CN103803064A - Belt-transmission four-rotor-wing aircraft - Google Patents
Belt-transmission four-rotor-wing aircraft Download PDFInfo
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- CN103803064A CN103803064A CN201210462416.6A CN201210462416A CN103803064A CN 103803064 A CN103803064 A CN 103803064A CN 201210462416 A CN201210462416 A CN 201210462416A CN 103803064 A CN103803064 A CN 103803064A
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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 8
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 15
- 230000005540 biological transmission Effects 0.000 abstract description 12
- 230000000712 assembly Effects 0.000 abstract description 2
- 238000000429 assembly Methods 0.000 abstract description 2
- 239000011295 pitch Substances 0.000 abstract 3
- 239000000446 fuel Substances 0.000 abstract 1
- 230000002035 prolonged effect Effects 0.000 abstract 1
- 230000000630 rising effect Effects 0.000 abstract 1
- 230000001133 acceleration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000029058 respiratory gaseous exchange Effects 0.000 description 1
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Abstract
The invention relates to a belt-transmission four-rotor-wing aircraft. The belt-transmission four-rotor-wing aircraft is provided with an engine, a main rack, a power distribution and transmission system and a flight control system, wherein a plurality of brackets are outwards extended from the power distribution and transmission system and are uniformly spaced to form cross shapes and the like, and rotor wing assemblies with changeable propeller pitches are arranged at the front ends of the brackets and comprise rotor wing rotation driving components and rotor wing propeller pitch changing components. According to the belt-transmission four-rotor-wing aircraft, four shafts and four rotor wings are driven by the engine, and the size of rising power of all the shafts is changed through changing the propeller pitches of all the rotor wings, so as to realize the change of the flight attitude of the aircraft; the fuel-driven engine is adopted, so that the effective payload is increased, and the flight time is prolonged, thus the gear-transmission four-rotor-wing aircraft is particularly applicable to long-time and long-distance operation.
Description
Technical field
The invention belongs to aeronautical product technical field, relate to a kind of multiaxis multi-rotor aerocraft.
Background technology
Multiaxis multi-rotor aerocraft operates on it control by wireless remote control system and independent flight control system, to realize the landing of aircraft, flight all around, acceleration and deceleration and direction control etc.Manipulative capability, stability, effective mission payload and cruise duration are the important indicators of investigating multiaxis multi-rotor aerocraft, and under identical manipulative capability and stability condition, user pursues larger effective mission payload and long-time duration flight ability.
Thereby traditional multiaxis multi-rotor aerocraft is installed respectively electrical motor to drive screw propeller to reach the object of flight on the S. A. of screw propeller place, thereby by changing lift size that the rotating speed of electrical motor changes each axle to control flight attitude.There is following shortcoming in this frame mode, it is the state of kinematic motion that each screw propeller of multiaxis multi-rotor aerocraft needs to expend much electricity and go to control aircraft, want long-time effectively continuation of the journey just to require storage battery can store abundant electric energy, this has increased own wt and the manufacturing cost of aircraft, simultaneously because service lifetime of accumulator is limited, the electric energy of storage is also limited, thereby is difficult to meet the requirement of long-time continuation of the journey.
Summary of the invention
The object of the invention is to overcome deficiency of the prior art, the quadrotor of the Novel waistband transmission that high, the effective mission payload of a kind of manipulative capability and stability is large, flying power is strong is provided.
To achieve these goals, the present invention realizes by following technical scheme:
A kind of bel-drivenn quadrotor, comprise flight control system, engine, mainframe, power distribution driving system, by outward extending four supports of mainframe, be positioned at the rotor assembly 1 of each support front end, its special character is that described flight control system comprises four Servo-controllers; Described power distribution driving system comprises the input shaft gear 3 being driven by engine, 2 output gears and 2 the reverse output gear groups that are driven and be uniform staggered with around input shaft circumference by input shaft gear; Described reverse output gear group comprises track adjusting wheel 2 and output gear and track adjusting wheel and the input shaft gear engagement of coaxial setting; Described each output gear drives the work of corresponding rotor assembly; The belt-driving that described output gear consists of belt pulley 10 and belt 12 drives the work of rotor assembly.
Above-mentioned rotor assembly comprise the rotor that is output gear drive rotate input shaft 9, be enclosed within rotor rotate sculler arm 8 on input shaft 9 and pushing disk 7, be fixed on that rotor mounting clamp pedestal 5, symmetry that rotor rotates input shaft 9 upper ends are arranged on rotor mounting clamp pedestal and along two rotor mounting clamps 4 of rotor mounting clamp pedestal place axis rotation, be fixed on the rotor on rotor mounting clamp 4; Described pushing disk 7 is arranged between sculler arm 8 and rotor mounting clamp 4 and overhanging two symmetrical hangers, on described each rotor mounting clamp 4, is provided with overhanging lug, between described lug and corresponding hanger, is hinged with connecting rod 6; Between described sculler arm 8 and Servo-controller, be hinged with L-type Control arm, the middle flex point of L-type Control arm is arranged on rotor assembly pedestal.
Beneficial effect of the present invention is:
Drive four rotors of four axles with an engine, thereby change each axle lift size to realize the change of aircraft flight attitude by changing the pitch of each rotor, reduced aircraft own wt and energy loss; Adopt the moving engine of oil to drive four rotors of four axles can increase effective mission payload, extend the flight time, be particularly useful for long-time and remote job.In addition, the present invention adopts belt 1 transmission that belt pulley 10 and belt 12 form to drive the work of rotor assembly, can prevent that external interference is passed to engine by rotor, guarantees the normal work of the moving engine of oil.
Accompanying drawing explanation
Fig. 1 is a kind of bel-drivenn quadrotor of the present invention drive system structure figure.
Fig. 2 is that bel-drivenn quadrotor of the present invention is from transmission component and rotor assembly structure chart.
The specific embodiment
Be illustrated in figure 1 a kind of bel-drivenn quadrotor of the present invention drive system structure figure, mainly formed by rotor assembly 1, track adjusting wheel 2, input shaft gear 3.Input shaft gear 3 belongs to parts in power distribution driving system, this gear directly driven by the moving engine of oil or by the gear that is arranged on the moving engine output shaft of oil by with input shaft gear 3 engaged transmission.
Power distribution driving system four supports that stretch out, the even interval of above-mentioned support composition is cross etc., and each support front end is equipped with the rotor assembly 1 that can change rotor pitch simultaneously.
In this structure, power distribution driving system is criss-cross by the outward extending support of input shaft gear 3, wherein there are two symmetrical rotor assemblies by band transmission by driven gear directly and input shaft gear 3 engaged transmission, two other symmetrical rotor assembly is engaged with track adjusting wheel 2 by driven gear by band transmission, lead via track adjusting wheel 2, track adjusting wheel 2 engages with input shaft gear 3 object that reaches transmission again; The hand of rotation of the rotor assembly after guiding is contrary with the hand of rotation of the rotor assembly not leading, and its objective is that eliminating himself in order to interact rotates the reactive torque power producing, and avoids aircraft spin orientation to fly.
Further, be illustrated in figure 2 bel-drivenn quadrotor of the present invention from transmission component and rotor assembly structure chart, the belt-driving that can be formed by belt pulley 10, cog belt 12 from transmission component.Rotor assembly rotates input shaft 9 and L-type Control arm 11 etc. by rotor mounting clamp 4, rotor mounting clamp pedestal 5, connecting rod 6, pushing disk 7, rotor assembly pedestal, sculler arm 8, rotor and forms.On each rotor mounting clamp pedestal 5, two rotor mounting clamps 4 are all installed, and these two rotor mounting clamps 4 are symmetrical installation along rotor mounting clamp pedestal 5 cross sections, place, center, rotor mounting clamp 4 can be along the 5 place axis rotations of rotor mounting clamp pedestal, a lug is stretched out in rotor mounting clamp 4 bottoms, lug is provided with a cylindrical boss, this cylindrical boss coordinates with the corresponding and circular hole of connecting rod 6 one end, and connecting rod 6 other end circular holes stretch out the respective cylindrical boss arranging on hanger on one side with pushing disk 7 and coordinate; The axis that pushing disk 7 can rotate input shaft 9 along rotor moves up and down, also can rotate input shaft 9 axis along rotor rotates, the pushing disk 7 each symmetries in both sides are stretched out hanger, on two hangers, are equipped with cylindrical boss, and cylindrical boss can coordinate with the corresponding circle hole on pushing disk 7 formation revolute pair; Sculler arm 8 is firmly rabbeted by its inner breathing ring structure with pushing disk 7, and be enclosed within on rotor rotation input shaft 9, thereby can along rotor rotate input shaft 9 move up and down drive pushing disk 7 move up and down, the protruding cylindrical boss of sculler arm 8, the hole mix proportion revolute of this cylindrical boss and L-type Control arm 11 ends, L-type Control arm 11 other ends are connected with sculler arm 8, the other end is connected with described Servo-controller, intermediate point is arranged on rotor assembly pedestal, can rotate around the anchor shaft at intermediate point place; Handle Servo-controller and pull Control arm 11, Control arm 11 rotates around the anchor shaft at intermediate point place, pull sculler arm 8 to move downward, thereby drive pushing disk 7 to move up and down, pushing disk 7 pulls two rotor mounting clamps 4 to rotate by connecting rod 6, drive screw propeller to rotate around rotor mounting clamp pedestal 5 center shafts, thereby change pitch, reach the object that changes screw propeller lift size.
Servo-controller is arranged on mainframe, is electrically connected with flight-control computer, and the given impulse singla of flight-control computer drives steering wheel motion, accomplishes that machinery combines with electric, reaches and controls aircraft object.
The moving engine speed speed of oil is changed by steering wheel control throttle.
Claims (2)
1. a bel-drivenn quadrotor, comprise flight control system, engine, mainframe, power distribution driving system, by outward extending four supports of mainframe, be positioned at the rotor assembly (1) of each support front end, it is characterized in that: described flight control system comprises four Servo-controllers; Described power distribution driving system comprises the input shaft gear (3) that driven by engine, two output gears that driven and be uniform staggered with around input shaft circumference by input shaft gear and two each and every one reverse output gear groups; Described reverse output gear group comprises track adjusting wheel (2) and output gear and track adjusting wheel and the input shaft gear engagement of coaxial setting; Described each output gear drives the work of corresponding rotor assembly; Described output gear drives the work of rotor assembly by belt pulley (10) and the belt-driving of belt (12) composition.
2. bel-drivenn quadrotor according to claim 1, is characterized in that: described rotor assembly comprise the rotor that is output gear drive rotate input shaft (9), be enclosed within rotor rotate sculler arm (8) on input shaft (9) and pushing disk (7), be fixed on that rotor mounting clamp pedestal (5), symmetry that rotor rotates input shaft (9) upper end are arranged on rotor mounting clamp pedestal and along two rotor mounting clamps (4) of rotor mounting clamp pedestal place axis rotation, be fixed on the rotor on rotor mounting clamp (4); Described pushing disk (7) is arranged between sculler arm (8) and rotor mounting clamp (4) and overhanging two symmetrical hangers, on described each rotor mounting clamp (4), is provided with overhanging lug, between described lug and corresponding hanger, is hinged with connecting rod (6); Between described sculler arm (8) and Servo-controller, be hinged with L-type Control arm, the middle flex point of L-type Control arm is arranged on rotor assembly pedestal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210462416.6A CN103803064A (en) | 2012-11-15 | 2012-11-15 | Belt-transmission four-rotor-wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210462416.6A CN103803064A (en) | 2012-11-15 | 2012-11-15 | Belt-transmission four-rotor-wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103803064A true CN103803064A (en) | 2014-05-21 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210462416.6A Withdrawn CN103803064A (en) | 2012-11-15 | 2012-11-15 | Belt-transmission four-rotor-wing aircraft |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104176248A (en) * | 2014-07-16 | 2014-12-03 | 沈阳航空航天大学 | Unmanned aerial vehicle with double engines, four shafts and four rotors |
| CN104210655A (en) * | 2014-09-03 | 2014-12-17 | 西北农林科技大学 | Double-rotor-wing unmanned plane |
| WO2015117509A1 (en) * | 2014-02-08 | 2015-08-13 | 杨华东 | Variable-pitch flight unit |
| CN104859838A (en) * | 2015-06-03 | 2015-08-26 | 中恒天信（天津）航空科技有限公司 | Oil-driving multi-rotor unmanned flying platform |
| CN104973241A (en) * | 2015-07-08 | 2015-10-14 | 芜湖万户航空航天科技有限公司 | Unmanned aerial vehicle with main and auxiliary multi-rotor structure |
| CN105015768A (en) * | 2015-08-26 | 2015-11-04 | 许博男 | Multi-rotor aircraft |
| CN105270619A (en) * | 2015-10-27 | 2016-01-27 | 中航维拓（北京）科技有限责任公司 | Oil-drive variable-pitch quad-rotor unmanned aerial vehicle |
| CN106143899A (en) * | 2016-06-29 | 2016-11-23 | 上海未来伙伴机器人有限公司 | Displacement rotor and include multi-rotor aerocraft and the flying method thereof of this displacement rotor |
| WO2017031945A1 (en) * | 2015-08-21 | 2017-03-02 | 河南三和航空工业有限公司 | Multi-shaft manned aircraft |
| CN106986009A (en) * | 2017-03-08 | 2017-07-28 | 贾杰 | Redundance dynamical system super large loads many rotor flying platforms |
| WO2017165039A3 (en) * | 2016-02-20 | 2017-12-21 | GeoScout, Inc. | Rotary-wing vehicle and system |
| CN109484629A (en) * | 2018-09-13 | 2019-03-19 | 嘉兴职业技术学院 | A kind of feather quadrotor |
| CN113002766A (en) * | 2021-03-29 | 2021-06-22 | 北京航空航天大学 | Variable-pitch multi-rotor unmanned aerial vehicle with noise reduction function by adopting scissor type blades |
| CN115071960A (en) * | 2022-06-10 | 2022-09-20 | 四川大学 | Coaxial aircraft with variable propeller pitch |
| JP7558592B2 (en) | 2020-09-17 | 2024-10-01 | 株式会社石川エナジーリサーチ | Flying device |
-
2012
- 2012-11-15 CN CN201210462416.6A patent/CN103803064A/en not_active Withdrawn
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015117509A1 (en) * | 2014-02-08 | 2015-08-13 | 杨华东 | Variable-pitch flight unit |
| CN104176248B (en) * | 2014-07-16 | 2016-05-25 | 沈阳航空航天大学 | Twin-engined four axle four rotor wing unmanned aerial vehicles |
| CN104176248A (en) * | 2014-07-16 | 2014-12-03 | 沈阳航空航天大学 | Unmanned aerial vehicle with double engines, four shafts and four rotors |
| CN104210655A (en) * | 2014-09-03 | 2014-12-17 | 西北农林科技大学 | Double-rotor-wing unmanned plane |
| CN104859838A (en) * | 2015-06-03 | 2015-08-26 | 中恒天信（天津）航空科技有限公司 | Oil-driving multi-rotor unmanned flying platform |
| CN104973241A (en) * | 2015-07-08 | 2015-10-14 | 芜湖万户航空航天科技有限公司 | Unmanned aerial vehicle with main and auxiliary multi-rotor structure |
| WO2017031945A1 (en) * | 2015-08-21 | 2017-03-02 | 河南三和航空工业有限公司 | Multi-shaft manned aircraft |
| CN105015768A (en) * | 2015-08-26 | 2015-11-04 | 许博男 | Multi-rotor aircraft |
| CN105270619A (en) * | 2015-10-27 | 2016-01-27 | 中航维拓（北京）科技有限责任公司 | Oil-drive variable-pitch quad-rotor unmanned aerial vehicle |
| WO2017165039A3 (en) * | 2016-02-20 | 2017-12-21 | GeoScout, Inc. | Rotary-wing vehicle and system |
| CN106143899A (en) * | 2016-06-29 | 2016-11-23 | 上海未来伙伴机器人有限公司 | Displacement rotor and include multi-rotor aerocraft and the flying method thereof of this displacement rotor |
| CN106143899B (en) * | 2016-06-29 | 2018-10-23 | 上海未来伙伴机器人有限公司 | Displacement rotor and the multi-rotor aerocraft including the displacement rotor and its flying method |
| CN106986009A (en) * | 2017-03-08 | 2017-07-28 | 贾杰 | Redundance dynamical system super large loads many rotor flying platforms |
| CN109484629A (en) * | 2018-09-13 | 2019-03-19 | 嘉兴职业技术学院 | A kind of feather quadrotor |
| JP7558592B2 (en) | 2020-09-17 | 2024-10-01 | 株式会社石川エナジーリサーチ | Flying device |
| CN113002766A (en) * | 2021-03-29 | 2021-06-22 | 北京航空航天大学 | Variable-pitch multi-rotor unmanned aerial vehicle with noise reduction function by adopting scissor type blades |
| CN113002766B (en) * | 2021-03-29 | 2022-05-10 | 北京航空航天大学 | Variable-pitch multi-rotor unmanned aerial vehicle with noise reduction function by adopting scissor type blades |
| CN115071960A (en) * | 2022-06-10 | 2022-09-20 | 四川大学 | Coaxial aircraft with variable propeller pitch |
| CN115071960B (en) * | 2022-06-10 | 2023-07-18 | 四川大学 | A pitch-variable coaxial aircraft |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C04 | Withdrawal of patent application after publication (patent law 2001) | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20140521 |