Integrated launching box with storage, transportation and launching functions

Abstract

The invention discloses an integrated launching box with storage, transportation and launching functions, and relates to the field of unmanned aerial vehicle launching boxes. The base is detachably connected to a transportation tool; one side of the square cabin is rotationally connected to one side of the top surface of the base, and the other side of the square cabin is connected with the base through an erecting device; one end of the erecting device is fixed to the base, and the other end of the erecting device extends into an equipment compartment in the square cabin. A first cabin, an equipment cabin, a second cabin and a command cabin are sequentially arranged in the square cabin in the length direction. The first cabin and the second cabin are each internally provided with a plurality of layers of unmanned aerial vehicle containing cavities. An electric appliance control system and an automatic oiling device are arranged in the equipment cabin; a task planning terminal, communication relay equipment and an unmanned aerial vehicle state monitoring device are arranged in the command cabin; a pod is hoisted on the rear side of the square cabin; a generator cabin and a tool box are arranged in the pod; and hoisting corner fittings are arranged in the circumferential direction of the top of the square cabin. Task requirements in different application scenes can be met, and further popularization and application expansion of the unmanned aerial vehicle technology are promoted.

Description

Technical Field

[0001] This application relates to the technical field of unmanned aerial vehicle launch boxes, and particularly to an integrated launch box with storage, transportation, and launch functions. Background Art

[0002] In recent years, unmanned aerial vehicle technology has made rapid progress, and its application fields have gradually expanded to many fields such as disaster relief, logistics transportation, agricultural plant protection, environmental monitoring, and film shooting. With the continuous enrichment and diversification of application scenarios, higher requirements are put forward for the mission execution ability, environmental adaptability, and response speed of unmanned aerial vehicle systems. For example, in disaster relief scenarios, it is required that unmanned aerial vehicles can be quickly deployed to the disaster area to perform tasks such as real-time reconnaissance and material delivery; in the field of logistics transportation, it is required that unmanned aerial vehicles have efficient and reliable takeoff and landing and energy replenishment capabilities to ensure the timely delivery of goods.

[0003] Currently, traditional unmanned aerial vehicle launch systems mainly use fixed ground launch devices. Fixed ground launch devices are usually installed at specific locations. Although they have advantages such as stable structure and strong load-bearing capacity, they have significant defects such as fixed mission modes and insufficient environmental adaptability. In addition, there is a significant disconnection between the energy replenishment and launch processes of unmanned aerial vehicles. Traditional launch devices usually only focus on the storage or launch function of unmanned aerial vehicles, and energy replenishment operations such as fuel filling need to be completed by external independent devices. This separated design requires operators to transfer the unmanned aerial vehicle to a dedicated refueling station before launch, which not only increases the complexity of equipment deployment but also significantly extends the mission preparation time. Summary of the Invention

[0004] Embodiments of this application provide an integrated launch box with storage, transportation, and launch functions, thus solving the problems raised in the background art.

[0005] An embodiment of the present application provides an integrated launch box with storage, transportation, and launch functions, including a cabin, a base, and an erection device; the base is detachably connected to a transportation vehicle; one side of the cabin is rotatably connected to one side of the top surface of the base, and the other side is connected to the base through the erection device; one end of the erection device is fixed to the base, and the other end extends into the equipment cabin inside the cabin, for driving the cabin to flip to a preset launch angle; inside the cabin, a first cabin, an equipment cabin, a second cabin, and a command cabin are sequentially arranged along the length direction; multiple layers of unmanned aerial vehicle accommodation chambers are provided in both the first cabin and the second cabin; an electrical control system and an automatic fueling device are arranged in the equipment cabin, and the automatic fueling device is used to refuel multiple unmanned aerial vehicles; a mission planning terminal, a communication relay device, and an unmanned aerial vehicle status monitoring device are built in the command cabin; a pod is hoisted at the rear of the cabin; a generator cabin and a toolbox are arranged in the pod; hoisting corner fittings are circumferentially arranged on the top of the cabin.

[0006] In a possible implementation manner, the integrated launch box with storage, transportation, and launch functions further includes a plurality of anti-overturning supports; one end of each of the plurality of anti-overturning supports is hinged to the side wall of the base, and the other end of each of them abuts against the ground, and the plurality of anti-overturning supports are symmetrically distributed on both sides of the erection device.

[0007] In a possible implementation manner, the integrated launch box with storage, transportation, and launch functions further includes a plurality of leveling devices; the plurality of leveling devices are detachably arranged circumferentially at the bottom of the base; the leveling devices can be stored in the toolbox of the pod in a non-use state.

[0008] In a possible implementation, the automatic fueling device includes a controller, a gasoline oil tank, a lubricating oil tank, a gasoline oil pump, a lubricating oil pump, and a multi-channel mixing and distribution pipeline; the gasoline oil pump and the lubricating oil pump are both installed on the ground of the equipment cabin; the input end of the gasoline oil pump is connected to the output end of the gasoline oil tank through a first oil pipeline, and the output end is connected to the input end of the multi-channel mixing and distribution pipeline through a first flow meter and a first check valve; the input end of the lubricating oil pump is connected to the output end of the lubricating oil tank through a second oil pipeline, and the output end is connected to the input end of the multi-channel mixing and distribution pipeline through a second check valve; multiple output ends of the multi-channel mixing and distribution pipeline are docked with corresponding unmanned aircraft fuel tank interfaces, and electric control switch valves and second flow meters are arranged at multiple output ends of the multi-channel mixing and distribution pipeline; the gasoline oil pump is a fixed-displacement impeller pump, and the lubricating oil pump is a fixed-displacement magnetic pump driven by a servo motor; the controller is electrically connected to the gasoline oil pump, the lubricating oil pump, the first flow meter, the second flow meter, and the electric control switch valve; the controller is arranged in the electrical control system; the controller generates a lubricating oil supply instruction based on the gasoline flow signal collected by the first flow meter, and drives the servo motor to adjust the rotation speed of the fixed-displacement magnetic pump through a preset fuel-lubricating oil mixing ratio algorithm.

[0009] In a possible implementation, the integrated launch box with storage, transportation, and launch functions further includes two filters; the two filters are respectively installed between the output end of the gasoline oil tank and the input end of the gasoline oil pump, and between the output end of the lubricating oil tank and the input end of the lubricating oil pump.

[0010] In a possible implementation, the gasoline oil tank and the lubricating oil tank are fixedly arranged side by side in the equipment cabin and are located above the corresponding gasoline oil pump and lubricating oil pump; the lengths of the first oil pipeline and the second oil pipeline are equal.

[0011] In a possible implementation, the integrated launch box with storage, transportation, and launch functions further includes a plurality of hatch driving mechanisms; the plurality of hatch driving mechanisms are used to control the front hatch and the rear hatch of the corresponding drone accommodation chamber; the hatch driving mechanism includes a flipping connecting rod, a limiting guide rail, a slider, a connecting plate, a bracket, and a hatch flipping electric cylinder; the bracket is fixedly connected to the corresponding drone accommodation chamber; the hatch flipping electric cylinder is fixedly installed on the bracket; one end of the flipping connecting rod is fixedly arranged on the front hatch or the rear hatch of the corresponding drone accommodation chamber; both ends of the connecting plate are respectively hinged to the other end of the flipping connecting rod and the driving end of the hatch flipping electric cylinder; the limiting guide rail is arranged above the connecting plate and is fixedly connected to the bracket; one end of the slider is fixedly connected to the end of the connecting plate away from the flipping connecting rod, and the other end is slidably connected to the limiting guide rail.

[0012] In a possible implementation, the limiting guide rail, the flipping connecting rod, and the connecting plate are each provided with a plurality of weight reduction holes along their lengths.

[0013] In a possible implementation, the integrated launch box with storage, transportation, and launch functions further includes a plurality of external maintenance hatches; each external maintenance hatch is arranged between the corresponding rear hatch and the equipment chamber; the external maintenance hatch and the corresponding rear hatch form the rear sealing structure of the drone accommodation chamber; the external maintenance hatch is provided with a double-layer tempered glass observation window, and an environmental sensor is integrated on its inner side for monitoring the temperature and humidity inside the drone accommodation chamber.

[0014] In a possible implementation, the integrated launch box with storage, transportation, and launch functions further includes a plurality of folding ladders; the folding ladders are arranged between the rear hatch and the external maintenance hatch of the corresponding drone accommodation chamber.

[0015] One or more technical solutions provided in the embodiments of the present application have at least the following technical effects:

[0016] The integrated launch box with storage, transportation and launch functions provided by the present application includes a cabin, a base and an erection device. The present application breaks through the limitations of the traditional fixed ground launch device, which has a solidified mission mode and insufficient environmental adaptability. In emergency scenarios such as disaster relief, the launch box can be quickly deployed to the disaster-stricken area with the transportation tool, without the need to build an additional launch platform, to achieve instant storage, transportation and launch of the drone, significantly shorten the mission response time, and meet the high-timeliness mission requirements such as real-time reconnaissance and material delivery. In response to the problem of disconnection between energy replenishment and launch processes in traditional launch devices, the present application integrates an automatic refueling device in the equipment cabin, which can directly provide fuel filling services for drones, avoiding the cumbersome operation of transferring drones to dedicated refueling stations. This design simplifies the equipment deployment process, reduces the mission preparation time, improves the collaborative efficiency of drone energy replenishment and launch processes, and ensures that drones can quickly and reliably perform take-off and landing and energy replenishment in emergency missions. The launch box adopts a detachable connection design between the cabin and the base, and cooperates with the erection device to flip the cabin to a preset launch angle, so that the drone system can adapt to the launch requirements under different terrain and environmental conditions. In addition, the double cabins (first cabin and second cabin) and multi-layer UAV accommodating chambers set inside the square cabin can accommodate multiple UAVs at the same time, and realize multi-machine collaborative operation through the mission planning terminal, communication relay equipment and UAV status monitoring device in the command cabin, which significantly improves the mission execution capability and environmental adaptability of the UAV system. The generator cabin and toolbox set in the pod provide independent power supply and maintenance support capabilities for the UAV system, further enhancing the independence and reliability of the system. The hoisting corners set circumferentially on the top of the square cabin facilitate the overall hoisting and transportation of the launch box, improving the convenience of equipment deployment. This highly integrated design not only simplifies the equipment structure, but also reduces the complexity of the system, helps to reduce maintenance costs and improve overall combat effectiveness. The design of the launch box of this application fully considers the diversified application needs of UAV technology in disaster relief, logistics transportation, agricultural plant protection, environmental monitoring and other fields. By integrating storage, transportation, launch, energy supply, mission planning, communication relay and status monitoring functions, the launch box can provide all-round support for the UAV system, meet the mission requirements in different application scenarios, and promote the further popularization and application expansion of UAV technology. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following is a brief introduction to the drawings required for use in the description of the embodiments of the present application. Obviously, the drawings described below are some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0018] Figure 1Schematic diagram of the integrated launch box with storage, transportation and launch functions provided by the embodiment of the present application;

[0019] Figure 2 Schematic diagram of the erection device provided by the embodiment of the present application;

[0020] Figure 3 Schematic diagram of the leveling device provided by the embodiment of the present application;

[0021] Figure 4 Schematic diagram of the equipment compartment provided by the embodiment of the present application;

[0022] Figure 5 Schematic diagram of the automatic fueling device provided by the embodiment of the present application;

[0023] Figure 6 Schematic diagram of the controller provided by the embodiment of the present application;

[0024] Figure 7 Schematic diagram of the left side of the shelter provided by the embodiment of the present application;

[0025] Figure 8 Schematic diagram of the right side of the shelter provided by the embodiment of the present application;

[0026] Figure 9 Schematic diagram of the installation position of the folding ladder of the shelter provided by the embodiment of the present application;

[0027] Figure 10 Schematic diagram of the folding ladder of the shelter provided by the embodiment of the present application;

[0028] Figure 11 Schematic diagram of the shelter when the hatch driving mechanism is in the closed state provided by the embodiment of the present application;

[0029] Figure 12 Schematic diagram of the shelter when the hatch driving mechanism is in the fully opened position provided by the embodiment of the present application.

[0030] Icons: 1 - Mobile Cabin; 11 - Command Cabin; 12 - First Cabin; 121 - UAV Accommodation Chamber; 13 - Equipment Cabin; 131 - Electrical Control System; 132 - Automatic Refueling Device; 1321 - Gasoline Oil Tank; 1322 - Lubricating Oil Tank; 1323 - Controller; 1324 - Gasoline Oil Pump; 1325 - Lubricating Oil Pump; 1326 - Multi-channel Mixing and Distribution Pipeline; 1327 - First Flowmeter; 1328 - Second Flowmeter; 1329 - Electric Control Switch Valve; 13291 - First Check Valve; 13292 - Second Check Valve; 13293 - Filter; 14 - Second Cabin; 15 - Pod; 151 - Generator Cabin; 152 - Toolbox; 2 - Base; 3 - Erection Device; 4 - Anti-overturning Support; 5 - Levelling Device; 6 - Hatch Driving Mechanism; 61 - Flipping Connecting Rod; 62 - Limit Guide Rail; 63 - Slide Block; 64 - Connecting Plate; 65 - Bracket; 66 - Hatch Flipping Electric Cylinder; 67 - Weight Reduction Hole; 7 - Outer Maintenance Hatch; 8 - Folding Ladder; 9 - Access Ladder. Detailed Implementation Manner

[0031] Next, the technical solutions in the embodiments of the present application will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the scope of protection of the present application.

[0032] In the description of the embodiments of the present application, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing the embodiments of the present application 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 cannot be understood as a limitation to the present application. The terms "first", "second", and "third" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance. In addition, the terms "installation", "connection", and "connection" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present application can be understood according to specific circumstances.

[0033] The embodiments of the present application provide an integrated launch box with storage, transportation, and launch functions, such as Figures 1 to 12As shown in the figure. The launch box includes a shelter 1, a base 2, and an erection device 3. The base 2 is detachably connected to the transportation vehicle. Specifically, the base 2 is connected to the transportation vehicle by a suspension lock structure. The outer dimensions of the launch box are 6056×2389×2480 mm. The launch box can be transported by any transportation vehicle capable of transporting a 6-meter shelter 1 or container. The fixing method of the unmanned aerial vehicle in the shelter 1 can meet various vibration and shock requirements faced under normal transportation conditions.

[0034] One side of the shelter 1 is rotatably connected to one side of the top surface of the base 2, and the other side is connected to the base 2 through the erection device 3. Specifically, the launch box of the present application further includes a locking mechanism, which adopts an innovative three-outward-turning design. This design has many advantages such as simple structure and convenient operation. In the actual application scenario, when it is necessary to fix the shelter 1 and the base 2, only need to accurately install these three outward-turning locking mechanisms in place, then the reliable connection between the shelter 1 and the base 2 can be achieved, effectively preventing the relative movement between the shelter 1 and the base 2 during transportation, launching and other processes. When it is necessary to adjust the connection state between the shelter 1 and the base 2, the staff only need to operate the manual simple bolt to easily complete the unlocking operation; conversely, when it is necessary to re-fix, the locking can also be achieved by operating the manual simple bolt, and the shelter 1 and the base 2 are firmly connected again. This design not only improves the overall stability and reliability of the launch box, but also simplifies the operation process and reduces the operation difficulty.

[0035] One end of the erection device 3 is fixed to the base 2, and the other end extends into the equipment compartment 13 in the shelter 1, and is used to drive the shelter 1 to flip to a preset launch angle. Inside the shelter 1, a first cabin 12, an equipment compartment 13, a second cabin 14, and a command cabin 11 are sequentially arranged along the length direction. Multiple layers of unmanned aerial vehicle accommodation chambers 121 are provided in both the first cabin 12 and the second cabin 14. An electrical control system 131 and an automatic refueling device 132 are provided in the equipment compartment 13, and the automatic refueling device 132 is used to refuel multiple unmanned aerial vehicles. The command cabin 11 is internally provided with a mission planning terminal, a communication relay device, and an unmanned aerial vehicle status monitoring device. A pod 15 is hoisted at the rear of the shelter 1. A generator compartment 151 and a toolbox 152 are provided in the pod 15. The generator is arranged in the generator compartment 151 and is electrically connected to the electrical control system 131 of the equipment compartment 13. The present application is equipped with a 3kw generator to meet two power supply modes: mains power and self-generated power.

[0036] Lifting corner fittings are circumferentially arranged on the top of the shelter 1 for overall lifting and transportation.

[0037] Both the first cabin 12 and the second cabin 14 of this application are provided with four layers of UAV accommodation chambers 121, so as to realize the storage, transportation and launching functions of eight UAVs. The shelter 1 of this application has certain airtightness and heat insulation functions, as well as the ability to prevent salt spray, rust and mildew, and can meet the requirement that the effective storage life can reach more than 5 years after proper maintenance under the specified storage conditions.

[0038] Hooks are provided on both the rear side and the left side of the base 2 of this application for installing the boarding ladder 9. The boarding ladder 9 is installed in the middle of the tool cabin and the generator cabin 151, and can be removed by opening the lower lock.

[0039] It should be noted that the launch box of the present application integrates the functions of storage, transportation, and launch, breaking through the limitations of the traditional fixed ground launch device with a rigid mission mode and insufficient environmental adaptability. In emergency scenarios such as disaster relief, the launch box can be quickly deployed to the affected area with a transportation vehicle, eliminating the need for additional construction of a launch platform, enabling instant storage, transportation, and launch of drones, significantly shortening the mission response time, and meeting the requirements of high-timeliness tasks such as real-time reconnaissance and material delivery. To address the issue of the disconnection between energy supply and launch process in traditional launch devices, the present application integrates an automatic refueling device 132 in the equipment compartment 13, which can directly provide fuel filling services for drones, avoiding the cumbersome operations of transferring drones to dedicated refueling stations. This design simplifies the equipment deployment process, reduces the mission preparation time, improves the coordination efficiency of the drone energy supply and launch process, and ensures that drones can quickly and reliably take off, land, and refuel during emergency missions. The launch box adopts a detachable connection design between the shelter 1 and the base 2, and with the erection device 3, the shelter 1 can be flipped to a preset launch angle, enabling the drone system to adapt to launch requirements under different terrains and environmental conditions. In addition, the double cabins (the first cabin 12 and the second cabin 14) and the multi-layer drone accommodation chambers 121 provided inside the shelter 1 can accommodate multiple drones simultaneously, and through the mission planning terminal, communication relay equipment, and drone status monitoring device in the command cabin 11, multi-aircraft collaborative operations can be achieved, significantly enhancing the mission execution ability and environmental adaptability of the drone system. The generator cabin 151 and the toolbox 152 provided in the pod 15 provide independent power supply and maintenance support capabilities for the drone system, further enhancing the independence and reliability of the system. The lifting corner fittings circumferentially arranged on the top of the shelter 1 facilitate the overall lifting and transportation of the launch box, improving the convenience of equipment deployment. This highly integrated design not only simplifies the equipment structure but also reduces the system complexity, helping to reduce the maintenance cost and improve the overall combat effectiveness. The design of the launch box of the present application fully considers the diverse application requirements of drone technology in fields such as disaster relief, logistics transportation, agricultural plant protection, and environmental monitoring. By integrating functions such as storage, transportation, launch, energy supply, mission planning, communication relay, and status monitoring, the launch box can provide comprehensive support for the drone system, meet the mission requirements in different application scenarios, and promote the further popularization and application expansion of drone technology.

[0040] In the embodiment of the present application, the integrated launch box with storage, transportation, and launch functions further includes a plurality of anti-overturning supports 4. One end of each of the plurality of anti-overturning supports 4 is hinged to the side wall of the base 2, and the other end thereof abuts against the ground. The plurality of anti-overturning supports 4 are symmetrically distributed on both sides of the erection device 3.

[0041] During the launch process, the shelter 1 needs to withstand the huge reaction forces brought about by actions such as the erection and launch of the UAV. The presence of multiple anti-overturning supports 4 can provide additional support and restraint for the shelter 1, effectively reducing the sway and displacement of the shelter 1 during the launch process, and ensuring the accuracy and stability of the launch angle.

[0042] In the embodiment of the present application, the integrated launch box with storage, transportation and launch functions further includes a plurality of leveling devices 5. The plurality of leveling devices 5 are detachably arranged circumferentially at the bottom of the base 2. The leveling devices 5 can be stored in the toolbox 152 of the pod 15 in the non-use state. This design makes full use of the internal space of the launch box, avoids the leveling devices 5 occupying extra space during transportation, and also protects the leveling devices 5 from damage by the external environment. When needed, they can be conveniently taken out from the toolbox 152 and installed, improving the operation convenience.

[0043] In the embodiment of the present application, the automatic fueling device 132 includes a controller 1323, a gasoline oil tank 1321, a lubricating oil tank 1322, a gasoline oil pump 1324, a lubricating oil pump 1325 and a multi-channel mixing and distribution pipeline 1326. The gasoline oil pump 1324 and the lubricating oil pump 1325 are both installed on the ground of the equipment compartment 13. The input end of the gasoline oil pump 1324 is connected to the output end of the gasoline oil tank 1321 through a first oil pipeline, and the output end is connected to the input end of the multi-channel mixing and distribution pipeline 1326 through a first flowmeter 1327 and a first check valve 13291. The input end of the lubricating oil pump 1325 is connected to the output end of the lubricating oil tank 1322 through a second oil pipeline, and the output end is connected to the input end of the multi-channel mixing and distribution pipeline 1326 through a second check valve 13292. The multiple output ends of the multi-channel mixing and distribution pipeline 1326 are docked with the corresponding UAV fuel tank interfaces, and electric control switch valves 1329 and second flowmeters 1328 are arranged at the multiple output ends of the multi-channel mixing and distribution pipeline 1326. The gasoline oil pump 1324 is a fixed-displacement impeller pump, and the lubricating oil pump 1325 is a fixed-displacement magnetic pump driven by a servo motor. The controller 1323 is electrically connected to the gasoline oil pump 1324, the lubricating oil pump 1325, the first flowmeter 1327, the second flowmeter 1328 and the electric control switch valve 1329. The controller 1323 is arranged in the electrical control system 131. The controller 1323 generates a lubricating oil supply instruction based on the gasoline flow signal collected by the first flowmeter 1327, and drives the servo motor to adjust the speed of the fixed-displacement magnetic pump through a preset fuel-lubricating oil mixing ratio algorithm.

[0044] Specifically, the automatic fueling device 132 of the present application can accurately achieve the mixing of gasoline and lubricating oil at a fixed ratio of 40:1. Based on the gasoline flow signal collected by the first flowmeter 1327, the controller 1323 uses a preset fuel-lubricating oil mixing ratio algorithm to accurately generate a lubricating oil supply command and drive the servo motor to adjust the rotation speed of the metering magnetic pump (lubricating oil pump 1325), thereby ensuring that the two oils are strictly mixed according to the set ratio. This precise mixing ratio is crucial for the normal operation of the drone, can provide fuel with optimal performance for the drone's engine, ensure the stable operation of the engine, and extend the service life of the engine. The design of the multi-channel mixing and distribution pipeline 1326 enables the full mixing of gasoline and lubricating oil during transportation. After the evenly mixed oil enters the drone fuel tank, it can better adapt to the working requirements of the engine, reduce engine failures caused by uneven oil mixing, such as incomplete combustion and carbon deposition, and improve the overall performance and reliability of the drone.

[0045] The multiple output ends of the multi-channel mixing and distribution pipeline 1326 are docked with the corresponding drone fuel tank interfaces, and a flowmeter and an electric control switch valve 1329 are set for each path. This design enables multiple drone fuel tanks to be refueled simultaneously, and each path is independent and does not interfere with each other. During the refueling process, the controller 1323 can collect the refueling flow of each path in real time and accumulate and calculate the refueling amount. When a specified refueling amount is reached for a certain path, the controller 1323 automatically controls the electric control switch valve 1329 of this path to close, and the refueling of this path of oil ends. This efficient refueling method shortens the refueling time of the drone and improves the task execution efficiency, especially in scenarios where multiple drones need to be refueled simultaneously, the advantage is more obvious.

[0046] In the embodiment of the present application, the integrated launch box with storage, transportation, and launch functions further includes two filters 13293. The two filters 13293 are respectively installed between the output end of the gasoline oil tank 1321 and the input end of the gasoline pump 1324, and between the output end of the lubricating oil tank 1322 and the input end of the lubricating oil pump 1325, forming a two-stage filtration system.

[0047] In the embodiment of the present application, the gasoline oil tank 1321 and the lubricating oil tank 1322 are fixedly arranged side by side in the equipment compartment 13 and are located above the corresponding gasoline pump 1324 and lubricating oil pump 1325. The lengths of the first oil pipeline and the second oil pipeline are equal. This design has various considerations, mainly to ensure smooth oil absorption and mixing synchronization.

[0048] From the perspective of smooth oil suction, the gasoline oil tank 1321 and the lubricating oil tank 1322 are arranged above the corresponding gasoline oil pump 1324 and lubricating oil pump 1325, making clever use of the gravity to assist the delivery of oil to the corresponding oil pumps. When the gasoline oil pump 1324 and the lubricating oil pump 1325 are started, the oil in the gasoline oil tank 1321 and the lubricating oil tank 1322 can flow into the gasoline oil pump 1324 and the lubricating oil pump 1325 at a faster speed under the natural action of gravity. This gravity-assisted oil supply method effectively reduces the suction lift of the gasoline oil pump 1324 and the lubricating oil pump 1325. The reduction of the suction lift means that the resistance that the oil pump needs to overcome when pumping oil is reduced, thereby reducing the energy consumption of the gasoline oil pump 1324 and the lubricating oil pump 1325. In addition, since the oil pump does not need to "exert too much force" to suck oil, the wear on its internal mechanical components is also correspondingly reduced, which helps to extend the service life of the oil pump.

[0049] In terms of the synchronism of oil mixing, the design that the lengths of the first oil delivery pipeline and the second oil delivery pipeline are equal is crucial. During the oil delivery process, pipelines of equal length can ensure that factors such as the resistance and pressure changes experienced by gasoline and lubricating oil in the delivery path are basically the same. This enables gasoline and lubricating oil to flow from their respective oil tanks to the multi-channel mixing and distribution pipeline 1326 at similar flow rates, thus ensuring their synchronism during mixing. If the lengths of the two oil delivery pipelines are inconsistent, the longer pipeline will cause an increase in the oil delivery resistance and a slowdown in the flow rate, resulting in different arrival times of gasoline and lubricating oil at the mixing point, affecting the accuracy of the mixing ratio and reducing the mixing effect. However, this design of the present application effectively avoids the occurrence of such problems and provides a strong guarantee for the precise mixing of gasoline and lubricating oil.

[0050] The connection between the automatic refueling device 132 and the unmanned aerial vehicle is made by a quick connector. After refueling, it can be quickly disassembled manually, and the quick connector is fixed at a certain position on one side inside the accommodation chamber 121 of the unmanned aerial vehicle.

[0051] In the embodiments of the present application, the integrated launch box with storage, transportation, and launch functions further includes a plurality of hatch driving mechanisms 6. The plurality of hatch driving mechanisms 6 are used to control the front hatch and the rear hatch of the corresponding drone accommodation chamber 121. The hatch driving mechanism 6 includes a flipping connecting rod 61, a limiting guide rail 62, a slider 63, a connecting plate 64, a bracket 65, and a hatch flipping electric cylinder 66. The bracket 65 is fixedly connected inside the corresponding drone accommodation chamber 121. The hatch flipping electric cylinder 66 is fixedly installed on the bracket 65. One end of the flipping connecting rod 61 is fixedly arranged on the front hatch or the rear hatch of the corresponding drone accommodation chamber 121. The two ends of the connecting plate 64 are respectively hinged to the other end of the flipping connecting rod 61 and the driving end of the hatch flipping electric cylinder 66. The limiting guide rail 62 is arranged above the connecting plate 64 and is fixedly connected to the bracket 65. One end of the slider 63 is fixedly connected to the end of the connecting plate 64 away from the flipping connecting rod 61, and the other end is slidably connected to the limiting guide rail 62.

[0052] It should be noted that when the launch box is in the closed state, the front hatch and the rear hatch of the drone accommodation chamber 121 are in the closed position. At this time, the hatch flipping electric cylinder 66 is in the contracted state. The connecting plate 64 maintains a relatively stable position through the hinges with the flipping connecting rod 61 and the driving end of the hatch flipping electric cylinder 66. The position of the slider 63 on the limiting guide rail 62 is also at the initial set point, ensuring that the entire hatch driving mechanism 6 is in a stable static state.

[0053] When the front hatch or the rear hatch needs to be opened, the hatch flipping electric cylinder 66 starts to extend, and its driving end pushes one end of the connecting plate 64. Since the connecting plate 64 is hinged to the other end of the flipping connecting rod 61, as the connecting plate 64 moves, it will drive the flipping connecting rod 61 to rotate around its end fixed to the front hatch or the rear hatch.

[0054] At the same time, the slider 63 fixedly connected to the end of the connecting plate 64 away from the flipping connecting rod 61 slides on the limiting guide rail 62. The limiting guide rail 62 plays a role in guiding and restricting the movement trajectory of the slider 63, ensuring that the connecting plate 64 moves in a predetermined direction and angle. As the connecting plate 64 moves, the flipping connecting rod 61 drives the front hatch or the rear hatch to rotate around its connection point with the drone accommodation chamber 121, realizing the opening of the front hatch or the rear hatch.

[0055] The slider 63 of the present application enables the hatch flipping electric cylinder 66 to only perform reciprocating linear motion.

[0056] In the embodiments of the present application, a plurality of weight reduction holes 67 are provided along the length direction of the limiting guide rail 62, the flipping connecting rod 61, and the connecting plate 64.

[0057] In the embodiments of the present application, the integrated launch box with storage, transportation, and launch functions further includes a plurality of outer maintenance hatches 7. Each outer maintenance hatch 7 is disposed between the corresponding rear hatch and the equipment compartment 13. The outer maintenance hatch 7 and the corresponding rear hatch form a rear sealing structure of the UAV accommodation chamber 121. The outer maintenance hatch 7 is provided with a double-layer tempered glass observation window, and an environmental sensor is integrated on its inner side for monitoring the temperature and humidity in the UAV accommodation chamber 121.

[0058] Each outer maintenance hatch 7 is disposed between the corresponding rear hatch and the equipment compartment 13, forming an independent maintenance passage. When it is necessary to perform maintenance on the equipment or UAV in the UAV accommodation chamber 121, there is no need to open the entire rear hatch, and only the outer maintenance hatch 7 needs to be opened. The double-layer tempered glass observation window provided on the outer maintenance hatch 7 enables the operator to observe the state of the UAV in the UAV accommodation chamber 121 in real time, including the attitude of the UAV and whether there is any damage to its appearance.

[0059] In the embodiments of the present application, the integrated launch box with storage, transportation, and launch functions further includes a plurality of folding ladders 8. The folding ladders 8 are disposed between the rear hatch of the corresponding UAV accommodation chamber 121 and the outer maintenance hatch 7. Its design purpose is to provide convenience for the staff, facilitating the staff to enter the shelter 1 for maintenance operations and perform maintenance work on the UAV. When in a non-working state, the folding ladders 8 can be easily flipped and retracted, and have a reliable mechanical locking function to ensure that the ladders remain stable during the movement and transportation of the launch box and will not accidentally unfold, thus ensuring the safety of personnel and equipment.

[0060] The various embodiments in this specification are described in a progressive manner. For the same or similar parts between the various embodiments, reference can be made to each other. The key points of each embodiment are the differences from other embodiments.

[0061] The above embodiments are only used to illustrate the technical solutions of the present application and do not limit the present application. Although the present application has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements on some or all of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the present application.

Claims

1. An integrated launch box with storage, transportation and launch functions, characterized in that: It comprises a shelter (1), a base (2) and an erecting device (3); The base (2) is detachably connected to a transportation vehicle; One side of the cabin (1) is rotatably connected to one side of the top surface of the base (2), and the other side is connected to the base (2) via the erecting device (3); One end of the erecting device (3) is fixed to the base (2), and the other end extends into the equipment compartment (13) in the cabin (1), and is used to drive the cabin (1) to flip to a preset launch angle; The interior of the square cabin (1) is provided with a first cabin (12), an equipment cabin (13), a second cabin (14) and a command cabin (11) in sequence along the length direction; The first cabin (12) and the second cabin (14) are both provided with a multi-layered drone accommodating chamber (121); An electrical control system (131) and an automatic refueling device (132) are arranged in the equipment cabin (13), and the automatic refueling device (132) is used to refuel a plurality of drones; The command cabin (11) has a built-in mission planning terminal, communication relay equipment and a drone status monitoring device; A pod (15) is suspended on the rear side of the square cabin (1); The pod (15) is provided with a generator compartment (151) and a tool box (152); A lifting corner piece is arranged around the top of the square cabin (1).

2. The integrated launch box with storage, transportation and launch functions according to claim 1 is characterized in that: Also includes a plurality of anti-overturning supports (4); One end of each of the anti-overturning supports (4) is hinged to the side wall of the base (2), and the other end thereof is in contact with the ground. The anti-overturning supports (4) are symmetrically distributed on both sides of the erecting device (3).

3. The integrated launch box with storage, transportation and launch functions according to claim 1 is characterized in that: Also includes a plurality of leveling devices (5); A plurality of the leveling devices (5) are detachably arranged on the circumference of the bottom of the base (2); The leveling device (5) can be stored in a tool box (152) of the pod (15) when not in use.

4. The integrated launch box with storage, transportation and launch functions according to claim 1 is characterized in that: The automatic refueling device (132) comprises a controller (1323), a gasoline tank (1321), a lubricating oil tank (1322), a gasoline pump (1324), a lubricating oil pump (1325) and a multi-channel mixing distribution pipeline (1326); The gasoline pump (1324) and the lubricating oil pump (1325) are both installed on the ground of the equipment cabin (13); The input end of the gasoline pump (1324) is connected to the output end of the gasoline tank (1321) through a first oil pipeline, and the output end is connected to the input end of the multi-channel mixing distribution pipeline (1326) through a first flow meter (1327) and a first check valve (13291); The input end of the lubricating oil pump (1325) is connected to the output end of the lubricating oil tank (1322) through a second oil pipeline, and the output end is connected to the input end of the multi-channel mixing distribution pipeline (1326) through a second check valve (13292); The multiple output ends of the multi-channel mixing distribution pipeline (1326) are connected to the corresponding UAV fuel tank interface, and the multiple output ends of the multi-channel mixing distribution pipeline (1326) are all provided with an electrically controlled switch valve (1329) and a second flow meter (1328); The gasoline pump (1324) is a quantitative impeller pump, and the lubricating oil pump (1325) is a quantitative magnetic pump driven by a servo motor; The controller (1323) is electrically connected to the gasoline pump (1324), the lubricating oil pump (1325), the first flow meter (1327), the second flow meter (1328) and the electrically controlled switch valve (1329); The controller (1323) is arranged in the electrical control system (131); based on the gasoline flow signal collected by the first flow meter (1327), the controller (1323) generates a lubricating oil supply instruction through a preset fuel-lubricating oil mixing ratio algorithm, and drives the servo motor to adjust the rotation speed of the quantitative magnetic pump.

5. The integrated launch box with storage, transportation and launch functions according to claim 4 is characterized in that: Also included are two filters (13293); The two filters (13293) are respectively installed between the output end of the gasoline tank (1321) and the input end of the gasoline pump (1324), and between the output end of the lubricating oil tank (1322) and the input end of the lubricating oil pump (1325).

6. The integrated launch box with storage, transportation and launch functions according to claim 4 is characterized in that: The gasoline tank (1321) and the lubricating oil tank (1322) are fixedly arranged side by side in the equipment cabin (13), and are located above the corresponding gasoline pump (1324) and the lubricating oil pump (1325); The first oil pipeline and the second oil pipeline are equal in length.

7. The integrated launch box with storage, transportation and launch functions according to claim 1, characterized in that: It also includes a plurality of hatch cover driving mechanisms (6); the plurality of hatch cover driving mechanisms (6) are used to control the corresponding front hatch covers and rear hatch covers of the drone accommodating chamber (121); The hatch cover driving mechanism (6) comprises a flip connecting rod (61), a limiting guide rail (62), a sliding block (63), a connecting plate (64), a bracket (65) and a hatch door flipping electric cylinder (66); The bracket (65) is fixedly connected to the corresponding drone accommodating chamber (121); The door flipping electric cylinder (66) is fixedly mounted on the bracket (65); One end of the flip connection rod (61) is fixedly arranged on the front hatch or the rear hatch of the corresponding drone accommodating chamber (121); The two ends of the connecting plate (64) are respectively hinged to the other end of the flip connecting rod (61) and the driving end of the cabin door flip electric cylinder (66); The limiting guide rail (62) is arranged above the connecting plate (64) and is fixedly connected to the bracket (65); One end of the sliding block (63) is fixedly connected to an end of the connecting plate (64) away from the flip connecting rod (61), and the other end is slidably connected to the limiting guide rail (62).

8. The integrated launch box with storage, transportation and launch functions according to claim 7 is characterized in that: The position-limiting guide rail (62), the flip connecting rod (61), and the connecting plate (64) are all provided with a plurality of weight-reducing holes (67) along their length directions.

9. The integrated launch box with storage, transportation and launch functions according to claim 7, characterized in that: Also included are a plurality of external inspection hatch covers (7); Each of the external inspection hatch covers (7) is arranged between the corresponding rear hatch cover and the equipment cabin (13); The external inspection hatch cover (7) and the corresponding rear hatch cover constitute a rear sealing structure of the drone accommodating chamber (121); The external inspection hatch cover (7) is provided with a double-layer tempered glass observation window, and an environmental sensor is integrated inside the window for monitoring the temperature and humidity inside the drone accommodation chamber (121).

10. The integrated launch box with storage, transportation and launch functions according to claim 9, characterized in that: Also includes a plurality of foldable step ladders (8); The foldable step ladder (8) is arranged between the rear hatch cover and the external inspection hatch cover (7) corresponding to the drone accommodating chamber (121).

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