CN108025810A - A kind of inclination angle while the quadrotor jet aircraft of dynamic change - Google Patents
A kind of inclination angle while the quadrotor jet aircraft of dynamic change Download PDFInfo
- Publication number
- CN108025810A CN108025810A CN201680055534.1A CN201680055534A CN108025810A CN 108025810 A CN108025810 A CN 108025810A CN 201680055534 A CN201680055534 A CN 201680055534A CN 108025810 A CN108025810 A CN 108025810A
- Authority
- CN
- China
- Prior art keywords
- rotor
- direct current
- current generator
- axle sleeve
- aircraft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 16
- 239000004917 carbon fiber Substances 0.000 claims description 16
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 16
- 229910000831 Steel Inorganic materials 0.000 claims description 10
- 239000010959 steel Substances 0.000 claims description 10
- 239000002184 metal Substances 0.000 claims description 9
- 238000013016 damping Methods 0.000 claims description 7
- 230000000694 effects Effects 0.000 claims description 2
- 239000000446 fuel Substances 0.000 claims 1
- 230000003139 buffering effect Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012857 repacking Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/20—Vertical take-off and landing [VTOL] aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
- B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U40/00—On-board mechanical arrangements for adjusting control surfaces or rotors; On-board mechanical arrangements for in-flight adjustment of the base configuration
- B64U40/10—On-board mechanical arrangements for adjusting control surfaces or rotors; On-board mechanical arrangements for in-flight adjustment of the base configuration for adjusting control surfaces or rotors
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
A kind of inclination angle while the quadrotor jet aircraft of dynamic change, the same rotor (2 of the opposite rotating speed in two direction of rotation is symmetrically installed on the both sides of aircraft fuselage (1), 8,9,10), the rotary rpm of rotor is adjusted, the lift on fuselage both sides is can adjust, so as to adjust the left-right balance of aircraft.Four rotors are adjusted relative to corner of the wing (5,6) along fuselage direction, can adjust the pitching of aircraft.In addition, by rotor fixator (3), rotor can be fixed on the direction parallel with fuselage, so that as fixed wing aircraft, by the active flight of jet engine (40).
Description
There are three types of a kind of quadrotor jet aircraft aircraft of inclination angle dynamic change simultaneously is current: fixed-wing formula aircraft, helicopter, multi-rotor aerocraft.
The advantages of fixed wing aircraft is that loading capacity is big, and speed is fast.The disadvantage is that being unable to VTOL.
The advantages of helicopter is that loading capacity is big, energy VTOL, the disadvantage is that speed is slower, the extremely complex valuableness of device.
The advantages of quadrotor is that device is simply cheap, but speed is very slow, and load-carrying is larger.
The present invention has concentrated the advantage of three kinds of aircraft respectively, can loading capacity is big and VTOL, moreover it is possible to high-speed flight.The complex mechanism of lifting airscrew head is resolved into simple structure by it, and the requirement of material there is not helicopter so high yet.
Briefly: the same rotor of the opposite revolving speed in two direction of rotation being symmetrically installed on the both sides of aircraft fuselage.For the wing 5 on the left side, rotor 2 is with rotor 8 because as revolving speed, and direction of rotation is on the contrary, 8 generation lift of rotor 2 and rotor.Without torque.For the wing 6 on the right, rotor 9 is with rotor 10 because as revolving speed, and direction of rotation is on the contrary, 10 generation lift of rotor 9 and rotor.Without torque.So, it is only necessary to adjust rotor 2, rotor 8, rotor 9, the rotary rpm of rotor 10, so that it may which the lift for reaching adjustment fuselage both sides when aircraft flight, can also adjust the left-right balance of aircraft.
For the adjustment of aircraft pitching, it is only necessary to while four rotors are adjusted relative to wing along the corner in fuselage direction, also just achieve the goal.Horizontal axis 23 and horizontal axis 34 are symmetrically installed on the wing on fuselage both sides, in horizontal axis 23 and horizontal axis 34 is by bearing 24 and bearing 27 covers Upper shaft sleeve 35 and 33. direct current generator 13 of axle sleeve respectively and direct current generator 26 is mounted on axle sleeve 35.Direct current generator 36 and direct current generator 37 are mounted on axle sleeve 33.Only need to adjust the angle of steering engine 31 in this way, band movable gear shaft 30 rotates.Band moving gear 28 and gear 32, gear 28 are fixed on axle sleeve 35 gear shaft 30 again, have also just driven the rotation of axle sleeve 35, direct current generator 13 and 26 also just has rotated, and rotor 2 and rotor 8 also just have rotated corresponding angle.Last effect also just has adjusted the pitching of fuselage.
And after aircraft is liftoff, so that it may start jet engine 40, with the increase of speed, the lift that wing 5 and wing 6 generate also constantly increases.The revolving speed of direct current generator can be reduced.
After reaching certain speed, that is, when the lift that generates of wing 5 and wing 6 is enough to hold up aircraft, by rotor fixator 3, rotor 2 is fixed on the direction parallel with fuselage.Rotor 8, rotor 9 and rotor 10 are also all fixed on the direction parallel with fuselage.
At this moment aircraft is just as fixed wing aircraft, as long as jet engine power is sufficiently large, the flying speed of the aircraft is not also just limited by helicopter tip velocity because the aircraft oneself through no rotary rotor, flying speed is also just and fixed-wing is similar.Only resistance can be more a little bigger than fixed wing aircraft.
Specific embodiment: from big part, which includes fuselage 1, port wing 5, starboard wing 6, rotor 2, rotor 8, rotor 9, rotor 10, rotor fixator 3, rotor fixator 41, rotor fixator 42, rotor fixator 43.
Port wing 5 and starboard wing 6 are symmetrically mounted on fuselage both sides.Rotor 2 and rotor 8 are mounted on port wing 5, and rotor 9 and rotor 10 are mounted on starboard wing.The Plane of rotation of rotor 2, rotor 8, rotor 9, rotor 10 is parallel with ground, and rotor 2 is with the direction of rotation of rotor 8 on the contrary, but as revolving speed.Rotor 9 is with the direction of rotation of rotor 10 on the contrary, but as revolving speed.
On the wing of the lower section of each rotor and fix a rotor fixator: rotor fixator 3 is mounted on the lower section of rotor 2, and rotor fixator 41 is mounted on the lower section of rotor 8.Rotor fixator 42 is mounted on the lower section of rotor 9, the lower section rotor 2 that rotor fixator 43 is mounted on rotor 10 is fixed on direct current generator 13, rotor 8 is fixed on direct current generator 26, and rotor 9 is fixed on direct current generator 36, and rotor 10 is fixed on direct current generator 37.
Direct current generator 13 and direct current generator 26 are fixed on axle sleeve 35, and direct current generator 36 and direct current generator 37 are fixed on axle sleeve 33.And axle sleeve 35 penetrates carbon fiber horizontal axis 23 by bearing 24 and bearing 27, axle sleeve 33 penetrates carbon fiber horizontal axis 34 by bearing 38 and bearing 39.Carbon fiber horizontal axis 23 is fixed on carbon fiber plate 22, and carbon fiber horizontal axis 34 is fixed on carbon fiber plate 45.
Steering engine 31 is fixed on fuselage, and gear shaft 30 is connected with steering engine 31, gear shaft 30 again with gear 28, gear 32 be connected.And gear 28 and axle sleeve 35 are fixed.Gear 32 and the fixed of axle sleeve 33
In this way, can be by the variation of the angle of steering engine, rotor 2, rotor 8, rotor 9, rotor 10 also can and then mutually deserved variation simultaneously.
Rotor fixator 3 is fixed on carbon fiber plate 22.Two columns 14 and 21 are installed on the both sides of direct current generator main shaft 4, fixes damping device 15 on the face opposite with direct current generator main shaft 4 of column 14, fixes damping device 20 on the face opposite with direct current generator main shaft 4 of column 21.The fixed coil 16 among column 14 and direct current generator main shaft, sliding metal magnet steel 17 are then mounted in coil 17.In column 21 and the intermediate fixed coil 19 of direct current generator main shaft 4, sliding metal magnet steel 18 is then mounted in coil 19.
The working principle of rotor is: when the speed of aircraft improves, when the lift that wing 5 and wing 6 generate can hold up aircraft, the speed for making rotor very slow rotates, it is powered simultaneously to coil 19, and sliding metal magnet steel 18 just will receive the thrust in the magnetic field generated by the energization of coil 18, stretch out upwards, and be more than the height of the rotation of rotor 2.When rotor wing rotation encounters sliding metal magnet steel 18, just stop rotating, and damping device 20 is the impact strength for buffering rotor 2 and sliding metal magnet steel 18.This is to be powered again to coil 16, and sliding magnet steel 17 stretches out and be more than the height of rotor 2.Rotor 2 is secured between column 14 and column 21 in this way.
The also principle and structure with rotor 3-sample of fixator of rotor fixator 41,42,43.
By above repacking, aircraft is in takeoff and landing, as long as controlling the difference of the revolving speed of the revolving speed and rotor 9 and rotor 10 of rotor 2 and rotor 8, it just can control the left-right balance of aircraft, control rotor 2 and rotor 8, and rotor 9 and rotor 10 just can control the anterior-posterior balance of aircraft along the inclination angle in fuselage direction and wing.After aircraft takeoff is liftoff, start jet engine 40, with the raising of aircraft speed, the lift of wing 5 and wing 6 also constantly increases, and the revolving speed of rotor 2 and rotor 8 and rotor 9 and rotor 10 can slow down, when the lift of wing 5 and wing 6, which arrives greatly, individually to hold aircraft, enable 4 rotor fixators 3,41,42,43. are fixed to rotor 2 and rotor 8 and rotor 9 and rotor 10 and the fuselage same direction.Aircraft at this time is just at fixed wing aircraft.Fig. 1 is the front view of aircraft,
Fig. 2 is the top view of aircraft,
Fig. 3 is the wing figure for removing covering,
Fig. 4 is the location drawing after aircraft starting rotor fixator, that is, rotor location drawing when cruise.
Fig. 5 is the internal structure chart of rotor fixator
Number in figure is described as follows-serial number number title
11 fuselages
22 rotors
33 rotor fixators
44 direct current generator main shafts
55 port wings
66 starboard wings
77 wheels
88 rotors
99 rotors
10 10 rotors
11 13 direct current generators
12 14 columns
13 15 damping devices
14 16 coils
15 17 sliding metal magnet steel
16 18 sliding metal magnet steel
17 19 coils
18 20 damping devices
、
19 21 columns
20 22 carbon fiber plates
21 23 carbon fiber horizontal axis
22 24 bearings
23 26 direct current generators
24 27 bearings
25 28 gears
26 30 gear shafts
27 31 steering engines
28 32 gears
29 33 axle sleeves
30 34 horizontal axis
31 35 axle sleeves
32 36 direct current generators
33 37 direct current generators
34 38 bearings
35 39 bearings
36 40 jet engines
37 41 rotor fixators
38 42 rotor fixators
39 43 rotor fixators
40 44 ground
41 45 carbon fiber plates
Claims (1)
- The quadrotor jet aircraft of a kind of inclination angle of claims while dynamic change, it is characterized in that:1, the same rotor of the opposite revolving speed in two direction of rotation is symmetrically installed on the both sides of aircraft fuselage 1, the Plane of rotation of rotor is parallel to the ground.Rotor 2 is identical with 8 revolving speed of rotor, and direction of rotation is opposite.Rotor 9 is identical with 10 revolving speed of rotor, and direction of rotation is opposite.Direct current generator can be brshless DC motor, be also possible to the fuel engines of propeller type.One jet engine is installed behind fuselage 1.It can not certainly fill.2, according to feature 1, in wing 5, carbon fiber plate 22 is installed, carbon fiber horizontal axis 23 is mounted on carbon fiber plate 22, in wing 6, installs carbon fiber horizontal axis 34.By bearing 24 and bearing 27, axle sleeve 35 is inserted in carbon fiber horizontal axis 23, and by bearing 38 and bearing 39, axle sleeve 33 is inserted in carbon fiber horizontal axis 34.Direct current generator 13 and direct current generator 26 are fixed on axle sleeve 35, and direct current generator 36 and direct current generator 37 are fixed on axle sleeve 33.Gear 28 is connected with axle sleeve 35, and gear 32 is connected with axle sleeve 33, and gear shaft 30 is connected with gear 28 and gear 32, and gear shaft 30 is connected with steering engine 31 again.Steering engine 31 is fixed on the fuselage 1.Rotor 2 is installed on direct current generator 13, is installed on direct current generator 26 and rotor 9 is installed on 8. direct current generator 36 of rotor, rotor 10 is installed on direct current generator 37.Effect is exactly the variation by controlling 31 angle of steering engine, and rotor 2 and rotor 8 also have corresponding angle change.3, according to feature 1, rotor fixator 3 and rotor fixator 41 are installed on the lower section of rotor 2 and rotor 8 and axle sleeve 35, rotor fixator 42 and rotor fixator 43. are installed on the lower section of rotor 9 and rotor 10 and axle sleeve 334, according to feature 3, two columns 14 and 21 are installed on the both sides of direct current generator main shaft 4, fixes damping device 15 on the face opposite with direct current generator main shaft 4 of column 14, fixes damping device 20 on the face opposite with direct current generator main shaft 4 of column 21.In column 14 and the intermediate fixed coil 16 of direct current generator main shaft 4, sliding metal magnet steel 17 is then mounted in coil 16.In column 21 and the intermediate fixed coil 19 of direct current generator main shaft 4, sliding metal magnet steel 18 is then mounted in coil 19.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CNPCT/CN2015/000660 | 2015-09-24 | ||
PCT/CN2015/000660 WO2017049422A1 (en) | 2015-09-24 | 2015-09-24 | Four-rotor aircraft with dynamical variations |
PCT/CN2016/000248 WO2017049806A1 (en) | 2015-09-24 | 2016-05-09 | Quadrotor jet aircraft with simultaneously dynamically varying pitches |
Publications (2)
Publication Number | Publication Date |
---|---|
CN108025810A true CN108025810A (en) | 2018-05-11 |
CN108025810B CN108025810B (en) | 2022-01-04 |
Family
ID=58385453
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN201680055534.1A Expired - Fee Related CN108025810B (en) | 2015-09-24 | 2016-05-09 | Four-rotor jet aircraft with inclination angle capable of being dynamically changed simultaneously |
Country Status (2)
Country | Link |
---|---|
CN (1) | CN108025810B (en) |
WO (2) | WO2017049422A1 (en) |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN107685872A (en) * | 2017-09-30 | 2018-02-13 | 深圳市道通智能航空技术有限公司 | Unmanned vehicle |
CN108827302A (en) * | 2018-04-24 | 2018-11-16 | 大连理工大学 | Multi-rotor aerocraft air navigation aid based on rotor tachometric survey |
CN110092000A (en) * | 2019-06-04 | 2019-08-06 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of all-electric tilting rotor wing unmanned aerial vehicle |
CN110422328A (en) * | 2019-08-26 | 2019-11-08 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of tilting rotor wing unmanned aerial vehicle linear power configuration method and structure |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN1907806A (en) * | 2005-08-02 | 2007-02-07 | 韩培洲 | helicopter with tilted front rotary wing |
US20100193644A1 (en) * | 2008-04-25 | 2010-08-05 | Abe Karem | Aircraft with Integrated Lift and Propulsion System |
US20110315827A1 (en) * | 2009-03-12 | 2011-12-29 | Bob Collins | Wing Extension Control Surface |
CN202728576U (en) * | 2012-02-10 | 2013-02-13 | 田瑜 | Transformable composite aircraft formed by fixed wing and electric multi-propeller |
CN103935511A (en) * | 2014-04-15 | 2014-07-23 | 西安交通大学 | Tilt-three-rotor craft |
Family Cites Families (11)
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DE202005003894U1 (en) * | 2005-03-10 | 2005-06-30 | Schraufstetter, Wilfried | Vertical take off and landing aircraft has lift and propulsion producing rotors, whose axes are not coaxial, and a control pod and main coupling unit linked by control lines via carrying pipes to rotor couplings |
CN101314409B (en) * | 2008-07-10 | 2012-04-18 | 周武双 | Swallow type inclined rotation rotorcraft |
KR20100026130A (en) * | 2008-08-29 | 2010-03-10 | 임채호 | Taking off and landing airplane using variable rotary wings |
PT2551198E (en) * | 2011-07-29 | 2013-12-27 | Agustawestland Spa | Convertiplane |
DE102013109392A1 (en) * | 2013-08-29 | 2015-03-05 | Airbus Defence and Space GmbH | Fast-flying, vertically launchable aircraft |
RU2547950C1 (en) * | 2013-12-19 | 2015-04-10 | Общество с ограниченной ответственностью научно-производственное предприятие "Измерон-В" (ООО НПП "Измерон-В") | Quadrocopter |
CN104210655A (en) * | 2014-09-03 | 2014-12-17 | 西北农林科技大学 | Double-rotor-wing unmanned plane |
CN204279937U (en) * | 2014-10-27 | 2015-04-22 | 深圳九星智能航空科技有限公司 | The collapsible double-rotor aerobat overhang of lower blade |
CN204279938U (en) * | 2014-10-27 | 2015-04-22 | 深圳九星智能航空科技有限公司 | The rotor unmanned aircraft that blade can be dismantled separately |
CN104369863A (en) * | 2014-10-31 | 2015-02-25 | 吴建伟 | Composite vertical take-off/landing aircraft |
CN104859836A (en) * | 2015-05-06 | 2015-08-26 | 浙江工业大学之江学院 | Unmanned aerial vehicle |
-
2015
- 2015-09-24 WO PCT/CN2015/000660 patent/WO2017049422A1/en active Application Filing
-
2016
- 2016-05-09 CN CN201680055534.1A patent/CN108025810B/en not_active Expired - Fee Related
- 2016-05-09 WO PCT/CN2016/000248 patent/WO2017049806A1/en active Application Filing
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN1907806A (en) * | 2005-08-02 | 2007-02-07 | 韩培洲 | helicopter with tilted front rotary wing |
US20100193644A1 (en) * | 2008-04-25 | 2010-08-05 | Abe Karem | Aircraft with Integrated Lift and Propulsion System |
US20110315827A1 (en) * | 2009-03-12 | 2011-12-29 | Bob Collins | Wing Extension Control Surface |
CN202728576U (en) * | 2012-02-10 | 2013-02-13 | 田瑜 | Transformable composite aircraft formed by fixed wing and electric multi-propeller |
CN103935511A (en) * | 2014-04-15 | 2014-07-23 | 西安交通大学 | Tilt-three-rotor craft |
Also Published As
Publication number | Publication date |
---|---|
WO2017049806A1 (en) | 2017-03-30 |
WO2017049422A1 (en) | 2017-03-30 |
CN108025810B (en) | 2022-01-04 |
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