Vehicle-mounted multi-type electromagnetic ejection device

Abstract

The utility model discloses a vehicle-mounted multi-type electromagnetic ejection device, which relates to the technical field of vehicle-mounted unmanned aerial vehicles and comprises a vehicle head and a carriage, an energy storage unit is arranged at the bottom of one end of the carriage, and a charger is arranged at the top of the energy storage unit; a driving system is arranged on one side of the energy storage unit, a control unit is arranged in the driving system, and a switching unit is arranged on one side of the driving system; a hangar is arranged at the other end of the compartment, and an adjustable electromagnetic ejection unit is arranged on one side of the hangar. According to the vehicle-mounted multi-type electromagnetic catapult, only one set of power supply equipment and one set of driving system need to be adopted, catapulting tasks of unmanned aerial vehicles of various types can be adapted at the same time, high-frequency continuous launching of the unmanned aerial vehicles of different types is achieved, the adaptive capacity of the vehicle-mounted multi-type electromagnetic catapulting device is wider, and the launching flexibility and efficiency of the multi-type unmanned aerial vehicles are improved; compared with multiple sets of electromagnetic launching units launched by a single unmanned aerial vehicle, the continuous launching capability of multiple types of unmanned aerial vehicles is improved, and the manufacturing and maintenance cost of the device is saved.

Description

Technical Field

[0001] The utility model relates to the technical field of vehicle-mounted unmanned aerial vehicles, and particularly relates to a vehicle-mounted multi-type electromagnetic catapult device. Background Art

[0002] With the gradual and mature application of unmanned aerial vehicles in military, industrial, civilian and other fields, especially the outstanding performance of various unmanned aerial vehicles in recent years in warfare, their importance has even reached the level of being able to influence the battlefield situation, which has further promoted the rapid development of unmanned aerial vehicle technology. For catapult-type unmanned aerial vehicles, since their bodies discard the driving devices, high-power power supply devices or chemical energy and their devices for launching, only the cruise power supply and motion control devices are retained, and some cruise missiles even discard the cruise power supply and motion control devices. This means that more functional modules can be placed in the same volume specification, making the equipment performance better, richer and lighter. Because of this, the development of unmanned aerial vehicles has also put forward higher and broader requirements for catapult equipment and methods. At present, the methods of unmanned aerial vehicle catapulting include: slingshot catapulting, high-pressure air bag catapulting, pyrotechnic catapulting, hydraulic and pneumatic reciprocating piston catapulting, electromagnetic catapulting, etc.

[0003] In related technologies, electromagnetic catapulting can enable unmanned aerial vehicles to obtain extremely large energy within a very short stroke, and the electromagnetic catapulting equipment occupies a small space, has low catapulting noise and high launching frequency, and is convenient for vehicle-mounted integration. It is an ideal catapulting method. However, the current vehicle-mounted electromagnetic catapulting can only catapult unmanned aerial vehicles of one size specification and speed requirement with one set of system, which is not conducive to dealing with the battlefield or special situations, has a small application range, and cannot meet the use requirements of various combat deployments. Summary of the Utility Model

[0004] The purpose of the utility model is to provide a vehicle-mounted multi-type electromagnetic catapult device to solve at least one of the problems and defects mentioned in the above background art.

[0005] To achieve the above purpose, the utility model provides the following technical solutions:

[0006] A vehicle-mounted multi-type electromagnetic catapult device, comprising:

[0007] The vehicle head and the carriage, at the bottom of one end of the carriage, there is an energy storage unit, and at the top of the energy storage unit, there is a charger;

[0008] On one side of the energy storage unit, there is a drive system, inside the drive system, there is a control unit, and on one side of the drive system, there is a switching unit;

[0009] At the other end of the carriage, there is an aircraft hangar, and on one side of the aircraft hangar, there is an adjustable electromagnetic catapult unit.

[0010] The vehicle-mounted multi-type electromagnetic catapult device according to this solution has at least the following technical effects:

[0011] Compared with the traditional electromagnetic catapult device, this vehicle-mounted multi-type electromagnetic catapult device only needs to adopt a set of power supply equipment and a set of drive systems, and can simultaneously adapt to the catapult tasks of multiple types of unmanned aerial vehicles (UAVs). Through the energy storage unit, the power requirement for the charger can be greatly reduced. During the process of loading the UAV each time by the launch system, the charger can complete the charging work of the energy storage unit. And by inputting instructions for the specified catapult track to the drive system and the switching unit through the control unit, it can meet the launch functions of different models, realize the high-frequency continuous launch of different types of UAVs, making the adaptability of this vehicle-mounted multi-type electromagnetic catapult device wider, and it can quickly deploy this device to different environments, adapt to various combat requirements, and effectively improve the launch flexibility and efficiency of multiple types of UAVs.

[0012] Through the switching unit, the continuous launch function of the electromagnetic catapult unit for multiple types of UAVs is realized, enabling each unit of the entire system to be fully utilized, with high integration, effectively reducing the requirement for vehicle-mounted space, reducing the volume of the overall device, facilitating hiding in complex terrains, effectively enhancing the concealment of combat deployment, and improving the diversity and reliability of tactical options; at the same time, compared with multiple sets of electromagnetic catapult units for single UAV launches, it effectively improves the continuous launch ability of multiple types of UAVs and saves the manufacturing and maintenance costs of this device.

[0013] As a further solution of the present invention: The electromagnetic catapult unit is provided with a number of catapult tracks, and the number of catapult tracks respectively adapt to UAVs of corresponding models.

[0014] Since the electromagnetic catapult unit is provided with a number of catapult tracks, and the number of catapult tracks respectively adapt to UAVs of corresponding models, different types of UAVs can be selected and launched according to specific mission requirements, meeting the continuous launch mission requirements of different types of UAVs, and improving the launch efficiency of UAVs and the flexibility of tactical deployment.

[0015] As a further solution of the present invention: A catapult mover is respectively arranged in a number of the catapult tracks.

[0016] By respectively arranging catapult movers in a number of catapult tracks, the catapult mover can generate a powerful thrust in an extremely short time, enabling the UAV to quickly reach the required speed and altitude, ensuring the rapid launch of the UAV, and thus enabling the UAV to perform its flight mission.

[0017] As a further solution of the present invention: A base is arranged at the rear end of the bottom of the electromagnetic catapult unit, the bottom of the base is connected to the bottom of the carriage, and the top of the base is hinged to the rear end of the bottom of the electromagnetic catapult unit.

[0018] As a further solution of the present invention: a hydraulic pitching adjustment mechanism is provided at the front end of the bottom of the electromagnetic catapult unit, the bottom of the hydraulic pitching adjustment mechanism is connected to the bottom of the carriage, and the top of the hydraulic pitching adjustment mechanism is connected to the front end of the bottom of the electromagnetic catapult unit.

[0019] Since a base is provided at the rear end of the bottom of the electromagnetic catapult unit, the bottom of the base is connected to the bottom of the carriage, and the top of the base is hinged to the rear end of the bottom of the electromagnetic catapult unit; a hydraulic pitching adjustment mechanism is provided at the front end of the bottom of the electromagnetic catapult unit, the bottom of the hydraulic pitching adjustment mechanism is connected to the bottom of the carriage, and the top of the hydraulic pitching adjustment mechanism is connected to the front end of the bottom of the electromagnetic catapult unit, it is possible to flexibly adjust the launch angle of the UAV, adjust the launch angle of the UAV according to different models of UAVs or tactical requirements, launch the UAV to a predetermined height range, and can adapt to different environments or uneven terrains, ensuring the launch flexibility and applicability of the UAV.

[0020] As a further solution of the present invention: the included angle between the electromagnetic catapult unit and the bottom of the carriage is 0° - 80°.

[0021] Since the included angle between the electromagnetic catapult unit and the bottom of the carriage is 0° - 80°, the adjustable range of the UAV launch angle is relatively large, further improving the launch effect of the UAV in different environments or uneven terrains and meeting the combat deployment requirements.

[0022] As a further solution of the present invention: the switching unit inputs a specified catapult track command through the control unit of the drive system.

[0023] Since the switching unit inputs a specified catapult track command through the control unit of the drive system, it is possible to quickly switch to the catapult track adapted to the UAV according to combat requirements, realize the flexible launch of multiple types of UAVs, improve the adaptability and response ability of the device, and through the control unit inputting commands, make different catapult tracks automatically match the corresponding UAVs, reducing the complexity of manual adjustment and improving the launch efficiency of the UAV.

[0024] As a further solution of the present invention: the switching unit switches the primary circuit and the control circuit to be connected to the specified catapult track according to the command.

[0025] Since the switching unit switches the primary circuit and the control circuit to be connected to the specified catapult track according to the command, the device can transmit signals more quickly, the launch command can be immediately fed back to the electromagnetic catapult unit, ensuring that the switching between the control circuit and the primary circuit can be carried out quickly and accurately, improving the consistency and reliability of the entire operation process of the catapult system, avoiding operation errors caused by signal distortion, and meeting the continuous launch requirements of multiple types of UAVs.

[0026] As a further solution of the present invention: The charger and the energy storage unit jointly supply electrical energy to the switching unit through the drive system.

[0027] Since the charger and the energy storage unit jointly supply electrical energy to the switching unit through the drive system, during the continuous launch of multiple types of unmanned aerial vehicles, while ensuring continuous high-power power supply to the switching unit, the requirements for the respective powers of the charger and the energy storage unit by the system are greatly reduced, thereby reducing the usage cost. Description of the Drawings

[0028] For the convenience of those skilled in the art to understand, the following further describes the present utility model in conjunction with the drawings.

[0029] Figure 1 It is a three-dimensional structural schematic diagram of a vehicle-mounted multi-type electromagnetic catapult device;

[0030] Figure 2 It is a structural schematic diagram of the unmanned aerial vehicle launch state of a vehicle-mounted multi-type electromagnetic catapult device;

[0031] Figure 3 It is a schematic diagram of the control system principle of a vehicle-mounted multi-type electromagnetic catapult device.

[0032] Reference Signs:

[0033] 1, vehicle head; 2, carriage; 3, energy storage unit; 4, charger; 5, drive system; 6, switching unit; 7, hangar; 8, electromagnetic catapult unit; 81, catapult track; 82, catapult mover; 9, base; 10, hydraulic pitch adjustment mechanism. Detailed Embodiment

[0034] The following details the embodiments of the present utility model. The examples of the embodiments are shown in the drawings, where the same or similar reference numerals represent the same or similar elements or elements with the same or similar functions throughout. The embodiments described below with reference to the drawings are exemplary and are only used to explain the present utility model and should not be construed as a limitation to the present utility model.

[0035] In the description of the present utility model, it should be understood that for the orientation description, such as the orientation or positional relationship indicated by up, down, front, back, left, right, etc., is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present utility model.

[0036] In the description of the present utility model, the meaning of "a number of" is one or more, the meaning of "a plurality of" is two or more, and understandings such as "greater than", "less than", "exceeding", etc. do not include the corresponding number, while understandings such as "above", "below", "within", etc. include the corresponding number. If there is a description of "first" and "second", it is only for the purpose of distinguishing technical features and cannot be understood as indicating or implying relative importance or implicitly indicating the quantity of the indicated technical features or implicitly indicating the sequence relationship of the indicated technical features.

[0037] In the description of the present utility model, unless otherwise clearly defined, words such as "set", "installed", "connected", etc. should be understood in a broad sense, and those skilled in the art can reasonably determine the specific meanings of the above words in the present utility model in combination with the specific content of the technical solution.

[0038] In order to make the purpose, technical solution and advantages of the present utility model clearer, the following further details the present utility model in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present utility model and are not used to limit the present utility model, that is, the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments. Generally, the components of the embodiments of the present utility model described and shown in the accompanying drawings herein can be arranged and designed in various different configurations.

[0039] Therefore, the following detailed description of the embodiments of the present utility model provided in the accompanying drawings is not intended to limit the scope of the claimed present utility model, but merely represents the selected embodiments of the present utility model. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art without creative efforts belong to the scope of protection of the present utility model.

[0040] As Figures 1-3 shown in the embodiments of the present utility model, a vehicle-mounted multi-type electromagnetic catapult device includes: a vehicle head 1 and a carriage 2. A energy storage unit 3 is provided at the bottom of one end of the carriage 2, and a charger 4 is provided on the top of the energy storage unit 3; a drive system 5 is provided on one side of the energy storage unit 3, a control unit is provided inside the drive system 5, and a switching unit 6 is provided on one side of the drive system 5; a hangar 7 is provided at the other end of the carriage 2, and an adjustable electromagnetic catapult unit 8 is provided on one side of the hangar 7.

[0041] Specifically, the vehicle-mounted multi-type electromagnetic catapult device can be used to launch military drones such as reconnaissance drones, tactical drones, and transport drones. Compared with traditional electromagnetic catapult devices, only one set of power supply equipment and one set of drive systems are required, which can simultaneously adapt to the catapult tasks of multiple types of drones. Through the energy storage unit 3, the power requirement for the charger 2 can be greatly reduced. During the process of loading the drone each time by the launch system, the charger 2 can complete the charging work for the energy storage unit 3. And by inputting instructions for the specified catapult track to the drive system 5 and the switching unit 6 through the control unit, it can meet the launch functions of different models, achieve the high-frequency continuous launch of different types of drones, making the vehicle-mounted multi-type electromagnetic catapult device have a wider adaptability, and can quickly deploy the device to different environments, adapt to various combat requirements, and effectively improve the launch flexibility and efficiency of multi-type drones.

[0042] The continuous launch function of the electromagnetic catapult unit 8 for multi-type drones is realized through the switching unit 6, enabling full utilization of each unit of the entire system, with high integration, effectively reducing the requirement for vehicle-mounted space, reducing the volume of the overall device, facilitating hiding in complex terrains, effectively enhancing the concealment of combat deployment, and improving the diversity and reliability of tactical options. At the same time, compared with multiple sets of electromagnetic catapult units for single-drone launch, it effectively improves the continuous launch ability of multi-type drones and saves the manufacturing and maintenance costs of the device.

[0043] As Figure 1 and Figure 2 shown, the electromagnetic catapult unit 8 is provided with a plurality of catapult tracks 81, and the plurality of catapult tracks 81 are respectively adapted to corresponding types of drones.

[0044] Specifically, since the electromagnetic catapult unit 8 is provided with a plurality of catapult tracks 81, and the plurality of catapult tracks 81 are respectively adapted to corresponding types of drones, different types of drones can be selected and launched according to specific mission requirements, meeting the continuous launch mission requirements of different types of drones, and improving the launch efficiency of drones and the deployment flexibility of tactics.

[0045] As Figure 2 shown, a catapult mover 82 is respectively arranged in a plurality of catapult tracks 81.

[0046] Specifically, by respectively arranging the catapult mover 82 in a plurality of catapult tracks 81, the catapult mover 82 can generate a powerful thrust in a very short time, enabling the drone to quickly reach the required speed and altitude, ensuring the rapid launch of the drone, and thus enabling the drone to perform its flight mission.

[0047] As Figure 1As shown, a base 9 is provided at the rear end of the bottom of the electromagnetic catapult unit 8. The bottom of the base 9 is connected to the bottom of the carriage 2, and the top of the base 9 is hinged to the rear end of the bottom of the electromagnetic catapult unit 8. A hydraulic pitching adjustment mechanism 10 is provided at the front end of the bottom of the electromagnetic catapult unit 8. The bottom of the hydraulic pitching adjustment mechanism 10 is connected to the bottom of the carriage 2, and the top of the hydraulic pitching adjustment mechanism 10 is connected to the front end of the bottom of the electromagnetic catapult unit 8.

[0048] Specifically, since a base 9 is provided at the rear end of the bottom of the electromagnetic catapult unit 8, the bottom of the base 9 is connected to the bottom of the carriage 2, and the top of the base 9 is hinged to the rear end of the bottom of the electromagnetic catapult unit 8. A hydraulic pitching adjustment mechanism 10 is provided at the front end of the bottom of the electromagnetic catapult unit 8. The bottom of the hydraulic pitching adjustment mechanism 10 is connected to the bottom of the carriage 2, and the top of the hydraulic pitching adjustment mechanism 10 is connected to the front end of the bottom of the electromagnetic catapult unit 8, it is possible to flexibly adjust the launch angle of the UAV. According to different models of UAVs or tactical requirements, the launch angle of the UAV can be adjusted to launch the UAV to a predetermined height range, and it can adapt to different environments or uneven terrains, ensuring the launch flexibility and applicability of the UAV.

[0049] Furthermore, the included angle between the electromagnetic catapult unit 8 and the bottom of the carriage 2 is 0° - 80°.

[0050] Specifically, since the included angle between the electromagnetic catapult unit 8 and the bottom of the carriage is 0° - 80°, the adjustable range of the UAV launch angle is relatively large, further improving the launch effect of the UAV in different environments or uneven terrains and meeting the requirements of combat deployment.

[0051] According to an embodiment of the present invention, the switching unit 6 inputs an instruction for specifying the catapult track 81 through the control unit of the drive system 5.

[0052] Specifically, since the switching unit 6 inputs an instruction for specifying the catapult track 81 through the control unit of the drive system 5, it is possible to quickly switch to the catapult track 81 adapted to the UAV according to combat requirements, realize the flexible launch of multiple types of UAVs, improve the adaptability and response ability of the device, and through the control unit inputting instructions, make different catapult tracks automatically match the corresponding UAVs, reducing the complexity of manual adjustment and improving the launch efficiency of the UAV.

[0053] Furthermore, the switching unit 6 switches the primary circuit and the control circuit to be connected to the specified catapult track 81 according to the instruction.

[0054] Specifically, since the switching unit 6 switches the primary circuit and the control circuit to be connected to the specified ejection track 81 according to the instruction, the device can transmit signals more quickly, and the launch instruction can be immediately fed back to the electromagnetic ejection unit 8, ensuring that the switching between the control circuit and the primary circuit can be carried out quickly and accurately, improving the consistency and reliability of the entire operation process of the ejection system, avoiding operation errors caused by signal distortion, and meeting the continuous launch requirements of multiple types of unmanned aerial vehicles.

[0055] Further, the charger 4 and the energy storage unit 3 jointly supply electrical energy to the switching unit 6 through the drive system 5.

[0056] Specifically, since the charger 4 and the energy storage unit 3 jointly supply electrical energy to the switching unit 6 through the drive system 5, during the continuous launch of multiple types of unmanned aerial vehicles, while ensuring the continuous high-power power supply of the switching unit 6, the requirements for the respective powers of the charger and the energy storage unit by the system are greatly reduced, thereby reducing the usage cost.

[0057] The present utility model also discloses a control method for the vehicle-mounted multi-type electromagnetic ejection device. Start the system, turn on the charger 4, and supply the electrical energy generated by the charger 4 to the energy storage unit 3 through the drive system 5; match and install unmanned aerial vehicles of different models on the ejection track 81 of the electromagnetic ejection unit 8 and adjust the launch angle; input the specified ejection track 81 instruction to the drive system 5 and the switching unit 6 through the control unit, and the switching unit 6 switches the primary circuit and the control circuit to the specified ejection track according to the instruction; the drive system 5 receives the instruction from the control unit, adjusts its power supply and control mode, jointly supplies electrical energy to the switching unit 6 through the drive system 5 by the charger 4 and the energy storage unit 3, and supplies it to the specified ejection track 81, and at the same time controls the ejection mover 82 to launch the unmanned aerial vehicle.

[0058] Specifically, through the control method of the vehicle-mounted multi-type electromagnetic ejection device, it ensures the efficient utilization of electrical energy in the ejection process by a set of power supply system, and according to the launch requirements of the unmanned aerial vehicle, through the electromagnetic ejection unit 8 and the switching unit 6, different models of unmanned aerial vehicles can be quickly matched and continuously launched. At the same time, by adjusting the angle of the electromagnetic ejection unit 8, it can flexibly meet the flight requirements of various combat environments and tasks, improving the continuity and efficiency of the unmanned aerial vehicle launch.

[0059] The above content is only an example and description of the structure of the present utility model. Those skilled in the art of this technology make various modifications or supplements to the described specific embodiments or use similar methods for substitution. As long as they do not deviate from the structure of the utility model or exceed the scope defined by this claim book, they should all fall within the protection scope of the present utility model.

Claims

1. A vehicle-mounted multi-type electromagnetic ejection device, characterized in that Including: A locomotive head (1) and a carriage (2), at the bottom of one end of the carriage (2) there is an energy storage unit (3), and at the top of the energy storage unit (3) there is a charger (4); On one side of the energy storage unit (3) there is a drive system (5), inside the drive system (5) there is a control unit, and on one side of the drive system (5) there is a switching unit (6); At the other end of the carriage (2) there is an aircraft hangar (7), and on one side of the aircraft hangar (7) there is an adjustable electromagnetic catapult unit (8).

2. The vehicle-mounted multi-type electromagnetic ejection device according to claim 1, characterized in that The electromagnetic catapult unit (8) is provided with a number of catapult tracks (81), and the number of catapult tracks (81) respectively adapt to corresponding models of unmanned aerial vehicles.

3. The vehicle-mounted multi-type electromagnetic ejection device according to claim 2, characterized in that, Inside the number of catapult tracks (81) there are respectively catapult movers (82).

4. The vehicle-mounted multi-type electromagnetic ejection device according to claim 3, characterized in that, At the rear end of the bottom of the electromagnetic catapult unit (8) there is a base (9), the bottom of the base (9) is connected to the bottom of the carriage (2), and the top of the base (9) is hinged to the rear end of the bottom of the electromagnetic catapult unit (8).

5. The vehicle-mounted multi-type electromagnetic ejection device according to claim 4, characterized in that, At the front end of the bottom of the electromagnetic catapult unit (8) there is a hydraulic pitching adjustment mechanism (10), the bottom of the hydraulic pitching adjustment mechanism (10) is connected to the bottom of the carriage (2), and the top of the hydraulic pitching adjustment mechanism (10) is connected to the front end of the bottom of the electromagnetic catapult unit (8).

6. The vehicle-mounted multi-type electromagnetic ejection device according to claim 5, characterized in that The included angle between the electromagnetic catapult unit (8) and the bottom of the carriage (2) is 0° - 80°.

7. The vehicle-mounted multi-type electromagnetic catapult device according to claim 3, wherein The switching unit (6) inputs an instruction for a specified catapult track (81) through the control unit of the drive system (5).

8. The vehicle-mounted multi-type electromagnetic ejection device according to claim 7, characterized in that, The switching unit (6) switches the primary circuit and the control circuit to be connected to the specified catapult track (81) according to the instruction.

9. The vehicle-mounted multi-type electromagnetic catapult device according to claim 8, wherein, The charger (4) and the energy storage unit (3) jointly supply electrical energy to the switching unit (6) through the drive system (5).

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