Charging device for vertical take-off and landing aircraft

Abstract

The invention provides a charging device for a vertical take-off and landing aircraft, and belongs to the technical field of take-off and landing aircrafts, and the charging device for the vertical take-off and landing aircraft is composed of a main cabinet, a charging terminal, an automatic charging interface and a ground induction type opening and closing cover plate. The main cabinet is responsible for voltage conversion and charging control and is connected with a plurality of charging terminals. The automatic charging interface realizes five-degree-of-freedom movement through a telescopic arm, a base turntable, a fine adjustment sliding rail, a mechanical arm, a guide cylinder, a rotating assembly, a driving assembly and the like, and is accurately butted with an aircraft; the induction type opening and closing cover plate consists of an inductor and a cover plate, and is controlled by the inductor; the system is designed to be used for automatically charging the vertical take-off and landing aircraft and is provided with a liquid cooling system and a terminal control system, and efficient charging is ensured; the aircraft charging device and the aircraft can be automatically docked, the environmental adaptability is high, and the safety is high.

Description

Technical Field

[0001] The present invention belongs to the technical field of take-off and landing aircraft, and in particular, relates to a charging device for a vertical take-off and landing aircraft. Background Art

[0002] With the continuous advancement of science and technology, vertical take-off and landing aircraft (VTOL aircraft for short) has become one of the important directions of development in the current aviation field. Compared with traditional fixed-wing aircraft, vertical take-off and landing aircraft have the advantages of simple take-off and landing, flexible flight, and strong maneuverability, showing broad application prospects in many fields such as urban transportation, rescue search, and military applications.

[0003] The battery power supply system of a vertical take-off and landing aircraft is one of its core components. Since vertical take-off and landing aircraft require a lot of energy when taking off and landing, and they consume power quickly during flight, the problem of battery charging has become a key factor affecting its practicality. At present, there are two common ways to charge vertical take-off and landing aircraft: one is manual charging, that is, connecting the battery pack to the charging equipment through manual operation on the ground to complete the charging process; the other is automatic docking charging, which uses the charging interface to automatically dock to a dedicated charging pile to complete charging.

[0004] Manual charging requires pilots or ground staff to perform tedious charging operations, which is not only inefficient but also poses certain safety risks. Although automatic docking charging can improve charging efficiency, there are some problems with the existing technology: first, the charging interface requires high alignment accuracy, which is difficult to adapt to the random docking position of vertical take-off and landing aircraft; second, the charging device is easily affected by harsh environments (such as dust, moisture, etc.) and has poor safety; third, there is a lack of perfect temperature monitoring and safety protection mechanisms, which is prone to overload, overheating and other faults.

[0005] Therefore, it is very necessary to develop a vertical take-off and landing aircraft charging device that can automatically dock and charge, has strong environmental adaptability, and is safe and reliable. Summary of the invention

[0006] In view of this, the present invention provides a charging device for a vertical take-off and landing aircraft, which can automatically dock the aircraft charging device with the aircraft, has strong environmental adaptability and high safety.

[0007] The present invention is achieved in that:

[0008] The present invention provides a charging device for a vertical take-off and landing aircraft, comprising:

[0009] Main cabinet, charging terminal, automatic charging interface, inductive opening and closing cover;

[0010] The main cabinet includes a main cabinet control system, a liquid-cooled charging module, an AC / DC input system, a DC output system, and a liquid cooling system; the main cabinet control system communicates with the liquid-cooled charging module and the terminal control system in the charging terminal to control the input and output of the liquid-cooled charging module and convert the AC or DC input system voltage into a charging voltage suitable for the vertical take-off and landing aircraft; the main cabinet is connected to a plurality of the charging terminals;

[0011] The charging terminal includes a charging interface liquid cooling system, a main cabinet connection device, a charging interface connection device, and a terminal control system;

[0012] The automatic charging interface includes a telescopic arm, a base turntable, a fine-tuning slide rail, a mechanical arm, a guide cylinder, a rotating component, a control and drive component, a winch, an aircraft interface sensor, and a charging interface; the automatic charging interface realizes 5-degree-of-freedom movement;

[0013] The inductive opening and closing cover comprises a sensor and a cover;

[0014] The main cabinet, the charging terminal, and the automatic charging interface are all installed underground, and the inductive opening and closing cover is installed on the ground;

[0015] Among them, the telescopic arm is used for the vertical lifting and lowering of the automatic charging interface and extending out of the ground; the base turntable is placed on the base, driving the mechanical structure above the base to rotate 360 ​​degrees freely; the fine-tuning slide rail includes a horizontal fine-tuning slide rail and a vertical fine-tuning slide rail, the horizontal fine-tuning slide rail is used to adjust the coordinates of the charging interface, and the vertical fine-tuning slide rail is used for the free plugging of the charging interface and the aircraft after the coordinates and angles are adjusted; the mechanical arm is installed with the fine-tuning slide rail; the guide cylinder has the rotating assembly and the aircraft interface sensor built in, and the aircraft interface sensor provides the interface target position coordinates; the rotating assembly adjusts the angle of the charging interface; the winch is placed in the base, used to reel in and unroll the connecting cable to control the release length of the connecting cable; the control and drive assembly is placed in the base, used to control the motion trajectory of each mechanical structure and provide power output.

[0016] On the basis of the above technical solution, the charging device for a vertical take-off and landing aircraft of the present invention can also be improved as follows:

[0017] Wherein, the heat generated by the liquid-cooled charging module and the charging interface is naturally dissipated through the liquid cooling system via the ambient temperature difference;

[0018] The automatic charging interface meets the requirements of automatic charging and docking within a certain radius coverage;

[0019] When the sensor senses that the charging port is lifted or lowered, the cover automatically opens and closes.

[0020] Furthermore, when the aircraft needs to be recharged, the automatic charging interface rises, the inductive opening and closing cover automatically opens, the automatic charging interface rises to the ground and adjusts the position coordinates and angle of the charging interface, automatically docks with the aircraft, and completes charging.

[0021] Furthermore, the main cabinet also includes a cooling fan system, a temperature monitoring system, and a safety protection system;

[0022] The heat dissipation fan system is arranged inside the main cabinet for forced convection heat dissipation;

[0023] The temperature monitoring system includes a plurality of temperature sensors, which are distributed at a plurality of locations inside the main cabinet to monitor the temperature of each component in real time;

[0024] The safety protection system includes an overcurrent protection module, an overvoltage protection module, and a short circuit protection module, which are used to cut off power supply in abnormal situations.

[0025] Furthermore, the automatic charging interface also includes a dustproof and waterproof component, a buffer shock absorption component, and an emergency power-off component;

[0026] The dustproof and waterproof component is arranged outside the automatic charging interface to prevent dust and moisture from entering;

[0027] The buffer shock-absorbing component is arranged at the contact part between the automatic charging interface and the ground, so as to reduce the influence of ground vibration on the charging process;

[0028] The emergency power-off component is electrically connected to the charging interface and is used to quickly cut off power in an emergency.

[0029] Furthermore, the heat dissipation fan system includes a main fan, an auxiliary fan, and an air duct;

[0030] The main fan is arranged at the back of the main cabinet and is used to extract external cold air;

[0031] The auxiliary fan is arranged in a hot spot area inside the main cabinet for local forced convection;

[0032] The air duct runs through the interior of the main cabinet to guide the airflow through each heating element;

[0033] The temperature monitoring system also includes a temperature display screen, which is arranged outside the main cabinet and displays the internal temperature status in real time;

[0034] The safety protection system also includes a leakage protector, which is connected in series with the power input terminal of the main cabinet to detect leakage and cut off the power supply in time.

[0035] Furthermore, the main fan of the cooling fan system is a variable speed fan, which automatically adjusts the speed according to the temperature detected by the temperature monitoring system;

[0036] The temperature monitoring system also includes a temperature alarm module, which triggers an audible and visual alarm when the detected temperature exceeds a preset threshold;

[0037] The safety protection system also includes an insulation monitoring module, which continuously monitors the insulation resistance between each conductive component inside the main cabinet and the ground. When the insulation resistance is lower than a safe value, an alarm is triggered and the power supply is cut off.

[0038] Furthermore, the dustproof and waterproof component includes a sealing ring, a waterproof coating, and a drainage hole;

[0039] The sealing ring is arranged at the edge of the automatic charging interface in contact with the ground to form a sealing barrier;

[0040] The waterproof coating covers the outer surface of the automatic charging interface to enhance the waterproof performance;

[0041] The drainage hole is provided at the bottom of the automatic charging interface for draining the moisture that may be accumulated;

[0042] The buffer shock absorbing assembly includes a shock absorbing pad, a spring shock absorber, and a hydraulic shock absorber;

[0043] The shock-absorbing pad is arranged at the bottom of the automatic charging interface to absorb small vibrations;

[0044] The spring shock absorber connects the automatic charging interface and the ground to buffer a large impact;

[0045] The hydraulic shock absorber is arranged at a key position inside the automatic charging interface for fine-tuning the shock absorption effect.

[0046] Furthermore, the emergency power-off assembly includes an emergency power-off button, a fast circuit breaker, and a backup power supply;

[0047] The emergency power-off button is arranged at a position outside the automatic charging interface that is easy to operate;

[0048] The fast circuit breaker is connected in series with the charging port and is triggered by the emergency power-off button;

[0049] The backup power supply provides emergency power to the automatic charging interface to ensure that the retraction action can be completed after a power outage;

[0050] The dustproof and waterproof component also includes a self-cleaning system, which includes a cleaning nozzle and a cleaning liquid storage tank for regularly cleaning the outer surface of the automatic charging interface.

[0051] Furthermore, the multiple positions are specifically a power module, a liquid-cooled charging module, an AC-DC conversion module, a main control board, a cooling fan air inlet, a cooling fan air outlet, a liquid cooling system water inlet, and a liquid cooling system water outlet.

[0052] The device of the present invention has the following technical advantages:

[0053] 1. Automatic charging function: It adopts a 5-degree-of-freedom automatic charging interface, which can autonomously identify the position of the aircraft and accurately dock, greatly improving the charging efficiency and reducing the burden on ground staff.

[0054] 2. Strong environmental adaptability: Most of the main body of the charging device is buried underground, with only the automatic charging port exposed above the ground. It is equipped with dust-proof and waterproof, buffering and shock-absorbing measures, and can adapt to harsh outdoor environments to ensure safe and stable operation.

[0055] 3. Intelligent temperature control and safety protection: The device is equipped with a temperature monitoring system and multiple safety protection mechanisms, which can monitor the temperature of key components in real time and quickly cut off the power supply in abnormal situations such as overload and overheating to ensure a safe and reliable charging process.

[0056] 4. Integrated design: The main cabinet integrates core functional modules such as AC / DC conversion and liquid cooling to achieve integrated management, greatly improving system integration and reliability.

[0057] In general, the vertical take-off and landing aircraft charging device of the present invention effectively solves the limitations of existing charging technology through multiple innovations such as automatic docking, environmental adaptation, and intelligent temperature control, and provides a safe and efficient charging solution for vertical take-off and landing aircraft. It is of great significance in promoting the large-scale application of vertical take-off and landing aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0058] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings required for use in the description of the embodiments of the present invention will be briefly introduced below. Obviously, the accompanying drawings in the following description are only some embodiments of the present invention. For ordinary technicians in this field, other accompanying drawings can be obtained based on these accompanying drawings without paying creative labor.

[0059] Figure 1 is a schematic diagram of a charging device for a vertical take-off and landing aircraft;

[0060] Figure 2 is a front view of a charging device for a vertical take-off and landing aircraft;

[0061] In the accompanying drawings, the components represented by the reference numerals are listed as follows:

[0062] 1. Charging port; 2. Vertical fine-tuning slide rail; 3. Horizontal fine-tuning slide rail; 4. Robotic arm; 5. Base; 6. Guide cylinder; 7. Telescopic arm; 8. Base turntable. DETAILED DESCRIPTION

[0063] In order to make the purpose, technical solution and advantages of the embodiments of the present invention more clear, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention.

[0064] like Figure 1 , Figure 2 As shown, it is a first embodiment of a charging device for a vertical take-off and landing aircraft provided by the present invention. In this embodiment, the charging device determines the optimal docking scheme through an automatic docking optimization equation group, and the automatic docking optimization equation group includes a position optimization equation, an angle optimization equation, a speed optimization equation, a torque optimization equation and an energy consumption optimization equation, which are specifically expressed as follows:

[0065] (1) Position optimization equation:

[0067]

[0068] In the formula, Optimize the objective function for the location; is the current position coordinate of the charging interface, mm; (x0, y0, z0) is the target position coordinate of the aircraft interface, mm; t is the time of the docking process, s; α1, β1, γ1, ω1 are unknown coefficients; ε1 is the error term.

[0069] Among them, the parameter acquisition method is as follows: (x, y, z) is measured in real time by a high-precision laser positioning system; (x0, y0, z0) is provided by the GPS and inertial navigation system on the aircraft; t is recorded by the system timer; the unknown coefficients α1, β1, γ1, ω1 are obtained by nonlinear regression analysis of historical docking data.

[0070] (2) Angle optimization equation:

[0071]

[0072] In the formula, Optimize the objective function for the angle; is the current attitude angle of the charging interface, rad; (θ x0 ,θ y0 ,θ z0 ) is the target attitude angle of the aircraft interface, rad; t is the time of the docking process, s; α2, γ2, ω2 are unknown coefficients; ε2 is the error term.

[0073] The parameter acquisition method is: (θ x ,θ y ,θ z ) is measured in real time by a gyroscope; (θ x0 ,θ y0 ,θ z0 ) is provided by the aircraft attitude control system; t is recorded by the system timer; the unknown coefficients α2, γ2, ω2 are obtained by least squares fitting.

[0074] (3) Speed ​​optimization equation:

[0075]

[0076] In the formula, Optimize the objective function for speed; is the current velocity vector of the charging interface, mm / s; is the ideal docking velocity vector, mm / s; |·|2 represents the Euclidean norm; t is the time of the docking process, s; t0 is the expected docking time, s; α3, β3, γ3 are unknown coefficients; ε3 is the error term.

[0077] The parameter acquisition method is: Real-time measurement via Doppler velocity sensor; It is obtained based on the statistics of historical successful docking data; t is recorded by the system timer; t0 is pre-calculated by the docking trajectory planning algorithm; and the unknown coefficients α3, β3, and γ3 are solved by the particle swarm optimization algorithm (PSO).

[0078] (4) Torque optimization equation:

[0079]

[0080] In the formula, is the objective function for moment optimization; is the current torque vector applied by the charging interface, N·m; is the ideal docking torque vector, N·m; |·|2 represents the Euclidean norm; t is the time of the docking process, s; μ, σ are the mean and standard deviation of the Gaussian function, respectively; α4, γ4 are unknown coefficients; ε4 is the error term.

[0081] The parameter acquisition method is: Real-time measurement through torque sensor; It is calculated based on the mass of the aircraft and the characteristics of the docking interface; t is recorded by the system timer; μ, σ are determined by analyzing historical docking data; and the unknown coefficients α4, γ4 are obtained by optimizing the genetic algorithm (GA).

[0082] (5) Energy consumption optimization equation:

[0083]

[0084] Where f5(E) is the energy consumption optimization objective function; E is the total energy consumption of the docking process, J; P m (t) is the mechanical system power, W; P e (t) is the electrical system power, W; T is the total docking time, s; t is the time of the docking process, s; α5, β5, γ5 are unknown coefficients; ε5 is the error term.

[0085] Among them, the parameter acquisition method is: m (t) measured in real time by a mechanical power meter; P e (t) is measured in real time by the power analyzer; T is recorded by the system timer; the unknown coefficients α5, β5, and γ5 are optimized by the simulated annealing algorithm (SA).

[0086] The solution process of the automatic docking optimization equation set is as follows:

[0087] Step 1: Construct a multi-objective optimization problem:

[0088]

[0089] Step 2: Identify the constraints:

[0090]

[0091] g5(E)=EE max ≤0;

[0092] Where, d max is the maximum allowable position deviation, mm; θ max is the maximum allowable angle deviation, rad; v max is the maximum permissible speed, mm / s; M max is the maximum allowable moment, N·m; E max is the maximum allowable energy consumption, J.

[0093] Step 3: Apply a multi-objective optimization algorithm, such as NSGA-II (Non-dominated Sorting Genetic Algorithm II):

[0094] Initialize the population P t ;

[0095] P t Perform non-dominated sorting;

[0096] Calculate the crowding distance;

[0097] Selection, crossover and mutation operations generate the offspring population Q t ;

[0098] Merge P t and Q t Form R t =P t ∪Q t ;

[0099] R t Perform non-dominated sorting;

[0100] Select a new parent population P t+1 ;

[0101] Repeat the above steps until the termination condition is reached.

[0102] Step 4: From the obtained Pareto optimal solution set, select the final docking solution according to actual needs.

[0103] Among them, d max ,θ max ,v max ,M max ,E max The value of is determined according to the physical limitations of the charging device and the aircraft; the parameters of the NSGA-II algorithm are set as follows: the population size is 100, the maximum number of iterations is 500, the crossover probability is 0.9, and the mutation probability is 0.1.

[0104] A specific embodiment of the present invention is as follows:

[0105] The main cabinet is an integrated structure, which includes the main cabinet control system M cabi 、Liquid-cooled charging module M cha 、AC / DC input system M ac2dc 、DC output system M dc 、Liquid cooling system M liq . Main cabinet control system M cabi Through communication connection with liquid-cooled charging module M cha The terminal control system in the charging terminal interacts with the data to realize the liquid-cooled charging module M cha Input and output control, and input AC or DC into the system M ac2dc The voltage is converted into a charging voltage suitable for vertical take-off and landing aircraft. cabi A plurality of charging terminals are also connected.

[0106] Charging terminal including charging interface liquid cooling system M cha,cool , Main cabinet connection device M cabi,con , Charging interface connection device M cha,con 、Terminal control system M term .

[0107] Automatic charging port including telescopic arm M ext 、Base turntable Mbase , Horizontal fine-tuning slide rail M h,adj , Vertical fine-tuning slide rail M v,adj 、Robotic Arm M arm 、Guide tube M guid 、Rotation assembly M rot 、Control and drive components M ctr 、Winch M ree 、Aircraft interface sensor M sen 、Charging port M cha,int The automatic charging interface realizes 5 degrees of freedom movement and can flexibly complete charging docking.

[0108] Inductive opening and closing cover includes sensor M sen,lid and cover plate M lid . Main cabinet M cabi , charging terminals and automatic charging ports are installed underground, and the inductive opening and closing cover M lid Installed on the ground.

[0109] The specific working process is as follows: When the aircraft needs to be recharged, the automatic charging interface M cha,int Rise, sensor M sen,lid Sense and drive cover M lid Automatic opening. Automatic charging port M cha,int Rise to the ground and adjust the horizontal slide rail M h,adj And vertical fine adjustment slide M v,adj Adjust the position and angle of the charging port and automatically dock with the aircraft to complete charging.

[0110] The liquid-cooled charging module M cha And charging port M cha,int The heat generated is cooled by the liquid cooling system M liq It is naturally dissipated through the ambient temperature difference. Automatic charging port M cha,int Meet the needs of automatic charging and docking within a certain radius.

[0111] Main cabinet M cabi Also includes cooling fan system M fan , Temperature monitoring system M temp 、Safety protection system M safe . Cooling fan system M fan Including main fan M f,main 、Auxiliary fan M f,aux Japanese style M duct , used for forced convection cooling. Temperature monitoring system M temp Includes multiple temperature sensors T sens and temperature display M disp ,,Real-time monitoring of the temperature of each component. Safety protection system M safeIncluding overcurrent protection module, overvoltage protection module, short circuit protection module and leakage protection module eleak ,,Used to cut off power supply in abnormal circumstances.

[0112] Automatic charging port M cha,int Also includes dust and water resistant components M dust 、Buffer shock absorbing component M shock and emergency power off module M emg . Dust and water proof component M dust Including seal ring M seal , waterproof coating M coat and drainage hole M drain ,,Used to prevent dust and moisture from entering. Buffer shock absorbing component M shock Including shock pads M pad 、Spring shock absorber M spring and hydraulic shock absorbers M damp ,,Used to reduce the impact of ground vibration on the charging process. Emergency power off component M emg Including emergency power off button M btn 、Fast circuit breaker M break and backup power supply M batt ,, used to quickly cut off the power supply in an emergency. In addition, the dust and water-proof component M dust Also includes a self-cleaning system, including a cleaning nozzle and a cleaning fluid reservoir, for regular cleaning of the automatic charging port M cha,int Outer surface.

[0113] The present invention provides a second embodiment of a charging device for a vertical take-off and landing aircraft. In this embodiment, a typical vertical take-off and landing aircraft automatic charging scenario is described.

[0114] An airline uses the VTOL aircraft charging device of the present invention to provide charging services for its fixed-wing aircraft and VTOL UAV. The main components of the charging device are configured as follows:

[0115] Table 1, main component parameter configuration

[0116]

[0117] The charging device is mainly installed under the aircraft apron at an airport, with only the automatic charging interface exposed on the ground. The system operation process is as follows:

[0118] When a vertical take-off and landing aircraft (such as a company's V-22 vertical take-off and landing drone) lands at a designated parking position, the automatic charging port will automatically rise and drive the inductive opening and closing cover on the ground to open. The charging port is precisely aligned with the charging port position of the aircraft through horizontal and vertical fine-tuning slides, and automatic docking is achieved. After the aircraft landing system detects that the docking is successful, it will send a charging command to the control system of the main cabinet.

[0119] The main cabinet control system then starts the AC / DC input system to convert the mains voltage into a charging voltage of 300-400VDC. At the same time, the control system will also adjust the cooling power of the liquid cooling system to ensure that the temperature of key components (such as liquid cooling charging modules, charging interfaces, etc.) is controlled within a safe range during the charging process. The temperature monitoring system will collect temperature data of each component in real time. Once any abnormal situation (such as excessive temperature) is detected, the safety protection system will be immediately triggered to cut off the power supply to avoid unsafe accidents.

[0120] During the charging process, the winch will automatically control the length of the connecting cable to ensure that it will not interfere with the take-off and landing of the aircraft. At the same time, the dust and water-proof components can also effectively block external dust and moisture to ensure the reliability of the charging interface. In case of emergency (such as emergency take-off of the aircraft), the operator only needs to press the emergency power-off button, and the system will immediately cut off the power supply to prevent danger.

[0121] When the VTOL aircraft is fully charged, the main cabinet control system will send a charging completion signal, the automatic charging interface will slowly retract to the ground, and the inductive opening and closing cover will automatically close. The entire charging process is fully automated, without the need for manual intervention, greatly improving work efficiency.

[0122] In this embodiment, the AC / DC input system of the main cabinet adopts 380VAC / 50Hz three-phase input, and realizes voltage conversion through high-frequency switching power supply topology, with a conversion efficiency of more than 97%. The maximum output power of the liquid-cooled charging module is 75kW, which can meet the fast charging requirements of high-power vertical take-off and landing aircraft. The cooling power of the liquid cooling system is designed to be 100kW, which can effectively dissipate the heat generated during the charging process and ensure that the temperature of each key component is controlled within a safe range.

[0123] The temperature monitoring system uses 6 temperature sensors, which are arranged in the power module, liquid cooling charging module, AC / DC conversion module, main control board, cooling fan air inlet and outlet. When the temperature of any measuring point exceeds 80℃, the system will trigger an audible and visual alarm, and cut off the power supply through the safety protection system. In addition, there is a variable speed main fan on the back of the main cabinet, which can adjust the speed according to the real-time temperature to further optimize the heat dissipation effect.

[0124] The automatic charging port adopts a 5-degree-of-freedom mechanical structure, including a telescopic arm with a stroke of 1.2m, a rotation angle of ±180°, and fine-tuning rails in the horizontal and vertical directions. This design can not only adapt to aircraft in different parking positions, but also accurately align the charging port to ensure reliable docking. At the same time, the automatic charging port is also equipped with dust-proof and waterproof components with an IP65 protection level, as well as a buffering and shock-absorbing device that can withstand an impact force of 5kN, which can effectively resist the influence of harsh environmental conditions. In the event of an emergency, the operator only needs to press the emergency power-off button, the system will cut off the power within 50ms, and the backup power supply will drive the automatic charging port to complete the retraction action, ensuring safety and reliability.

[0125] In general, the vertical take-off and landing aircraft charging device in this embodiment integrates multiple technologies such as automatic docking, intelligent temperature control, and safety protection. It can provide fast, safe, and reliable charging services for vertical take-off and landing aircraft, and shows good practicality in actual application scenarios such as airports.

[0126] The present invention provides a third embodiment of a charging device for a vertical take-off and landing aircraft. In this embodiment, a scenario is described in which a city's emergency rescue center uses the vertical take-off and landing aircraft charging device of the present invention to provide charging support for its drone formation.

[0127] The emergency rescue center has a fleet of vertical take-off and landing drones, which are mainly used for emergency rescue and disaster monitoring in the city. The center is equipped with a vertical take-off and landing drone landing apron, and the charging device of the present invention is used to charge the drones in the fleet. The main parameters of the charging device are as follows:

[0128] Table 2, main component parameter configuration

[0129]

[0130]

[0131] The charging device is mainly buried underground in the apron, and the automatic charging interface is partially exposed on the ground. The system operation process is as follows:

[0132] When a vertical take-off and landing drone lands at a designated parking position, the automatic charging port will automatically rise and drive the inductive opening and closing cover to open. The charging port is first accurately positioned directly below the drone's charging port through the horizontal fine-tuning slide rail, and then the contact angle is adjusted using the vertical fine-tuning slide rail and the rotating assembly to achieve reliable automatic docking. The drone landing system will detect that the charging docking is successful and then send a charging command to the host cabinet control system.

[0133] The main cabinet control system immediately starts the AC / DC input system to convert 380VAC mains power into a charging voltage of 360-400VDC. At the same time, the control system will also adjust the cooling power of the liquid cooling system to maintain the operating temperature of key components (such as liquid cooling charging modules, charging interfaces, etc.) within a safe range. The temperature monitoring system will collect temperature data from 10 measuring points in real time. Once the temperature of any component exceeds 85°C, an audible and visual alarm will be triggered immediately and the power will be cut off to ensure a safe and reliable charging process.

[0134] During charging, the winch will automatically adjust the length of the connecting cable to prevent interference with the take-off and landing of the drone. The dustproof and waterproof components can effectively block external dust and moisture, and have the function of regular self-cleaning. The buffer shock-absorbing components can also absorb small vibrations from the ground to reduce the impact on charging. In case of emergency (such as emergency take-off of the drone), the operator only needs to press the emergency power-off button, the system will cut off the power within 30ms, and the backup power supply will drive the automatic charging interface to complete the retraction action.

[0135] When the drone is fully charged, the main cabinet control system will send a charging completion signal, the automatic charging interface will slowly retract to the ground, and the inductive opening and closing cover will automatically close. The entire charging process does not require manual intervention, and the maximum charging power can reach 100kW, which can complete the rapid charging of the drone within 10-20 minutes.

[0136] In this embodiment, the main cabinet uses a higher-power liquid-cooled charging module (100kW) and a liquid cooling system (cooling power 150kW) to meet the centralized charging needs of the vertical take-off and landing UAV formation. The conversion efficiency of the AC / DC input system is further improved to more than 98%, reducing the operating power consumption.

[0137] The temperature monitoring system has increased the number of measuring points to 10, distributed in key parts such as the power module, liquid cooling charging module, AC / DC conversion module, main control board, cooling fan inlet and outlet, and liquid cooling system water inlet and outlet. When the temperature of any measuring point exceeds 85°C, the system will trigger an audible and visual alarm and cut off the power supply through the safety protection system. The main fan adopts variable frequency speed regulation technology, which can adjust the speed in real time according to temperature changes to further optimize the heat dissipation effect.

[0138] The safety protection system has added an insulation monitoring module to continuously monitor the insulation resistance between each conductive component in the main cabinet and the ground. When it is lower than the safe value, it will promptly alarm and cut off the power supply to prevent leakage accidents. In addition, the emergency power-off component has been further optimized, the power-off time has been shortened to 30ms, and 30 seconds of backup power support is provided to ensure safe and reliable emergency response.

[0139] The mechanical structure of the automatic charging port has also been strengthened, the telescopic arm travel has been increased to 1.5m, and the rotation angle has been expanded to ±210°, which can adapt to a wider range of drone parking positions. The protection level of the dust and water-proof components has been increased to IP66, and the automatic cleaning system has been optimized, greatly improving the ability to resist harsh environments. The buffer shock-absorbing components have also been further improved to withstand an impact force of 8kN, ensuring a smooth charging process.

[0140] In general, the VTOL aircraft charging device in this embodiment is optimized for special application scenarios such as emergency rescue. It not only has core functions such as fast charging, intelligent temperature control and safety protection, but also has significant improvements in key parameters and environmental adaptability. It can provide reliable charging support for VTOL UAV formations and play a key role in important tasks such as emergency rescue.

[0141] The vertical take-off and landing aircraft charging device of the present invention is mainly composed of four parts: a main cabinet, a charging terminal, an automatic charging interface and an inductive opening and closing cover. Its working principle is as follows:

[0142] The main cabinet integrates core functional units such as charging control system, power conversion module and heat dissipation system, which can convert AC power or DC power into charging voltage suitable for vertical take-off and landing aircraft, and intelligently control the charging process through communication connection. As the intermediate connection layer between the main cabinet and the automatic charging interface, the charging terminal provides mechanical and electrical interfaces to ensure the reliability and scalability of the entire charging system.

[0143] The automatic charging port is the key to achieving automatic charging of the aircraft. It adopts a 5-degree-of-freedom mechanical structure, including telescopic arms, fine-tuning slide rails, rotating components, etc., which can autonomously identify the position of the aircraft and accurately dock, greatly improving docking accuracy and adaptability. At the same time, the automatic charging port is also equipped with dust-proof and waterproof, buffer and shock-absorbing components, which can effectively resist the impact of harsh environments.

[0144] It is worth mentioning that the present invention also cleverly utilizes the inductive opening and closing cover. When the aircraft needs to be charged, the automatic charging interface will automatically rise and drive the opening and closing cover to open, exposing the charging interface; after charging is completed, the charging interface will automatically retract and the opening and closing cover will also close, thus achieving the beautification and safety protection of the ground.

[0145] In addition, a complete temperature monitoring and safety protection mechanism is integrated inside the main cabinet. By measuring the temperature of key components in real time and cutting off the power supply in time when abnormal conditions occur, it effectively avoids the occurrence of overload, overheating and other faults, greatly improving the safety and reliability of the entire charging system.

Claims

1. A charging device for a vertical take-off and landing aircraft, characterized in that: include: Main cabinet, charging terminal, automatic charging interface, inductive opening and closing cover; The main cabinet includes a main cabinet control system, a liquid-cooled charging module, an AC / DC input system, a DC output system, and a liquid cooling system; the main cabinet control system communicates with the liquid-cooled charging module and the terminal control system in the charging terminal to control the input and output of the liquid-cooled charging module and convert the AC or DC input system voltage into a charging voltage suitable for the vertical take-off and landing aircraft; the main cabinet is connected to a plurality of the charging terminals; The charging terminal includes a charging interface liquid cooling system, a main cabinet connection device, a charging interface connection device, and a terminal control system; The automatic charging interface includes a telescopic arm, a base turntable, a fine-tuning slide rail, a mechanical arm, a guide cylinder, a rotating component, a control and drive component, a winch, an aircraft interface sensor, and a charging interface; the automatic charging interface realizes 5-degree-of-freedom movement; The inductive opening and closing cover comprises a sensor and a cover; The main cabinet, the charging terminal, and the automatic charging interface are all installed underground, and the inductive opening and closing cover is installed on the ground; Among them, the telescopic arm is used for the vertical lifting and lowering of the automatic charging interface and extending out of the ground; the base turntable is placed on the base, driving the mechanical structure above the base to rotate 360 ​​degrees freely; the fine-tuning slide rail includes a horizontal fine-tuning slide rail and a vertical fine-tuning slide rail, the horizontal fine-tuning slide rail is used to adjust the coordinates of the charging interface, and the vertical fine-tuning slide rail is used for the free plugging of the charging interface and the aircraft after the coordinates and angles are adjusted; the mechanical arm is installed with the fine-tuning slide rail; the guide cylinder has the rotating assembly and the aircraft interface sensor built in, and the aircraft interface sensor provides the interface target position coordinates; the rotating assembly adjusts the angle of the charging interface; the winch is placed in the base, used to reel in and unroll the connecting cable to control the release length of the connecting cable; the control and drive assembly is placed in the base, used to control the motion trajectory of each mechanical structure and provide power output.

2. A charging device for a vertical take-off and landing aircraft according to claim 1, characterized in that: The heat generated by the liquid-cooled charging module and the charging interface is naturally dissipated through the liquid cooling system via the ambient temperature difference; The automatic charging interface meets the requirements of automatic charging and docking within a certain radius coverage; When the sensor senses that the charging port is lifted or lowered, the cover automatically opens and closes.

3. A charging device for a vertical take-off and landing aircraft according to claim 2, characterized in that: When the aircraft needs to be recharged, the automatic charging interface rises, the inductive opening and closing cover automatically opens, the automatic charging interface rises to the ground and adjusts the position coordinates and angle of the charging interface, automatically docks with the aircraft, and completes charging.

4. A charging device for a vertical take-off and landing aircraft according to claim 3, characterized in that: The main cabinet also includes a cooling fan system, a temperature monitoring system, and a safety protection system; The heat dissipation fan system is arranged inside the main cabinet for forced convection heat dissipation; The temperature monitoring system includes a plurality of temperature sensors, which are distributed at a plurality of locations inside the main cabinet to monitor the temperature of each component in real time; The safety protection system includes an overcurrent protection module, an overvoltage protection module, and a short circuit protection module, which are used to cut off power supply in abnormal situations.

5. A charging device for a vertical take-off and landing aircraft according to claim 4, characterized in that: The automatic charging interface also includes a dust and water proof component, a buffer shock absorbing component, and an emergency power off component; The dustproof and waterproof component is arranged outside the automatic charging interface to prevent dust and moisture from entering; The buffer shock-absorbing component is arranged at the contact part between the automatic charging interface and the ground, so as to reduce the influence of ground vibration on the charging process; The emergency power-off component is electrically connected to the charging interface and is used to quickly cut off power in an emergency.

6. A charging device for a vertical take-off and landing aircraft according to claim 5, characterized in that: The heat dissipation fan system includes a main fan, an auxiliary fan, and an air duct; The main fan is arranged at the back of the main cabinet and is used to extract external cold air; The auxiliary fan is arranged in a hot spot area inside the main cabinet for local forced convection; The air duct runs through the interior of the main cabinet to guide the airflow through each heating element; The temperature monitoring system also includes a temperature display screen, which is arranged outside the main cabinet and displays the internal temperature status in real time; The safety protection system also includes a leakage protector, which is connected in series with the power input terminal of the main cabinet to detect leakage and cut off the power supply in time.

7. A charging device for a vertical take-off and landing aircraft according to claim 6, characterized in that: The main fan of the cooling fan system is a variable speed fan, which automatically adjusts the speed according to the temperature detected by the temperature monitoring system; The temperature monitoring system also includes a temperature alarm module, which triggers an audible and visual alarm when the detected temperature exceeds a preset threshold; The safety protection system also includes an insulation monitoring module, which continuously monitors the insulation resistance between each conductive component inside the main cabinet and the ground. When the insulation resistance is lower than a safe value, an alarm is triggered and the power supply is cut off.

8. The charging device for a vertical take-off and landing aircraft according to claim 7, characterized in that: The dustproof and waterproof component includes a sealing ring, a waterproof coating, and a drainage hole; The sealing ring is arranged at the edge of the automatic charging interface in contact with the ground to form a sealing barrier; The waterproof coating covers the outer surface of the automatic charging interface to enhance the waterproof performance; The drainage hole is provided at the bottom of the automatic charging interface for draining the moisture that may be accumulated; The buffer shock absorbing assembly includes a shock absorbing pad, a spring shock absorber, and a hydraulic shock absorber; The shock-absorbing pad is arranged at the bottom of the automatic charging interface to absorb small vibrations; The spring shock absorber connects the automatic charging interface and the ground to buffer a large impact; The hydraulic shock absorber is arranged at a key position inside the automatic charging interface for fine-tuning the shock absorption effect.

9. A charging device for a vertical take-off and landing aircraft according to claim 8, characterized in that: The emergency power-off assembly includes an emergency power-off button, a fast circuit breaker, and a backup power supply; The emergency power-off button is arranged at a position outside the automatic charging interface that is easy to operate; The fast circuit breaker is connected in series with the charging port and is triggered by the emergency power-off button; The backup power supply provides emergency power to the automatic charging interface to ensure that the retraction action can be completed after a power outage; The dustproof and waterproof component also includes a self-cleaning system, which includes a cleaning nozzle and a cleaning liquid storage tank for regularly cleaning the outer surface of the automatic charging interface.

10. A charging device for a vertical take-off and landing aircraft according to any one of claims 1 to 9, characterized in that: The multiple positions specifically include a power module, a liquid-cooled charging module, an AC / DC conversion module, a main control board, a cooling fan air inlet, a cooling fan air outlet, a liquid cooling system water inlet, and a liquid cooling system water outlet.

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