CN104859853A - Six-rotor hybrid aircraft - Google Patents
Six-rotor hybrid aircraft Download PDFInfo
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- CN104859853A CN104859853A CN201510291240.6A CN201510291240A CN104859853A CN 104859853 A CN104859853 A CN 104859853A CN 201510291240 A CN201510291240 A CN 201510291240A CN 104859853 A CN104859853 A CN 104859853A
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Abstract
The invention discloses a six-rotor hybrid aircraft. The six-rotor hybrid aircraft comprises a fuselage main body (1), and a rotor assembly (2), wherein airborne equipment is arranged in the fuselage main body (1), and the rotor assembly (2) consists of fixed rotor assemblies and a bending moment rotor assembly. The hybrid aircraft is characterized in that four fixed rotors are respectively arranged at the front part and the rear part of a fuselage, two bending moment rotors are arranged in the middle, engines (5) are directly connected with the bending moment rotors, and the engines (5) drive coaxial generators (8) to generate electricity; the generated electricity can be stored in a lithium battery (7), the lithium battery (7) outputs electric energy to provide energy sources for the working of brushless motors (15) of the fixed rotors , so that the fixed rotors and the bending moment rotors work at the same time. The hybrid aircraft disclosed by the invention effectively solves many problems of a conventional pure electric-driven or pure oil-driven multi-rotor aircraft, greatly prolongs the hang time of the multi-rotor aircraft, greatly increases payloads, and improves operating and controlling performance during flight, so that such aircraft is wider in application scope during production and life.
Description
Technical field
The present invention relates to a kind of six rotor fuel-electric hybrid aircrafts, particularly a kind of oil electricity mixing Parallel opertation power and electric power, its medium power provides the main lift of aircraft and generator power, and electric power provides the rotor craft of time lift and held stationary flight.
Background technology
Existing rotor craft is all control the rotating speed of multiple rotor by flight controller or realize the having a smooth flight property of aircraft by changing Propeller variable pitch, and these two kinds of aircraft all use as brushless motor, electricity adjust device, lithium cell and flight controller parts etc. to achieve flare maneuver.
The existing pure electric aircraft flight time is generally at about 20 minutes, mission payload is too small again, in military affairs, scientific research, industry, agricultural plant protection, land mapping, patrol in ocean, rescue and relief work, the actual value of service that power-line patrolling stringing and police patrol such as to arrest at the field is not high, and these fields are that requirement is high to the cruise duration of unmanned vehicle and these two technical indexs the most basic of capacity weight, and the application major part of existing unmanned vehicle also rests on low-end market, as ship model toy, the use of the toys properties such as individual takes photo by plane is more, and in this field, the cruise duration of existing multi-rotor aerocraft and capacity weight also only can meet the most basic user demand, also only toy can be referred to as at most.Use pure electric energy to supply the energy needed for aircraft, its lithium battery energy storage battery is little, then cause the flight time short; Need cruise duration long, just need high capacity cell, then cause again battery weight excessive, cause bare weight excessive, take the problems such as actual capacity weight.
Certainly for these two actual use in short-leg, also having relative terms of settlement, as adopted full fuel power or oil electric mixed dynamic, improving cruise duration and the load of aircraft, but adopt these two kinds of dynamic methods to be also have its drawback and circumscribed.The aircraft everything of simple employing fuel power all must provide power by fuel engines, particularly in order to keep flight stability by flying to control the blade fine setting or adjustment of rotational speed that the instruction that sends carries out, considerable fuel load will be expended, the noise simultaneously brought is large, vibration is large, is all the unfavorable factor affecting aircraft; Adopt the aircraft of oil electric mixed dynamic, the aircraft of existing so-called oil electricity mixing, although be that fuel oil kinetic energy and electric energy have been arranged on aircraft on the surface simultaneously, but be entirely almost the mode of operation of full oil or full electricity, namely fuel engines work provides energy, and storage battery does not participate in energy supply, or exports energy by storage battery completely, and fuel engines does not work and do not export energy, it is the still single energy-provision way separated in essence.
Summary of the invention
The object of the invention is to provide a kind of six rotorcraft for overcoming the deficiencies in the prior art, particularly a kind of oil electricity mixing Parallel opertation power and electric power, the power that wherein driving engine exports drives the rotation of two bending moment rotors to provide aircraft main lift, drive integral shaft generator generating simultaneously, to lithium cell charging, and the brushless motor work being all the other four fixing rotors by lithium cell output electric energy provides the energy, these four fixing rotors and two bending moment rotors are worked simultaneously, keep the steady of flight, and the adjustment to flight attitude.
According to one six rotor fuel-electric hybrid aircraft that the present invention proposes, comprise fuselage main body (1), rotor assemblies (2), it is characterized in that, comprise brushless electricity in fuselage main body (1) and adjust device (3), flight controller (4), driving engine (5), power-transfer clutch (6), lithium cell (7), integral shaft generator (8), voltage stabilizer (9), GPS module (10), charger (11), fuel tank (12), synchronous pulley (13) and Timing Belt (14), described rotor assemblies (2) is made up of fixing rotor assemblies and bending moment rotor assemblies, comprise brushless motor (15), fixing screw blade (16), bending moment screw blade (17), digital rudder controller (18), bending moment screw blade assembly (19), hold-down arm one (20) and hold-down arm two (21).
Described hold-down arm one (20) one end and fuselage main body (1) are for being rigidly connected, the other end overlaps fixing rotor assemblies respectively and is connected to form the fixing rotor of forebody and four, rear portion with four, hold-down arm two (21) one end adopts elastic damping structure to be connected with fuselage main body (1), and the other end overlaps bending moment rotor assemblies respectively and is connected to form waist two bending moment rotors with two.
Described driving engine (5), power-transfer clutch (6), integral shaft generator (8) and synchronous pulley (12) composition driving engine parallel power electric power exports assembly, be connected by synchronous pulley (13) and Timing Belt (14) and waist two bending moment rotors, and drive the bending moment screw blade (17) of these two bending moment rotors to rotate, produce main lift.
Described driving engine (5) is except directly exporting power and drive two bending moment rotor wing rotations, the power that driving engine (5) exports simultaneously drives integral shaft generator (8) generating, generate electricity and can export and be stored in lithium cell (7) after voltage stabilizer (9) process, lithium cell (7) output electric energy is that brushless motor (15) work of all the other four fixing rotors provides the energy, and these four fixing rotors and two bending moment rotors are worked simultaneously.
Principle of work of the present invention is, the power produced after fuel engines runs not only can directly drive two bending moment rotor wing rotations to produce the required main lift of flight, the energy that fuel engines exports after running simultaneously can also drive integral shaft generator to generate electricity simultaneously, electrical generator generates electricity and can directly can be stored in carry-on lithium cell after voltage stabilizing process, export electric energy to the brushless motor of four fixing rotors by lithium cell again, four fixing rotors and two bending moment rotors are worked simultaneously.
The present invention compared with prior art remarkable advantage is: described driving engine (5) is connected by synchronous pulley (13) and Timing Belt (14) and waist two bending moment rotors, and drive the bending moment screw blade (17) of these two bending moment rotors to rotate, power is directly provided to produce lift by driving engine, increase lift, improve capacity weight and maneuverability.
Described driving engine (5) is except directly exporting power and drive two bending moment rotor wing rotations, drive integral shaft generator (8) to generate electricity simultaneously, generate electricity and can be stored in lithium cell (7), lithium cell (7) output electric energy is that brushless motor (15) work of all the other four fixing rotors provides the energy, these four fixing rotors and two bending moment rotors are worked simultaneously and improves flight stability, add cruise duration.
Described hold-down arm two (21) one end and fuselage main body (1) adopt elastic damping connection mode, absorb vibrations when driving engine (5) runs, the vibrations produced are avoided to pass to aircraft body, cause integrally-built flutter, not only increase the flight stability of aircraft, Simultaneous Stabilization increase is also beneficial to the operation of airborne equipment.As the shooting environmental of Airborne Camera greatly can be improved, improve the image quality of shooting gained video image and photo.
Two described bending moment rotors are positioned at both sides, fuselage main body (1) middle part, and left and right is put relatively, and screw propeller hand of rotation is relative, solve the torque torsion that monomotor produces, achieve torsion balance, improve the stability of flight, be convenient to the work of airborne equipment.
Described forebody and rear portion are four fixing rotors, and waist is two bending moment rotors, makes aircraft fuselage structures reasonable in design, good looking appearance, and fuselage spatial accommodation is large.
Two described bending moment rotors are connected with Timing Belt (14) by the synchronous pulley (13) on driving engine (5), and drive this two bending moment rotor wing rotations, rotor lift size changes rotor head total distance size by flight controller (4) control figure steering wheel (18) and realizes, solve the uncontrollable problem of existing cyclogyro lift, improve flight handling and safety.
Two in four described fixing rotors are positioned at aircraft front portion, two fixing rotors are positioned at aircraft rear portion, lay respectively at fuselage main body (1) both sides, left and right is put relatively, four fixing rotors, by lithium cell (7) directly energy supply, control its stability maintenance completing flight course and maneuvering flight action by flight controller (4).
Described lithium cell (7) and fuel tank (12) lay respectively at fuselage main body (1) front portion or rear portion, reducing the possibility that electric leakage causes pilot fuel, improve flight reliability and safety.
Described driving engine (5) is positioned at fuselage main body (1) middle part, center of gravity is positioned at aircraft middle part, makes flight more steady.
Described driving engine (5) remains constant revolution in flight course, is beneficial to steadily drive electrical generators generating for a long time, also just adds the cruise duration of aircraft.
Described another kind of alternative structure, two described bending moment screw blade assemblies (19) install a driving engine (5) respectively, driving engine (5) is connected with bending moment screw blade assembly (19), direct drive bending moment screw blade (17) rotates, substantially increase the lift of aircraft, also just significantly increase the mission payload of aircraft simultaneously, make its Applicable scope wider.
The described respective integral shaft generator (8) in parallel of driving engine (5) laid respectively on two bending moment screw blade assemblies (19) drives it to generate electricity, for lithium cell charging in the middle of fuselage, two bending moment rotor wing rotation directions that two driving engines (5) directly drive are contrary, considerably increase electric energy generated in flight course, be not only needed for aircraft flight itself and provide more multiple-energy-source, also for the airborne plug-in device added is as camera, radar and radio etc. provide the sufficient energy, improve the task variety of aircraft, aircraft can be made more to maximize and intellectuality, it is made to apply more extensive, two bending moment rotor wing rotation directions that two driving engines (5) directly drive are contrary, serve the effect counteracted apart from turning power equally, provide larger lift, add stability and the capacity weight of flight.
Accompanying drawing explanation
The integral structure schematic diagram of Fig. 1, a kind of six rotor fuel-electric hybrid aircrafts.
Fig. 2, driving engine schematic diagram.
Fig. 3, oily electric Parallel opertation schematic diagram.
Fig. 4, bending moment rotor assembly schematic diagram.
The twin-engined schematic diagram of Fig. 5, alternative structure.
reference numerals list
1, fuselage main body 2, rotor assemblies 3, brushless electricity adjusts device 4, flight controller 5, driving engine 6, power-transfer clutch 7, lithium cell 8, integral shaft generator 9, voltage stabilizer 10, GPS module 11, charger 12, fuel tank 13, synchronous pulley 14, Timing Belt 15, brushless motor 16, fixing screw blade 17, bending moment screw blade 18, digital rudder controller 19, bending moment screw blade assembly 20, hold-down arm 1, hold-down arm two.
Detailed description of the invention
Below by embodiment, and by reference to the accompanying drawings, technical scheme of the present invention is described in further detail.
The object of invention is for rotor craft provides a kind of technical scheme, the power that driving engine of the present invention exports is except the rotation of drive two bending moment rotors, drive integral shaft generator generating simultaneously, generate electricity and can export after voltage stabilizer process and be stored in lithium cell, export by lithium cell the brushless motor work that electric energy is all the other four fixing rotors and the energy is provided, these four fixing rotors and two bending moment rotors are worked simultaneously.
Fig. 1, Fig. 2, Fig. 3, a kind of six rotor fuel-electric hybrid aircrafts shown in Fig. 4 and Fig. 5, its structure comprises fuselage main body (1), rotor assemblies (2), brushless electricity adjusts device (3), flight controller (4), driving engine (5), power-transfer clutch (6), lithium cell (7), integral shaft generator (8), voltage stabilizer (9), GPS module (10), charger (11), fuel tank (12), synchronous pulley (13), Timing Belt (14), rotor assemblies (2), brushless motor (15), fixing screw blade (16), bending moment screw blade (17), digital rudder controller (18), bending moment screw blade assembly (19), hold-down arm one (20) and hold-down arm two (21).
Shown in Fig. 1, comprise brushless electricity in wherein said fuselage main body (1) and adjust device (3), flight controller (4), driving engine (5), lithium cell (7), integral shaft generator (8), voltage stabilizer (9), GPS module (10), charger (11), fuel tank (12), wherein flight controller (4) is by control chip, three-axis gyroscope, sensor, accelerometer and weather gauge composition, lithium cell (7) and fuel tank (12) are arranged on front portion or the rear portion of fuselage main body (1) respectively, each parts are fixed on fuselage main body (1) interior relevant position, be connected by wire between parts.
Shown in Fig. 2, described driving engine (5) comprises power-transfer clutch (6), integral shaft generator (8), synchronous pulley (13) and Timing Belt (14), described driving engine (5) is synchronous pulley (13), integral shaft generator (8), power-transfer clutch (6) and driving engine (5) from top to bottom successively, Timing Belt (14) one end is connected with synchronous pulley (13), and the gear in other end bending moment rotor assembly is connected.
Shown in Fig. 1, Fig. 3 and Fig. 4, described Rotary-Wing Department divides and comprises brushless motor (15), fixing screw blade (16), bending moment screw blade (17), digital rudder controller (18), bending moment screw blade assembly (19) and hold-down arm (20), wherein form the fixing rotor of forebody and four, rear portion by brushless motor (15), fixing screw blade (16), fix and be connected by hold-down arm one (20) between rotor with fuselage main body (1), hold-down arm one (20) and fuselage are rigid connection structure; Waist two bending moment rotors are formed by bending moment screw blade (17), digital rudder controller (18), bending moment screw blade assembly (19), be connected by hold-down arm two (21) between displacement rotor with fuselage main body (1), hold-down arm two (21) and fuselage are elastic damping connection structure.
Figure 5 shows that a kind of replacement scheme structure, described driving engine (5) is positioned on two bending moment rotors, and two driving engines integral shaft generator (8) in parallel respectively.
Preferred as one, described driving engine (5) is except directly driving two bending moment rotor wing rotations, drive integral shaft generator (8) to generate electricity simultaneously, generate electricity and can export and be stored in lithium cell (7), lithium cell (7) exports electric energy to the brushless motor (15) of four fixing rotors, these four fixing rotors and two bending moment rotors are worked simultaneously, awing driving engine (5) remains constant revolution, integral shaft generator (8) is driven to provide steady current to be lithium cell (7) charging, solve the problem of battery power deficiency, add cruise duration and the capacity weight of aircraft.
Described hold-down arm two (21) adopts elastic damping connection mode with fuselage main body (1), significantly reduce the vibrations produced when driving engine (5) runs, not only increase the flight stability of aircraft, Simultaneous Stabilization increase is also beneficial to the operation of airborne equipment, greatly can improve the shooting environmental of Airborne Camera, improve image quality.
Preferred as one, two described bending moment rotors are positioned at both sides, fuselage main body (1) middle part, left and right is put relatively, screw propeller hand of rotation is relative, main lift needed for aircraft is directly provided by driving engine (5), counteracting apart from turning power, providing larger lift, adding stability and the capacity weight of flight.
Preferred as one, described driving engine parallel power electric power exports assembly, the bending moment screw blade (17) of two bending moment rotors is directly driven to rotate by synchronous pulley (13) and Timing Belt (14), produce main lift, lift size changes rotor head total distance size by flight controller (4) control figure steering wheel (18) and realizes, substantially increase lift size, also solve the uncontrollable problem of opening force size simultaneously.
Preferred as one, two in four described fixing rotors are positioned at aircraft front portion, two fixing rotors are positioned at aircraft rear portion, lay respectively at fuselage main body (1) both sides, left and right is put relatively, and these four fixing rotors, by the direct energy supply of battery, improve the stability of flight course, decrease the loss of main lift, add aircraft cruise duration.
Preferred as one, described lithium cell (7) and fuel tank (12) lay respectively at the anterior or rear portion of fuselage main body (1) and to be separated by layout, reduce the possibility that electric leakage causes pilot fuel, improve flight reliability and safety.
Preferred as one, described driving engine (5) is positioned at fuselage main body (1) middle part, the center of gravity of aircraft is made to be positioned at the centre of Flight Vehicle Structure, be beneficial to the flight stability of aircraft, reduce fixing screw propeller adjusting frequency to flight attitude, also just save the fuel oil consumption of driving engine, add the cruise duration of aircraft.
Preferred as one, described driving engine (5) remains constant revolution in flight course, is beneficial to steadily drive electrical generators generating for a long time, also just adds the cruise duration of aircraft.
Preferred as one, described another kind of alternative structure, two bending moment screw blade assemblies (19) are installed respectively a driving engine (5), driving engine (5) is connected with bending moment screw blade assembly (19), direct drive bending moment screw blade (17) rotates, substantially increase the lift of aircraft, also just significantly increase the mission payload of aircraft simultaneously, make its Applicable scope wider.
Preferred as one, the described respective integral shaft generator (8) in parallel of driving engine (5) laid respectively on two bending moment screw blade assemblies (19) drives it to generate electricity, it is lithium cell charging in the middle of fuselage simultaneously, considerably increase electric energy generated in flight course, be not only needed for aircraft flight itself and provide more multiple-energy-source, also for the airborne plug-in device added is as camera, radar and radio etc. provide the sufficient energy, improve the task variety of aircraft, aircraft can be made more to maximize and intellectuality, it is made to apply more extensive, two bending moment rotor wing rotation directions that two driving engines (5) directly drive are contrary, serve the effect counteracted apart from turning power equally, provide larger lift, add stability and the capacity weight of flight.
Preferred as one, described battery can dismounting and change, also charges by usb data mouth.
Preferred as one, the fixing screw blade hand of rotation of described same column is identical, and selects with the screw blade arranged that to fill direction relative.
Claims (9)
1. a rotor fuel-electric hybrid aircraft, comprise fuselage main body (1), rotor assemblies (2), it is characterized in that, comprise brushless electricity in fuselage main body (1) and adjust device (3), flight controller (4), driving engine (5), power-transfer clutch (6), lithium cell (7), integral shaft generator (8), voltage stabilizer (9), GPS module (10), charger (11), fuel tank (12), synchronous pulley (13) and Timing Belt (14), described rotor assemblies (2) is made up of fixing rotor assemblies and bending moment rotor assemblies, comprise brushless motor (15), fixing screw blade (16), bending moment screw blade (17), digital rudder controller (18), bending moment screw blade assembly (19), hold-down arm one (20) and hold-down arm two (21), described hold-down arm one (20) one end and fuselage main body (1) are for being rigidly connected, the other end overlaps fixing rotor assemblies respectively and is connected to form the fixing rotor of forebody and four, rear portion with four, hold-down arm two (21) one end adopts elastic damping structure to be connected with fuselage main body (1), and the other end overlaps bending moment rotor assemblies respectively and is connected to form waist two bending moment rotors with two, described driving engine (5), power-transfer clutch (6), integral shaft generator (8) and synchronous pulley (12) composition driving engine parallel power electric power export assembly, be connected by synchronous pulley (13) and Timing Belt (14) and waist two bending moment rotors, and drive the bending moment screw blade (17) of these two bending moment rotors to rotate, produce driving engine (5) described in main lift except directly being exported by power and drive two bending moment rotor wing rotations, the power that driving engine (5) exports simultaneously drives integral shaft generator (8) generating, generate electricity and can export and be stored in lithium cell (7) after voltage stabilizer (9) process, lithium cell (7) output electric energy is that brushless motor (15) work of all the other four fixing rotors provides the energy, these four fixing rotors and two bending moment rotors are worked simultaneously.
2. a kind of six rotor fuel-electric hybrid aircrafts according to claim 1, it is characterized in that: two described bending moment rotors are positioned at both sides, fuselage main body (1) middle part, left and right is put relatively, screw propeller hand of rotation is relative, directly provides main lift needed for aircraft by driving engine (5).
3. a kind of six rotor fuel-electric hybrid aircrafts according to claim 1, it is characterized in that: two described bending moment rotors are connected with Timing Belt (14) by the synchronous pulley (13) on driving engine (5), and driving this two bending moment rotor wing rotations, rotor lift size changes rotor head total distance size by flight controller (4) control figure steering wheel (18) and realizes.
4. a kind of six rotor fuel-electric hybrid aircrafts according to claim 1, it is characterized in that: two in four described fixing rotors are positioned at aircraft front portion, another two fixing rotors are positioned at aircraft rear portion, lay respectively at fuselage main body (1) both sides, left and right is put relatively, four fixing rotors, by lithium cell (7) directly energy supply, control its stability maintenance completing flight course and maneuvering flight action by flight controller (4).
5. a kind of six rotor fuel-electric hybrid aircrafts according to claim 1, is characterized in that: described lithium cell (7) and fuel tank (12) lay respectively at fuselage main body (1) front portion or rear portion.
6. a kind of six rotor fuel-electric hybrid aircrafts according to claim 1, is characterized in that: described driving engine (5) is positioned at fuselage main body (1) middle part.
7. a kind of six rotor fuel-electric hybrid aircrafts according to claim 1, is characterized in that: described driving engine (5) remains constant revolution in flight course.
8. a kind of six rotor fuel-electric hybrid aircrafts according to claim 1, it is characterized in that: another kind of alternative structure, two bending moment screw blade assemblies (19) are installed respectively a driving engine (5), driving engine (5) is connected with bending moment screw blade assembly (19), directly drives bending moment screw blade (17) to rotate.
9. a kind of six rotor fuel-electric hybrid aircrafts according to claim 8, it is characterized in that: the described respective integral shaft generator (8) in parallel of driving engine (5) laid respectively on two bending moment screw blade assemblies (19) drives it to generate electricity, for lithium cell charging in the middle of fuselage, two bending moment rotor wing rotation directions that two driving engines (5) directly drive are contrary.
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| CN201510291240.6A CN104859853A (en) | 2015-06-01 | 2015-06-01 | Six-rotor hybrid aircraft |
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| CN105329448A (en) * | 2015-11-24 | 2016-02-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Oil-electricity mixed power system of vertical taking-off and landing unmanned aerial vehicle |
| CN105346709A (en) * | 2015-11-05 | 2016-02-24 | 广州地理研究所 | Multi-rotor craft capable of transforming combination |
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| CN105346709A (en) * | 2015-11-05 | 2016-02-24 | 广州地理研究所 | Multi-rotor craft capable of transforming combination |
| CN105329448A (en) * | 2015-11-24 | 2016-02-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Oil-electricity mixed power system of vertical taking-off and landing unmanned aerial vehicle |
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| CN108602558A (en) * | 2015-12-21 | 2018-09-28 | 空客直升机德国有限公司 | Multi-rotor aerocraft |
| CN105644776A (en) * | 2016-03-17 | 2016-06-08 | 秦建法 | Multi-rotor unmanned helicopter |
| CN105711826A (en) * | 2016-03-31 | 2016-06-29 | 陈萌 | Tandem type oil-electric hybrid unmanned aerial vehicle |
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