CN107458593B - Duct propulsion system based on multi-rotor unmanned aerial vehicle - Google Patents
Duct propulsion system based on multi-rotor unmanned aerial vehicle Download PDFInfo
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- CN107458593B CN107458593B CN201710790821.3A CN201710790821A CN107458593B CN 107458593 B CN107458593 B CN 107458593B CN 201710790821 A CN201710790821 A CN 201710790821A CN 107458593 B CN107458593 B CN 107458593B
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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
- B64U10/13—Flying platforms
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
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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
- B64U50/13—Propulsion using external fans or propellers
- B64U50/14—Propulsion using external fans or propellers ducted or shrouded
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention discloses a duct propulsion system based on a multi-rotor unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles; the system comprises a multi-rotor unmanned aerial vehicle, a cradle head interface I, a duct lift module and a cradle head interface II. The multi-rotor unmanned aerial vehicle is rigidly connected with the cradle head interface I, and the lower part of the cradle head interface I is rigidly connected with the duct lift module; the upper part of the cradle head interface II is rigidly connected with the duct lift module, the lower part of the cradle head interface II is provided with a reserved interface, and the reserved interface can be connected with the carried cradle head or other equipment. The invention uses the universal cradle head interface, can be rigidly and mechanically combined with consumer multi-rotor unmanned aerial vehicle with various models, can carry different ducts or batteries according to different load demands to improve the maximum lift force, does not need to be additionally provided with a complex duct control system, has great modification potential and design allowance, and saves great cost compared with the design of a duct unmanned aerial vehicle.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a duct propulsion system based on a multi-rotor unmanned aerial vehicle.
Background
Existing quad-rotor (or multi-rotor) aircraft employ four (or more) rotors as a direct source of power for the flight. Taking four rotor unmanned aerial vehicle as an example, rotor symmetric distribution is in the front and back of organism, left and right sides four directions, and four rotors are in same altitude plane, and four rotor's structure and radius are the same, and four motors are installed at the support end of aircraft symmetrically, and flight control computer and external equipment are laid in the space in the middle of the support.
The aircraft is driven by adopting the small brushless motor and the rotor (propeller), and the pull force of the small brushless motor currently used for the multi-rotor unmanned aerial vehicle is 800g-2000 g/shaft at maximum, the manufacturing cost is high, and the aircraft is mainly used for the industrial multi-rotor unmanned aerial vehicle. The current consumer unmanned plane has a pulling force of only 350g-400 g/shaft, the carrying capacity is insufficient due to lower pulling force, and the rotating speed of the propeller is improved but the efficiency of the propeller is also reduced when the propeller with a fixed diameter provides a larger pushing force due to the inherent pneumatic problem of the propeller. Namely, when the unmanned aerial vehicle carries a heavy load, the propeller provides a large thrust, so that the rotating speed of the propeller is increased, the efficiency of the propeller is reduced, and the flight time and the flight distance of the unmanned aerial vehicle are obviously shortened when the unmanned aerial vehicle carries the heavy load. Because the small brushless motor carried by the consumer unmanned aerial vehicle is limited in power, the load carrying efficiency is low, and the task of carrying a heavy load cannot be completed.
The existing consumer-grade four-rotor (multi-rotor) obviously shortens the flight time and the flight radius of the unmanned aerial vehicle under the condition of carrying an overload task load because of cost and design problems, and cannot carry the task load exceeding self thrust.
The ratio of the effective power of the propeller to the output power of the engine is called the propeller efficiency
In order to solve the problem that the flight time and the flight distance of an unmanned aerial vehicle are obviously shortened when carrying a heavy load, the prior art scheme has the following two types:
(1) Patent name: tilting double-duct unmanned plane (application number: 20160382189.4)
This patent is a tilting double duct unmanned aerial vehicle, and the structure includes: a central wing, a flight control device, avionics, electrical devices, and a duct tilting control mechanism inside the central wing; avionics, electrical equipment, and ducted tilting control mechanisms are respectively connected with the flight control equipment.
The bypass unmanned aerial vehicle takes the bypass as a power system of the unmanned aerial vehicle, and the bypass control system and the power supply system are arranged in the unmanned aerial vehicle flight control and are integrally connected with the unmanned aerial vehicle, so that the design cost and the manufacturing cost are high, and the maintenance and the replacement are inconvenient.
(2) Patent name: electric bypass rotor unmanned plane (application number: 201610872892)
The patent is an electric duct rotor unmanned aerial vehicle, and it relates to an unmanned aerial vehicle. In this patent, a plurality of first plastics rings and a plurality of second plastics rings coaxial setting and connect in turn and form the duct body, a plurality of axial supports are erect on the duct body, the top of every axial support is connected with last support frame, the screw, support for the guide vane and support for the steering wheel from last to suit in proper order on the output shaft of motor down, a plurality of guide vanes are established on the support for the guide vane, the both ends of every guide vane can be dismantled with the support for the guide vane and the inner wall of duct body respectively and be connected, a plurality of rudder pieces are established on the support for the steering wheel, the both ends of every rudder piece can be dismantled with the inner wall of support for the steering wheel and duct body respectively and be connected.
The patent arranges the control system and the power system in the duct, takes the duct fan as the external structure of the whole machine body, and the duct and the unmanned aerial vehicle are integrated, so that the design difficulty is high, the technical difficulty is high, the design cost and the manufacturing cost are high, and the duct is inconvenient to maintain and replace.
The two representative prior art drawbacks described above are: the novel ducted unmanned aerial vehicle is redesigned on the basis of the traditional multi-rotor unmanned aerial vehicle. And complicated duct control systems and avionics equipment are added, so that the design cost and the manufacturing cost are high, and the ducts and other matched equipment are inconvenient to maintain and replace.
The technical problems to be solved by the invention are as follows: the existing ducted propulsion system cannot be suitable for consumer multi-rotor unmanned aerial vehicles on the market.
Disclosure of Invention
In order to improve the loading capacity of the multi-rotor aircraft, the invention additionally installs an independent ducted lift module under the traditional multi-rotor aircraft, and utilizes the characteristic that the ducted fan can generate larger thrust than an isolated propeller with the same diameter under the same power, integrates the ducted fan and a power supply and a control system thereof into one ducted lift module, and is used as an external attachment of the consumer multi-rotor unmanned aerial vehicle, thereby providing additional lift, increasing the flight time and flight distance of the unmanned aerial vehicle and enabling the traditional consumer multi-rotor aircraft to load heavier task loads to execute tasks.
A duct propulsion system based on a multi-rotor unmanned aerial vehicle comprises a multi-rotor unmanned aerial vehicle 10, a cradle head interface I20, a duct lift module 30 and a cradle head interface II 40. The ducted lift module 30 and the multi-rotor unmanned aerial vehicle 10 are independent modules.
The multi-rotor unmanned aerial vehicle 10 is rigidly connected with the cradle head interface I20, and the lower part of the cradle head interface I20 is rigidly connected with the duct lift module 30; the upper part of the cradle head interface II 40 is rigidly connected with the duct lift module 30, and a reserved interface is arranged at the lower part of the cradle head interface II 40 and can be connected with the carried cradle head or other equipment.
The ducted lift module 30 is composed of a battery 3010, a power switch 3020, a left ducted fan 3030, a right ducted fan 3040, a left electronic speed regulator 3050, a right electronic speed regulator 3060, an electric speed regulator server 3070, a remote control signal receiver 3080, and a mode controller 3090.
The battery 3010 provides power for the left ducted fan 3030, the right ducted fan 3040, the left electronic governor 3050, the right electronic governor 3060, the electronic governor server 3070, the remote control signal receiver 3080, and the mode controller 3090.
The power switch 3020 is a single pole single throw switch for controlling the on/off of the battery 3010.
The left ducted fan 3030 and the right ducted fan 3040 are a pair of forward and reverse propeller ducted fans and are arranged at two sides of the multi-rotor unmanned aerial vehicle 10, and the left ducted fan 3030 and the right ducted fan 3040 provide thrust for the ducted lift module 30.
The left electronic speed regulator 3050 is connected with the left ducted fan 3030, the right electronic speed regulator 3060 is connected with the right ducted fan 3040, and the left electronic speed regulator 3050 and the right electronic speed regulator 3060 regulate the rotation speeds of the left ducted fan 3030 and the right ducted fan 3040 through the electric speed regulating server 3070 or the remote control signal receiver 3080 so as to regulate the thrust.
The electric tuning server 3070 has a gear adjusting function, the electric tuning server 3070 is respectively connected with the electronic speed regulator 3050 and the right electronic speed regulator 3060, and the electric tuning server 3070 controls the left electronic speed regulator 3050 and the right electronic speed regulator 3060 so as to control the rotation speeds of the left ducted fan 3030 and the right ducted fan 3040.
The remote control signal receiver 3080 is connected with the left electronic speed regulator 3050 and the right electronic speed regulator 3060, and the remote control signal receiver 3080 receives a radio signal sent by an external duct remote controller of the multi-rotor unmanned aerial vehicle 10 and sends the radio signal to the left electronic speed regulator 3050 and the right electronic speed regulator 3060, so as to control the rotation speeds of the left duct fan 3030 and the right duct fan 3040.
The mode controller 3090 is a single pole double throw switch, and is used to control the switching of the electric tuning server 3070 and the remote control signal receiver 3080.
The rigid connection is screw connection, mortise-tenon connection or slide rail connection.
The control takeoff flow of the multi-rotor unmanned aerial vehicle 10 is as follows:
when the multi-rotor unmanned aerial vehicle 10 is not additionally provided with the ducted lift module 30, the take-off flow of the multi-rotor unmanned aerial vehicle 10 is as follows: after the power supply of the multi-rotor unmanned aerial vehicle 10 is firstly connected, the multi-rotor unmanned aerial vehicle 10 is unlocked through the unmanned aerial vehicle remote controller, a take-off instruction is sent to the multi-rotor unmanned aerial vehicle 10 through the unmanned aerial vehicle remote controller, the rotating speed of the propeller of the multi-rotor unmanned aerial vehicle 10 is accelerated, lift force is provided, and the multi-rotor unmanned aerial vehicle 10 takes off.
When the load is required to be increased, the duct lift module 30 is additionally arranged on the multi-rotor unmanned aerial vehicle 10, and the specification of the duct lift module 30 is changed according to different loads. The takeoff flow at this time is as follows:
step 1: the unmanned aerial vehicle flying hand is connected with the power supply of the multi-rotor unmanned aerial vehicle 10.
Step 2: the unmanned aerial vehicle flying hand turns on the power switch 3020 communicated with the duct lift module 30, so that the duct lift module 30 is in an on state.
Step 3: the unmanned aerial vehicle operator selects the relevant mode of the ducted lift module 30 using the mode selector 3090, such as the switch up to manual mode and the switch down to remote mode.
Step 4A-1: if manual mode is selected, the drone fly manually adjusts the gear on the electric adjustment server 3070, causing the ducted lift module 30 to generate lift according to the selected gear.
Step 4A-2: unmanned aerial vehicle flying hands pass through many rotor unmanned aerial vehicle 10 of unmanned aerial vehicle remote controller unblock, and unmanned aerial vehicle flying hands control unmanned aerial vehicle remote controller sends the instruction of taking off to many rotor unmanned aerial vehicle 10, and many rotor unmanned aerial vehicle 10 receive the instruction of taking off and start the screw, and many rotor unmanned aerial vehicle 10 is in this moment take off under the combined action of the lift that duct lift module 30 and self screw provided.
Step 4B-1: if the remote control mode is selected, the unmanned aerial vehicle fly opens the external duct remote controller to send an instruction to the duct lift module 30, and the duct lift module 30 receives the instruction of the external duct remote controller to generate lift.
Step 4B-2: unmanned aerial vehicle flying hands pass through many rotor unmanned aerial vehicle 10 of unmanned aerial vehicle remote controller unblock to control unmanned aerial vehicle remote controller sends the instruction of taking off to many rotor unmanned aerial vehicle 10, many rotor unmanned aerial vehicle 10 start screw, many rotor unmanned aerial vehicle 10 are taking off this moment under the combined action of the lift that duct lift module 30 and self screw provided.
The invention uses the universal cradle head interface, can be rigidly and mechanically combined with consumer multi-rotor unmanned aerial vehicle with various models on the market, can carry different culverts or batteries according to different load demands to improve the maximum lift force, does not need to be additionally provided with a complex culvert control system, has great modification potential and design allowance, and saves great cost compared with the design of a culvert unmanned aerial vehicle.
Drawings
Fig. 1 is a diagram of a structure of an unmanned aerial vehicle based on a ducted propulsion module.
FIG. 2 is a schematic structural view of a ducted lift module.
Fig. 3 is a top view of a unmanned aerial vehicle based on a ducted propulsion module.
Fig. 4 is a schematic diagram of a takeoff operation flow of the unmanned aerial vehicle when the ducted lift module is not added.
Fig. 5 is a schematic diagram of a takeoff operation flow of the unmanned aerial vehicle when the ducted lift module is additionally arranged.
Detailed Description
As shown in fig. 1-5, a ducted propulsion system based on a multi-rotor unmanned aerial vehicle includes a multi-rotor unmanned aerial vehicle 10, a cradle head interface i 20, a ducted lift module 30, and a cradle head interface ii 40.
The multi-rotor unmanned aerial vehicle 10 is rigidly connected with the cradle head interface I20, and the lower part of the cradle head interface I20 is rigidly connected with the duct lift module 30; the upper part of the cradle head interface II 40 is rigidly connected with the duct lift module 30, and a reserved interface is arranged at the lower part of the cradle head interface II 40 and can be connected with the carried cradle head or other equipment.
The ducted lift module 30 is composed of a battery 3010, a power switch 3020, a left ducted fan 3030, a right ducted fan 3040, a left electronic speed regulator 3050, a right electronic speed regulator 3060, an electric speed regulator server 3070, a remote control signal receiver 3080, and a mode controller 3090.
The battery 3010 provides power for the left ducted fan 3030, the right ducted fan 3040, the left electronic governor 3050, the right electronic governor 3060, the electronic governor server 3070, the remote control signal receiver 3080, and the mode controller 3090.
The power switch 3020 is a single pole single throw switch for controlling the on/off of the battery 3010.
The left ducted fan 3030 and the right ducted fan 3040 are a pair of forward and reverse propeller ducted fans and are arranged at two sides of the multi-rotor unmanned aerial vehicle 10, and the left ducted fan 3030 and the right ducted fan 3040 provide thrust for the ducted lift module 30.
The left electronic speed regulator 3050 is connected with the left ducted fan 3030, the right electronic speed regulator 3060 is connected with the right ducted fan 3040, and the left electronic speed regulator 3050 and the right electronic speed regulator 3060 regulate the rotation speeds of the left ducted fan 3030 and the right ducted fan 3040 through the electric speed regulating server 3070 or the remote control signal receiver 3080 so as to regulate the thrust.
The electric tuning server 3070 has a gear adjusting function, the electric tuning server 3070 is respectively connected with the electronic speed regulator 3050 and the right electronic speed regulator 3060, and the electric tuning server 3070 controls the left electronic speed regulator 3050 and the right electronic speed regulator 3060 so as to control the rotation speeds of the left ducted fan 3030 and the right ducted fan 3040.
The remote control signal receiver 3080 is connected with the left electronic speed regulator 3050 and the right electronic speed regulator 3060, and the remote control signal receiver 3080 receives a radio signal sent by an external duct remote controller of the multi-rotor unmanned aerial vehicle 10 and sends the radio signal to the left electronic speed regulator 3050 and the right electronic speed regulator 3060, so as to control the rotation speeds of the left duct fan 3030 and the right duct fan 3040.
The mode controller 3090 is a single pole double throw switch, and is used to control the switching of the electric tuning server 3070 and the remote control signal receiver 3080.
The rigid connection is screw connection, mortise-tenon connection or slide rail connection.
The control of the examples is described below:
when the multi-rotor unmanned aerial vehicle 10 is not additionally provided with the ducted lift module 30, the take-off flow of the multi-rotor unmanned aerial vehicle 10 is as follows: after the power supply of the multi-rotor unmanned aerial vehicle 10 is firstly connected, the multi-rotor unmanned aerial vehicle 10 is unlocked through the unmanned aerial vehicle remote controller, a take-off instruction is sent to the multi-rotor unmanned aerial vehicle 10 through the unmanned aerial vehicle remote controller, the rotating speed of the propeller of the multi-rotor unmanned aerial vehicle 10 is accelerated, lift force is provided, and the multi-rotor unmanned aerial vehicle 10 takes off.
When the load is required to be increased, the duct lift module 30 is additionally arranged on the multi-rotor unmanned aerial vehicle 10, and the specification of the duct lift module 30 is changed according to different loads. The takeoff flow at this time is as follows:
step 1: the unmanned aerial vehicle flying hand is connected with the power supply of the multi-rotor unmanned aerial vehicle 10.
Step 2: the unmanned aerial vehicle flying hand turns on the power switch 3020 communicated with the duct lift module 30, so that the duct lift module 30 is in an on state.
Step 3: the unmanned aerial vehicle operator selects the relevant mode of the ducted lift module 30 using the mode selector 3090, such as the switch up to manual mode and the switch down to remote mode.
Step 4A-1: if manual mode is selected, the drone fly manually adjusts the gear on the electric adjustment server 3070, causing the ducted lift module 30 to generate lift according to the selected gear.
Step 4A-2: unmanned aerial vehicle flying hands pass through many rotor unmanned aerial vehicle 10 of unmanned aerial vehicle remote controller unblock, and unmanned aerial vehicle flying hands control unmanned aerial vehicle remote controller sends the instruction of taking off to many rotor unmanned aerial vehicle 10, and many rotor unmanned aerial vehicle 10 receive the instruction of taking off and start the screw, and many rotor unmanned aerial vehicle 10 is in this moment take off under the combined action of the lift that duct lift module 30 and self screw provided.
Step 4B-1: if the remote control mode is selected, the unmanned aerial vehicle fly opens the external duct remote controller to send an instruction to the duct lift module 30, and the duct lift module 30 receives the instruction of the external duct remote controller to generate lift.
Step 4B-2: unmanned aerial vehicle flying hands pass through many rotor unmanned aerial vehicle 10 of unmanned aerial vehicle remote controller unblock to control unmanned aerial vehicle remote controller sends the instruction of taking off to many rotor unmanned aerial vehicle 10, many rotor unmanned aerial vehicle 10 start screw, many rotor unmanned aerial vehicle 10 are taking off this moment under the combined action of the lift that duct lift module 30 and self screw provided.
The multi-rotor unmanned aerial vehicle 10 is composed of a power system, an avionics control system, a cradle head interface and an unmanned aerial vehicle remote controller.
The types and specifications of the ducted lift modules 30 can be changed according to different load requirements, for example, when carrying a load of 1 kg level, a pair of 50 mm ducts with a single thrust of 900g can be selected as the power source of the ducted lift modules 30. For example, when carrying a 5 kg load, a pair of 90 mm culverts with a single thrust of 3.5 kg may be selected as the source of power for the culvert lift module 30. And the same ducted lift module can provide thrust with different magnitudes.
Claims (1)
1. A control method of a ducted propulsion system based on a multi-rotor unmanned aerial vehicle is characterized by comprising the following steps of: the duct propulsion system comprises a multi-rotor unmanned aerial vehicle (10), a cradle head interface I (20), a duct lift module (30) and a cradle head interface II (40); the ducted lift module (30) and the multi-rotor unmanned aerial vehicle (10) are mutually independent modules;
the multi-rotor unmanned aerial vehicle (10) is rigidly connected with the cradle head interface I (20), and the lower part of the cradle head interface I (20) is rigidly connected with the duct lift module (30); the upper part of the cradle head interface II (40) is rigidly connected with the culvert lifting module (30), a reserved interface is arranged at the lower part of the cradle head interface II (40), and the reserved interface can be connected with the carried cradle head;
the ducted lift module (30) consists of a battery (3010), a power switch (3020), a left ducted fan (3030), a right ducted fan (3040), a left electronic speed regulator (3050), a right electronic speed regulator (3060), an electric speed regulator server (3070), a remote control signal receiver (3080) and a mode controller (3090);
the battery (3010) provides power for the left ducted fan (3030), the right ducted fan (3040), the left electronic speed regulator (3050), the right electronic speed regulator (3060), the electric speed regulation server (3070), the remote control signal receiver (3080) and the mode controller (3090);
the power switch (3020) is a single-pole single-throw switch and is used for controlling the on/off of the battery (3010);
the left ducted fan (3030) and the right ducted fan (3040) are a pair of forward and reverse propeller ducted fans and are arranged on two sides of the multi-rotor unmanned aerial vehicle (10), and the left ducted fan (3030) and the right ducted fan (3040) provide thrust for the ducted lift modules (30);
the left electronic speed regulator (3050) is connected with the left ducted fan (3030), the right electronic speed regulator (3060) is connected with the right ducted fan (3040), and the left electronic speed regulator (3050) and the right electronic speed regulator (3060) regulate the rotating speeds of the left ducted fan (3030) and the right ducted fan (3040) through an electric speed regulation server (3070) or a remote control signal receiver (3080) so as to regulate the thrust;
the electric control servo (3070) has a gear adjusting function, the electric control servo (3070) is respectively connected with the left electronic speed regulator (3050) and the right electronic speed regulator (3060), the left electronic speed regulator (3050) and the right electronic speed regulator (3060) are controlled through the electric control servo (3070), and then the rotating speeds of the left ducted fan (3030) and the right ducted fan (3040) are controlled;
the remote control signal receiver (3080) is connected with the left electronic speed regulator (3050) and the right electronic speed regulator (3060), the remote control signal receiver (3080) receives radio signals sent by an external duct remote controller of the multi-rotor unmanned aerial vehicle (10) and sends the radio signals to the left electronic speed regulator (3050) and the right electronic speed regulator (3060), and further the rotating speeds of the left duct fan (3030) and the right duct fan (3040) are controlled;
the mode controller (3090) is a single-pole double-throw switch and is used for controlling the opening and closing of the electric modulation server (3070) and the remote control signal receiver (3080);
the rigid connection is screw connection, mortise-tenon connection or slide rail connection;
the method for controlling take-off of the multi-rotor unmanned aerial vehicle (10) comprises the following steps:
when the multi-rotor unmanned aerial vehicle (10) is not additionally provided with the duct lift module (30), the take-off flow of the multi-rotor unmanned aerial vehicle (10) is as follows: firstly, after a power supply of a multi-rotor unmanned aerial vehicle (10) is connected, unlocking the multi-rotor unmanned aerial vehicle (10) through an unmanned aerial vehicle remote controller, sending a take-off instruction to the multi-rotor unmanned aerial vehicle (10) through the unmanned aerial vehicle remote controller, accelerating the rotating speed of a propeller of the multi-rotor unmanned aerial vehicle (10), providing lifting force, and taking off the multi-rotor unmanned aerial vehicle (10);
when the load is required to be increased, a ducted lift module (30) is additionally arranged on the multi-rotor unmanned aerial vehicle (10), and the specification of the ducted lift module (30) is changed according to different loads; the takeoff control method at this time is as follows:
step 1: the unmanned aerial vehicle flying hand is connected with a power supply of the multi-rotor unmanned aerial vehicle (10);
step 2: the unmanned aerial vehicle flying hand opens a power switch (3020) communicated with the duct lift module (30) to enable the duct lift module (30) to be in an open state;
step 3: the unmanned aerial vehicle fly utilizes a mode controller (3090) to select a relevant mode of the ducted lift module (30), for example, a switch is in a manual mode upwards, and a switch is in a remote control mode downwards;
step 4A-1: if the manual mode is selected, the unmanned aerial vehicle fly manually adjusts the gear on the electric adjustment server (3070) so that the ducted lift module (30) generates lift according to the selected gear;
step 4A-2: the unmanned aerial vehicle flying hand unlocks the multi-rotor unmanned aerial vehicle (10) through the unmanned aerial vehicle remote controller, the unmanned aerial vehicle flying hand controls the unmanned aerial vehicle remote controller to send a take-off instruction to the multi-rotor unmanned aerial vehicle (10), the multi-rotor unmanned aerial vehicle (10) receives the take-off instruction to start the propeller, and at the moment, the multi-rotor unmanned aerial vehicle (10) takes off under the combined action of the lift provided by the ducted lift module (30) and the self propeller;
step 4B-1: if a remote control mode is selected, an unmanned aerial vehicle fly opens an external duct remote controller to send an instruction to the duct lift module (30), and the duct lift module (30) receives the instruction of the external duct remote controller to generate lift;
step 4B-2: unmanned aerial vehicle flying hands pass through many rotor unmanned aerial vehicle (10) of unmanned aerial vehicle remote controller unblock to control unmanned aerial vehicle remote controller sends the instruction of taking off to many rotor unmanned aerial vehicle (10), many rotor unmanned aerial vehicle (10) start screw, and many rotor unmanned aerial vehicle (10) unmanned aerial vehicle are in this moment take off under the combined action of the lift that duct lift module (30) and self screw provided.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710790821.3A CN107458593B (en) | 2017-09-05 | 2017-09-05 | Duct propulsion system based on multi-rotor unmanned aerial vehicle |
| PCT/CN2017/118524 WO2019047429A1 (en) | 2017-09-05 | 2017-12-26 | Multi-rotor unmanned aerial vehicle-based duct propulsion system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710790821.3A CN107458593B (en) | 2017-09-05 | 2017-09-05 | Duct propulsion system based on multi-rotor unmanned aerial vehicle |
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| CN107458593A CN107458593A (en) | 2017-12-12 |
| CN107458593B true CN107458593B (en) | 2023-09-12 |
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| CN107458593B (en) * | 2017-09-05 | 2023-09-12 | 北京工业大学 | Duct propulsion system based on multi-rotor unmanned aerial vehicle |
| CN109159633A (en) * | 2018-08-31 | 2019-01-08 | 长春工程学院 | A kind of amphibious unmanned plane |
| CN114954930A (en) * | 2022-06-16 | 2022-08-30 | 南京大学 | Double-rotor tail seat type unmanned aerial vehicle based on electric ducted fan |
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| WO2019047429A1 (en) | 2019-03-14 |
| CN107458593A (en) | 2017-12-12 |
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