CN119079164A - A vertical take-off and landing drone - Google Patents
A vertical take-off and landing drone Download PDFInfo
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- CN119079164A CN119079164A CN202411578547.XA CN202411578547A CN119079164A CN 119079164 A CN119079164 A CN 119079164A CN 202411578547 A CN202411578547 A CN 202411578547A CN 119079164 A CN119079164 A CN 119079164A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/20—Vertical take-off and landing [VTOL] aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/30—Supply or distribution of electrical power
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/30—Supply or distribution of electrical power
- B64U50/32—Supply or distribution of electrical power generated by fuel cells
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02T90/40—Application of hydrogen technology to transportation, e.g. using fuel cells
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Abstract
本发明公开了一种垂直起降无人机，涉及飞行器技术领域，包括无人机主体、能源动力系统和着降装置，所述无人机主体包括机身主体、机翼和尾翼，所述机身主体的两侧均设置有所述机翼，所述尾翼设置于所述机身主体的尾部；所述无人机主体上还设置有旋翼组件和螺旋桨组件，所述能源动力系统设置于所述机身主体内，所述着降装置设置于所述机身主体的底部；其中，所述能源动力系统包括储氢瓶、氢燃料电池和蓄电池，所述储氢瓶与所述氢燃料电池连接，用于为所述氢燃料电池提供氢气，以产生电能，所述氢燃料电池与所述螺旋桨组件电连接，所述蓄电池与所述旋翼组件电连接。本发明垂直起降无人机续航时间长，机动性高且适应性强。
The present invention discloses a vertical take-off and landing UAV, which relates to the technical field of aircraft, and includes a UAV main body, a power system and a landing device, wherein the UAV main body includes a fuselage main body, wings and a tail, the wings are arranged on both sides of the fuselage main body, and the tail is arranged at the tail of the fuselage main body; the UAV main body is also provided with a rotor assembly and a propeller assembly, the power system is arranged in the fuselage main body, and the landing device is arranged at the bottom of the fuselage main body; wherein the power system includes a hydrogen storage bottle, a hydrogen fuel cell and a storage battery, the hydrogen storage bottle is connected to the hydrogen fuel cell, and is used to provide hydrogen for the hydrogen fuel cell to generate electrical energy, the hydrogen fuel cell is electrically connected to the propeller assembly, and the storage battery is electrically connected to the rotor assembly. The vertical take-off and landing UAV of the present invention has a long flight time, high maneuverability and strong adaptability.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a vertical take-off and landing unmanned aerial vehicle.
Background
When a flight task is executed in a complex environment such as a forest, a mountain and the like, because the taking-off and landing conditions are limited, the unmanned aerial vehicle is often required to have the capability of taking off and landing vertically at any time, the current unmanned aerial vehicle taking off and landing vertically mainly takes a rotorcraft, a storage battery is generally adopted for providing power, and the problems of low cruising speed, short cruising time and the like exist.
Therefore, a vertical take-off and landing unmanned aerial vehicle is provided to solve the above problems existing in the prior art.
Disclosure of Invention
The invention aims to provide a vertical take-off and landing unmanned aerial vehicle, which solves the problems of the prior art, and has long endurance time, high maneuverability and strong adaptability.
In order to achieve the above object, the present invention provides the following solutions:
The invention provides a vertical take-off and landing unmanned aerial vehicle, which comprises an unmanned aerial vehicle body, an energy power system and a landing device, wherein the unmanned aerial vehicle body comprises a body main body, wings and tail wings, the wings are arranged on two sides of the body main body, the tail wings are arranged at the tail part of the body main body, a rotor wing assembly and a propeller assembly are further arranged on the unmanned aerial vehicle main body, the energy power system is arranged in the body main body, the landing device is arranged at the bottom of the body main body, the energy power system comprises a hydrogen storage bottle, a hydrogen fuel cell and a storage battery, the hydrogen storage bottle is connected with the hydrogen fuel cell and is used for providing hydrogen for the hydrogen fuel cell to generate electric energy, the hydrogen fuel cell is electrically connected with the propeller assembly, and the storage battery is electrically connected with the rotor wing assembly.
Preferably, the unmanned aerial vehicle main part includes fuselage main part, wing and fin, the both sides of fuselage main part all are provided with the wing, both sides the below of wing is close to wing root department and all is provided with a tail and props, the tail prop is followed the length direction of fuselage main part sets up, the fin sets up in both sides between the afterbody of tail prop.
Preferably, the cross section of the fuselage main body is in a flat elliptic shape, the wings are wings with large aspect ratio, the rear edge positions of the wings on both sides are provided with flaps, the flaps are connected with servo steering engines, and the servo steering engines can control the corresponding flaps to be unfolded or retracted so as to control the posture of the unmanned aerial vehicle main body.
Preferably, the tail fin is an inverted V-shaped tail fin, and the inverted V-shaped tail fin is provided with two direction elevators, wherein the two direction elevators are symmetrically distributed at the middle rear edge of the inverted V-shaped tail fin, and the direction elevators can deflect different angles so as to control the pitching and the yawing of the unmanned aerial vehicle main body.
Preferably, the rotor wing assemblies are provided with four groups, the four groups of rotor wing assemblies are respectively arranged at the front ends and the middle parts of the two tail supports, and the two groups of rotor wing assemblies on the same tail support are respectively positioned at two sides corresponding to the wings;
Any one of the rotor assemblies comprises a rotor and a first driving motor, the first driving motor is fixed on the tail boom, the rotor is mounted on the first driving motor, the first driving motor can drive the rotor to rotate, and the storage battery is electrically connected with the first driving motor.
Preferably, the propeller assembly is arranged at the tail part of the main body of the machine body and comprises a propeller and a second driving motor, the second driving motor is fixed at the tail part of the main body of the machine body, the propeller is arranged on the second driving motor, the second driving motor can drive the propeller to rotate, and the hydrogen fuel cell is electrically connected with the second driving motor.
Preferably, the energy power system further comprises a power manager, and the hydrogen fuel cell and the storage battery are connected with the power manager;
The hydrogen storage bottles are transversely arranged in parallel and detachably arranged in the machine body, and the air outlets of the hydrogen storage bottles are also provided with pressure reducing valves;
the storage battery is a lithium battery.
Preferably, the landing gear comprises two landing gears, wherein the two landing gears are respectively positioned at two sides below the belly of the main body of the machine body and are distributed in longitudinal rows;
And an parachuting module is additionally arranged in the main body of the machine body.
Preferably, a cabin door is further arranged at the bottom of the belly of the main body of the airframe, the cabin door is connected with a cabin door steering engine, and the cabin door steering engine can control the opening and closing of the cabin door.
Preferably, the system further comprises a communication control system, wherein the communication control system comprises a flight controller, a GPS antenna, a graph transmission module and a data transmission module, the flight controller is in signal connection with the GPS antenna, the graph transmission module and the data transmission module, and the graph transmission module and the data transmission module are in signal connection with a ground control station.
Compared with the prior art, the invention has the following technical effects:
The unmanned aerial vehicle main body comprises a main body, wings and tail wings, the main body of the unmanned aerial vehicle is also provided with the rotor wing assembly and the propeller assembly, so that the two modes of the rotor wing mode and the fixed wing mode (wings) are converted and fly, the unmanned aerial vehicle can cruise fast forward in the fixed wing mode, has the characteristics of high maneuverability and the like, and can realize vertical take-off and landing and hovering in the air in the rotor wing mode.
The energy power system comprises a hydrogen storage bottle, a hydrogen fuel cell and a storage battery, is driven by adopting a hybrid power system of the hydrogen fuel cell and the storage battery, has the advantages of being more environment-friendly, avoiding the risk caused by possible leakage of fuel, having low noise, no pollution, zero emission and the like compared with the traditional fuel power unmanned aerial vehicle, greatly improving the endurance capability, having obvious advantages in the aspects of temperature adaptability and the like compared with the pure electric unmanned aerial vehicle, and particularly keeping stable power output of the hydrogen fuel power system in the extremely low-temperature environment of-40 ℃, having almost no attenuation in performance and being free from fire caused by high-temperature runaway.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic structural diagram of a vertical take-off and landing unmanned aerial vehicle according to an embodiment of the present invention;
fig. 2 is a bottom view of a vertical lift drone according to an embodiment of the present invention;
fig. 3 is a schematic partial view of a vertical lift unmanned aerial vehicle according to an embodiment of the present invention;
fig. 4 is a side view of a vertical lift drone (door closed) in an embodiment of the present invention;
Fig. 5 is a side view of a vertical lift drone (with door open) in an embodiment of the present invention.
In the figure, a main body of a machine body 1, a 2-rotor wing, a 3-first driving motor, a 4-wing, a 5-flap, a 6-propeller, a 7-inverted V-shaped tail wing, an 8-direction elevator, a 9-tail boom, a 10-landing gear, an 11-second driving motor, a 12-power manager, a 13-hydrogen storage bottle, a 14-pressure reducing valve, a 15-hydrogen fuel cell, a 16-lithium battery, a 17-image transmission module, a 18-data transmission module, a 19-flight controller, a 20-GPS antenna and a 21-cabin door.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention aims to provide a vertical take-off and landing unmanned aerial vehicle, which solves the problems of the prior art, and has long endurance time, high maneuverability and strong adaptability.
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
Example 1
As shown in fig. 1-5, the embodiment provides a vertical take-off and landing unmanned aerial vehicle, mainly comprising an unmanned aerial vehicle main body, an energy power system and a landing device, wherein the unmanned aerial vehicle main body comprises a main body 1, wings 4 and tail wings, the wings 4 are arranged on two sides of the main body 1, the tail wings are arranged at the tail part of the main body 1, a rotor assembly and a propeller assembly are further arranged on the unmanned aerial vehicle main body, the energy power system is arranged in the main body 1, the landing device is arranged at the bottom of the main body 1, the energy power system comprises a hydrogen storage bottle 13, a hydrogen fuel cell 15 and a storage battery, the hydrogen storage bottle 13 is connected with the hydrogen fuel cell 15 and is used for providing hydrogen for the hydrogen fuel cell 15 so as to generate electric energy, the hydrogen fuel cell 15 is electrically connected with the propeller assembly, and the storage battery is electrically connected with the rotor assembly.
According to the embodiment, the rotor wing mode and the fixed wing mode (the wing 4) are switched to fly, the cruise speed of the fixed wing mode is high, the maneuverability is high, the vertical take-off and landing and the hovering can be realized in the rotor wing mode, compared with a conventional fixed wing unmanned aerial vehicle, the conventional runway restriction is eliminated, the requirement on the condition of a take-off and landing site is lower, and the adaptability to a task scene is stronger. The vertical landing device comprises a rotor assembly, a fixed wing, a landing point, a fixed wing mode, a landing point, a fixed point vertical landing platform, a fixed wing mode, a lifting force control system and a control system.
Furthermore, the hydrogen fuel cell 15 and the storage battery hybrid power system are adopted for driving, compared with a traditional fuel power unmanned aerial vehicle, the environment-friendly type unmanned aerial vehicle has the advantages of avoiding risks caused by possible fuel leakage, being low in noise, free of pollution, free of emission and the like, greatly improving the endurance, being obvious in temperature adaptability and the like compared with a pure electric unmanned aerial vehicle, and particularly capable of keeping stable power output in a-40 ℃ extremely low-temperature environment, almost not attenuating performance, and avoiding fire caused by out-of-control of high temperature.
In this embodiment, a strip-shaped tail support 9 is disposed at a position right below the wing 4 and close to the wing root, the tail support 9 is disposed along the length direction of the fuselage main body 1 and is fastened and connected with the corresponding wing 4 through two bolts, and the tail wing is disposed between the tail portions of the tail supports 9 at both sides and is fastened and fixed with the tail support 9 through a buckle.
In this embodiment, the cross section of the main body 1 is in a flat ellipse shape, the wing 4 serving as the main lifting surface is a wing with a high aspect ratio, the aspect ratio is preferably 13.3 (usually, the wing aspect ratio is more than 10, that is, the wing with the high aspect ratio) and the wing root is located in the middle of the cross section of the main body 1, so as to form an unmanned aerial vehicle main body with a flat body and a single wing in the high aspect ratio, wherein the longer wing 4 enables the whole machine to have better lateral stability and higher lifting efficiency, the flat body increases the available space inside, the wing 4 and the main body 1 are highly integrated by combining the two, and the configuration of wing body fusion is beneficial to improving airflow in the flight process, reducing flight resistance and improving lift-drag ratio.
Further, the wing flaps 5 are arranged at the rear edge positions of the wings 4 at two sides, the wing flaps 5 are connected with servo steering engines, and the servo steering engines can control the corresponding wing flaps 5 to be unfolded or retracted so as to control the posture of the unmanned aerial vehicle main body.
In this embodiment, the tail fin is preferably an inverted V-shaped tail fin 7, the inverted V-shaped tail fin 7 simplifies the tail structure of the main body of the unmanned aerial vehicle, reduces airflow disturbance, improves flight stability, and is further provided with two direction elevators 8 on the inverted V-shaped tail fin 7, wherein the two direction elevators 8 are symmetrically distributed on the middle rear edge of the inverted V-shaped tail fin 7, and the direction elevators 8 can deflect different angles to control pitching and yawing of the main body of the unmanned aerial vehicle.
In this embodiment, the rotor assemblies are preferably provided with four groups, the four groups of rotor assemblies are respectively disposed at the front ends and the middle parts of the two tail supports 9, and the two groups of rotor assemblies on the same tail support 9 are respectively disposed at two sides of the wing 4, wherein any one group of rotor assemblies includes a rotor 2 and a first driving motor 3, the first driving motor 3 is fixed on the tail support 9, the rotor 2 is mounted on an output shaft of the first driving motor 3, the first driving motor 3 can drive the rotor 2 to rotate, and the storage battery is electrically connected with the first driving motor 3 for supplying power to the first driving motor 3.
In this embodiment, the propeller assembly is disposed at the tail of the main body 1 and includes a propeller 6 and a second driving motor 11, the second driving motor 11 is fixed at the tail of the main body 1, the propeller 6 is mounted on an output shaft of the second driving motor 11, and the second driving motor 11 can drive the propeller 6 to rotate, where the hydrogen fuel cell 15 is electrically connected with the second driving motor 11 and is used for supplying power to the second driving motor 11.
In this embodiment, the energy power system further includes a power manager 12, the hydrogen fuel cells 15 and the storage battery are connected to the power manager 12, where the hydrogen storage bottles 13 may be provided with a plurality of hydrogen storage bottles, preferably two hydrogen storage bottles 13, and the two hydrogen storage bottles 13 are arranged in parallel, and the two hydrogen storage bottles 13 are integrated in a highly modularized manner and detachably mounted in the middle and rear section of the main body 1, so that more hydrogen can be carried to increase the endurance time, and the hydrogen storage bottles 13 can be integrally detached and replaced by new hydrogen storage bottles 13, thereby completing the fast supply of unmanned aerial vehicle energy, and the air outlet of the hydrogen storage bottles 13 is further provided with a pressure reducing valve 14, while the storage battery is preferably a lithium battery 16.
In the flying process, hydrogen in the hydrogen storage bottle 13 is regulated by the pressure reducing valve 14 and then is conveyed to the hydrogen fuel cell 15, electrochemical reaction with oxygen in the air is directly converted into electric energy, the electric energy is distributed by the power manager 12, on one hand, energy is supplied to the second driving motor 11, the driving propeller 6 generates forward flying thrust to realize cruise flying in a fixed wing mode, on the other hand, when the power is excessive, the power manager 12 can also store the excessive electric energy generated by the hydrogen fuel cell 15 in the lithium battery 16 for energy charging, the lithium battery 16 is used as an auxiliary energy source, mainly provides electric energy for the four first driving motors 3, drives the four rotors 2 to rotate, and jointly generates vertical upward lifting force, so that the aircraft smoothly realizes vertical take-off and landing and air hovering, when the unmanned aircraft rises to a safe height, the aircraft gradually transits to a forward flying state, and finally the lifting force generated by the wings 4 replaces the lifting force generated by the rotors 2 to realize flat flying, at the moment, the first driving motor 3 and the corresponding rotors 2 stop working, the blades of the rotors 2 and the tail boom 9 keep parallel and in a locking position, wind resistance in the flying process is reduced, in addition, when the climbing aircraft is accelerated, the lithium battery is high in power management peak power is required by the intelligent power management device 12, and the intelligent power management is ensured, and the specific instantaneous power requirements are satisfied when the climbing aircraft is required to be controlled.
In this embodiment, the landing gear includes two landing gears 10, where the two landing gears 10 are respectively located at two sides below the belly of the main body 1 and are distributed in a column, and the landing gears 10 are preferably flat spring type landing gears, which play a supporting role on the unmanned aerial vehicle, and most importantly, can absorb part of energy, effectively buffer the impact of the ground on the body during landing, so as to protect the internal devices from being damaged. If necessary, the parachute landing package module can be additionally arranged in the main body 1 of the unmanned aerial vehicle, and the parachute can be ejected and unfolded through the release mechanism under emergency, so that the unmanned aerial vehicle can land stably.
In the embodiment, the cabin door 21 is further arranged at the bottom of the cabin of the main body 1, the cabin door 21 is connected with a cabin door steering engine, the cabin door steering engine can control the opening and closing of the cabin door 21, the overhaul of the internal equipment of the main body 1, the disassembly, assembly and replacement of the hydrogen storage bottle 13 and the like are facilitated, the hydrogen storage bottle 13 with large capacity can be replaced for different task scenes such as long-distance large-area uninterrupted inspection, the endurance time is prolonged, the hydrogen storage bottle 13 with small volume can be replaced for disaster emergency rescue and the like, the cabin space is reserved, the task load is carried by a specific loading mechanism, the air-drop rescue materials are released to a designated place, the multiple purposes of one machine are really achieved, and the equipment redundancy is avoided.
In this embodiment, the vertical take-off and landing unmanned aerial vehicle further includes a communication control system, where the communication control system includes a flight controller 19, a GPS antenna 20, a graph transmission module 17 and a data transmission module 18, where the flight controller 19 is in signal connection with the GPS antenna 20, the graph transmission module 17 and the data transmission module 18, and the graph transmission module 17 and the data transmission module 18 are in signal connection with a ground control station.
In this embodiment, the image transmission module 17 and the data transmission module 18 are both communication links between the unmanned aerial vehicle and the ground control station, the former is mainly used for transmitting real-time video, image and other data, the latter is mainly used for transmitting telemetry data, the two communication modes complement each other and work cooperatively to ensure accuracy of data transmission feedback and controllability of the unmanned aerial vehicle, the flight controller 19 is used for reading data of various sensors such as an accelerometer, a barometer and a gyroscope on the unmanned aerial vehicle and sending control instructions according to the data to adjust flight attitude and flight path of the unmanned aerial vehicle, and the GPS antenna 20 is used for positioning the unmanned aerial vehicle by receiving satellite signals.
The principles and embodiments of the present invention have been described in detail with reference to specific examples, which are provided herein to facilitate understanding of the principles and embodiments of the present invention and to provide further advantages and practical applications for those of ordinary skill in the art in light of the present teachings. In view of the foregoing, this description should not be construed as limiting the invention.
Claims (10)
1. The vertical take-off and landing unmanned aerial vehicle is characterized by comprising an unmanned aerial vehicle main body, an energy power system and a landing device, wherein the unmanned aerial vehicle main body comprises a body main body, wings and tail wings, the wings are arranged on two sides of the body main body, the tail wings are arranged at the tail part of the body main body, a rotor wing assembly and a propeller assembly are further arranged on the unmanned aerial vehicle main body, the energy power system is arranged in the body main body, the landing device is arranged at the bottom of the body main body, the energy power system comprises a hydrogen storage bottle, a hydrogen fuel cell and a storage battery, the hydrogen storage bottle is connected with the hydrogen fuel cell and used for providing hydrogen for the hydrogen fuel cell to generate electric energy, the hydrogen fuel cell is electrically connected with the propeller assembly, and the storage battery is electrically connected with the rotor wing assembly.
2. The vertical take-off and landing unmanned aerial vehicle of claim 1, wherein a tail support is arranged below the wings at two sides and close to the wing root, the tail support is arranged along the length direction of the main body of the aircraft body, and the tail wing is arranged between the tail parts of the tail supports at two sides.
3. The vertical take-off and landing unmanned aerial vehicle of claim 2, wherein the cross section of the main body of the unmanned aerial vehicle is in a flat elliptic shape, the wings are wings with large aspect ratio, the rear edge positions of the wings on two sides are provided with flaps, the flaps are connected with servo steering engines, and the servo steering engines can control the corresponding flaps to be unfolded or retracted so as to control the posture of the main body of the unmanned aerial vehicle.
4. The vertical take-off and landing unmanned aerial vehicle of claim 2, wherein the tail wing is an inverted V-shaped tail wing, and the inverted V-shaped tail wing is provided with two direction elevators, wherein the two direction elevators are symmetrically distributed on the middle rear edge of the inverted V-shaped tail wing, and the direction elevators can deflect different angles to control the pitching and the yawing of the unmanned aerial vehicle body.
5. The vertical take-off and landing unmanned aerial vehicle of claim 2, wherein the rotor assemblies are four groups, the four groups of rotor assemblies are respectively arranged at the front ends and the middle parts of two tail supports, and the two groups of rotor assemblies on the same tail support are respectively positioned at two sides corresponding to the wings;
Any one of the rotor assemblies comprises a rotor and a first driving motor, the first driving motor is fixed on the tail boom, the rotor is mounted on the first driving motor, the first driving motor can drive the rotor to rotate, and the storage battery is electrically connected with the first driving motor.
6. The vertical take-off and landing unmanned aerial vehicle of claim 2, wherein the propeller assembly is arranged at the tail of the main body of the aircraft body and comprises a propeller and a second driving motor, the second driving motor is fixed at the tail of the main body of the aircraft body, the propeller is arranged on the second driving motor, the second driving motor can drive the propeller to rotate, and the hydrogen fuel cell is electrically connected with the second driving motor.
7. The vertical take-off and landing unmanned aerial vehicle of claim 1, wherein the energy power system further comprises a power manager, and wherein the hydrogen fuel cell and the storage battery are both connected to the power manager;
The hydrogen storage bottles are transversely arranged in parallel and detachably arranged in the machine body, and the air outlets of the hydrogen storage bottles are also provided with pressure reducing valves;
the storage battery is a lithium battery.
8. The vertical take-off and landing unmanned aerial vehicle of claim 1, wherein the landing gear comprises two landing gears which are respectively positioned at two sides below the belly of the main body of the aircraft body and are distributed in longitudinal columns, and wherein the landing gears are flat spring landing gears;
And an parachuting module is additionally arranged in the main body of the machine body.
9. The vertical take-off and landing unmanned aerial vehicle of claim 1, wherein a cabin door is further arranged at the bottom of the belly of the main body of the aircraft body, the cabin door is connected with a cabin door steering engine, and the cabin door steering engine can control opening and closing of the cabin door.
10. The vertical take-off and landing unmanned aerial vehicle of claim 1, further comprising a communication control system, wherein the communication control system comprises a flight controller, a GPS antenna, a graph transmission module and a data transmission module, the flight controller is in signal connection with the GPS antenna, the graph transmission module and the data transmission module, and the graph transmission module and the data transmission module are in signal connection with a ground control station.
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| CN202411578547.XA CN119079164A (en) | 2024-11-07 | 2024-11-07 | A vertical take-off and landing drone |
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| CN202411578547.XA CN119079164A (en) | 2024-11-07 | 2024-11-07 | A vertical take-off and landing drone |
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Application publication date: 20241206 |