Multipurpose ground unmanned aerial vehicle honeycomb ejection device

Abstract

The invention discloses a multipurpose ground unmanned aerial vehicle honeycomb catapulting device, and relates to the technical field of unmanned aerial vehicle launching equipment, the multipurpose ground unmanned aerial vehicle honeycomb catapulting device comprises a catapulting nest composed of a plurality of groups of catapulting units and a control unit, high-pressure CO2 gas is used as a power source, and the catapulting units receive instructions launched by the control unit and send the instructions to the control unit. The electric push rod upwards pushes a push plate mounted at the opening of the high-pressure gas cylinder to drive the high-pressure gas cylinder to move upwards, so that the gas cylinder is in contact with the pricking needle; the pricking needle pierces the gas cylinder protection film, the gas cylinder releases high-pressure CO2 gas, the bearing bush and the unmanned aerial vehicle are pushed to be ejected upwards, and the unmanned aerial vehicle is ejected out of the cylinder. The unmanned aerial vehicle can be integrated on various ground and water surface devices, and rapid ejection launching, multi-task adaptation and convenient secondary filling of the unmanned aerial vehicle are achieved; the unmanned aerial vehicle is adaptive to unmanned aerial vehicles of various load types, meets the requirements of multi-scene combat and task such as reconnaissance, strike and bait throwing, and has extremely high practicability and environmental adaptability.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of unmanned aerial vehicle launching, in particular to a multipurpose ground unmanned aerial vehicle honeycomb launching device. BACKGROUND

[0002] With the rapid development of unmanned aerial vehicle technology, its application in military and civilian scenarios such as reconnaissance, attack, escort, etc. is becoming more and more widespread. However, the existing unmanned aerial vehicle launching device has many limitations: some launching devices have fixed structures and cannot adapt to unmanned aerial vehicles of different task types, and have single functions; most launching devices have complex loading processes, low secondary launching efficiency, and cannot meet the rapid response requirements in battlefield scenarios; and the integrated adaptability of the launching device is poor, and it cannot be flexibly carried on various ground or water surface equipment, limiting its application range. In addition, the traditional launching power source may have safety hazards or unstable power output, affecting the launching reliability. Therefore, there is an urgent need for a modular, multipurpose, convenient-to-load and stable-launching unmanned aerial vehicle launching device. SUMMARY

[0003] The purpose of the present application is to provide a multipurpose ground unmanned aerial vehicle honeycomb launching device to solve the problems of poor adaptability, low loading efficiency and single function in the prior art, and to realize the rapid launching, multi-task adaptation and flexible integration of unmanned aerial vehicles.

[0004] To achieve the above-mentioned purpose, the present application provides the following technical scheme: a multipurpose ground unmanned aerial vehicle honeycomb launching device, characterized in that it comprises a launching nest composed of a plurality of launching units and a control unit, each launching unit comprising a launching sleeve, a bearing, a retainer ring, a spike, a push plate, a high-pressure gas cylinder, an electric push rod and a gas cylinder mounting seat; the launching unit uses high-pressure CO2 filled in the high-pressure gas cylinder as a power source, wherein the bearing is sleeved on the launching sleeve, the retainer ring is fixed on the launching sleeve by a fastening screw, the spike is bonded to the center of the bottom surface of the bearing, the high-pressure gas cylinder and the electric push rod are installed in the corresponding hole positions of the gas cylinder mounting seat, and the push plate is screwed on the mouth of the high-pressure gas cylinder; The control unit adopts an STM32H745 micro dual-core controller as a main control module, and integrates a small inductive proximity switch sensor and a compatible wireless communication module; the sensor is used to detect whether the unmanned aerial vehicle is in place, and to control at least one launching unit according to the control instruction output by the man-machine interaction unit; after the launching unit is assembled, the corresponding unmanned aerial vehicle will enter the launching sleeve to wait; After receiving the instruction sent by the control unit, the electric push rod pushes the push plate installed at the mouth of the high-pressure gas cylinder upward, drives the high-pressure gas cylinder to move upward, and makes the gas cylinder contact with the needle; the needle pierces the protective film of the gas cylinder, and the high-pressure CO2 gas in the gas cylinder is released to push the bush and the unmanned aerial vehicle upward; after the unmanned aerial vehicle is ejected from the cylinder, the bush falls back to reset, the electric push rod resets synchronously, and the high-pressure gas cylinder is replaced by unscrewing the gas cylinder mounting seat, and the preparation for secondary filling is completed.

[0005] Further, the ejection unit adopts a matrix layout, supports modular disassembly and rapid secondary loading, and forms a reconnaissance unit, a strike unit and a decoy unit according to a task scene, and the ejection nest is adaptively loaded and integrated in a tank, an armored vehicle, an unmanned ship or an unmanned vehicle.

[0006] The present application has the following beneficial effects: 1. Strong modular adaptability: the ejection unit can be combined into ejection nests with different functions as needed, is adapted to various equipment such as tanks and armored vehicles, supports multi-task switching such as reconnaissance and strike, and solves the problems of single function and poor adaptability of traditional devices; 2. High launching efficiency: the ejection time is ≤0.5s, the secondary filling time is ≤30s, batch rapid launching of multiple units can be realized, and the rapid response requirement in a battlefield scene is met; 3. High safety and stability: high-pressure CO2 gas power is used, there is no risk of gunpowder explosion, the power output is stable, the parameter error of ejection height and time is ≤5%, and damage to the unmanned aerial vehicle is avoided; 4. Strong environmental adaptability: the honeycomb ejection device can stably work in a temperature range of -30℃ to +50℃, and the components of the ejection unit adopt high-temperature-resistant and corrosion-resistant materials to ensure reliability in complex environments; 5. Good operation convenience: the ejection unit is light in weight (≤8kg), disassembly does not require professional tools, the gas cylinder replacement process is simple, the skill requirement of the operator is reduced, and rapid operation in a complex environment such as a battlefield is suitable. BRIEF DESCRIPTION OF DRAWINGS

[0007] Figure 1 is a cross-sectional view of the honeycomb launching device; The drawing number explanation: ejection sleeve 1, bush 2, retainer 3, needle 4, push plate 5, high-pressure gas cylinder 6, electric push rod 7, gas cylinder mounting seat 8. DETAILED DESCRIPTION

[0008] The present application will be further described in detail below in combination with the drawings and specific embodiments.

[0009] As Figure 1As shown, a multi-purpose ground unmanned aerial vehicle honeycomb launching device includes a launching nest composed of a plurality of groups of launching units and a control unit, each launching unit including: a launching sleeve 1, a bearing 2, a check ring 3, a spike 4, a push plate 5, a high-pressure gas cylinder 6, an electric push rod 7, and a gas cylinder mounting seat 8; the launching unit is powered by high-pressure CO2 filled in the high-pressure gas cylinder 6, wherein the bearing 2 is sleeved on the launching sleeve 1, the check ring 3 is fixed on the launching sleeve 1 by a fastening screw, the spike 4 is bonded to the center of the bottom surface of the bearing 2, the high-pressure gas cylinder 6 and the electric push rod 7 are installed in the corresponding hole positions of the gas cylinder mounting seat 8, and the push plate 5 is screwed on the mouth of the high-pressure gas cylinder 6; The control unit is used to control at least one group of launching units according to the control instructions output by the human-computer interaction unit, and after the assembly of the launching unit is completed, the corresponding unmanned aerial vehicle will enter the launching sleeve 1 for waiting; the control unit adopts an STM32H745 micro dual-core controller as a main control module, the operating frequency can reach 480MHz (-40℃~+50℃ environment normal work), and a small inductive proximity switch sensor (detecting whether the unmanned aerial vehicle is in place) and a wireless communication module compatible with 1.4GHz / 2.4GHz / 5.8GHz frequency bands are integrated.

[0010] The launching unit adopts a matrix layout, supports modular disassembly and rapid secondary assembly, and forms a reconnaissance unit, a strike unit, and a decoy unit according to a task scene, and the launching nest is adaptively loaded and integrated in a tank, an armored vehicle, an unmanned ship, or an unmanned vehicle.

[0011] The launching process of the launching device is as follows: 1. The launching unit receives a launching instruction; 2. The electric push rod pushes the push plate installed on the mouth of the CO2 gas cylinder upward; 3. The push plate drives the CO2 gas cylinder to move upward, so that the gas cylinder contacts the spike; 4. The spike pierces the protective film of the CO2 gas cylinder, and the gas cylinder releases high-pressure gas; 5. The high-pressure gas pushes the bearing and the unmanned aerial vehicle installed in the launching unit upward, the launching height is ≥1.5m, and the launching time is ≤0.5s; 6. After the unmanned aerial vehicle is launched out of the cylinder, the bearing falls back to reset, and the electric push rod is reset synchronously; 7. The operator twists off the gas cylinder mounting seat from the bottom, replaces the CO2 gas cylinder, and completes the secondary filling preparation.

[0012] Example 1: reconnaissance task configuration integrated in an armored vehicle Device assembly: select 6 groups of launching units, all configured as reconnaissance units (unmanned aerial vehicles carrying reconnaissance pods), splice to form a set of launching nests, fixed through the standardized mounting interface on the top of the armored vehicle, and connect the launching nest with the power supply system of the armored vehicle; Task execution: After the armored vehicle arrives at the task area, the operator sends the launch command, and the 6 groups of launch units are started synchronously. All the UAVs are launched within 0.5s, and the UAVs form a reconnaissance formation after taking off to complete the regional reconnaissance task. Secondary deployment: After the task is completed, the operator replaces the gas cylinder of the launch unit, and a group of units is loaded within 30s. After reloading the UAV, the next round of reconnaissance task can be performed.

[0013] Example 2: Integrated in the unmanned ship strike + decoy task configuration 1. Device assembly: Select 8 groups of launch units, 4 groups of which are strike units (unmanned aerial vehicles carrying armor-piercing / blast-kill warheads), and 4 groups of which are decoy units (unmanned aerial vehicles carrying infrared / radar decoys), which are alternately arranged to form a launch nest integrated on the deck of the unmanned ship. The control system of the unmanned ship is used to issue commands. 2. Task execution: After the unmanned ship approaches the target area, 4 groups of decoy units are launched first, and the UAVs release infrared / radar decoys to interfere with enemy detection systems. After 10s, 4 groups of strike units are launched, and the UAVs fly to the target according to the preset path to complete the strike task. The entire process of the launch device is fault-free, and the flight attitude of the UAV is stable. 3. Recovery and maintenance: After the task is completed, the unmanned ship returns, and the operator cleans the launch unit (removes sea salt), checks the bushings, needles and other components for wear to ensure the reliability of subsequent use.

[0014] The multipurpose ground unmanned aerial vehicle honeycomb launch device of the present application solves the technical problems of existing launch devices through modular design, high-pressure CO2 power system and high-efficiency loading structure, and can be widely used in military, anti-terrorism, border defense, fire fighting and other fields. Its core components (such as CO2 gas cylinder, electric push rod, bushing, etc.) are mature mass-produced components, with low manufacturing cost, simple assembly process and high industrial applicability and market promotion value.

[0015] The above examples are only preferred embodiments of the present application, and are not limiting. In actual application, the number, function type and integrated platform of the launch unit can be adjusted according to task requirements, for example: in the urban anti-terrorism scene, the launch nest can be integrated on the unmanned vehicle, and the unmanned aerial vehicle carrying non-lethal load (tear gas / smoke) can be carried; in the border patrol scene, it can be integrated on the armored vehicle, and the unmanned aerial vehicle carrying reconnaissance + lethal load can be carried; at the same time, the power of the electric push rod, the capacity of the CO2 gas cylinder and other parameters can be optimized to further improve the performance of the launch device. These adjustments are all within the protection scope of the present application.

[0016] Any modification, equivalent replacement, and improvement made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A multi-purpose ground drone honeycomb launching device, characterized in that, The application relates to a launching nest and a control unit which are composed of a plurality of launching units, each launching unit comprising a launching sleeve (1), a bearing bush (2), a check ring (3), a spike needle (4), a push plate (5), a high-pressure gas cylinder (6), an electric push rod (7) and a gas cylinder mounting seat (8); the launching unit takes high-pressure CO2 filled in the high-pressure gas cylinder (6) as a power source, wherein the bearing bush (2) is sleeved on the launching sleeve (1), the check ring (3) is fixed on the launching sleeve (1) through fastening screws, the spike needle (4) is bonded on the center of the bottom surface of the bearing bush (2), the high-pressure gas cylinder (6) and the electric push rod (7) are mounted in corresponding hole positions of the gas cylinder mounting seat (8), and the push plate (5) is screwed on the mouth of the high-pressure gas cylinder (6); The control unit adopts an STM32H745 micro dual-core controller as a main control module, and is integrated with a small inductive proximity switch sensor and a compatible wireless communication module; the sensor is used for detecting whether a UAV is in place; the control unit is used for controlling at least one launching unit according to a control instruction output by a man-machine interaction unit; after the launching unit is assembled, the corresponding UAV will enter the launching sleeve (1) to wait; After the launching unit receives the instruction transmitted by the control unit, the electric push rod (7) pushes the push plate (5) mounted on the mouth of the high-pressure gas cylinder (6) upwards, drives the high-pressure gas cylinder (6) to move upwards, and makes the gas cylinder contact with the spike needle (4); the spike needle (4) penetrates the protective film of the gas cylinder, the gas cylinder releases high-pressure CO2 gas, the bearing bush (2) and the UAV are pushed upwards to be launched, the bearing bush (2) falls back to reset after the UAV is launched out of the cylinder, the electric push rod (7) is synchronously reset, the high-pressure gas cylinder (6) is replaced by unscrewing the gas cylinder mounting seat (8), and secondary filling preparation is completed.

2. The multi-purpose ground drone hive launcher of claim 1, wherein, The launching unit adopts a matrix layout, supports modular disassembly and assembly and rapid secondary assembly, forms a reconnaissance unit, a striking unit and a decoy unit according to a task scene, and the launching nest is adaptively loaded and integrated in a tank, an armored vehicle, an unmanned ship or an unmanned vehicle.

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