CN108639331A - One kind is verted double-rotor aerobat - Google Patents
One kind is verted double-rotor aerobat Download PDFInfo
- Publication number
- CN108639331A CN108639331A CN201810695828.1A CN201810695828A CN108639331A CN 108639331 A CN108639331 A CN 108639331A CN 201810695828 A CN201810695828 A CN 201810695828A CN 108639331 A CN108639331 A CN 108639331A
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- China
- Prior art keywords
- rotor
- verts
- fuselage
- double
- connecting rod
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- 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.)
- Pending
Links
- 230000000712 assembly Effects 0.000 claims abstract description 40
- 238000000429 assembly Methods 0.000 claims abstract description 40
- 238000002485 combustion reaction Methods 0.000 claims description 8
- 230000007246 mechanism Effects 0.000 claims description 8
- 239000000446 fuel Substances 0.000 claims description 3
- 239000002828 fuel tank Substances 0.000 claims description 3
- 230000005611 electricity Effects 0.000 claims 1
- 238000009434 installation Methods 0.000 claims 1
- 230000008901 benefit Effects 0.000 abstract description 4
- 230000000694 effects Effects 0.000 description 4
- 239000003502 gasoline Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000008859 change Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000010006 flight Effects 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 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 1
- 238000001514 detection method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
Classifications
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
Abstract
It verts double-rotor aerobat, including fuselage the invention discloses one kind, the both sides of the fuselage are symmetrically arranged with fixed-wing, and the tail portion of the fuselage is provided with fixed empennage；The end of each fixed-wing is rotatablely equipped with rotor assemblies, and the component that verts is equipped between the fixed-wing and rotor assemblies, for driving rotor assemblies rotation to be tilted facing towards along fuselage front and back with the rotor for adjusting rotor assemblies.The double-rotor aerobat that verts of the present invention has many advantages, such as that simple in structure, headway is fast and can hover.
Description
Technical field
The invention mainly relates to vehicle technology field, refers in particular to one kind and vert double-rotor aerobat.
Background technology
Currently, small aircraft is used for carrying various measuring instruments mostly（Such as camera）, carry out aerological sounding or high-altitude
On object is thrown, it can apply in various fields such as agricultural, detection, meteorological, hazard forecasting and rescues.
Existing aircraft is divided into two kinds of Fixed Wing AirVehicle and rotor craft.Fixed Wing AirVehicle mainly passes through acquisition
Larger initial velocity forms lift in aerofoil and realizes flight, but can not hover, and stability is poor when low speed, be easy because stall and
Air crash, and need larger ground run distance.In addition Fixed Wing AirVehicle is generally turned to using two methods, a kind of pure
It is turned to by vertical tail, one is wing aileron cooperation tailplanes to turn to.Wherein purely the case where ratio is turned to by vertical tail
It is more rare because vertical tail in addition to have control aircraft turn function other than, there are one most important function be just to maintain it is winged
The stabilization of machine, it is impossible to significantly be turned using vertical tail.And wing aileron cooperation tailplane turns to, and is to pass through pair
The lifting of the wing, fuselage is tilted, and is turned round by the effect of centrifugal force, and this mode needs aircraft itself to have inclined effect,
It applies on personal aircraft, the security risk of driver can be increased, be not suitable for personal aircraft and use.
Another is rotor craft, and wherein rotor is primarily used to form lift, and flying speed needs by adjusting appearance
State forms lateral resultant force and could realize, larger and headway is relatively low so as to cause energy expenditure.In addition rotor craft is big
More is all to realize that attitude of flight vehicle changes by change of flight device engine output, or change blade screw pitch；And it is
So that aircraft smooth flight when adjusting each flight attitude needs the rotating speed for accurately calculating engine and change
The screw pitch of blade, process is cumbersome, is not suitable for flight environment of vehicle complicated and changeable, and still will appear inclination in flight course,
The same security risk for increasing driver.
Invention content
The technical problem to be solved in the present invention is that：For technical problem of the existing technology, the present invention provides one
The double-rotor aerobat that verts that kind is simple in structure, speed is fast and can hover.
In order to solve the above technical problems, technical solution proposed by the present invention is：
One kind is verted double-rotor aerobat, including fuselage, and the both sides of the fuselage are symmetrically arranged with fixed-wing, the tail of the fuselage
Portion is provided with fixed empennage；The end of each fixed-wing is rotatablely equipped with rotor assemblies, the fixed-wing and rotor assemblies
Between the component that verts is installed, for drive rotor assemblies rotation to adjust the rotor of rotor assemblies facing towards along fuselage front and back
It tilts.
As a further improvement of the above technical scheme：
The rotor assemblies include mounting bracket, rotor and force piece, and the force piece is installed on the mounting bracket, the power
The output shaft of part is connect with the rotor.
The force piece is internal combustion engine or motor；When the force piece is internal combustion engine, oil is provided on the fuselage
Case carries out fuel feeding for unified to each internal combustion engine；When the force piece is motor, the fuselage is equipped with electric energy unit,
For unified electric energy is provided to each motor.
The component that verts includes actuator and link mechanism, and one end of the link mechanism is connected with the actuator,
The other end is connected with the rotor assemblies.
The link mechanism includes cursor, first connecting rod and second connecting rod, is fixed in the middle part of the cursor described
On the output shaft of actuator, one end of the first connecting rod and one end of the cursor are hinged, one end of the second connecting rod
Hinged with the other end of the cursor, the other end of the first connecting rod and second connecting rod is hinged on the rotor assemblies
On.
The first connecting rod and second connecting rod are ball head connecting rod, and ball screw is provided in the rotor assemblies, described
Ball head connecting rod is connected with ball screw.
The actuator is servo motor or stepper motor or steering engine.
A fixing axle for running through fuselage both sides fixed-wing is provided on the fuselage, the both ends of the fixing axle are arranged with
Bearing is equipped with bearing block in the rotor assemblies, and the bearing is installed in the bearing block.
The bottom of the fuselage is provided with undercarriage.
The rotor includes rotor seat and polylith rotary blade, and rotary blade is evenly distributed on rotor seat described in polylith.
Compared with the prior art, the advantages of the present invention are as follows：
Fixed Wing AirVehicle is carried out depth with rotor craft and is combined, i.e., in fixation by the double-rotor aerobat that verts of the present invention
The end of the wing is rotatablely equipped with rotor assemblies, can gather the advantage of Fixed Wing AirVehicle and rotor craft, headway is fast,
It can hover, can be suitably used for flight environment of vehicle complicated and changeable；And it is simple in structure, be easily achieved；In fixed-wing and each rotor assemblies
Between be mounted on the component that verts, for drive rotor assemblies rotate so that rotor face direction along fuselage front and back tilt,
To realize the adjustment of the various state of flights such as aircraft landing, steering, translation and hovering, in the process, fuselage is located always
In stable horizontality, ensure the traffic safety and riding comfort of driver or passenger.
Description of the drawings
Fig. 1 is the three-dimensional structure diagram of the present invention.
Fig. 2 is the overlooking structure figure of the present invention.
Fig. 3 is the structural schematic diagram of rotor and the component that verts in the present invention.
Figure label indicates：1, fuselage；101, fixed-wing；102, empennage；103, fixing axle；2, rotor assemblies；201, pacify
It shelves；202, force piece；203, rotor；3, vert component；301, actuator；302, cursor；303, first connecting rod；304,
Two connecting rods；305, ball screw.
Specific implementation mode
Below in conjunction with Figure of description and specific embodiment, the invention will be further described.
As depicted in figs. 1 and 2, the double-rotor aerobat that verts of the present embodiment, including fuselage 1, the bottom of fuselage 1 are equipped with
Undercarriage（It is not shown in figure）, the both sides of fuselage 1 are symmetrically arranged with fixed-wing 101, and the tail portion of fuselage 1 is provided with fixed empennage
102；The end of each fixed-wing 101 is rotatablely equipped with rotor assemblies 2, is installed between fixed-wing 101 and rotor assemblies 2
Vert component 3, for driving the rotation of rotor assemblies 2 to be tilted facing towards along 1 front and back of fuselage with the rotor for adjusting rotor assemblies 2,
To realize the adjustment of the state of flights such as aircraft landing, steering, translation and hovering.The double-rotor aerobat that verts of the present invention,
Fixed Wing AirVehicle is carried out depth with rotor craft to be combined, i.e., is rotatablely equipped with rotor assemblies in the end of fixed-wing 101
2, the advantage of Fixed Wing AirVehicle and rotor craft can be gathered, headway is fast, can hover, fly suitable for complicated and changeable
Row environment；And it is simple in structure, be easily achieved.
In the present embodiment, rotor assemblies 2 include mounting bracket 201, rotor 203 and force piece 202, and force piece 202 is installed on
On mounting bracket 201, the output shaft of force piece 202 is connect with rotor 203.It is provided with one in its middle fuselage 1 and runs through 1 both sides of fuselage
The both ends of the fixing axle 103 of fixed-wing 101, fixing axle 103 are arranged with bearing, and axis is equipped on the mounting bracket 201 of rotor assemblies 2
Bearing, bearing are installed in bearing block, i.e., mounting bracket 201 can be rotated around fixing axle 103.In addition, force piece 202 be internal combustion engine or
Motor；When force piece 202 is internal combustion engine, such as gasoline engine, the unified fuel tank by fuselage 1 of each gasoline engine carries out
Unified fuel feeding, the mode of independent oil tank is configured relative to each gasoline engine, can ensure fuel tank weight at each rotor assemblies 2
Consistency, consequently facilitating carrying out flight control.Certainly, force piece 202 or motor, by installing on the fuselage 1
Accumulator to provide the mode that electric energy or gasoline engine drive generator to produce electricl energy to each motor be that each motor carries
For electric energy, and suitable accumulator is assisted to carry out the work such as electric energy feedback, redundancy protecting.In the present embodiment, rotor 203 includes rotation
Wing seat and three pieces of rotary blades, three pieces of rotary blades are evenly distributed on rotor seat.It is understood that herein not to rotary blade
Quantity is defined, and in other embodiments, can also use the rotary blade of two panels, four or more the piece numbers.
As shown in figure 3, in the present embodiment, the component 3 that verts includes actuator 301 and link mechanism, and wherein actuator 301 is
Steering engine, stepper motor or servo motor, wherein it is preferred that steering engine, link mechanism include then cursor 302,303 and of first connecting rod
The middle part of second connecting rod 304, cursor 302 is fixed on the output shaft of steering engine and rotates with it, one end of first connecting rod 303 with
One end of cursor 302 is hinged, and one end of second connecting rod 304 is hinged with the other end of cursor 302, first connecting rod 303 and the
The other end of two connecting rods 304 is hinged in mounting base；Wherein first connecting rod 303 and second connecting rod 304 is ball head connecting rod, peace
Dress seat is provided with ball screw 305 in the both sides of bearing block, and ball head connecting rod is connected with ball screw 305.When steering engine receives
When to control command, predetermined angular is rotated, corresponding cursor 302 rotates, exists by first connecting rod 303 and second connecting rod 304
Pullling in opposite direction drives mounting bracket 201 to rotate, to making the rotor 203 on mounting bracket 201 towards the front of fuselage 1 or
Back sweep.
The double-rotor aerobat that verts of the present invention, corresponding attitude adjusting method are as follows：
When needing that aircraft is made to be in forward travel state, the angle of both sides rotor assemblies 2 is adjusted by the component 3 that verts, makes rotor
The front for facing fuselage 1 tilts, and making aircraft, there are one forward motive forces, push aircraft forward flight.
When needing that aircraft is made to be in retrogressing or braking state, passes through the component 3 that verts and adjust both sides rotor assemblies 2
Angle makes the rotor of both sides rotor assemblies 2 face the back sweep of fuselage 1, and making aircraft, there are one motive forces backward, push
Aircraft flies or brakes backward
When needing that aircraft is made to bend to right, the rotor assemblies 2 in left side is made to turn forward, while making the rotor assemblies 2 on right side
It tilts backwards, i.e., there is forward thrust, right side to there is thrust backward, collective effect to make it to the right in aircraft on the left of aircraft
It turns to.
When needing that aircraft is made to turn to the left, the rotor assemblies 2 in left side is made to tilt backwards, while making the rotor group on right side
Part 2 turns forward, i.e., has thrust backward on the left of aircraft, right side has forward thrust, collective effect to make it in aircraft
It turns to the left.
The above is only the preferred embodiment of the present invention, protection scope of the present invention is not limited merely to above-described embodiment,
All technical solutions belonged under thinking of the present invention all belong to the scope of protection of the present invention.It should be pointed out that for the art
For those of ordinary skill, several improvements and modifications without departing from the principles of the present invention should be regarded as the protection of the present invention
Range.
Claims (10)
- The double-rotor aerobat 1. one kind is verted, which is characterized in that including fuselage（1）, the fuselage（1）Both sides be symmetrically arranged with Fixed-wing（101）, the fuselage（1）Tail portion be provided with fixed empennage（102）；Each fixed-wing（101）End turn It is dynamic that rotor assemblies are installed（2）, the fixed-wing（101）With rotor assemblies（2）Between the component that verts is installed（3）, for driving Dynamic rotor assemblies（2）Rotation is to adjust rotor assemblies（2）Rotor facing towards along fuselage（1）Front and back tilt.
- 2. the double-rotor aerobat according to claim 1 that verts, which is characterized in that the rotor assemblies（2）Including installation Frame（201）, rotor（203）And force piece（202）, the force piece（202）It is installed on the mounting bracket（201）On, it is described dynamic Power part（202）Output shaft and the rotor（203）Connection.
- 3. the double-rotor aerobat according to claim 2 that verts, which is characterized in that the force piece（202）For internal combustion engine Or motor；When the force piece（202）For internal combustion engine when, the fuselage（1）On be provided with fuel tank, for unified to each internal combustion Machine carries out fuel feeding；When the force piece（202）For motor when, the fuselage（1）It is equipped with electric energy unit, for unified to each Motor provides electric energy.
- 4. the double-rotor aerobat according to claim 1 or 2 or 3 that verts, which is characterized in that the component that verts（3）Packet Include actuator（301）And link mechanism, one end of the link mechanism and the actuator（301）Be connected, the other end with it is described Rotor assemblies（2）It is connected.
- 5. the double-rotor aerobat according to claim 4 that verts, which is characterized in that the link mechanism includes cursor （302）, first connecting rod（303）And second connecting rod（304）, the cursor（302）Middle part be fixed on the actuator（301） Output shaft on, the first connecting rod（303）One end and the cursor（302）One end it is hinged, the second connecting rod （304）One end and the cursor（302）The other end it is hinged, the first connecting rod（303）And second connecting rod（304）It is another One end is hinged on the rotor assemblies（2）On.
- 6. the double-rotor aerobat according to claim 5 that verts, which is characterized in that the first connecting rod（303）With second Connecting rod（304）It is ball head connecting rod, the rotor assemblies（2）On be provided with ball screw（305）, the ball head connecting rod and bulb Screw（305）It is connected.
- 7. the double-rotor aerobat according to claim 4 that verts, which is characterized in that the actuator（301）For servo electricity Machine or stepper motor or steering engine.
- 8. the double-rotor aerobat according to claim 1 or 2 or 3 that verts, which is characterized in that the fuselage（1）Upper setting There is one to run through fuselage（1）Both sides fixed-wing（101）Fixing axle（103）, the fixing axle（103）Both ends be arranged with axis It holds, the rotor assemblies（2）On bearing block is installed, the bearing is installed in the bearing block.
- 9. the double-rotor aerobat according to claim 1 or 2 or 3 that verts, which is characterized in that the fuselage（1）Bottom It is provided with undercarriage.
- 10. the double-rotor aerobat according to claim 2 or 3 that verts, which is characterized in that the rotor（203）Including rotation Wing seat and polylith rotary blade, rotary blade described in polylith are evenly distributed on rotor seat.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810695828.1A CN108639331A (en) | 2018-06-29 | 2018-06-29 | One kind is verted double-rotor aerobat |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810695828.1A CN108639331A (en) | 2018-06-29 | 2018-06-29 | One kind is verted double-rotor aerobat |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108639331A true CN108639331A (en) | 2018-10-12 |
Family
ID=63749925
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810695828.1A Pending CN108639331A (en) | 2018-06-29 | 2018-06-29 | One kind is verted double-rotor aerobat |
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| CN (1) | CN108639331A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110576964A (en) * | 2019-09-24 | 2019-12-17 | 中国人民解放军战略支援部队航天工程大学 | Rotor wing tilting device for four-axis unmanned aerial vehicle |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101181931A (en) * | 2007-12-06 | 2008-05-21 | 武汉理工大学 | Helicopter advancing and steering mechanism |
| CN102126553A (en) * | 2010-01-12 | 2011-07-20 | 北京航空航天大学 | Vertically taking off and landing small unmanned aerial vehicle |
| CN103241376A (en) * | 2012-02-01 | 2013-08-14 | 北京安翔动力科技有限公司 | Vector power vertical takeoff and landing aircraft and vector power system thereof |
| CN203419259U (en) * | 2013-10-16 | 2014-02-05 | 罗光俊 | Micro tilt-rotor aircraft |
| CN104843178A (en) * | 2015-04-30 | 2015-08-19 | 江苏数字鹰科技发展有限公司 | Flying motorcycle or automobile and flight attitude adjustment method thereof |
| CN105035319A (en) * | 2015-07-27 | 2015-11-11 | 江阴市翔诺电子科技有限公司 | Novel vertical take-off and landing air vehicle and control method thereof |
| CN204979219U (en) * | 2015-08-10 | 2016-01-20 | 红河学院 | Four screws gyroplane that verts |
| CN105564642A (en) * | 2016-03-03 | 2016-05-11 | 辽宁猎鹰航空科技有限公司 | Tilt-rotor UAV (Unmanned Aerial Vehicle) |
| CN106585976A (en) * | 2016-11-30 | 2017-04-26 | 北京航空航天大学 | Aircraft layout of tilt rotors/lift fan during high-speed long endurance |
| CN106926272A (en) * | 2017-02-27 | 2017-07-07 | 哈尔滨工业大学深圳研究生院 | A kind of flying bird robot empennage governor motion |
| CN107097938A (en) * | 2017-03-20 | 2017-08-29 | 长光卫星技术有限公司 | A kind of inclining rotary mechanism for the quadrotor that verts |
| CN107176297A (en) * | 2017-06-20 | 2017-09-19 | 北京迪鸥航空科技有限公司 | A kind of aircraft |
| CN107364572A (en) * | 2017-08-11 | 2017-11-21 | 红河学院 | Fixed-wing vector unmanned plane |
| CN208360498U (en) * | 2018-06-29 | 2019-01-11 | 长沙市云智航科技有限公司 | One kind is verted double-rotor aerobat |
-
2018
- 2018-06-29 CN CN201810695828.1A patent/CN108639331A/en active Pending
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101181931A (en) * | 2007-12-06 | 2008-05-21 | 武汉理工大学 | Helicopter advancing and steering mechanism |
| CN102126553A (en) * | 2010-01-12 | 2011-07-20 | 北京航空航天大学 | Vertically taking off and landing small unmanned aerial vehicle |
| CN103241376A (en) * | 2012-02-01 | 2013-08-14 | 北京安翔动力科技有限公司 | Vector power vertical takeoff and landing aircraft and vector power system thereof |
| CN203419259U (en) * | 2013-10-16 | 2014-02-05 | 罗光俊 | Micro tilt-rotor aircraft |
| CN104843178A (en) * | 2015-04-30 | 2015-08-19 | 江苏数字鹰科技发展有限公司 | Flying motorcycle or automobile and flight attitude adjustment method thereof |
| CN105035319A (en) * | 2015-07-27 | 2015-11-11 | 江阴市翔诺电子科技有限公司 | Novel vertical take-off and landing air vehicle and control method thereof |
| CN204979219U (en) * | 2015-08-10 | 2016-01-20 | 红河学院 | Four screws gyroplane that verts |
| CN105564642A (en) * | 2016-03-03 | 2016-05-11 | 辽宁猎鹰航空科技有限公司 | Tilt-rotor UAV (Unmanned Aerial Vehicle) |
| CN106585976A (en) * | 2016-11-30 | 2017-04-26 | 北京航空航天大学 | Aircraft layout of tilt rotors/lift fan during high-speed long endurance |
| CN106926272A (en) * | 2017-02-27 | 2017-07-07 | 哈尔滨工业大学深圳研究生院 | A kind of flying bird robot empennage governor motion |
| CN107097938A (en) * | 2017-03-20 | 2017-08-29 | 长光卫星技术有限公司 | A kind of inclining rotary mechanism for the quadrotor that verts |
| CN107176297A (en) * | 2017-06-20 | 2017-09-19 | 北京迪鸥航空科技有限公司 | A kind of aircraft |
| CN107364572A (en) * | 2017-08-11 | 2017-11-21 | 红河学院 | Fixed-wing vector unmanned plane |
| CN208360498U (en) * | 2018-06-29 | 2019-01-11 | 长沙市云智航科技有限公司 | One kind is verted double-rotor aerobat |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110576964A (en) * | 2019-09-24 | 2019-12-17 | 中国人民解放军战略支援部队航天工程大学 | Rotor wing tilting device for four-axis unmanned aerial vehicle |
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