CN112623207A - Multi-mode, high-performance rotor unmanned aerial vehicle - Google Patents
Multi-mode, high-performance rotor unmanned aerial vehicle Download PDFInfo
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- CN112623207A CN112623207A CN202011620716.3A CN202011620716A CN112623207A CN 112623207 A CN112623207 A CN 112623207A CN 202011620716 A CN202011620716 A CN 202011620716A CN 112623207 A CN112623207 A CN 112623207A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F3/00—Ground installations specially adapted for captive aircraft
- B64F3/02—Ground installations specially adapted for captive aircraft with means for supplying electricity to aircraft during flight
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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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
- B64U50/34—In-flight charging
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
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Abstract
The invention discloses a multi-mode high-performance rotor unmanned aerial vehicle, which comprises: the power supply system comprises a power supply system, a power subsystem and a power supply mechanism for supplying power to the power supply system and the power subsystem; the power supply mechanism is provided with a battery bin for mounting a battery and a mooring interface for connecting with a mooring airborne power supply; the battery is arranged in the battery compartment and supplies power to the power supply system and the power subsystem, and the unmanned aerial vehicle is in a flying mode; under mooring interface and the connected state of mooring airborne power supply, mooring airborne power supply supplies power for electrical power generating system and power subsystem, and unmanned aerial vehicle is in the mooring mode. The multi-mode high-performance rotor unmanned aerial vehicle provided by the invention can select the working mode according to different actual conditions, and can be switched between the mooring mode and the flying mode, so that the same unmanned aerial vehicle can work according to different working modes.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicle equipment, in particular to a multi-mode high-performance rotor unmanned aerial vehicle.
Background
The fixed wing unmanned aerial vehicle in the prior art has large wingspan and difficult loading, and the unmanned aerial vehicle needs manual assembly when being loaded after being assembled, so that the vehicle-mounted takeoff cannot be completed; mooring unmanned aerial vehicle generally can only use in mooring mode in on-vehicle unmanned aerial vehicle, and the unmanned aerial vehicle of flying of letting generally only can use in the mode of flying of letting, and the usage pattern is single.
In summary, how to increase the working mode of the rotor unmanned aerial vehicle is a problem to be solved urgently by those skilled in the art.
Disclosure of Invention
In view of the above, an object of the present invention is to provide a multi-mode, high-performance rotorcraft that is provided with a battery compartment and a tethered interface, and that can be switched between a flying mode and a tethered mode by installing a battery or by connecting the tethered interface to a tethered onboard power supply.
In order to achieve the above purpose, the invention provides the following technical scheme:
a multi-mode, high-performance rotorcraft, comprising: the power supply system comprises a power supply system, a power subsystem and a power supply mechanism for supplying power to the power supply system and the power subsystem;
the power supply mechanism is provided with a battery bin for mounting a battery and a mooring interface for connecting with a mooring airborne power supply;
the battery is arranged in the battery cabin, the battery supplies power to the power supply system and the power subsystem, and the unmanned aerial vehicle is in a flying mode;
the mooring interface is connected with the mooring airborne power supply, the mooring airborne power supply supplies power to the power system and the power subsystem, and the unmanned aerial vehicle is in a mooring mode.
Preferably, the mooring interface is disposed inside the battery compartment, and the mooring interface is covered by the battery when the battery is mounted in the battery compartment.
Preferably, the battery compartment is located the lower part of unmanned aerial vehicle's fuselage, but the lower part of fuselage is provided with quick assembly disassembly the quick detach mechanism of battery.
Preferably, the quick release mechanism comprises a lock catch, a lock seat for mounting the lock catch and a machine body lock groove matched with the lock catch for locking or unlocking;
and when the battery is installed in place, the lock catch is matched and locked with the machine body lock groove.
Preferably, unmanned aerial vehicle's undercarriage is hollow composite structure, just the bottom of undercarriage is provided with the steel sheet with the spear magnetic suction plate complex in the vehicle.
Preferably, the steel sheet is provided with transverse grains.
Preferably, the power subsystem is of a four-shaft eight-propeller structure, each of the power shafts is provided with a propeller at the upper and lower parts, and the mounting angle of the propellers arranged at the lower part of each of the power shafts is 3 degrees.
Preferably, still including doing benefit to radiating heat dissipation aluminum plate, unmanned aerial vehicle's wireless transmission system power supply system all with heat dissipation aluminum plate laminating sets up, just wireless transmission system with between the heat dissipation aluminum plate power supply system with all be scribbled heat transfer material between the heat dissipation aluminum plate.
Preferably, the power subsystem is provided with at least two electronic speed regulators, and the electronic speed regulators are arranged at intervals between every two adjacent electronic speed regulators.
Preferably, the fuselage of the unmanned aerial vehicle is provided with a sealed nacelle hanger, a power compartment sealing ring, a flap sealing rubber strip and a battery sealing ring, so that the fuselage is in a completely sealed state.
In the process of using the multi-mode high-performance rotor unmanned aerial vehicle provided by the invention, if a mooring mode is required, the battery is taken out from the battery bin, and the mooring airborne power supply is connected with the mooring interface, so that the mooring airborne power supply supplies power to the power supply system and the power subsystem and is in the mooring mode; when the mode of flying is put in needs use, need to be with the disconnection of being connected between mooring airborne power and the mooring interface, install the power in the battery compartment, make the power supply for electrical power generating system and power subsystem power supply, unmanned aerial vehicle is in the mode of flying.
Compared with the prior art, the multi-mode high-performance rotor unmanned aerial vehicle provided by the invention can select the working mode according to different actual conditions, and can be switched between the mooring mode and the flying mode, so that the same unmanned aerial vehicle can work according to different working modes.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
Fig. 1 is a schematic structural view of a particular embodiment of a multi-mode, high-performance rotary-wing drone provided by the present invention;
fig. 2 is a top view of the multi-mode, high-performance rotary-wing drone of fig. 1;
fig. 3 is a front view of the multi-mode, high-performance rotary-wing drone of fig. 1;
fig. 4 is a side view of the multi-mode, high-performance rotary-wing drone of fig. 1;
fig. 5 is a schematic cross-sectional view of the multi-mode, high-performance rotary-wing drone of fig. 1;
FIG. 6 is a schematic structural diagram of a quick release mechanism according to the present invention;
fig. 7 is an information interaction diagram of a multi-mode, high-performance rotorcraft provided by the present invention.
In FIGS. 1-7:
the system comprises a power subsystem 1, a double differential antenna 2, a navigation flight control computer 3, a system expansion interface 4, a wireless transmission airborne terminal 5, a task load subsystem 6, a wireless transmission ground terminal 7, ground station software 8, a ground differential station 9, a lock catch 10, a lock seat 11, a machine body lock groove 12, a propeller 13 and a machine body 14.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The core of the invention is to provide a multi-mode high-performance rotor unmanned aerial vehicle, and the suspended unmanned aerial vehicle can be switched between a mooring mode and a flying mode by arranging a mooring interface and a battery bin for installing a battery.
Referring to fig. 1-7, fig. 1 is a schematic structural diagram of an embodiment of a multi-mode, high-performance rotorcraft in accordance with the present invention; fig. 2 is a top view of the multi-mode, high-performance rotary-wing drone of fig. 1; fig. 3 is a front view of the multi-mode, high-performance rotary-wing drone of fig. 1; fig. 4 is a side view of the multi-mode, high-performance rotary-wing drone of fig. 1; fig. 5 is a schematic cross-sectional view of the multi-mode, high-performance rotary-wing drone of fig. 1; FIG. 6 is a schematic structural diagram of a quick release mechanism according to the present invention; fig. 7 is an information interaction diagram of a multi-mode, high-performance rotorcraft provided by the present invention.
This particular embodiment provides a multi-mode, high performance's rotor unmanned aerial vehicle, includes: the power supply system comprises a power supply system, a power subsystem 1 and a power supply mechanism for supplying power to the power supply system and the power subsystem 1; the power supply mechanism is provided with a battery bin for mounting a battery and a mooring interface for connecting with a mooring airborne power supply; the battery is arranged in the battery compartment, the battery supplies power to the power supply system and the power subsystem 1, and the unmanned aerial vehicle is in a flying mode; under mooring interface and the connected state of mooring airborne power supply, mooring airborne power supply supplies power for electrical power generating system and power subsystem 1, and unmanned aerial vehicle is in the mooring mode.
The unmanned aerial vehicle consists of an unmanned aerial vehicle platform subsystem, a task load subsystem 6, a measurement and control subsystem and a maintenance and guarantee subsystem, wherein the unmanned aerial vehicle platform subsystem comprises a body structure subsystem, a power subsystem 1, an electric subsystem and a navigation flight control subsystem; the measurement and control subsystem comprises a wireless transmission system and ground station software 8; mission load subsystem 6 is a photovoltaic pod.
After the unmanned aerial vehicle takes off from the vehicle-mounted platform, the unmanned aerial vehicle flies according to a preset task route, and after the unmanned aerial vehicle reaches a target area, the photoelectric pod is started to execute a task. After the task is completed, the unmanned aerial vehicle navigates back and lands.
In the process of using the multi-mode high-performance rotor unmanned aerial vehicle provided by the embodiment, if the mooring mode is needed, the battery is taken out of the battery bin, and the mooring airborne power supply is connected with the mooring interface, so that the mooring airborne power supply supplies power to the power supply system and the power subsystem 1, and the unmanned aerial vehicle is controlled to fly and is in the mooring mode; when the mode of flying is put to needs use, need to be with the disconnection of being connected between mooring airborne power and the mooring interface, install the power in the battery compartment, make the power supply for electrical power generating system and power subsystem 1 power supply, unmanned aerial vehicle is in the mode of flying.
Compare in prior art, the rotor unmanned aerial vehicle of multi-mode, high performance that this embodiment provided can select the mode according to actual conditions's difference to can switch between mooring the mode and the mode of flying off, can make same unmanned aerial vehicle work according to the mode of difference.
Preferably, rotor unmanned aerial vehicle adopts the mooring interface of reserving at lithium cell group kneck, demolishs the lithium cell group when mooring the mode, reserves the repacking that the interface directly links to each other just can realize mooring the mode with mooring airborne power and communication interface and aircraft end. The electric energy is transmitted to the power supply module and the power subsystem 1, and is also respectively connected with the flight control navigation module and the photoelectric pod for supplying power, so that the mooring working state in a battery-free mode is completed.
When the flight mode is adopted, the rotor unmanned aerial vehicle installs the battery into the battery bin, the electric energy of the lithium battery pack is transmitted to the power module and the power subsystem 1, and is connected with the flight control navigation module and the photoelectric pod to supply power to the whole system.
The mooring interface is arranged inside the battery compartment, and the battery is arranged in the battery compartment, and the mooring interface is covered by the battery.
The mooring interface is blocked by the battery, so that the situation that the battery is forgotten to be taken down in a mooring mode can be avoided, and misoperation is avoided.
The battery compartment is located the lower part of unmanned aerial vehicle's fuselage 14, and the lower part of fuselage 14 is provided with the quick detach mechanism of quick assembly disassembly battery.
The quick release mechanism comprises a lock catch 10, a lock seat 11 for installing the lock catch 10 and a machine body lock groove 12 matched with the lock catch 10 to lock or unlock; when the battery is installed in place, the lock catch 10 is locked with the body lock groove 12.
When the unmanned aerial vehicle is installed in the battery, the quick release mechanism receives the elasticity of the torsion spring, the lock catch 10 automatically slides into the body lock groove 12 along with the continuous increase of the depth of the battery, and a locking state is achieved, when the power battery needs to be disassembled, the lock catch 10 is pulled downwards, namely, the direction indicated by an arrow in fig. 6 enables the lock catch 10 to slide out of the body lock groove 12, so that unlocking is facilitated.
In another embodiment, unmanned aerial vehicle's undercarriage is hollow combined material structure, and the bottom of undercarriage be provided with the spear type magnetism suction plate complex steel sheet in the vehicle, hollow combined material structure can make the weight loss of undercarriage, and the cooperation of steel sheet and spear type magnetism suction plate in the vehicle can realize unmanned aerial vehicle's rising and falling.
Preferably, the steel sheet is provided with transverse grains.
The steel sheet that is used for sealing is provided with to the bottom terminal surface of undercarriage, is in order to make better and the undercarriage veneer of steel sheet ability, and the steel sheet is provided with horizontal line, can increase its area with the undercarriage veneer. A spear type magnetic suction plate can be placed on the vehicle to complete vehicle-mounted take-off and landing.
Under the condition of airborne rise and fall, the unmanned aerial vehicle and the vehicle are precisely positioned, attitude measured and precisely landed by adopting the advanced high-precision dynamic RTK differential measurement, high-precision navigation or inertial navigation combined navigation equipment and matched special equipment. In the dynamic RTK mode, navigation modules in the vehicle-mounted navigation flight control system and the airborne navigation flight control system receive differential data uploaded by a differential reference station in real time, and in the dynamic RTK differential positioning mode, the integrated navigation flight control system performs KALMAN filtering information fusion on the bucket RTK satellite navigation and inertial navigation and outputs high-precision course, posture, position and other parameters of the vehicle and the unmanned aerial vehicle respectively. The airborne navigation flight control system accurately measures parameters such as the attitude, the speed and the position of the unmanned aerial vehicle in real time, outputs information such as the course, the attitude angle, the speed, the position and the time of the unmanned aerial vehicle, and simultaneously downloads the parameters to the ground station and the vehicle through a data link; the navigation flight control system accurately measures parameters such as the attitude, the speed and the position of the vehicle in real time, outputs information such as the course, the attitude angle, the speed, the position and the time of the vehicle to the unmanned aerial vehicle, and uploads the parameters to the unmanned aerial vehicle airborne flight control system through the data link. The flight control system carries out control law resolving according to the deviation, outputs control instructions to control actuating mechanisms such as a motor and a steering engine, and then controls the attitude, the speed, the position and the like of the unmanned aerial vehicle, finally enables the unmanned aerial vehicle to be aligned with the landing point, and controls the unmanned aerial vehicle to accurately land.
The gap that has a plurality of undercarriage sizes on the vehicle-mounted platform, unmanned aerial vehicle slow speed reduction, scratch into the gap behind the undercarriage touching descending platform to it is fixed through magnetism.
The mooring unmanned aerial vehicle provides continuous power supply through the vehicle-mounted mooring cable, can be left empty for a long time, executes tasks such as reconnaissance and communication relay, and realizes maneuvering through a vehicle-mounted mode. Mooring unmanned aerial vehicle system mainly contains unmanned aerial vehicle platform, navigation flight control, measurement and control link, ground equipment etc. and the work of doing is in non-mooring mode: the unmanned aerial vehicle disconnects the ground power supply, removes the airborne primary power supply and the emergency battery, and replaces the power battery.
The typical mission profile of a tethered drone system is: and (3) taking off and landing on a vehicle, carrying a photoelectric load, ascending to a mooring height of 100m, performing a multi-angle staring (or stably tracking a moving target) task to a landing point target after being left empty for 8-12 hours, descending at a constant speed by the task height after the work is finished, and then completing system withdrawal.
In another embodiment, the power subsystem 1 has a four-shaft eight-propeller structure, each power shaft is provided with one propeller 13 at the upper and lower parts, and the mounting angle of the propeller 13 arranged at the lower part of the power shaft is 3 °.
The power subsystem 1 provides lift and attitude control power for unmanned aerial vehicle system work through four symmetrical arrangement with eight motors, electricity accent, screw 13 combination, maintains that the unmanned aerial vehicle platform is balanced, carries out the service task.
Unmanned aerial vehicle's power subsystem 1 adopts sharing mount pad integrated design, eight power module of group altogether, install two sets of power module on every power support arm, constitute a driving system, adopt the screw to screw up fixedly from support arm covering excircle to power module mounting point, adopt single face auricle and motor to link to each other between motor and the electricity regulation, the electricity is transferred and is leaned on one's side the body and put immediately, another face auricle and power support arm fix with screw, extend the auricle of corresponding installation with it on the motor installation face, the auricle mounting hole is the screw hole is transferred to the electricity, the electricity is transferred and is transferred between the electricity and stagger certain distance, the erection angle of.
The unmanned aerial vehicle adopts four shafts and eight propellers, and the propellers 13 which are coaxially arranged and arranged in a double-propeller mode and are positioned at the lower part can be interfered by the rotating airflow of the propellers 13 at the upper part, so that power loss is generated; in order to improve the efficiency of the propeller 13 of the unmanned aerial vehicle and increase the time and range of the flight, a method of changing the installation angle of the coaxial lower propellers is adopted, and the power loss is reduced. A four-shaft eight-paddle system with high power efficiency is designed through theoretical calculation and a large number of tests. The lower oar is a propeller 13 located at the lower part, and the upper oar is a propeller 13 located at the upper part.
According to the theory of the momentum of the leaf elements, the induced speed of the upper paddle to the lower paddle is calculated, the installation angle of the lower paddle is selected, an experiment is carried out, and the installation angle value of the lower paddle with the highest pneumatic efficiency is searched. And obtaining the result of the highest combination efficiency when the lower paddle mounting angle is 3 degrees through a power test experiment of the mounting angle of 0-4 degrees. From experimental data, when a 5-kilogram pulling force is set for cruise, the maximum force effect of the lower paddle at the installation angle of 0 degrees is 9.909575, the maximum force effect of the lower paddle at the installation angle of 3 degrees is 11.3554, and the force effective value is improved by 13%.
Related heat dissipation still including doing benefit to radiating heat dissipation aluminum plate, unmanned aerial vehicle's wireless transmission system, electrical power generating system all set up with the laminating of heat dissipation aluminum plate, and between wireless transmission system and the heat dissipation aluminum plate, all be coated with heat transfer material between electrical power generating system and the heat dissipation aluminum plate.
The power subsystem 1 is provided with at least two electronic speed regulators, and the adjacent electronic speed regulators are arranged at intervals.
Airflow of the power system enters the support arm through the heat dissipation holes, the airflow in the support arm is sucked outwards by the high-speed rotation of the motor, and the electrically adjusted cooling fins are positioned in an airflow loop; the integrated design of the power modules sharing the mounting seat is adopted, eight groups of power modules are provided, two groups of power modules are mounted on each power support arm to form a power system, and the positions of the electronic speed regulators are staggered, so that the air flow in the support arms can be sucked outwards when the motor rotates at a high speed, and the radiating fins of the power system are always in an air flow loop. The reliability and the heat dissipation performance of the motor system are guaranteed.
Preferably, the fuselage 14 of the unmanned aerial vehicle is provided with a sealed nacelle hanger, a power compartment sealing ring, a flap sealing rubber strip and a battery sealing ring, so that the fuselage 14 is in a completely sealed state; the bottom of the body 14 is provided with a waterproof vent valve, and the air permeability can be rapidly recovered after the body is contacted with liquid.
As shown in fig. 7, the system comprises a power subsystem 1, a double differential antenna 2, a navigation flight control computer 3, a system expansion interface 4, a wireless transmission airborne terminal 5, a task load subsystem 6, a wireless transmission ground terminal 7, ground station software 8 and a ground differential station 9; the navigation flight control computer 3 collects the motion state information of the unmanned aerial vehicle, sends a control instruction to the power subsystem 1 after the flight control law is resolved, and electrically adjusts and controls the motor speed of the rotor power system to realize the flight control of the unmanned aerial vehicle. Meanwhile, the navigation flight control computer 3 receives a remote control instruction of a ground operator from the measurement and control subsystem, manages and controls the flight task and the photoelectric pod, and sends information such as the motion state information of the unmanned aerial vehicle, the working state of airborne equipment, the working state video image of the photoelectric pod and the like back to the ground station through the measurement and control subsystem; wherein the information interaction relationship is shown as 7.
The remote control information of the ground station software 8 and the differential information of the ground differential station 9 are sent to the navigation flight control computer 3 through the wireless transmission airborne terminal 5, the double differential antenna 2 provides positioning and orientation information for the navigation flight control computer 3, the task load subsystem 6 provides information such as images and the like for the navigation flight control computer 3, and the power subsystem 1 provides information such as voltage, current, temperature, motor rotating speed, motor running state, fault state and the like for the navigation flight control computer 3 to drive the power subsystem 1 and the task load system. Meanwhile, the navigation flight control computer 3 transmits the information of the attitude, the position and the like of the unmanned aerial vehicle to the ground station software 8 through the wireless transmission airborne terminal 5. Unmanned aerial vehicle possesses mooring extension function and relay extension function, and mooring extension function includes: the device is provided with an SDI interface, and 3 paths of asynchronous RS422 interfaces (2 paths of connection flight control and 1 path of connection difference) are provided for transmitting image screen information; the lithium battery pack power supply interface is multiplexed with the mooring expansion power supply interface.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. Any combination of all embodiments provided by the present invention is within the scope of the present invention, and will not be described herein.
The multi-mode high-performance rotor unmanned aerial vehicle provided by the invention is described in detail above. The principles and embodiments of the present invention are explained herein using specific examples, which are presented only to assist in understanding the method and its core concepts. It should be noted that, for those skilled in the art, it is possible to make various improvements and modifications to the present invention without departing from the principle of the present invention, and those improvements and modifications also fall within the scope of the claims of the present invention.
Claims (10)
1. A multi-mode, high performance rotorcraft, comprising: the power supply system comprises a power supply system, a power subsystem (1) and a power supply mechanism for supplying power to the power supply system and the power subsystem (1);
the power supply mechanism is provided with a battery bin for mounting a battery and a mooring interface for connecting with a mooring airborne power supply;
the battery is arranged in the battery cabin, the battery supplies power to the power supply system and the power subsystem (1), and the unmanned aerial vehicle is in a flying mode;
the mooring interface is connected with the mooring airborne power supply, the mooring airborne power supply supplies power to the power system and the power subsystem (1), and the unmanned aerial vehicle is in a mooring mode.
2. A multi-mode, high-performance rotary-wing drone according to claim 1, wherein the tethered interface is disposed inside the battery compartment, and the battery is mounted in the battery compartment state, the tethered interface being covered by the battery.
3. A multi-mode, high-performance rotary-wing drone according to claim 1, characterized in that the battery compartment is located in the lower part of the drone's fuselage (14), the lower part of the fuselage (14) being provided with a quick-release mechanism that allows quick disassembly of the battery.
4. A multi-mode, high-performance rotary-wing drone according to claim 3, characterized in that the quick release mechanism comprises a shackle (10), a lock seat (11) to which the shackle (10) is mounted, and a fuselage lock slot (12) which cooperates with the shackle (10) to lock or unlock;
and when the battery is installed in place, the lock catch (10) is matched and locked with the machine body lock groove (12).
5. A multi-mode, high-performance rotary-wing drone according to any one of claims 1 to 4, characterized in that the landing gear of the drone is of hollow composite structure and the bottom of the landing gear is provided with steel sheets cooperating with the spear magnetic suction plates in the vehicle.
6. A multi-mode, high-performance rotary-wing drone according to claim 5, characterized in that said steel sheet is provided with transverse veins.
7. A multi-mode, high-performance rotary-wing drone according to claim 5, characterized in that the power subsystem (1) is of four-shaft eight-propeller configuration, one propeller (13) being provided one above and one below each power shaft, and the mounting angle of the propellers (13) provided on the lower part of the power shaft is 3 °.
8. The multi-mode, high-performance rotary wing unmanned aerial vehicle of claim 5, further comprising a heat dissipating aluminum plate facilitating heat dissipation, wherein the wireless transmission system of the unmanned aerial vehicle, the power system and the heat dissipating aluminum plate are both attached to each other, and heat transfer materials are coated between the wireless transmission system and the heat dissipating aluminum plate, and between the power system and the heat dissipating aluminum plate.
9. A multi-mode, high-performance rotary-wing drone according to claim 8, characterized in that the power subsystem (1) is provided with at least two electronic governors, with a spacing between adjacent ones.
10. A multi-mode, high-performance rotary-wing drone according to claim 5, characterized in that the drone fuselage (14) is provided with a sealed nacelle pylon, a power pod gasket, a flap gasket, and a battery gasket, so as to keep the fuselage (14) in a completely sealed condition.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011620716.3A CN112623207A (en) | 2020-12-30 | 2020-12-30 | Multi-mode, high-performance rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011620716.3A CN112623207A (en) | 2020-12-30 | 2020-12-30 | Multi-mode, high-performance rotor unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112623207A true CN112623207A (en) | 2021-04-09 |
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ID=75287395
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011620716.3A Pending CN112623207A (en) | 2020-12-30 | 2020-12-30 | Multi-mode, high-performance rotor unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112623207A (en) |
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2020
- 2020-12-30 CN CN202011620716.3A patent/CN112623207A/en active Pending
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