CN104058089B - Some many oars of twin shaft aircraft - Google Patents
Some many oars of twin shaft aircraft Download PDFInfo
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- CN104058089B CN104058089B CN201410187173.9A CN201410187173A CN104058089B CN 104058089 B CN104058089 B CN 104058089B CN 201410187173 A CN201410187173 A CN 201410187173A CN 104058089 B CN104058089 B CN 104058089B
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- 238000010276 construction Methods 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000033001 locomotion Effects 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 238000010835 comparative analysis Methods 0.000 description 1
- 230000001186 cumulative effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- YGANSGVIUGARFR-UHFFFAOYSA-N dipotassium dioxosilane oxo(oxoalumanyloxy)alumane oxygen(2-) Chemical compound [O--].[K+].[K+].O=[Si]=O.O=[Al]O[Al]=O YGANSGVIUGARFR-UHFFFAOYSA-N 0.000 description 1
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- 238000005516 engineering process Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 229910052627 muscovite Inorganic materials 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
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Abstract
The present invention relates to some many oars of twin shaft aircraft, comprise fixed support, gondola, line shaft, power rotor, power motor, attitude rotor and attitude motor, fixed support is horizontally disposed transverse and longitudinal intersection cross bracket, fixed support lower end is coaxially fixed with gondola, line shaft is coaxially installed in fixed support upper end, the power rotor parallel with fixed support is installed on this line shaft, this power rotor is driven and is rotated by the power motor that is arranged on its underpart, adopt coaxial double-oar structure, the overlapping vertical layout of two oars. The present invention is simple in structure, safe and reliable, save space, be convenient to mobilely, facilitates field work, upper end screw control attitude, the multiple screws in below provide power to do, aerial bearing capacity is large, fully meet take photo by plane, the work requirements such as communication.
Description
Technical field
The invention belongs to unmanned plane field, especially a kind of some many oars of twin shaft aircraft.
Background technology
In field, the world today, the flight control mode of gyroplane has four kinds:
The one, single rotor structure, most of helicopters all adopt this structure in the world;
The 2nd, coaxial double-oar structure, represents that type has Muscovite cassette series model, as card-50, and card-28 etc.;
The 3rd, the two paddle structures of twin shaft, represent that type has the C-47 of the U.S. to prop up slave's dry type helicopter;
The 4th, many rotor structures, mainly adopt in SUAV field. Be characterized in: by adjusting the rotating speed of each rotorRealize the attitude control of aircraft. Mainly contain at grade the types such as four rotors, six rotors, eight rotors, all adoptAutomatically controlled posture adjustment state regulates and controls the direction of motion of aircraft. The present invention also adopts automatically controlled, but is not the differential posture adjustment of adjusting a rotor,But adjust heading by the attitude of adjusting upper axle.
And the aircraft of present patent application to be outside above four kinds of gyroplanes flight control structure system the 5th kind flyRow control mode, is therefore a kind of innovation of the control mode of flying, in current gyroplane field or peerless.
Find other patent documents of following near field through retrieval:
A kind of multi-rotor aerocraft (CN102806993A), this aircraft comprises four main rotor system, two secondary rotorsSystem, body and be arranged on the flight integrated system in body; The initial point of aircraft body axis system is the center of gravity of aircraft, zUpwards, x axle is perpendicular to z axle for axle vertical, directed forward, and y axle is determined by the right-hand rule; Four main rotor system are distributed in respectively machineIn four quadrants of body coordinate system xy plane, each rotation of four main rotor system becomes one with the z axle of body axis systemAngle theta, and projection and the pivot of each rotation in body axis system xoy plane connects to body axis system initial pointThe projection of line in body axis system xoy plane overlaps. The present invention is by regulating four main rotor system and two secondary rotors to beThe rotating speed of system can be realized aircraft movements and attitude and change, and aircraft can be realized VTOL, frontly flies, inverted flight, hovering, rolling etc.Action, stability and control is good.
A kind of small-sized VTOL morphing aircraft (CN202414160U), wing panel, main wing section in the middle of aircraft comprises,Folding wing panel, fold mechanism, vertical fin, power section and recce pack, the vertical fin of aircraft is symmetrical in the upper table of aircraftFace and lower surface, be symmetrically installed with between the middle wing panel and main wing section of aircraft, and the middle wing of aircraft is stretched out in the rear end of vertical finThe afterbody of section; Main wing section is connected by fold mechanism with folding wing panel, fold mechanism comprise one parallel with aircraft axisFolding rotary shaft, fold mechanism is placed in main wing section, and folding wing panel is carried out 180 ° at the uniform velocity folding around folding rotary shaft. The present invention makesBy a kind of brand-new variant mode, can change aspect ratio and aerofoil profile simultaneously, its deformation range is wider and flying quality is more excellentMore, and this variant mechanism is comparatively simple, and engineering realizability is stronger.
Through comparative analysis, there is internal difference in working method and above aircraft in present patent application, here onlyCompare with many gyroplanes, this aircraft has following characteristics:
1, take up room little: multi-rotor aerocraft is plane figure, and rotor takes up room larger more; The present invention is rotorOverlapping layout, not only takes up room little, and compact conformation, is easy to carry.
2, can realize modular mode and promote complete machine usefulness: many rotors can promote load-carrying by increasing rotor quantity, thisInvention can improve load-carrying by the mode that increases rotor quantity equally, just one horizontally disposed, one is arranged vertically.
3,, with the comparison of many gyroplanes, body angle of inclination problem while not there is not posture adjustment, has improved observation thus greatlyPrecision.
Many rotors are adjusting when aspect, must complete machine inclination certain angle, could adjust operation direction, this forStorehouse is hung in the observation that body rigidity connects, the corresponding angle that also must tilt, if in the situation that wind-force is larger, body mustMust adjust frequently attitude and could keep aerial and must stablize, if used as aerial observation platform, the precision of its observation mustSo can be influenced. The present invention, because adopt upper lower shaft to connect by the mode of universal joint articulated, only needs to go up on axle by adjustmentThe inclination angle of rotor is capable of regulating flight attitude, irrelevant with lower shaft, also just with lower shaft below observation to hang storehouse more irrelevant. That is to sayNo matter go up rotor and how to move, lower shaft and observation are hung storehouse all the time in level, and therefore the precision of observation just can not be subject toImpact.
4, be a aircraft of realizing non-structure weight: no matter which kind of aircraft, the design maximum target of pursuit justTo improve flight usefulness by alleviating construction weight. Construction weight of the present invention is very little, and construction weight is for the shadow of flightSound is negligible, and in the situation that power is identical, overall efficiency is all more much higher than other any aircraft.
Summary of the invention
The object of the invention is to overcome the deficiencies in the prior art part, a kind of demonstration simple in structure, convenient, safety are providedReliably, space-saving some many oars of twin shaft aircraft.
The present invention solves its technical problem and takes following technical scheme to realize:
Some many oars of twin shaft aircraft, comprise that fixed support, gondola, line shaft, power rotor, power motor, attitude revolveThe wing and attitude motor, fixed support is horizontally disposed transverse and longitudinal intersection cross bracket, fixed support lower end is coaxially fixed withGondola, line shaft is coaxially installed in fixed support upper end, and the power rotor parallel with fixed support is installed on this line shaft, and this is movingPower rotor is driven and is rotated by the power motor that is arranged on its underpart, it is characterized in that: adopt coaxial double-oar structure, two oar weightsFolded vertical layout; Described coaxial double-oar structure comprise attitude rotor, attitude motor, rotating shaft, stand, expansion link, swinging mounting withAnd attitude axle, the upper end, four summits of described support bracket fastened cross bracket is all by a rotating shaft hinge dress stand, four standsOutside is all provided with an expansion link, these four stand upper ends be jointly provided with one with criss-cross swinging mounting, this swinging mountingThe coaxial Installation posture axle in middle part, installs by the motor-driven attitude rotor of attitude on this attitude axle, and attitude rotor is provided with an appearanceState motor.
And, between described swinging mounting and attitude axle, angle controller is installed.
And coaxial order is installed multiple power rotors on described line shaft, power rotor is all provided with power motor.
And, on described fixed support, be laterally shaped with uniformly at intervals multiple through holes.
Advantage of the present invention and good effect are:
1, this structure will adopt the coaxial up and down multiple rotors of longitudinal one-point type, and the angle of the rotor at top is adjustable, logicalCross the aerial statue of the angle control aircraft that changes top rotor, remove the rotor that flank and other angles are installed from, significantlySave space, stronger for the adaptability of flight space and memory space.
2, the attitude rotor of this structure adopts with power rotor the twin shaft design not being connected, and power rotor shaft is vertical workMake axle and drive power rotor High Rotation Speed to produce pulling force upwards, rise and aerial major impetus of being detained as aircraft,Attitude rotor shaft can need to be carried out angular adjustment according to flight.
3, the power rotor of this structure can longitudinally superpose and install multiplely, and bearing capacity is cumulative, is convenient to calculate, and structure is installedFor simply, and structural reliability is strong.
4, the present invention simple in structure, safe and reliable, save space, be convenient to mobilely, facilitate field work, upper end screw controlAttitude processed, the multiple screws in below provide power to do, aerial bearing capacity is large, fully meet take photo by plane, the work requirements such as communication.
Brief description of the drawings
Fig. 1 is structural representation of the present invention;
Fig. 2 is that Fig. 1 removes anterior support bracket fastened structural representation;
Fig. 3 is the top view of Fig. 1;
Fig. 4 is the structural representation that the present invention increases the quantity of motor and rotor.
Mark in accompanying drawing: 1 attitude rotor; 2 attitude motors; 3 angle controllers; 4 power motors; 5 power rotors; 6 swingSupport; 7 stands; 8 expansion links; 9 rotating shafts; 10 fixed supports; 11 gondolas; 12 line shafts; 13 attitude axles.
Detailed description of the invention
Below in conjunction with accompanying drawing and by specific embodiment, the invention will be further described, and following examples are descriptive, not determinate, can not limit protection scope of the present invention with this.
A kind of some many oars of twin shaft aircraft, comprise fixed support 10, gondola 11, line shaft 12, power rotor 5 and movingForce motor 4, fixed support is that horizontally disposed transverse and longitudinal is intersected cross bracket, on fixed support all lateral separation uniform be shaped with manyIndividual through hole, Stability Analysis of Structures and total quality are light; Fixed support lower end is coaxially fixed with gondola, and this gondola is used for carrying video cameraDeng equipment; Line shaft is coaxially installed in fixed support upper end, and the power rotor parallel with fixed support is installed on this line shaft, shouldPower rotor is driven and is rotated by the power motor that is arranged on its underpart, thereby produces pulling force upwards, will as active forceAircraft is raised to aerial and provides power that aircraft is detained aloft from ground.
Innovative point of the present invention is:
Adopt coaxial double-oar structure, this pair of overlapping vertical layout of oar, but its control system remains by link rod control and revolvesThe attitude of the wing regulates and controls heading. The motor of upper axle is to become hinged with the motor of lower shaft with oar universal drive shaft to be associated in one with oarRise. The more overlapping layout of axle and lower shaft in formation. Therefore say some twin shafts. The regulation and control of flight attitude are to become 90 by upper axle belowTwo steering wheels of degree horizontal arrangement are realized.
The concrete structure of the present embodiment is:
Coaxial double-oar structure comprise attitude rotor 1, attitude motor 2, rotating shaft 9, stand 7, expansion link 8, swinging mounting 6 withAnd attitude axle 13, described power rotor top is hinged with an attitude rotor, and the angle of this attitude rotor can be carried out multidimensional angleRegulate, attitude rotor is provided with an attitude motor, and attitude motor, as the auxiliary motor of electrical machinery of active force, provides auxiliary power, adjustsWhole mooring product attitude aloft, concrete mounting structure is referring to Figure of description, four tops of support bracket fastened cross bracketPoint upper end is all by a rotating shaft hinge dress stand, and four stand outsides are all provided with an expansion link, and pacify jointly these four stand upper endsBe equipped with one with criss-cross swinging mounting, the coaxial Installation posture axle in this swinging mounting middle part, installs by attitude electricity on this attitude axleThe attitude rotor that machine drives. When work, the expansion link of rotation support one side extends, and the expansion link of rotation support opposite side shortens,Stand is around rotating shaft rotation, thereby drives the certain angle of swinging mounting rotation, and attitude rotor is along with rotation support carries out rotation,Thereby provide the propulsive force of different directions to aircraft.
In order to control more accurately the angle of attitude rotor, between described swinging mounting and attitude axle, angle control is installedDevice 3 processed.
Whole aircraft can improve load-carrying by the quantity that increases motor and rotor on lower shaft, can on described line shaftWith coaxial order, multiple power rotors are installed, power rotor lower end is all provided with power motor, every group of power gyroplane power electricMachine can provide the lift of 10kg.
Aircraft is in the past that the rotor of the many oars of twin shaft or multi-rotor aerocraft in one plane launches, and therefore accounts forLarge with spatial area. Although and the overlapping vertical layout of coaxial double-oar of the present invention two oar, its control system remain by connectionThe attitude of bar control rotor regulates and controls heading.
Difference of the present invention is: two oars or many oars are overlapping is arranged vertically, the motor of upper axle and oar are and the motor of lower shaftBecoming hinged with oar with universal drive shaft is linked togather. The more overlapping layout of axle and lower shaft in formation. Therefore say some twin shafts. Flight attitudeRegulation and control be to become two steering wheels of 90 degree horizontal arrangement to realize by upper axle below.
In a word, twin shaft arranged perpendicular, controls flight attitude with the drift angle of axle in transmission mechanism control, to increase rotor numberAmount improves load-carrying, is technical essential of the present invention. Also be innovation and the invention of gyroplane flight control mode.
Claims (4)
1. 1 many oars of twin shaft aircraft, comprises fixed support, gondola, line shaft, power rotor, power motor, attitude rotorAnd attitude motor, fixed support is horizontally disposed transverse and longitudinal intersection cross bracket, fixed support lower end is coaxially fixed with and hangsCabin, line shaft is coaxially installed in fixed support upper end, the power rotor parallel with fixed support is installed, this power on this line shaftRotor is driven and is rotated by the power motor that is arranged on its underpart, it is characterized in that: adopt coaxial double-oar structure, two oars are overlappingVertical layout;
Described coaxial double-oar structure comprises attitude rotor, attitude motor, rotating shaft, stand, expansion link, swinging mounting and attitudeAxle, the upper end, four summits of described support bracket fastened cross bracket is all by a rotating shaft hinge dress stand, and four stand outsides are allOne expansion link is installed, and these four stand upper ends are provided with a criss-cross swinging mounting jointly, and this swinging mounting middle part is coaxialInstallation posture axle, installs by the motor-driven attitude rotor of attitude on this attitude axle, and attitude rotor is provided with an attitude motor.
2. many oars of twin shaft aircraft more according to claim 1, is characterized in that: described swinging mounting and attitude axle itBetween angle controller is installed.
3. many oars of twin shaft aircraft more according to claim 1, is characterized in that: coaxial order peace on described line shaftFill multiple power rotors, power rotor is all provided with power motor.
4. many oars of twin shaft aircraft more according to claim 1, is characterized in that: lateral separation on described fixed supportUniformly be shaped with multiple through holes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410187173.9A CN104058089B (en) | 2014-05-06 | 2014-05-06 | Some many oars of twin shaft aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410187173.9A CN104058089B (en) | 2014-05-06 | 2014-05-06 | Some many oars of twin shaft aircraft |
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| Publication Number | Publication Date |
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| CN104058089A CN104058089A (en) | 2014-09-24 |
| CN104058089B true CN104058089B (en) | 2016-05-25 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107395947A (en) * | 2014-12-10 | 2017-11-24 | 陈国栋 | Suitable for ensureing the outdoor security protection camera of clearly monitored picture |
| CN105109704B (en) * | 2015-09-02 | 2018-06-08 | 南京国业科技有限公司 | A kind of mooring system based on more rotor flying platforms |
| CN106428543B (en) * | 2016-11-11 | 2018-11-13 | 杨超峰 | A kind of rotor control mechanism and DCB Specimen unmanned plane |
| CN108522472A (en) * | 2018-04-08 | 2018-09-14 | 吴李海 | A kind of plant protection multi-rotor unmanned aerial vehicle |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4531692A (en) * | 1982-03-15 | 1985-07-30 | Ernesto Mateus | Helicopter flight control and transmission system |
| US6886777B2 (en) * | 2001-02-14 | 2005-05-03 | Airscooter Corporation | Coaxial helicopter |
| JP4343167B2 (en) * | 2005-11-10 | 2009-10-14 | 株式会社タイヨー | Radio controlled helicopter toy |
| JP2010042792A (en) * | 2008-08-14 | 2010-02-25 | Hirobumi Seki | Multifunctional airplane |
| CN202070153U (en) * | 2011-04-06 | 2011-12-14 | 深圳市艾特航模股份有限公司 | Rotor drive device of coaxial dual-propeller model helicopter |
| CN202506123U (en) * | 2012-03-17 | 2012-10-31 | 广东奥飞动漫文化股份有限公司 | Assembled remote controlled toy helicopter |
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Effective date of registration: 20240607 Address after: 264211 No. 269-2 Kaiyuan East Road, Caomiozi Town, Lingang Economic and Technological Development Zone, Weihai City, Shandong Province (self declared) Patentee after: Weihai Feiteng Aviation Technology Co.,Ltd. Country or region after: China Address before: 300350 No.75 Chongqing Street, changqingke industrial and Trade Park, Jinnan District, Tianjin Patentee before: CHINA-TIMES AEROSPACE TECHNOLOGY Co.,Ltd. Country or region before: China |
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