CN107364572A - Fixed-wing vector unmanned plane - Google Patents
Fixed-wing vector unmanned plane Download PDFInfo
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- CN107364572A CN107364572A CN201710684839.5A CN201710684839A CN107364572A CN 107364572 A CN107364572 A CN 107364572A CN 201710684839 A CN201710684839 A CN 201710684839A CN 107364572 A CN107364572 A CN 107364572A
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- fuselage
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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 claims abstract description 14
- 238000009434 installation Methods 0.000 claims abstract description 5
- 230000003014 reinforcing effect Effects 0.000 claims description 8
- 230000003044 adaptive effect Effects 0.000 abstract description 3
- 238000013461 design Methods 0.000 description 5
- 238000011161 development Methods 0.000 description 5
- 238000011160 research Methods 0.000 description 3
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 2
- 229910052744 lithium Inorganic materials 0.000 description 2
- 230000036544 posture Effects 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 230000033228 biological regulation Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000009172 bursting Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000009432 framing Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/32—Wings specially adapted for mounting power plant
-
- 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
- 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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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
This fixed-wing vector unmanned plane proposed by the present invention,It has fuselage,Steering wheel,Flight control system,Propeller and brushless electric machine,Fuselage is made up of wing plate and upper and lower fuselage side plate,Front fuselage is fixed with motor fixing seat,Rotation bracing ring is installed by runing rest in motor fixing seat,Bracing ring is rotated to rotate around its longitudinal axis,Bracing ring is rotated built with cross runing rest,Brushless electric machine is installed in cross rotation,Propeller is installed on brushless electric machine axle,Installation deflection steering wheel and upper and lower deflection steering wheel in fuselage,Each steering wheel is connected with rotation bracing ring and cross runing rest respectively by ball-head tension rod,Control the deflection of propeller and brushless electric machine axial line,Flight control system includes remote controlled floor remote control,Remote-control receiver and APM on fuselage fly control device,With deflection steering wheel and up and down, deflection tiller room electrically connects flight control system.The vector of the present invention adaptive can rotate, and provide timely pulling force for different actions, reduction aircraft is liftoff and touchdown speed, shortens aircraft ground run distance, saves power consumption.
Description
Technical field
The invention belongs to a kind of unmanned aerial vehicle technology, specifically a kind of fixed-wing vector unmanned plane.
Background technology
1903, U.S. Lai Te brother successfully developed the first manned vehicle in human history.The spy of aircraft
Rope is also from that point on.Afterwards due to the restriction of scientific and technical backwardness and knowwhy, the research of vector power aerial vehicle is not
Good development can be obtained.In recent years, as scientific and technological theoretical progress, the U.S. obtain great prominent in vectored thrust technical elements
It is broken, countries in the world are held a safe lead already, turn into the country for successfully developing vector power aerial vehicle in the world.The vector of famous American
Power aerial vehicle masterpiece has F-35B.
External vector power aerial vehicle is the model version of U.S. Military Aircraft " F-35B ", but aircraft version F35-B only has
Standby stronger sight, mobility and stability are poor, and practicality is relatively low, and airframe structure uses super light material completely, into
This is higher.
" X-Hound " and a vector unmanned plane that the unmanned plane enterprise " proud gesture science and technology " in China develops at present, by four
Individual rotor composition.
China's current also primary stage of place to develop in terms of vector power technology.Due to starting late, core technology
Do not grasp also, also need to continue to grope and study for reference.This problem is broken through in face of core technology, we not only need inversely to grind
Hair, with greater need for bursting forth for initiative spirit.
With aviation development, science and technology, the breakthrough of aviation knowledge, various innovation model plane are such as emerged rapidly in large numbersBamboo shoots after a spring rain, species
It is various.The now either domestic at present or external research for aircraft mainly in terms of conventional fixed-wing and multiaxis, than
Such as：The aircraft such as four axles, six axles, eight axles, all the marketization and commercialization, fixed-wing model plane come relative to multiaxis model plane for these
Say there is the advantages of voyage is remote, and posture is easily stable, and energy efficiency is high.Fixed-wing model plane turn into a kind of novel, winged gradually in development
Row is stable, the emerging product of various superior performances, the development of model plane is strided forward new research field.
But due to the upper obstruction in design and manufacture, do not occur vector unmanned plane also in model airplane machine at present, spy
It is not that vector can need the fixed-wing unmanned plane that change with flight, governs the lifting of model airplane machine performance in this respect.
The content of the invention
Therefore, the present invention proposes a kind of fixed-wing vector unmanned plane, it is allowed to change traditional fixed-wing unmanned plane power motor
Only fixed-direction pulling force the drawbacks of, vector mechanism can adaptive rotary power motor, for aircraft complete different actions provide it is timely
Different directions accurate pulling force, reduce that aircraft is liftoff and touchdown speed, shorten aircraft ground run distance, save power consumption.
This fixed-wing vector unmanned plane proposed by the present invention, it has fuselage, steering wheel, flight control system, propeller and brushless
Motor, it is characterised in that fuselage is made up of wing plate and upper and lower fuselage side plate, and front fuselage is fixed with motor fixing seat, and motor is fixed
Rotation bracing ring is installed by runing rest on seat, rotation bracing ring rotates around its longitudinal axis, and rotation bracing ring is built with ten
Word runing rest, cross, which rotates, installs brushless electric machine, and propeller is installed on brushless electric machine axle, deflection rudder is installed in fuselage
Machine and deflection steering wheel up and down, deflection steering wheel and up and down deflection steering wheel are by ball-head tension rod respectively with rotating bracing ring and cross
Runing rest connects, and controls the deflection of propeller and brushless electric machine axial line, and flight control system includes remote controlled floor remote control, fuselage
On remote-control receiver and APM fly control device, flight control system and deflection steering wheel and the upper and lower tiller room that deflects electrically connect.
There is middle reinforcing plate on the fuselage, to reinforce the bonding strength of wing plate and upper and lower fuselage side sheet room.
The motor fixing seat is that a cross fork inserts sleeve in middle reinforcing plate and upper and lower fuselage side plate.
There is a connection cross to strengthen fixing between motor fixing seat and runing rest.
Runing rest is a pair of bracket of right angle type, and the connection between bracket of right angle type and rotation bracing ring connects for bearing pin.
Rotate and also connected between bracing ring and cross runing rest for bearing pin.
The ball-head tension rod of deflection steering wheel is arranged on the left and right sides of fuselage epipleural, and the bulb for deflecting steering wheel up and down is drawn
Bar is arranged on the both sides up and down of wing plate.
Rudder plate on wing plate has corresponding steering wheel to connect.
Underbelly is equipped with sliding wheel.
The operation principle of the present invention is as follows：
After propeller starts, the elevation angle of flight control system adjust automatically propeller, provide a vector forward and up for fuselage and draw
Power, the air-flow difference of the upper and lower both sides of wing plate then produce the liter lifting force to fuselage, and aircraft just flies to sky.When needing to turn to, left and right is inclined
Machine of coming about pulls rotation bracing ring to be rotated around its longitudinal axis by ball-head tension rod, the vector on the axial line of motor and propeller
Just turn left or turn right, it is necessary to when rising or falling, deflect steering wheel up and down and cross runing rest is pulled around its axle by ball-head tension rod
Heart line is rotated, and the vector on the axial line of motor and propeller is just faced upward or had a down dip.Deflection steering wheel and up and down deflection steering wheel
When acting simultaneously, the vector on the axial line of motor and propeller is just as needed in the deflection taper angular region that front allows
Rotate, realize different postures and different actions.
The new product that this fixed-wing vector unmanned plane of the present invention develops as fixed-wing, break fixed-wing power motor only
Possesses the characteristic of fixed direction of pull.The unique design of Vector Rotation mechanism, Vector Rotation system is set to complete phase for aircraft
The action answered and realize synchronization, provide the accurate pulling force of different directions for the flight of unmanned plane.Use flying for vector power technology
The circulation lift of machine is advantageous to reduce the liftoff and touchdown speed of aircraft in lift direction, shortens the ground run distance of aircraft.For
Air is than leaner place（Such as Tibet Plateau）, common aircraft needs very big speed doing each serial flare maneuver
Degree and power, compare the waste energy, and the direction of pull that the aircraft of newly-increased Vector Rotation mechanism can directly change motor is made relatively
The action answered.Vector Rotation system is combined with new fuselage carries out innovative design, unmanned plane is possessed double mode flight function, i.e.,
The aerobatics of four ailerons, the high-speed flight of dalta wing, Vector Rotation mechanism controls power motor is front and rear under four aileron patterns
Left rotation and right rotation instead of the tailplane and vertical tail of aircraft respectively, can make a series of actions of fixed-wing, realize nothing
Two kinds of man-machine offline mode.
In a word, the present invention changes traditional fixed-wing unmanned plane power motor and only has the drawbacks of fixed-direction pulling force, vector machine
The adaptive rotary power motor of structure energy, the accurate pulling force of timely different directions is provided for the different actions of aircraft completion, reduces aircraft
Liftoff and touchdown speed, shorten aircraft ground run distance, save power consumption.
Brief description of the drawings
Fig. 1 is the schematic perspective view of the present invention.
Fig. 2 is brushless electric machine, deflection steering wheel, deflects steering wheel up and down, rotation bracing ring, the integrated solid of motor fixing seat
Figure.
Fig. 3 is the integrated solid of brushless electric machine, cross runing rest, rotation bracing ring, rotary support and motor fixing seat
Figure.
Fig. 4 is cross runing rest front view.
Fig. 5 is cross runing rest left view.
Fig. 6 is cross runing rest top view.
Fig. 7 is rotation bracing ring front view（Broken section）.
Fig. 8 is rotation bracing ring left view（Broken section）.
Fig. 9 is each part annexation figure of the present invention.
Deflection vector steering wheel 1 and deflection vector steering wheel 2 in Fig. 9 represent deflection steering wheel and up and down deflection rudder respectively
Machine.
The parts label of each several part is as follows in Fig. 1-8：
1- propellers；2- brushless electric machines；3- rotates bracing ring；4- rotary supports；5- connection crosses；6- fuselage epipleurals；7-
Wing plate；8- fuselage lower side panels；9- wing rudder plates；10- deflection steering wheels；11- steering wheel rocking arms；12- ball-head tension rods；13- motors
Fixed seat；Reinforcing plate among 14-；15- universal ball ends；16- cross runing rests；17- deflects steering wheel up and down.
In Fig. 1-3, marked as the ball-head tension rod that ball-head tension rod represents whole steering wheels；Rotary support marked as 4 represents
Lower two rotary supports；Steering wheel rocking arm marked as 11 represents whole steering wheel rocking arms.
Embodiment
Below in conjunction with the accompanying drawings the present invention is further illustrated with example.
Form fuselage wing plate 7, fuselage epipleural 6, fuselage lower side panel 8, and the grade part of middle reinforcing plate 14 with it is existing
As mould machine it is roughly the same, the rudder plate 9 on wing plate is also such.The place of change is mainly that deflection steering wheel is left on fuselage
10 and up and down deflection steering wheel 17 installation site.Specifically, deflection steering wheel is arranged on the middle part of fuselage, deflects steering wheel up and down
Installed in fuselage middle front part.Certainly, the steering wheel of rudder plate is driven, and flight control system not marked etc. is arranged on machine and common boat
The situation of mould is similar.Thinless table herein.
Because side plate above and below fuselage and middle reinforcing plate form a cross, motor fixing seat 13 makes one accordingly
Cross nested structure, with can by motor fixing seat firmly sleeve on side plate above and below middle reinforcing plate and fuselage and with screw etc.
It is connected.
There is a connection cross 5 fixed thereto being integrated in the front end of motor fixing seat, the connection cross frame
Upper and lower two lattice framing is longer, to facilitate installation rotary support 4.
As described above, rotary support is the part of two structure of right angle tyoe, one side of part is fixed on connection cross, another
Perforate on side, rotation bracing ring 3 is installed by bearing pin.It is an annulus to rotate bracing ring, and upper and lower and two pairs of left and right is provided with ring
Mounting hole.Upper and lower a pair of mounting holes corresponding rotation bearing, pair of right and left mounting hole correspond to cross runing rest 16, cross rotation branch
The mounting means of frame and rotation bracing ring is also bearing pin.Brushless electric machine 2 is arranged on cross runing rest.Brushless electric machine installs
Propeller 1 is installed on brushless electric machine axle again afterwards.So the axial line of brushless electric machine and propeller can be in rotation bracing ring
Direction vector change that is upper to deflect, being formed at unmanned plane head.
Between deflection steering wheel and rotation bracing ring, and connecting through between deflection steering wheel and runing rest up and down
Respective steering wheel rocking arm 11 and ball head connecting rod 12 are realized.Certainly, also respectively there is a universal ball end 15 at ball head connecting rod both ends.
The electricity consumption of brushless electric machine, each steering wheel, flight control system etc. is unified to be provided by lithium battery, lithium battery and respective accessory,
And remote-control receiver in flight control system and APM fly control device and are also mounted on fuselage, flight control system and deflection steering wheel and
Up and down deflection tiller room have sliding wheel under electrical connection, including fuselage etc. remaining compared with fixed-wing model airplane machine.
It is existing model plane controller that APM, which flies control device, and it is equipped with fixed-wing program, it is possible to achieve aircraft is controlled from steady
System, the accident rate of flight is reduced, manual control can also be carried out to each steering wheel by the remote control on ground and transfer motor vector
Rotation, the pulling force of each action different directions is quickly and accurately done for aircraft.Pass through two sections of switch controls of ground remote control device
Conversion between dalta wing pattern and four aileron patterns.The major function of earth station is to be realized by digital transmission module to fixed-wing vector
The overall flight condition of unmanned plane carries out monitoring and parameter regulation in real time.
APM fly program on control device can according to specific needs, by user oneself or commission related development business design or
Person adjusts.
Fuselage, the brushless electric machine of the present invention, and the parameter such as power requirements size of propeller is according to existing airplane design
Textbook determine.The brushless electric machine of this example is bright space 2814/1450Kv motors, and propeller is from 9 inches of diameter, the English of pitch 6
Very little, speed reducing ratio is 0.6 9060 oars.The shape and size of corresponding cross runing rest and rotation bracing ring are as Figure 4-8.
Make prototype test in kind by the system of unit to determine, this fixed-wing vector unmanned plane during flying attitude stabilization of the present invention,
Flying speed is fast, and vector is adjusted promptly and accurately, and radius of turn is small, and take-off distance is short, obtains the favorable comment of shutting mechanism.
Claims (9)
1. a kind of fixed-wing vector unmanned plane, it has fuselage, steering wheel, flight control system, propeller and brushless electric machine, it is characterised in that
Fuselage is made up of wing plate and upper and lower fuselage side plate, and front fuselage is fixed with motor fixing seat, passes through rotation branch in motor fixing seat
Frame installation rotation bracing ring, rotation bracing ring rotate around its longitudinal axis, and rotation bracing ring is built with cross runing rest, cross
Brushless electric machine is installed in rotation, propeller is installed on brushless electric machine axle, installation deflection steering wheel deflects rudder with upper and lower in fuselage
Machine, up and down deflection steering wheel and deflection steering wheel are connected with rotation bracing ring and cross runing rest respectively by ball-head tension rod,
The deflection of propeller and brushless electric machine axial line is controlled, flight control system includes the remote control reception on remote controlled floor remote control, fuselage
Machine and APM fly control device, and with deflection steering wheel and up and down, deflection tiller room electrically connects flight control system.
2. fixed-wing vector unmanned plane according to claim 1, it is characterised in that have middle reinforcing plate on fuselage.
3. fixed-wing vector unmanned plane according to claim 1, it is characterised in that motor fixing seat is that a cross fork is inserted,
Sleeve is in middle reinforcing plate and upper and lower fuselage side plate.
4. fixed-wing vector unmanned plane according to claim 1, it is characterised in that have one between motor fixing seat and runing rest
Individual connection cross.
5. fixed-wing vector unmanned plane according to claim 1, it is characterised in that runing rest is a pair of bracket of right angle type, directly
Connection between angular support frame and rotation bracing ring connects for bearing pin.
6. fixed-wing vector unmanned plane according to claim 1, it is characterised in that between rotation bracing ring and cross runing rest
Connected for bearing pin.
7. fixed-wing vector unmanned plane according to claim 1, it is characterised in that the ball-head tension rod of deflection steering wheel is set
In the left and right sides of fuselage epipleural, the ball-head tension rod for deflecting steering wheel up and down is arranged on the both sides up and down of wing plate.
8. fixed-wing vector unmanned plane according to claim 1, it is characterised in that the rudder plate on wing plate has corresponding steering wheel to connect
Connect.
9. according to one of the claim 1-8 fixed-wing vector unmanned planes, it is characterised in that underbelly is equipped with sliding wheel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710684839.5A CN107364572B (en) | 2017-08-11 | 2017-08-11 | Fixed wing vector unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710684839.5A CN107364572B (en) | 2017-08-11 | 2017-08-11 | Fixed wing vector unmanned plane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107364572A true CN107364572A (en) | 2017-11-21 |
| CN107364572B CN107364572B (en) | 2024-01-30 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108298071A (en) * | 2018-03-14 | 2018-07-20 | 长沙市云智航科技有限公司 | A kind of more rotor flying vehicles of manned duct |
| CN108298074A (en) * | 2018-03-14 | 2018-07-20 | 长沙市云智航科技有限公司 | The component that verts for the more rotor flying vehicles of manned duct |
| CN108639331A (en) * | 2018-06-29 | 2018-10-12 | 长沙市云智航科技有限公司 | One kind is verted double-rotor aerobat |
| CN109263868A (en) * | 2018-09-28 | 2019-01-25 | 上海歌尔泰克机器人有限公司 | A kind of unmanned plane rotor structure and unmanned plane during flying device |
| CN109606680A (en) * | 2018-12-26 | 2019-04-12 | 李昊泽 | The multi-modal aircraft of a kind of pair of hair full vector and flight system |
| JP2023076742A (en) * | 2020-01-27 | 2023-06-01 | 株式会社エアロネクスト | Flying body |
Citations (24)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6719244B1 (en) * | 2003-02-03 | 2004-04-13 | Gary Robert Gress | VTOL aircraft control using opposed tilting of its dual propellers or fans |
| DE212007000095U1 (en) * | 2007-04-17 | 2009-12-10 | Tian, Yu | control servo |
| US20110089287A1 (en) * | 2009-10-21 | 2011-04-21 | Deale Valentine | Power assisted toy flying device |
| US20110177748A1 (en) * | 2010-01-21 | 2011-07-21 | Zhihong Luo | Vtol model aircraft |
| JP2012083318A (en) * | 2010-10-14 | 2012-04-26 | Institute Of National Colleges Of Technology Japan | Weather observation device |
| CN203235257U (en) * | 2013-04-26 | 2013-10-16 | 深圳市沈氏彤创航天模型有限公司 | Propeller vector control structure of remote-control model plane |
| CN203916079U (en) * | 2014-05-20 | 2014-11-05 | 汕头市博迪科技有限公司 | Have the fixed wing aircraft toy of helicopter function concurrently |
| CN204223181U (en) * | 2014-10-31 | 2015-03-25 | 吴建伟 | A kind of combined type vertically taking off and landing flyer |
| CN204489181U (en) * | 2015-03-10 | 2015-07-22 | 广州天翔航空科技有限公司 | Variable motor angle four axle vertical takeoff and landing fixed-wing compound unmanned plane |
| CN204527614U (en) * | 2015-01-21 | 2015-08-05 | 西北农林科技大学 | A kind of steering unit of small capacity double rotor wing unmanned aerial vehicle |
| CN204979219U (en) * | 2015-08-10 | 2016-01-20 | 红河学院 | Four screws gyroplane that verts |
| CN105346719A (en) * | 2015-11-18 | 2016-02-24 | 何春旺 | Perpendicular take-off and landing aircraft |
| CN205060014U (en) * | 2015-08-21 | 2016-03-02 | 符星 | Novel multiaxis unmanned aerial vehicle |
| CN205216194U (en) * | 2015-06-05 | 2016-05-11 | 成都航空职业技术学院 | But fixed -wing aircraft of VTOL |
| CN105857605A (en) * | 2016-04-11 | 2016-08-17 | 河北科技大学 | Single sitting type fixed-wing unmanned aerial vehicle taking off and landing vertically |
| US20170152014A1 (en) * | 2015-10-07 | 2017-06-01 | Carbon Flyer LLC | Aircraft body and method of making the same |
| CN106823403A (en) * | 2017-03-07 | 2017-06-13 | 王长民 | Many oar telecontrolled aircrafts |
| CN106828916A (en) * | 2016-10-19 | 2017-06-13 | 吴瑞霞 | Unmanned vehicle |
| CN106882391A (en) * | 2017-03-17 | 2017-06-23 | 四川建筑职业技术学院 | A kind of spherical three axles joint control vector motor cabinet of unmanned plane |
| CN206278270U (en) * | 2016-12-09 | 2017-06-27 | 河北工业大学 | A kind of VUAV vector puller system |
| CN106915457A (en) * | 2017-02-22 | 2017-07-04 | 北京航空航天大学 | A kind of variable co-axial helicopter steerable system of upper and lower rotor inclinator depth of parallelism |
| CN106927039A (en) * | 2016-12-09 | 2017-07-07 | 河北工业大学 | Vector puller system and VUAV vector tensile strength control method |
| CN206381622U (en) * | 2017-01-10 | 2017-08-08 | 田巍巍 | A kind of aircraft model plane |
| CN207045728U (en) * | 2017-08-11 | 2018-02-27 | 红河学院 | Fixed-wing vector unmanned plane |
-
2017
- 2017-08-11 CN CN201710684839.5A patent/CN107364572B/en active Active
Patent Citations (24)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6719244B1 (en) * | 2003-02-03 | 2004-04-13 | Gary Robert Gress | VTOL aircraft control using opposed tilting of its dual propellers or fans |
| DE212007000095U1 (en) * | 2007-04-17 | 2009-12-10 | Tian, Yu | control servo |
| US20110089287A1 (en) * | 2009-10-21 | 2011-04-21 | Deale Valentine | Power assisted toy flying device |
| US20110177748A1 (en) * | 2010-01-21 | 2011-07-21 | Zhihong Luo | Vtol model aircraft |
| JP2012083318A (en) * | 2010-10-14 | 2012-04-26 | Institute Of National Colleges Of Technology Japan | Weather observation device |
| CN203235257U (en) * | 2013-04-26 | 2013-10-16 | 深圳市沈氏彤创航天模型有限公司 | Propeller vector control structure of remote-control model plane |
| CN203916079U (en) * | 2014-05-20 | 2014-11-05 | 汕头市博迪科技有限公司 | Have the fixed wing aircraft toy of helicopter function concurrently |
| CN204223181U (en) * | 2014-10-31 | 2015-03-25 | 吴建伟 | A kind of combined type vertically taking off and landing flyer |
| CN204527614U (en) * | 2015-01-21 | 2015-08-05 | 西北农林科技大学 | A kind of steering unit of small capacity double rotor wing unmanned aerial vehicle |
| CN204489181U (en) * | 2015-03-10 | 2015-07-22 | 广州天翔航空科技有限公司 | Variable motor angle four axle vertical takeoff and landing fixed-wing compound unmanned plane |
| CN205216194U (en) * | 2015-06-05 | 2016-05-11 | 成都航空职业技术学院 | But fixed -wing aircraft of VTOL |
| CN204979219U (en) * | 2015-08-10 | 2016-01-20 | 红河学院 | Four screws gyroplane that verts |
| CN205060014U (en) * | 2015-08-21 | 2016-03-02 | 符星 | Novel multiaxis unmanned aerial vehicle |
| US20170152014A1 (en) * | 2015-10-07 | 2017-06-01 | Carbon Flyer LLC | Aircraft body and method of making the same |
| CN105346719A (en) * | 2015-11-18 | 2016-02-24 | 何春旺 | Perpendicular take-off and landing aircraft |
| CN105857605A (en) * | 2016-04-11 | 2016-08-17 | 河北科技大学 | Single sitting type fixed-wing unmanned aerial vehicle taking off and landing vertically |
| CN106828916A (en) * | 2016-10-19 | 2017-06-13 | 吴瑞霞 | Unmanned vehicle |
| CN206278270U (en) * | 2016-12-09 | 2017-06-27 | 河北工业大学 | A kind of VUAV vector puller system |
| CN106927039A (en) * | 2016-12-09 | 2017-07-07 | 河北工业大学 | Vector puller system and VUAV vector tensile strength control method |
| CN206381622U (en) * | 2017-01-10 | 2017-08-08 | 田巍巍 | A kind of aircraft model plane |
| CN106915457A (en) * | 2017-02-22 | 2017-07-04 | 北京航空航天大学 | A kind of variable co-axial helicopter steerable system of upper and lower rotor inclinator depth of parallelism |
| CN106823403A (en) * | 2017-03-07 | 2017-06-13 | 王长民 | Many oar telecontrolled aircrafts |
| CN106882391A (en) * | 2017-03-17 | 2017-06-23 | 四川建筑职业技术学院 | A kind of spherical three axles joint control vector motor cabinet of unmanned plane |
| CN207045728U (en) * | 2017-08-11 | 2018-02-27 | 红河学院 | Fixed-wing vector unmanned plane |
Non-Patent Citations (2)
| Title |
|---|
| 谢良伟;杨哲毅;盛涛;肖刘鑫;: "可矢量控制姿态的旋翼机设计", 科技风, no. 11, pages 3 - 4 * |
| 高鹏波: "四旋翼直升机硬件设计与姿态、巡航控制算法实现", 中国优秀硕士学位论文全文数据库 (工程科技Ⅱ辑), pages 031 - 22 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108298071A (en) * | 2018-03-14 | 2018-07-20 | 长沙市云智航科技有限公司 | A kind of more rotor flying vehicles of manned duct |
| CN108298074A (en) * | 2018-03-14 | 2018-07-20 | 长沙市云智航科技有限公司 | The component that verts for the more rotor flying vehicles of manned duct |
| CN108639331A (en) * | 2018-06-29 | 2018-10-12 | 长沙市云智航科技有限公司 | One kind is verted double-rotor aerobat |
| CN109263868A (en) * | 2018-09-28 | 2019-01-25 | 上海歌尔泰克机器人有限公司 | A kind of unmanned plane rotor structure and unmanned plane during flying device |
| CN109606680A (en) * | 2018-12-26 | 2019-04-12 | 李昊泽 | The multi-modal aircraft of a kind of pair of hair full vector and flight system |
| JP2023076742A (en) * | 2020-01-27 | 2023-06-01 | 株式会社エアロネクスト | Flying body |
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