CN105129079A - Hybrid power long-endurance multi-shaft air vehicle - Google Patents
Hybrid power long-endurance multi-shaft air vehicle Download PDFInfo
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- CN105129079A CN105129079A CN201510630868.4A CN201510630868A CN105129079A CN 105129079 A CN105129079 A CN 105129079A CN 201510630868 A CN201510630868 A CN 201510630868A CN 105129079 A CN105129079 A CN 105129079A
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Abstract
The invention discloses a hybrid power long-endurance multi-shaft air vehicle. The hybrid power long-endurance multi-shaft air vehicle comprises a device installing platform. A fuel engine is fixed to the device installing platform, and a flight rotor wing used for producing lift force is arranged on a rotating outputting shaft of the fuel engine. A plurality of posture adjusting rotor-wing installing arms are arranged on the periphery of the device installing platform in a radial mode, the tail ends of the posture adjusting rotor-wing installing arms are fixedly controlled by reverse torsion adjusting steering engines of an air vehicle posture control system, direct current motors are vertically fixed to angle adjusting motor fixing supports of the reverse torsion adjusting steering engines, and posture adjusting rotor wings are arranged on rotating outputting shafts of the direct current motors. Air vehicle supporting foot frames are arranged below the device installing platform. The hybrid power long-endurance multi-shaft air vehicle has the advantages that the structure is reasonable, the weight is small, and cruising capacity is high.
Description
Technical field
The present invention relates to Multi-axis aircraft when a kind of hybrid power length is navigated.
Background technology
Current most of Multi-axis aircraft all adopts lithium polymer battery as power source, and because its energy density is well below biological fuel, so cruise duration is substantially all within 30 minutes, and battery is from great, causes aircraft load-carrying limited.And in actual use, pure electrodynamic Multi-axis aircraft discharge current is large, causes the number of recharge cycles of lithium polymer battery limited, causes tens of backwardness to change, thus make operating costs high.
The Multi-axis aircraft of pure fuel power in theory also can realize, and also has some correlative studys underway, but this kind of aircraft will lose the sharpest edges of existing Multi-axis aircraft, and namely structure is simple.The change of its complexity is total will make capacity weight, reliability, size, cost all become uncontrollable apart from structure.
Known patent number is " a kind of oil electric mixed dynamic four rotor unmanned aircraft " of CN103359284A, adopts the mode of engine power generation, direct motor drive rotor.This mode can ensure the simplicity of structure, but the energy is through the conversion of chemical power and electric energy, and loss in efficiency is larger.
Known patent number is " a kind of hybrid power quadrotor " of CN204210733U, fuel engines is adopted to provide the prevailing lift of flight, electrical motor is as auxiliary power, pose adjustment lift is provided, in this invention and the not mentioned anti-twisted problem overcoming fuel engines and bring aircraft, so not having to design the Multi-axis aircraft overcoming anti-twisted method is be difficult to flight.
Summary of the invention
The technical problem to be solved in the present invention is to provide Multi-axis aircraft when a kind of hybrid power length is navigated, and it has the features such as rational in infrastructure, lightweight, flying power is long.
For solving the problems of the technologies described above, the technical solution used in the present invention is:
Multi-axis aircraft during a kind of hybrid power length boat, comprise equipment erecting stage, equipment erecting stage fixes fuel engines, the rotating output shaft of fuel engines is provided with the flying rotor for generation of lift, four pose adjustment rotor hold-down arms are arranged with in equipment erecting stage surrounding, four pose adjustment rotor hold-down arm structures are identical, be the arc of K/UP, four pose adjustment rotors are a little more than flying rotor, the anti-twisted adjustment steering wheel of aircraft manufacturing technology system is fixedly controlled by the end of pose adjustment rotor hold-down arm, the angular adjustment motor fixed rack of anti-twisted adjustment steering wheel is vertically fixedly controlled by the brshless DC motor of aircraft manufacturing technology system, the rotating output shaft of brshless DC motor is provided with pose adjustment rotor, aircraft support foot rest is provided with in the below of equipment erecting stage.
The present invention improves further and is:
Described fuel engines is engine petrol, and described petrolic fuel tank is positioned at center-of-gravity position bottom equipment erecting stage.
The power supply of brshless DC motor is lithium cell.
The kinetic energy that the power supply of brshless DC motor produces for fuel engines supplies through electrical power generators.
The kinetic energy that the charge power supply of lithium cell produces for fuel engines supplies through electrical power generators.
Equipment erecting stage is disc.
The beneficial effect adopting technique scheme to produce is:
The present invention includes equipment erecting stage, equipment erecting stage fixes fuel engines, the rotating output shaft of fuel engines is provided with the flying rotor for generation of lift, fuel engines is adopted to provide the power of flight for Multi-axis aircraft, the fuel engines that lift is driven by biological fuel provides, and no longer relies on battery, because lift only need offset gravity substantially, so fuel engines rotating speed does not need frequent adjustment, it also can install simple spacing rotor.Because the energy density of biological fuel is much larger than battery, so the flight time of Multi-axis aircraft effectively can be improved.Be provided with multiple pose adjustment rotor hold-down arm equipment erecting stage surrounding is radial, the anti-twisted adjustment steering wheel of aircraft manufacturing technology system is fixedly controlled by the end of pose adjustment rotor hold-down arm, the angular adjustment motor fixed rack of anti-twisted adjustment steering wheel is vertically fixedly controlled by the DC machine of aircraft manufacturing technology system, the rotating output shaft of DC machine is provided with pose adjustment rotor; Motor is adopted to control the flight attitude of Multi-axis aircraft.By aircraft manufacturing technology Systematical control DC motor speed and anti-twisted adjustment steering wheel angle, when the change of fuel engines rotating speed has an impact to anti-twisted power, make the flight attitude of Multi-axis aircraft still held stationary, thus eliminate the anti-twisted impact on aircraft, like this compared with simple electronic Multi-axis aircraft, when ensureing normal flight, greatly enhance the flying power of Multi-axis aircraft; Four pose adjustment rotor hold-down arms are arranged with in equipment erecting stage surrounding, four pose adjustment rotor hold-down arm structures are identical, be the arc of K/UP, four pose adjustment rotors are a little more than flying rotor, meet aerodynamic principle, make it have a smooth flight, reduce energy resource consumption simultaneously; DC machine is brshless DC motor, working stability, long service life; Fuel engines is engine petrol, and weight is little, and power is large; Petrolic fuel tank is positioned at center-of-gravity position bottom equipment erecting stage, rational in infrastructure, steadily of centre of gravity; Equipment erecting stage is disc, and space availability ratio is high, barycentre steadiness.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention;
Fig. 2 is the mounting structure schematic diagram of pose adjustment rotor hold-down arm in Fig. 1, anti-twisted adjustment steering wheel and pose adjustment rotor;
Fig. 3 is the structural representation in flying rotor and pose adjustment rotor wing rotation direction under state of flight of the present invention;
Fig. 4 is that anti-twisted adjustment steering wheel makes brshless DC motor tilt angle schematic diagram;
Fig. 5 overcomes anti-twisted schematic diagram after brshless DC motor verts.
In the accompanying drawings: 1, equipment erecting stage; 2, fuel engines; 3, flying rotor; 4, pose adjustment rotor hold-down arm; 5, aircraft manufacturing technology system; 6, anti-twisted adjustment steering wheel; 7, angular adjustment motor fixed rack; 8, brshless DC motor; 9, pose adjustment rotor; 10, aircraft support foot rest; 11, fuel tank.
In the application, aircraft manufacturing technology system is from prior art.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the present invention is further elaborated.
From the embodiment shown in Fig. 1-3, the present embodiment comprises disc equipment erecting stage 1, equipment erecting stage 1 is fixed fuel engines 2, fuel engines 2 adopts engine petrol (model: ZENEP20 or OS38200GT-22), petrolic rotating output shaft is provided with the flying rotor 3 for generation of lift, be provided with four pose adjustment rotor hold-down arms 4 equipment erecting stage 1 surrounding is radial, four pose adjustment rotor hold-down arm 4 structures are identical, be the arc of K/UP, four pose adjustment rotors 9 are a little more than flying rotor 3; Aircraft manufacturing technology system 5(model is fixedly controlled by: anti-twisted adjustment steering wheel 6(model iFLY-F2A or CUAVARDUPILOTMEGA2.6): HitecHS-7955TG) at the end of pose adjustment rotor hold-down arm 4, the angular adjustment motor fixed rack 7 of anti-twisted adjustment steering wheel 6 is vertically fixedly controlled by the DC machine 8(model of aircraft manufacturing technology system 5: EMAXMT-3510 or DUALSKYXM4010TE-6), DC machine 8 adopts brshless DC motor, and the rotating output shaft of brshless DC motor is provided with pose adjustment rotor 9; Aircraft support foot rest 10 is provided with in the below of equipment erecting stage 1; Petrolic fuel tank 11 is positioned at center-of-gravity position bottom equipment erecting stage 1; The power supply of brshless DC motor can be lithium cell; The kinetic energy that the charge power supply of lithium cell produces for engine petrol supplies through electrical power generators; The kinetic energy that the power supply of brshless DC motor can also produce for engine petrol supplies through electrical power generators.
Principle of work:
When flying rotor 3 rotating speed on engine petrol output shaft raises, the anti-twisted power produced strengthens thereupon, and at this moment aircraft manufacturing technology system 5 controls pose adjustment rotor 5 and produces actuating, reaches the change making brshless DC motor vertical angle.Rotate by pose adjustment rotor 9 on brshless DC motor output shaft the thrust produced and reach the effect of offsetting the anti-twisted power of flying rotor 3.Overlook directly over Multi-axis aircraft and look down, flying rotor hand of rotation as being left-hand revolution, then can produce clockwise anti-twisted moment shown in Fig. 5; In order to overcome this anti-twisted moment, aircraft manufacturing technology system sends control command makes four groups of brshless DC motors tilt toward anticlockwise direction, adjusts the rotating speed of brshless DC motor simultaneously, thus shown in generation Fig. 5, anticlockwise direction overcomes anti-twisted moment.Realize eliminating anti-twisted power to the impact of Multi-axis aircraft, to ensure the smooth flight of Multi-axis aircraft.
Claims (6)
1. Multi-axis aircraft during a hybrid power length boat, it is characterized in that: comprise equipment erecting stage (1), at the upper fixing fuel engines (2) of described equipment erecting stage (1), the rotating output shaft of described fuel engines (2) is provided with the flying rotor (3) for generation of lift, four pose adjustment rotor hold-down arms (4) are arranged with in described equipment erecting stage (1) surrounding, described four pose adjustment rotor hold-down arm (4) structures are identical, be the arc of K/UP, described four pose adjustment rotors (9) are a little more than flying rotor (3), the anti-twisted adjustment steering wheel (6) of aircraft manufacturing technology system (5) is fixedly controlled by the end of described pose adjustment rotor hold-down arm (4), at the upper brshless DC motor (8) being vertically fixedly controlled by aircraft manufacturing technology system (5) of the angular adjustment motor fixed rack (7) of described anti-twisted adjustment steering wheel (6), the rotating output shaft of described brshless DC motor (8) is provided with pose adjustment rotor (9), aircraft support foot rest (10) is provided with in the below of described equipment erecting stage (1).
2. Multi-axis aircraft during a kind of hybrid power length boat according to claim 1, is characterized in that: described fuel engines (2) is engine petrol, and described petrolic fuel tank (11) is positioned at equipment erecting stage (1) bottom center-of-gravity position.
3. Multi-axis aircraft during a kind of hybrid power length boat according to claim 1, is characterized in that: the power supply of described brshless DC motor is lithium cell.
4. Multi-axis aircraft during a kind of hybrid power length boat according to claim 1, is characterized in that: the kinetic energy that the power supply of described brshless DC motor produces for fuel engines (2) supplies through electrical power generators.
5. Multi-axis aircraft during a kind of hybrid power length boat according to claim 3, is characterized in that: the kinetic energy that the charge power supply of described lithium cell produces for fuel engines (2) supplies through electrical power generators.
6. Multi-axis aircraft during a kind of hybrid power length boat according to claim 1, is characterized in that: described equipment erecting stage (1) is disc.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201510630868.4A CN105129079B (en) | 2015-09-29 | 2015-09-29 | A kind of long endurance Multi-axis aircraft of hybrid power |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510630868.4A CN105129079B (en) | 2015-09-29 | 2015-09-29 | A kind of long endurance Multi-axis aircraft of hybrid power |
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| CN105129079A true CN105129079A (en) | 2015-12-09 |
| CN105129079B CN105129079B (en) | 2017-08-25 |
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| CN106275415A (en) * | 2016-08-19 | 2017-01-04 | 广东容祺智能科技有限公司 | The aircraft that a kind of fixed-wing and many rotors can automatically switch |
| JP6156669B1 (en) * | 2016-04-27 | 2017-07-05 | 酒井 泰三郎 | Multicopter |
| CN107065904A (en) * | 2017-03-10 | 2017-08-18 | 武汉农帮科技有限责任公司 | Gasoline and electric hybrid aircraft balance control system |
| WO2018233570A1 (en) * | 2017-06-19 | 2018-12-27 | 河南省猎鹰消防科技有限公司 | Gasoline-electric hybrid multiaxis rotor type unmanned aerial vehicle |
| CN110733624A (en) * | 2019-01-23 | 2020-01-31 | 杭州零零科技有限公司 | Unmanned flight system and control system for unmanned flight system |
| JP7399521B2 (en) | 2020-09-17 | 2023-12-18 | 株式会社石川エナジーリサーチ | flight equipment |
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| CN106275415B (en) * | 2016-08-19 | 2018-06-05 | 广东容祺智能科技有限公司 | The aircraft that a kind of fixed-wing and more rotors can automatically switch |
| CN107065904A (en) * | 2017-03-10 | 2017-08-18 | 武汉农帮科技有限责任公司 | Gasoline and electric hybrid aircraft balance control system |
| WO2018233570A1 (en) * | 2017-06-19 | 2018-12-27 | 河南省猎鹰消防科技有限公司 | Gasoline-electric hybrid multiaxis rotor type unmanned aerial vehicle |
| CN110733624A (en) * | 2019-01-23 | 2020-01-31 | 杭州零零科技有限公司 | Unmanned flight system and control system for unmanned flight system |
| CN113619767A (en) * | 2019-01-23 | 2021-11-09 | 杭州零零科技有限公司 | Unmanned flight system and control system for unmanned flight system |
| JP7399521B2 (en) | 2020-09-17 | 2023-12-18 | 株式会社石川エナジーリサーチ | flight equipment |
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| CN105129079B (en) | 2017-08-25 |
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