CN207157519U - A kind of duct propulsion system based on multi-rotor unmanned aerial vehicle - Google Patents
A kind of duct propulsion system based on multi-rotor unmanned aerial vehicle Download PDFInfo
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- CN207157519U CN207157519U CN201721129963.7U CN201721129963U CN207157519U CN 207157519 U CN207157519 U CN 207157519U CN 201721129963 U CN201721129963 U CN 201721129963U CN 207157519 U CN207157519 U CN 207157519U
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- duct
- aerial vehicle
- speed regulator
- unmanned aerial
- ducted fan
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- 230000005540 biological transmission Effects 0.000 claims 1
- 238000000034 method Methods 0.000 abstract description 2
- 230000004048 modification Effects 0.000 abstract description 2
- 238000012986 modification Methods 0.000 abstract description 2
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 3
- 238000005183 dynamical system Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000008439 repair process Effects 0.000 description 3
- 230000033228 biological regulation Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
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Abstract
The utility model discloses a kind of duct propulsion system based on multi-rotor unmanned aerial vehicle, belong to unmanned air vehicle technique field；The system includes multi-rotor unmanned aerial vehicle, head interface I, duct lift module and head interface II.Multi-rotor unmanned aerial vehicle is with head interface I by being rigidly connected, and the bottom of head interface I is with duct lift module by being rigidly connected；The top of head interface II is with duct lift module by being rigidly connected, and the bottom of head interface II is provided with spare interface, and spare interface can be connected with the head or other equipment carried.The utility model uses general head interface, rigid mechanical can be carried out with the consumer level multi-rotor unmanned aerial vehicle of Multiple Type to be combined, and different ducts or battery can be carried according to different load-carrying demands to improve maximum lift, the duct control system of complexity need not be installed additional, there are very big potential modification and design margin, very big cost is saved than redesigning a duct unmanned aerial vehicle.
Description
Technical field
The utility model belongs to unmanned air vehicle technique field, and in particular to a kind of duct based on multi-rotor unmanned aerial vehicle promotes system
System.
Background technology
Existing four rotor (or more rotors) aircraft is using direct driving force source of four (or multiple) rotors as flight.
By taking four rotor wing unmanned aerial vehicles as an example, four direction, four rotors around that rotor is symmetrically distributed in body are in sustained height
Plane, and the structure of four rotors and radius are all identical, four motors are symmetrically mounted at the bracket end of aircraft, among support
Space lay flight-control computer and external equipment.
Above-mentioned aircraft is driven using small-sized brushless motor and rotor (propeller), and currently used for more rotors without
Man-machine small-sized brushless motor pulling force is up to 800g-2000g/ axles and involved great expense, and is used for technical grade multi-rotor unmanned aerial vehicle.
And the pulling force of consumer level unmanned plane is only 350g-400g/ axles at present, because pulling force is relatively low, cause load capacity insufficient, and because
The intrinsic aerodynamics problem of propeller, when providing compared with high thrust, revolution speed of propeller improves the propeller that diameter is fixed, but propeller
Efficiency can also decline.I.e. unmanned plane carries when carrying heavier load because propeller will provide compared with high thrust, revolution speed of propeller
Height, propeller efficiency decline, and cause unmanned plane flight time and flying distance when carrying heavier load substantially to shorten.Due to disappearing
It is limited to take the small-sized brushless motor power of level unmanned plane itself carrying, makes its load-carrying efficiency low, it is impossible to completes to carry heavier load
Task.
The i.e. existing rotor of consumer level four (more rotors) is carrying the situation of overweight mission payload because of cost and design problem
Lower unmanned plane during flying time and flying radius substantially shorten and it can not carry more than the mission payload of itself thrust.
The ratio between propeller effective power and engine output, are propeller efficiency
In order to solve the problems, such as that unmanned plane flight time and flying distance when carrying heavier load substantially shorten, existing skill
Art scheme has following two：
(1) patent name：One kind is verted double duct unmanned aerial vehicle (application numbers：20160382189.4)
The patent is that one kind is verted double duct unmanned aerial vehicles, and structure includes：Flight control inside central wing and central wing
Equipment, Aerial Electronic Equipment, electrical equipment, duct vert operating mechanism；Aerial Electronic Equipment, electrical equipment, duct vert operating mechanism point
It is not connected with flight control unit.
This duct unmanned aerial vehicle dynamical system overall using duct as unmanned plane, duct control system are put with electric power system
Fly control inside in unmanned plane, and be connected with unmanned, design cost is higher with manufacturing cost, and is not easy to repair and changes.
(2) patent name：A kind of electrodynamic type duct rotor wing unmanned aerial vehicle (application number：201610872892)
The patent is a kind of electrodynamic type duct rotor wing unmanned aerial vehicle, and it is related to a kind of unmanned plane.Multiple first modelings in the patent
Material annulus and multiple second plastic circle rings are coaxially disposed and alternately connection forms duct body, and multiple axially branch are erected at duct sheet
On body, the top of each axial support is connected with upper support frame, and propeller, flow deflector support and steering wheel support are from up to
Under be sleeved on successively on the output shaft of motor, multiple flow deflectors are located on flow deflector support, the both ends of each flow deflector difference
It is detachably connected with flow deflector with the inwall of support and duct body, multiple rudder pieces are located on steering wheel support, each rudder piece
Both ends are detachably connected with steering wheel with the inwall of support and duct body respectively.
Control system and dynamical system are placed in inside duct by the patent, are tied ducted fan as the outside of whole body
Structure, duct is an entirety with unmanned plane, and design difficulty is larger, and technical difficulty is high, and design cost is higher with manufacturing cost, and
It is not easy to repair and change duct.
Above two representativeness prior art shortcoming is：All done on the basis of traditional multi-rotor unmanned aerial vehicle larger
Change, redesign a new culvert type unmanned plane.And to install the duct control system and Aerial Electronic Equipment of complexity additional, make design
Cost is higher with manufacturing cost, and is not easy to repair and changes duct and other corollary equipments.
The technical problems to be solved in the utility model is：Existing culvert type propulsion system is not applied for disappearing in the market
Take level multi-rotor unmanned aerial vehicle.
Utility model content
The utility model installs one additional to improve the delivered payload capability of multi-rotor aerocraft under traditional multi-rotor aerocraft
Independent duct lift module, it can be produced using the isolated propeller of the more same diameter of ducted fan under same power bigger
The characteristics of thrust, by ducted fan and its power supply and control system integration in a duct lift module, as consumer level
The outer attachment of multi-rotor unmanned aerial vehicle, extra lift can be provided, increase flight time and the flying distance of unmanned plane, make existing
Consumer level multi-rotor aerocraft can load heavier mission payload and perform task.
A kind of duct propulsion system based on multi-rotor unmanned aerial vehicle, including multi-rotor unmanned aerial vehicle 10, head interface I 20, culvert
Road lift module 30 and head interface II 40.Duct lift module 30 and multi-rotor unmanned aerial vehicle 10 are separate module.
Multi-rotor unmanned aerial vehicle 10 with head interface I 20 by being rigidly connected, the bottom of head interface I 20 and duct lift mould
Block 30 is by being rigidly connected；The top of head interface II 40 with duct lift module 30 by being rigidly connected, head interface II 40
Bottom be provided with spare interface, spare interface can be connected with the head or other equipment carried.
The duct lift module 30 is by battery 3010, power switch 3020, left ducted fan 3030, right ducted fan
3040th, left electron speed regulator 3050, right electron speed regulator 3060, electricity adjust servomechanism 3070, remote control signal receiver 3080 and mould
Formula controller 3090 forms.
The battery 3010 is left ducted fan 3030, right ducted fan 3040, left electron speed regulator 3050, right electronics tune
Fast device 3060, electricity adjust servomechanism 3070, remote control signal receiver 3080 and mode controller 3090 to provide electric power.
The power switch 3020 is single-pole single-throw switch (SPST), to control cut-offfing for battery 3010.
The left ducted fan 3030 and right ducted fan 3040 are a pair of positive and negative oar ducted fans and are arranged on more rotors
The both sides of unmanned plane 10, left ducted fan 3030 and right ducted fan 3040 are that duct lift module 30 provides thrust.
The left electron speed regulator 3050 is connected with left ducted fan 3030, right electron speed regulator 3060 and right ducted fan
3040 connections, left electron speed regulator 3050 and right electron speed regulator 3060 adjust servomechanism 3070 or remote control signal receiver by electricity
Machine 3080 adjusts the rotating speed of left ducted fan 3030 and right ducted fan 3040, and then adjusts thrust.
The electricity adjusts servomechanism 3070 to have gear regulatory function, and electricity adjusts servomechanism 3070 respectively and electron speed regulator
3050th, right electron speed regulator 3060 connects, and adjusts servomechanism 3070 to control left electron speed regulator 3050 and right electronic speed regulation by electricity
Device 3060, and then control the rotating speed of left ducted fan 3030 and right ducted fan 3040.
Remote control signal receiver 3080 is connected with left electron speed regulator 3050 and right electron speed regulator 3060, remote signal
Receiver 3080 receives the radio signal that the outside duct remote control of multi-rotor unmanned aerial vehicle 10 is sent, and radio signal is sent out
Left electron speed regulator 3050 and right electron speed regulator 3060 are delivered to, and then controls left ducted fan 3030 and right ducted fan 3040
Rotating speed.
The mode controller 3090 is single-pole double-throw switch (SPDT), to control electricity to adjust servomechanism 3070 and the remote signal
The opening and closing of receiver 3080.
It is rigidly connected and is connected for screw connection, mortise-tenon joint or slide rail.
The control of multi-rotor unmanned aerial vehicle 10 flow of taking off is as follows：
When multi-rotor unmanned aerial vehicle 10 does not install duct lift module 30 additional, the flow of taking off of multi-rotor unmanned aerial vehicle 10 is as follows：It is first
After first connecting the power supply of multi-rotor unmanned aerial vehicle 10, multi-rotor unmanned aerial vehicle 10 is unlocked by unmanned controller, passes through no-manned machine distant control
Device sends to multi-rotor unmanned aerial vehicle 10 and taken off instruction, the quickening of the revolution speed of propeller of multi-rotor unmanned aerial vehicle 10, there is provided lift, more rotors without
Man-machine 10 take off.
When needing to increase load-carrying, duct lift module 30 is installed additional to multi-rotor unmanned aerial vehicle 10, duct lift module 30
Specification changes according to different load-carryings.Flow of now taking off is as follows：
Step 1：Unmanned plane flies hand and connects the power supply of multi-rotor unmanned aerial vehicle 10.
Step 2：Unmanned plane flies the power switch 3020 that hand opens connection duct lift module 30, makes duct lift module 30
In opening.
Step 3：Unmanned plane flies the associative mode that hand Land use models selector 3090 selects duct lift module 30, such as switchs
It is upwards manual mode, switch is downwards remote control mode.
Step 4A-1：If in the case of selecting manual mode, unmanned plane flies hand and adjusted manually on electricity tune servomechanism 3070
Gear, make duct lift module 30 according to selected gear produce lift.
Step 4A-2：Unmanned plane flies hand and unlocks multi-rotor unmanned aerial vehicle 10 by unmanned controller, and unmanned plane flies hand control
Unmanned controller sends instruction of taking off to multi-rotor unmanned aerial vehicle 10, and multi-rotor unmanned aerial vehicle 10 receives instruction of taking off and starts spiral
Oar, now multi-rotor unmanned aerial vehicle 10 risen under the collective effect for the lift that the duct lift module 30 and itself propeller provide
Fly.
Step 4B-1：If in the case of selecting remote control mode, unmanned plane flies hand and opens outside duct remote control to described
Duct lift module 30 sends instruction, and the instruction that duct lift module 30 receives outside duct remote control produces lift.
Step 4B-2：Unmanned plane flies hand and unlocks multi-rotor unmanned aerial vehicle 10 by unmanned controller, to control unmanned plane distant
Control device sends instruction of taking off to multi-rotor unmanned aerial vehicle 10, and multi-rotor unmanned aerial vehicle 10 starts propeller, now multi-rotor unmanned aerial vehicle 10
Unmanned plane takes off under the collective effect for the lift that the duct lift module 30 and itself propeller provide.
The utility model has used general head interface, can be revolved with the consumer level of Multiple Type on sale on the market more
Wing unmanned plane carries out rigid mechanical combination, and different ducts or battery can be carried according to different load-carrying demands to improve maximum
Lift, it is not necessary to install the duct control system of complexity additional, there is very big potential modification and design margin, than redesigning a culvert
Road unmanned plane saves very big cost.
Brief description of the drawings
A kind of unmanned plane structure charts based on duct propulsion die of Fig. 1.
The structural representation of Fig. 2 duct lift modules.
A kind of unmanned plane top views based on duct propulsion die of Fig. 3.
When Fig. 4 does not install duct lift module additional, unmanned plane takeoff operational schematic flow sheet.
When Fig. 5 installs duct lift module additional, unmanned plane takeoff operational schematic flow sheet.
Embodiment
As Figure 1-5, a kind of duct propulsion system based on multi-rotor unmanned aerial vehicle, including multi-rotor unmanned aerial vehicle 10, cloud
Platform interface I 20, duct lift module 30 and head interface II 40.
Multi-rotor unmanned aerial vehicle 10 with head interface I 20 by being rigidly connected, the bottom of head interface I 20 and duct lift mould
Block 30 is by being rigidly connected；The top of head interface II 40 with duct lift module 30 by being rigidly connected, head interface II 40
Bottom be provided with spare interface, spare interface can be connected with the head or other equipment carried.
The duct lift module 30 is by battery 3010, power switch 3020, left ducted fan 3030, right ducted fan
3040th, left electron speed regulator 3050, right electron speed regulator 3060, electricity adjust servomechanism 3070, remote control signal receiver 3080 and mould
Formula controller 3090 forms.
The battery 3010 is left ducted fan 3030, right ducted fan 3040, left electron speed regulator 3050, right electronics tune
Fast device 3060, electricity adjust servomechanism 3070, remote control signal receiver 3080 and mode controller 3090 to provide electric power.
The power switch 3020 is single-pole single-throw switch (SPST), to control cut-offfing for battery 3010.
The left ducted fan 3030 and right ducted fan 3040 are a pair of positive and negative oar ducted fans and are arranged on more rotors
The both sides of unmanned plane 10, left ducted fan 3030 and right ducted fan 3040 are that duct lift module 30 provides thrust.
The left electron speed regulator 3050 is connected with left ducted fan 3030, right electron speed regulator 3060 and right ducted fan
3040 connections, left electron speed regulator 3050 and right electron speed regulator 3060 adjust servomechanism 3070 or remote control signal receiver by electricity
Machine 3080 adjusts the rotating speed of left ducted fan 3030 and right ducted fan 3040, and then adjusts thrust.
The electricity adjusts servomechanism 3070 to have gear regulatory function, and electricity adjusts servomechanism 3070 respectively and electron speed regulator
3050th, right electron speed regulator 3060 connects, and adjusts servomechanism 3070 to control left electron speed regulator 3050 and right electronic speed regulation by electricity
Device 3060, and then control the rotating speed of left ducted fan 3030 and right ducted fan 3040.
Remote control signal receiver 3080 is connected with left electron speed regulator 3050 and right electron speed regulator 3060, remote signal
Receiver 3080 receives the radio signal that the outside duct remote control of multi-rotor unmanned aerial vehicle 10 is sent, and radio signal is sent out
Left electron speed regulator 3050 and right electron speed regulator 3060 are delivered to, and then controls left ducted fan 3030 and right ducted fan 3040
Rotating speed.
The mode controller 3090 is single-pole double-throw switch (SPDT), to control electricity to adjust servomechanism 3070 and the remote signal
The opening and closing of receiver 3080.
It is rigidly connected and is connected for screw connection, mortise-tenon joint or slide rail.
The control of embodiment is described as follows：
When multi-rotor unmanned aerial vehicle 10 does not install duct lift module 30 additional, the flow of taking off of multi-rotor unmanned aerial vehicle 10 is as follows：It is first
After first connecting the power supply of multi-rotor unmanned aerial vehicle 10, multi-rotor unmanned aerial vehicle 10 is unlocked by unmanned controller, passes through no-manned machine distant control
Device sends to multi-rotor unmanned aerial vehicle 10 and taken off instruction, the quickening of the revolution speed of propeller of multi-rotor unmanned aerial vehicle 10, there is provided lift, more rotors without
Man-machine 10 take off.
When needing to increase load-carrying, duct lift module 30 is installed additional to multi-rotor unmanned aerial vehicle 10, duct lift module 30
Specification changes according to different load-carryings.Flow of now taking off is as follows：
Step 1：Unmanned plane flies hand and connects the power supply of multi-rotor unmanned aerial vehicle 10.
Step 2：Unmanned plane flies the power switch 3020 that hand opens connection duct lift module 30, makes duct lift module 30
In opening.
Step 3：Unmanned plane flies the associative mode that hand Land use models selector 3090 selects duct lift module 30, such as switchs
It is upwards manual mode, switch is downwards remote control mode.
Step 4A-1：If in the case of selecting manual mode, unmanned plane flies hand and adjusted manually on electricity tune servomechanism 3070
Gear, make duct lift module 30 according to selected gear produce lift.
Step 4A-2：Unmanned plane flies hand and unlocks multi-rotor unmanned aerial vehicle 10 by unmanned controller, and unmanned plane flies hand control
Unmanned controller sends instruction of taking off to multi-rotor unmanned aerial vehicle 10, and multi-rotor unmanned aerial vehicle 10 receives instruction of taking off and starts spiral
Oar, now multi-rotor unmanned aerial vehicle 10 risen under the collective effect for the lift that the duct lift module 30 and itself propeller provide
Fly.
Step 4B-1：If in the case of selecting remote control mode, unmanned plane flies hand and opens outside duct remote control to described
Duct lift module 30 sends instruction, and the instruction that duct lift module 30 receives outside duct remote control produces lift.
Step 4B-2：Unmanned plane flies hand and unlocks multi-rotor unmanned aerial vehicle 10 by unmanned controller, to control unmanned plane distant
Control device sends instruction of taking off to multi-rotor unmanned aerial vehicle 10, and multi-rotor unmanned aerial vehicle 10 starts propeller, now multi-rotor unmanned aerial vehicle 10
Unmanned plane takes off under the collective effect for the lift that the duct lift module 30 and itself propeller provide.
Multi-rotor unmanned aerial vehicle 10 is made up of dynamical system, avionics control system, head interface and unmanned controller.
The species and specification of duct lift module 30 such as can carry 1 kilogram of rank according to different load-carrying changes in demand
During load-carrying, a pair of single thrusts can be selected as power resources of the 900g 50 millimeters of ducts as duct lift module 30.Such as
When carrying 5 kilograms of rank load-carryings, it is 3.5 kilograms of 90 millimeters of ducts as duct lift mould that can select a pair of single thrusts
The power resources of block 30.And same duct lift module can provide different size of thrust.
Claims (2)
- A kind of 1. duct propulsion system based on multi-rotor unmanned aerial vehicle, it is characterised in that：The system includes multi-rotor unmanned aerial vehicle (10), head interface I (20), duct lift module (30) and head interface II (40)；Duct lift module (30) and more rotors Unmanned plane (10) is separate module；Multi-rotor unmanned aerial vehicle (10) with head interface I (20) by being rigidly connected, the bottom of head interface I (20) and duct lift Module (30) is by being rigidly connected；The top of head interface II (40) with duct lift module (30) by being rigidly connected, head The bottom of interface II (40) is provided with spare interface, and spare interface can be connected with the head carried；The duct lift module (30) is by battery (3010), power switch (3020), left ducted fan (3030), right duct wind Fan (3040), left electron speed regulator (3050), right electron speed regulator (3060), electricity tune servomechanism (3070), remote control signal receiver Machine (3080) and mode controller (3090) composition；The battery (3010) is left ducted fan (3030), right ducted fan (3040), left electron speed regulator (3050), right electricity Sub- speed regulator (3060), electricity adjust servomechanism (3070), remote control signal receiver (3080) and mode controller (3090) to provide electricity Power；The power switch (3020) is single-pole single-throw switch (SPST), to control cut-offfing for battery (3010)；The left ducted fan (3030) and right ducted fan (3040) are a pair of positive and negative oar ducted fans and are arranged on more rotors The both sides of unmanned plane (10), left ducted fan (3030) and right ducted fan (3040) are that duct lift module (30) offer pushes away Power；The left electron speed regulator (3050) is connected with left ducted fan (3030), right electron speed regulator (3060) and right duct wind Fan (3040) connection, left electron speed regulator (3050) and right electron speed regulator (3060) and servomechanism (3070) or remote control are adjusted by electricity Signal receiver (3080) adjusts left ducted fan (3030) and the rotating speed of right ducted fan (3040), and then adjusts thrust；The electricity adjusts servomechanism (3070) to have gear regulatory function, and electricity adjusts servomechanism (3070) respectively and electron speed regulator 3050th, right electron speed regulator (3060) connection, adjusts servomechanism (3070) to control left electron speed regulator (3050) and right electricity by electricity Sub- speed regulator (3060), and then control the rotating speed of left ducted fan (3030) and right ducted fan (3040)；Remote control signal receiver (3080) is connected with left electron speed regulator (3050) and right electron speed regulator (3060), remote control letter Number receiver (3080) receives the radio signal of the outside duct remote control transmission of multi-rotor unmanned aerial vehicle (10), and by radio Signal is sent to left electron speed regulator (3050) and right electron speed regulator (3060), and then controls left ducted fan (3030) and the right side The rotating speed of ducted fan (3040)；The mode controller (3090) is single-pole double-throw switch (SPDT), to control electricity to adjust servomechanism (3070) and the remote signal The opening and closing of receiver (3080).
- A kind of 2. duct propulsion system based on multi-rotor unmanned aerial vehicle according to claim 1, it is characterised in that：Rigidity connects It is connected in screw connection, mortise-tenon joint or slide rail connection.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721129963.7U CN207157519U (en) | 2017-09-05 | 2017-09-05 | A kind of duct propulsion system based on multi-rotor unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201721129963.7U CN207157519U (en) | 2017-09-05 | 2017-09-05 | A kind of duct propulsion system based on multi-rotor unmanned aerial vehicle |
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| CN207157519U true CN207157519U (en) | 2018-03-30 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107458593A (en) * | 2017-09-05 | 2017-12-12 | 北京工业大学 | A kind of duct propulsion system based on multi-rotor unmanned aerial vehicle |
-
2017
- 2017-09-05 CN CN201721129963.7U patent/CN207157519U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107458593A (en) * | 2017-09-05 | 2017-12-12 | 北京工业大学 | A kind of duct propulsion system based on multi-rotor unmanned aerial vehicle |
| WO2019047429A1 (en) * | 2017-09-05 | 2019-03-14 | 北京工业大学 | Multi-rotor unmanned aerial vehicle-based duct propulsion system |
| CN107458593B (en) * | 2017-09-05 | 2023-09-12 | 北京工业大学 | Duct propulsion system based on multi-rotor unmanned aerial vehicle |
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Granted publication date: 20180330 |