schematic diagram of the utility model;

[0022] Figure 3 It is the structure split schematic diagram of the launching cabin of the utility model;

[0023] Figure 4 It is the local structure right view of the utility model;

[0024] Figure 5 It is the local structure three-dimensional schematic diagram of the utility model;

[0025] Figure 6 is a local structure split schematic view of the utility model;

[0026] Figure 7 is a three-dimensional structure schematic view of the utility model push clamp plate;

[0027] Figure 8 is a three-dimensional structure schematic view of the utility model ejection frame.

[0028] The figure mark is explained as follows:

[0029] 1, vehicle body;2, launch cabin;201, cabin cover;3, energy storage system;4, folding arm crane;5, unmanned aerial vehicle body;6, ejection frame;601, rotating seat;602, impact pulley;603, guide pulley;604, limit pulley;605, fixed pulley;7, push cylinder;701, telescopic end;702, movable pulley;8, pulley frame;9, push clamp plate;901, base;902, guide block;903, clamping mechanism;904, deceleration hook;10, ejection cable;11, deceleration device;11a, fixed plate;11b, spring;11c, sleeve;11d, movable plate;12, deceleration cable. Specific implementation

[0030] To make the purpose, technical scheme and advantages of the utility model more clear, the technical scheme of the utility model will be described in detail below. Obviously, the described embodiment is only a part of the embodiment of the utility model, not all the embodiment. Based on the embodiment in the utility model, all other implementation manners obtained by the ordinary skill in the art without making creative labor belong to the scope of the utility model.

[0031] Referring to Figures 1-8 As shown in the utility model provides a kind of self-adapting multimodal intelligent cold launch tactical system, including vehicle body 1 and multiple launch cabins 2, multiple launch cabins 2 are arranged in parallel in vehicle body 1 top, and unmanned aerial vehicle body 5 is provided in the middle of multiple launch cabins 2, and ejection frame 6 for supporting unmanned aerial vehicle body 5 is provided in the inside of launch cabin 2, two groups of push cylinder 7 for upwardly ejecting unmanned aerial vehicle body 5 are provided in the middle of ejection frame 6 transversely, and energy storage system 3 for supplying launch air pressure to push cylinder 7 is provided on the outside of vehicle body 1, by high-pressure gas preparation and transmission, the cold launch to aircraft is realized, with the characteristics of rapid deployment, low use cost and high mobility, in addition, launch cabin 2 uses modular installation, can launch not less than 6 unmanned aerial vehicles, and can be independently loaded and unloaded, and the function and performance of the rest system module are not affected;

[0032] The pusher plate 9 supporting the UAV body 5 is vertically slidably arranged at the bottom of the ejection frame 6, and the ejection cables 10 supporting the upward movement of the pusher plate 9 are arranged outside the two groups of push cylinders 7, and the deceleration cables 12 are arranged at the top of the ejection frame 6, the two ends of the deceleration cables 12 are connected with the deceleration devices 11 fixed to the inner side of the ejection frame 6, before the ejection process starts, the air compressor pressurizes the high-pressure air into the gas cylinder to store energy, and the UAV is installed and fixed in the ejection frame 6 in the launch cabin 2, when the ejection starts, the high-pressure gas in the gas cylinder enters the push cylinder 7 through the pipeline of the energy storage system 3, the high-pressure gas pushes the piston in the push cylinder 7 to move at high speed, the piston pushes the pulley 702 supporting the ejection cable 10 to drive the pusher plate 9 to make the UAV body 5 pop up to complete the launch.

[0033] As an optional embodiment, the launch cabin 2 is provided with two groups of split cabin covers 201 at the top, the impact pulleys 602 are arranged at the top of the ejection frame 6, the rotating seats 601 supporting the rotation of the impact pulleys 602 are arranged at the inner side of the ejection frame 6, and the fixed pulleys 605 are arranged at the bottom of the ejection frame 6.

[0034] The telescopic end 701 above the push cylinder 7 is provided with a pulley frame 8, the inner side of the pulley frame 8 is provided with a movable pulley 702, one end of the ejection cable 10 is fixed to the ejection frame 6, the other end of the ejection cable 10 extends downward along the movable pulley 702 to the fixed pulley 605, the ejection cable 10 extends upward to bypass the impact pulley 602 and is connected downward to the pusher plate 9; the pusher plate 9 includes a base 901 and a guide block 902 vertically slidingly matched with the ejection frame 6, the top of the base 901 is provided with two groups of clamping mechanisms 903 symmetrically arranged transversely and supporting the UAV body 5, and the base 901 is provided with two groups of deceleration hooks 904 with openings upward corresponding to the deceleration cables 12;

[0035] Specifically, the clamping mechanism 903 is shaped to fit the stress area of the aircraft and transmit the thrust to the aircraft, and is made of 7075 aluminum; the guide block 902 is used to fix the stress direction of the aircraft during the ejection process to always be in the ejection direction, and has a diameter of 16 mm and is made of 7075 aluminum; the pusher plate 9 is connected with the cable through a linear sliding bearing.

[0036] The inner side of the ejection frame 6 between the two groups of deceleration devices 11 is provided with a guide pulley 603 and a limiting pulley 604, the deceleration cable 12 extends along the top side of the guide pulley 603 to the bottom side of the limiting pulley 604, the deceleration device 11 includes a fixed plate 11a fixed to the inner side of the ejection frame 6, the bottom side of the fixed plate 11a is provided with a sleeve 11c vertically extendable, and the bottom end of the sleeve 11c is fixed with a movable plate 11d;

[0037] The sleeve 11c is sleeved with a spring 11b outside, the two ends of the spring 11b are respectively abutted against the fixed plate 11a and the movable plate 11d, the end of the deceleration steel cable 12 penetrates through the fixed plate 11a and is fixed to the top side of the movable plate 11d, specifically, the bottom end of the deceleration steel cable 12 penetrates through the fixed plate 11a and is knotted, so as to ensure that the deceleration steel cable 12 can pull the fixed plate 11a upward, and the top side of the vehicle body 1 is provided with a folding arm crane 4, which is a two-joint folding three-stage telescopic mechanism.

[0038] Before deceleration, the steel wire rope is horizontally stretched at the end of acceleration, when the deceleration hook 904 of the push clamp plate 9 hooks the deceleration steel cable 12, the spring 11b is compressed by the deceleration steel cable 12 to achieve primary deceleration.

[0039] After the first deceleration stroke, the push clamp plate 9 still continues to move upward, at this time, the push clamp plate 9 will hit the end impact pulley 602 at the end of deceleration, forming secondary deceleration, so as to realize the deceleration function, and then the push clamp plate 9 is pushed downward by the spring 11b to complete the retraction.

[0040] By adopting the above structure, the gas compressor designed in cooperation with the energy storage system 3 is used to prepare high-pressure gas, the working pressure range is 0.1MPa-100MPa, and the high-pressure compressed gas is delivered to the energy storage system 3 through the pipe by the cylinder piston combination structure. Before launching, the high-pressure gas source is rapidly transmitted to the cylinder piston of the push cylinder 7 of the launching device through the pipeline, the support movable pulley 702 is pulled upward by the launching steel cable 10, the push clamp plate 9 is pulled upward by the launching steel cable 10 around the fixed pulley 605 and the impact pulley 602, the pressure energy is converted into mechanical energy, the push clamp plate 9 pushes the unmanned aerial vehicle body 5 to move upward, after the launched aircraft is ejected from the cabin, the deceleration hook 904 on the push clamp plate 9 hooks the deceleration rope, the movable plate 11d is pulled upward to compress the spring 11b to achieve primary deceleration, when the deceleration hook 904 continues to move upward to the position of the impact pulley 602, the deceleration hook 904 contacts the impact pulley 602 to achieve secondary blocking deceleration, and then the push clamp plate 9 is slowed down and falls back to the original position under the support of the spring 11b;

[0041] The gas pressure energy is converted into mechanical kinetic energy to realize the launching operation. The launching energy mainly comes from the atmosphere, compared with the traditional thermal launching system, the system does not need to consume the initiating explosive, so the long-term use cost and daily maintenance cost are significantly reduced.

[0042] In the design, the air compressor providing pneumatic energy for the launching system adopts a piston structure or a rotary structure, and its performance characteristics can reach a working pressure of not less than 35 megapascals and a flow rate of not less than 500 liters per minute.

[0043] The pulley rope structure is adopted in the design, a large stroke launching demand is realized in a small space, different launching demands can be adapted, the initial speed launching requirement of 0 to 100 m / s is met, and therefore efficient launching performance is realized in limited space.

[0044] In the launching system part in the design, the component named "pushing clamp plate" is considered in the design, the mechanical properties are considered, the three-dimensional space occupied by the shape profile has a margin, the pushing clamp plate can be modified on demand in the three-dimensional space size, the clamping of the pushing clamp plate after modification is more flexible, the clamping ability of fixed-wing unmanned aerial vehicles, variable unmanned aerial vehicles, compound-wing unmanned aerial vehicles, small and medium-sized cannon shells and other multi-form carriers can be met, and therefore the application scenarios of the design are more abundant.

[0045] The above is only a specific implementation manner of the utility model, but the protection scope of the utility model is not limited to this, any person skilled in the art can easily think of changes or replacements within the technical range disclosed by the utility model, which should be covered in the protection scope of the utility model. Therefore, the protection scope of the utility model should be subject to the protection scope of the claims.

Claims

1. An adaptive multimodal intelligent cold-launch tactical system, characterized in that: The vehicle includes a vehicle body (1) and multiple launch bays (2). The multiple launch bays (2) are arranged side by side on the top of the vehicle body (1), and each launch bay (2) has a drone body (5) in the middle. The launch bay (2) has a catapult frame (6) that supports the drone body (5) inside. The catapult frame (6) has two sets of push cylinders (7) that eject the drone body (5) upwards in the middle. The vehicle body (1) has an energy storage system (3) that supplies launch air pressure to the push cylinders (7) on the outside. The bottom of the ejection frame (6) is vertically slidably provided with a push clamp plate (9) to support the UAV body (5). The outer sides of the two sets of push cylinders (7) are provided with ejection steel cables (10) to support the upward movement of the push clamp plate (9). The front and rear sides of the top of the ejection frame (6) are provided with deceleration steel cables (12). Both ends of the deceleration steel cables (12) are connected to deceleration devices (11) fixed to the inner side of the ejection frame (6).

2. The adaptive multimodal intelligent cold-launch tactical system according to claim 1, characterized in that: The launch chamber (2) is provided with two sets of split hatches (201) on the top. The ejection frame (6) is provided with impact pulleys (602) on the front and rear sides of the top. The ejection frame (6) is provided with a rotating seat (601) to support the rotation of the impact pulleys (602) on the inner side. The ejection frame (6) is provided with fixed pulleys (605) on the front and rear sides of the bottom.

3. The adaptive multimodal intelligent cold-launch tactical system according to claim 2, characterized in that: A pulley frame (8) is provided on the telescopic end (701) above the push cylinder (7). A movable pulley (702) is provided on the inner side of the pulley frame (8). One end of the ejection cable (10) is fixed to the ejection frame (6), and the other end of the ejection cable (10) extends downward along the movable pulley (702) to the fixed pulley (605). The ejection cable (10) then extends upward around the impact pulley (602) and downward to the push clamp plate (9).

4. The adaptive multimodal intelligent cold-launch tactical system according to claim 3, characterized in that: The push clamp (9) includes a base (901) and a guide block (902) that slides vertically with the ejection frame (6). The top of the base (901) is symmetrically provided with two sets of clamping mechanisms (903) that support the UAV body (5). The front and rear sides of the base (901) are provided with two sets of deceleration hooks (904) with openings facing upwards, corresponding to the deceleration cable (12).

5. The adaptive multimodal intelligent cold-launch tactical system according to claim 4, characterized in that: A guide pulley (603) and a limiting pulley (604) are provided on the inner side of the ejection frame (6) between the two sets of deceleration devices (11), and the deceleration cable (12) extends along the top side of the guide pulley (603) to the bottom side of the limiting pulley (604).

6. The adaptive multimodal intelligent cold-launch tactical system according to claim 5, characterized in that: The deceleration device (11) includes a fixed plate (11a) fixed to the inner side of the ejection frame (6), and a vertically extendable sleeve (11c) is provided on the bottom side of the fixed plate (11a), and a movable plate (11d) is fixed to the bottom end of the sleeve (11c).

7. The adaptive multimodal intelligent cold-launch tactical system according to claim 6, characterized in that: A spring (11b) is fitted on the outside of the sleeve (11c). The two ends of the spring (11b) abut against the fixed plate (11a) and the movable plate (11d) respectively. The end of the deceleration cable (12) passes through the fixed plate (11a) and is fixed downward to the top side of the movable plate (11d).

8. The adaptive multimodal intelligent cold-launch tactical system according to claim 7, characterized in that: The vehicle body (1) is equipped with a folding boom crane (4) on the top side. The folding boom crane (4) is a two-joint folding three-stage telescopic mechanism.

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