CN204527630U - A kind of oil electric mixed dynamic fixed-wing VUAV system - Google Patents
A kind of oil electric mixed dynamic fixed-wing VUAV system Download PDFInfo
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- CN204527630U CN204527630U CN201520215508.3U CN201520215508U CN204527630U CN 204527630 U CN204527630 U CN 204527630U CN 201520215508 U CN201520215508 U CN 201520215508U CN 204527630 U CN204527630 U CN 204527630U
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Abstract
The utility model relates to a kind of oil electric mixed dynamic fixed-wing VUAV system, comprise fuselage, wing I and wing II, described wing I is provided with vertical spin oar I and wing motor I, described wing II is provided with vertical spin oar II and wing motor II, fixed-wing horizontal propeller is circumscribed with in the front end of described fuselage, balance in pitch control rotor and balance in pitch direction controlling motor is provided with at the afterbody of described fuselage, wing motor I described in Based Intelligent Control is provided with in described fuselage, described wing motor II, the autopilot that described oily power engine and described balance in pitch direction controlling motor run.The beneficial effects of the utility model are: achieve unmanned plane take off rely on electrokinetic cell take off vertically, oily power driven fixed-wing rapid flight of hovering, make a return voyage the oil electric mixed dynamic flight repertoire of hovering to vertical landing, there is the ability of vertical takeoff and landing and hovering, have again the feature that speed is fast, voyage is far away, the time is long.
Description
Technical field
The utility model relates to unmanned plane field, is specifically related to a kind of oil electric mixed dynamic fixed-wing VUAV system.
Background technology
Due to unmanned plane have motor-driven fast, use cost is low, safeguard and use the features such as simple, therefore at home and abroad extensively used.But up to now, the unmanned plane used in the world is owing to being limited by landing technical limitation, and actual use still can not get comprehensive application.In fixed-wing VUAV, only in a few developed country of west, rarely have application in naval, and oil electric mixed dynamic fixed-wing VUAV or blank.Conventional unmanned plane landing technology is following four kinds:
1, landing modes is slided in traditional running take off: rely on manipulation hand telecontrolled aircraft on the straight runway of spaciousness, slide into takeoff speed and to take off lift-off, is switched to remote manual control aircraft slides landing on runway again during landing by manipulating hand.Weak point has three high: to runway require high, environmental conditions of taking off is high, high to the technical requirements of manipulation hand.Advantage is that safety factor is the highest.
2, launcher catapult-assisted take-off, Parachute Opening landing way of recycling: rely on the spring, elastic, pressurized air etc. of launcher in the air, unmanned plane to be taken off unmanned aerial vehicle ejecting, the landing ground that releases a parachute when unmanned plane returns takeoff point is reclaimed.Weak point is that ejection device is heavy, and assembling uses more multiple, professional, and cost is higher, and parachute-opening is reclaimed by wind effect very large, and operating needs environment is general, can not at sea boats and ships use.Advantage is that usage condition relatively easily meets by land, general to the technical requirements of manipulation hand.
3, vehicle-mounted unmanned aerial vehicle takes off, and bale out way of recycling: rely on car roof to carry unmanned plane, by automobile give it the gun on road reach unmanned plane takeoff speed after to take off lift-off, parachute-opening landing recovery after unmanned plane makes a return voyage.Weak point needs automobile peace straight way road just can take off, landing confined condition with above 2nd suitable.Advantage takes off that efficiency is high, safety is high.
4, rato, bale out way of recycling: rely on booster rocket that unmanned plane boosting is raised to airflight, weak point single use cost is the highest, operates professional height.Advantage has been very fast, and setup time is short, general to environmental requirement.Return landing and launch landing, vehicle-mounted landing is the same.
Conventional fixed-wing aircraft landing obtains lift by gliding motility and air relative velocity forward and takes off, and helicopter produces lift lift-off by high speed propeller and takes off.The former great advantage is that air speed is fast, the flight time is long, and the latter's great advantage to take off vertically, without the need to runway, little to site requirements.Fixed-wing VUAV gets both advantage, and the function of existing vertical takeoff and landing, has again the feature of rapid flight.But current VUAV has just passed on the certain advantages of fixed-wing and helicopter, disadvantage has been that cruise duration is short, and cost is also very high.Up to now, both at home and abroad the longest boat time VUAV be no more than 40 minutes cruise duration.What it adopted still realizes vertical takeoff and landing by the method that existing 4 axle aircraft and fixed wing aircraft combine, and its critical defect that many rotors airborne period is short, voyage is short could not be resolved.
Someone drives fixed-wing vertical take-off and landing aircraft (VTOL aircraft) and has vertical takeoff and landing function as helicopter, when having again a long boat of fixed wing aircraft, fireballing feature, has special purposes in military and civilian field.Although existing fixed-wing VUAV possesses vertical takeoff and landing function, during boat, short, load hour is its maximum short slab, and practical application meaning is not very large.
Utility model content
In sum, in order to overcome the deficiencies in the prior art, the utility model provides a kind of oil electric mixed dynamic fixed-wing VUAV system.
The technical scheme that the utility model solves the problems of the technologies described above is as follows: a kind of oil electric mixed dynamic fixed-wing VUAV system, comprise fuselage, wing I and wing II, described wing I is provided with vertical spin oar I and wing motor I, described wing motor I drives the rotation of described vertical spin oar I, described wing II is provided with vertical spin oar II and wing motor II, and described wing motor II drives the rotation of described vertical spin oar II;
Fixed-wing horizontal propeller is circumscribed with in the front end of described fuselage, front portion in described fuselage is provided with oily power engine and onboard generators, described oily power engine drives described fixed-wing horizontal propeller to rotate, be provided with balance in pitch control rotor and balance in pitch direction controlling motor at the afterbody of described fuselage, balance in pitch control rotor described in described balance in pitch direction controlling driven by motor runs;
In described fuselage, be provided with the autopilot that wing motor I described in Based Intelligent Control, described wing motor II, described oily power engine and described direction controlling motor run, described autopilot realize the taking off vertically of unmanned plane by the operation controlling described wing motor I, described wing motor II, described oily power engine and described balance in pitch direction controlling motor, hover, airflight and vertical landing;
The battery that described onboard generators is described wing motor I, the battery of described wing motor II, the described battery of balance in pitch direction controlling motor and the battery of described autopilot provide electric energy, also fuel-feed system is provided with in described fuselage, described fuel-feed system provides fuel for described oily power engine, and described oily power engine drives described onboard generators to generate electricity.
Further, when unmanned plane airflight, described onboard generators produces the battery charging that electric energy is the battery of described wing motor I, the battery of described wing motor II, the battery of described balance in pitch direction controlling motor and described autopilot.
Further, in described fuselage, be also provided with airborne electric power system, described onboard generators is the battery charging of the battery of described wing motor I, the battery of described wing motor II, the battery of described balance in pitch direction controlling motor and described autopilot by described airborne electric power system.
Further, described autopilot is by the operation of wing motor I, described wing motor II, described oily power engine and described balance in pitch direction controlling motor described in different electronic governors difference Based Intelligent Control.
Further, described wing motor I, described wing motor II and described balance in pitch direction controlling motor are all brushless motor.
The beneficial effects of the utility model are: collection vertical takeoff and landing, oil electric mixed dynamic drive, unmanned air vehicle technique be incorporated into one, except there are all advantages of above four kinds of landing technology, the vertical takeoff and landing technical capacity more having them not have, adaptive capacity to environment, technical personnel operation grasp ability, safety assurance ability.Achieve unmanned plane take off rely on electrokinetic cell take off vertically, oily power driven fixed-wing rapid flight of hovering, making a return voyage hovering to vertical landing oil electric mixed dynamic flight repertoire.Make the ability of its existing rotary wing aircraft vertical takeoff and landing and hovering, have again the feature that fixed wing aircraft speed is fast, voyage is far away, the time is long.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model;
Fig. 2 is functional block diagram of the present utility model.
In accompanying drawing, the list of parts representated by each label is as follows:
1, fuselage, 2, wing I, 3, wing II, 4, vertical spin oar I, 5, vertical spin oar II, 6, balance in pitch control rotor, 7, fixed-wing horizontal propeller.
Detailed description of the invention
Be described principle of the present utility model and feature below in conjunction with accompanying drawing, example, only for explaining the utility model, is not intended to limit scope of the present utility model.
As illustrated in fig. 1 and 2, a kind of oil electric mixed dynamic fixed-wing VUAV system, comprise fuselage 1, wing I 2 and wing II 3, described wing I 2 is provided with vertical spin oar I 4 and wing motor I, described wing motor I drives described vertical spin oar I 4 to rotate, described wing II 3 is provided with vertical spin oar II 5 and wing motor II, described wing motor II drives described vertical spin oar II 5 to rotate, vertical spin oar I 4 and vertical spin oar II 5 be mainly used in unmanned plane take off vertically or vertical landing time.Taking off vertically or vertical landing of unmanned plane, does not need when taking off or landing to slide, reduces unmanned plane to the environmental requirement of taking off or land.
Fixed-wing horizontal propeller 7 is circumscribed with in the front end of described fuselage 1, front portion in described fuselage 1 is provided with oily power engine and onboard generators, described oily power engine drives described fixed-wing horizontal propeller 7 to rotate, fixed-wing horizontal propeller 7 is mainly used in producing tractive force to unmanned plane, makes it fly aloft.Balance in pitch control rotor 6 and balance in pitch direction controlling motor is provided with at the afterbody of described fuselage 1, described in described balance in pitch direction controlling driven by motor, balance in pitch control rotor 6 runs, and controls by balance in pitch control rotor 6 heading adjusting unmanned plane.Described wing motor I, described wing motor II and described direction controlling motor are all brushless motor, can reduce the heavy burden of unmanned plane.
The autopilot that wing motor I described in Based Intelligent Control, described wing motor II, described oily power engine and described direction controlling motor run is provided with in described fuselage 1, described autopilot, by the operation of wing motor I, described wing motor II, described oily power engine and described balance in pitch direction controlling motor described in different electronic governors respectively Based Intelligent Control, realizes the taking off vertically of unmanned plane, hovers, airflight and vertical landing.
Described onboard generators is also in described fuselage 1, is also provided with fuel-feed system in described fuselage 1, and described fuel-feed system provides fuel for described oily power engine, and described oily power engine drives described onboard generators to generate electricity.Airborne electric power system is also provided with in described fuselage 1, when unmanned plane aloft flies, described onboard generators is the battery charging of the battery of described wing motor I, the battery of described wing motor II, the battery of described balance in pitch direction controlling motor and described autopilot by described airborne electric power system.
A complete unmanned plane is described below from taking off vertically, hover, to airflight, finally hovers, the process of vertical landing:
Take off vertically: autopilot controls symmetrical to be arranged on wing motor on wing and balance in pitch direction controlling motor, make vertical spin oar I 4, vertical spin oar II 5 and balance in pitch, lift that balance in pitch control rotor 6 produces is greater than the total weight of unmanned plane, it is contrary with gravity direction that lift produces direction, and unmanned plane vertical uplift leaves ground.When arriving predetermined altitude, autopilot controls wing motor and balance in pitch direction motor and realizes the total weight that lift that screw propeller produces equals unmanned plane, and unmanned plane keeps floating state aloft, so far completes the task of taking off vertically.
Airflight: after unmanned plane aloft hovers, autopilot controls oily power engine and provides power to fixed-wing horizontal propeller 7, unmanned plane is converted to fixed-wing pattern and airflight by floating state, and oily power engine now bears the active flight of unmanned plane fixed-wing oil.Floating state transfers fixed-wing pattern to and provides a conversion work instruction by multi-information fusion instrument, now, electric starter motor on oil power engine rotates fire an engine, and oily power engine drives fixed-wing horizontal propeller 7 to rotate and produces pulling force, makes unmanned plane high-speed forward flight.After unmanned plane acquisition speed, along with speed increases gradually, participate in taking off vertically, the wing motor that hovers and balance in pitch direction controlling motor quit work gradually.Fuel is provided by airborne fuel-feed system to oily power engine, the flight that can ensure that unmanned plane is longer when navigating during unmanned plane fixed-wing offline mode.After the flight of unmanned plane fixed-wing, oil power engine is while drive unmanned plane during flying, and drive onboard generators to power to the power in airborne electric power system and system battery, supplement the electricity consumed when taking off vertically, simultaneously also to mobile system power electronic equipment.
Vertical landing: aircraft transfer to fixed-wing flown cruising flight make a return voyage landing time, aircraft will by fixed-wing pattern change into hovering last vertical landing.Now, multi-information fusion instrument provides pwm enable signal to wing motor and balance in pitch direction controlling motor, and vertical spin oar I 4, vertical spin oar II 5 and balance in pitch control rotor start, and screw propeller produces thrust vertically upward.Meanwhile, multi-information fusion instrument moves driving engine to oil and provides flame-out instruction, engine off, and fixed-wing horizontal propeller 7 stops operating, and disappear to the tractive force of unmanned plane, unmanned plane is transformed into floating state.Multi-information fusion instrument provides vertical landing instruction, and unmanned plane enters slow vertical landing program, last safety, grease it in ground.
In sum, the utility model achieve unmanned plane take off rely on electrokinetic cell take off vertically, oily power driven fixed-wing rapid flight of hovering, making a return voyage hovering to vertical landing oil electric mixed dynamic flight repertoire.Achieving by electricity to oil, again by the working mode change of oil to electricity, is oil electric mixed dynamic fixed-wing VUAV truly.Solve the application of current unmanned plane market height is required to runway, environmental conditions of taking off is high, " three high " bottleneck restriction high to manipulation hand technical requirements.Use motorized motions when vertical takeoff and landing, be transformed into the dynamic driving of oil when fixed-wing flies.Oil, electricity mixed power is adopted to drive the maximum technical characterstic of unmanned plane to be the excellent properties of these two kinds of power to be all used, make the ability of its existing rotary wing aircraft vertical takeoff and landing and hovering, have again the feature that fixed wing aircraft speed is fast, voyage is far away, the time is long.The appearance of this technology will, forest fire protection emergent in aerial mapping, public security fire-fighting, mitigation, searching rescue, power-line patrolling, environmental monitoring, agricultural weather, maritime affairs be cruised, frontier defense patrol, the field unmanned plane such as military surveillance bring more simple, convenient, flexible, efficient, safe widespread use.
The foregoing is only preferred embodiment of the present utility model, not in order to limit the utility model, all within spirit of the present utility model and principle, any amendment done, equivalent replacement, improvement etc., all should be included within protection domain of the present utility model.
Claims (5)
1. an oil electric mixed dynamic fixed-wing VUAV system, comprise fuselage (1), wing I (2) and wing II (3), it is characterized in that, described wing I (2) is provided with vertical spin oar I (4) and wing motor I, described wing motor I drives described vertical spin oar I (4) to rotate, described wing II (3) is provided with vertical spin oar II (5) and wing motor II, and described wing motor II drives described vertical spin oar II (5) to rotate;
Fixed-wing horizontal propeller (7) is circumscribed with in the front end of described fuselage (1), front portion in described fuselage (1) is provided with oily power engine and onboard generators, described oily power engine drives described fixed-wing horizontal propeller (7) to rotate, be provided with balance in pitch control rotor (6) and balance in pitch direction controlling motor at the afterbody of described fuselage (1), balance in pitch control rotor (6) described in described balance in pitch direction controlling driven by motor runs;
In described fuselage (1), be provided with the autopilot that wing motor I described in Based Intelligent Control, described wing motor II, described oily power engine and described balance in pitch direction controlling motor run, described autopilot realize the taking off vertically of unmanned plane by the operation controlling described wing motor I, described wing motor II, described oily power engine and described balance in pitch direction controlling motor, hover, airflight and vertical landing;
The battery that described onboard generators is described wing motor I, the battery of described wing motor II, the described battery of balance in pitch direction controlling motor and the battery of described autopilot provide electric energy, also fuel-feed system is provided with in described fuselage (1), described fuel-feed system provides fuel for described oily power engine, and described oily power engine drives described onboard generators to generate electricity.
2. a kind of oil electric mixed dynamic fixed-wing VUAV system according to claim 1, it is characterized in that, when unmanned plane airflight, described onboard generators produces the battery charging that electric energy is the battery of described wing motor I, the battery of described wing motor II, the battery of described balance in pitch direction controlling motor and described autopilot.
3. a kind of oil electric mixed dynamic fixed-wing VUAV system according to claim 2, it is characterized in that, in described fuselage (1), be also provided with airborne electric power system, described onboard generators is the battery charging of the battery of described wing motor I, the battery of described wing motor II, the battery of described balance in pitch direction controlling motor and described autopilot by described airborne electric power system.
4. a kind of oil electric mixed dynamic fixed-wing VUAV system according to claim 1, it is characterized in that, described autopilot is by the operation of wing motor I, described wing motor II, described oily power engine and described balance in pitch direction controlling motor described in different electronic governors difference Based Intelligent Control.
5., according to the arbitrary described a kind of oil electric mixed dynamic fixed-wing VUAV system of Claims 1-4, it is characterized in that, described wing motor I, described wing motor II and described balance in pitch direction controlling motor are all brushless motor.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201520215508.3U CN204527630U (en) | 2015-04-10 | 2015-04-10 | A kind of oil electric mixed dynamic fixed-wing VUAV system |
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| CN201520215508.3U CN204527630U (en) | 2015-04-10 | 2015-04-10 | A kind of oil electric mixed dynamic fixed-wing VUAV system |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104843181A (en) * | 2015-04-10 | 2015-08-19 | 桂林航龙科讯电子技术有限公司 | Petrol-electric hybrid power fixed wing vertical take-off and landing unmanned plane system |
| 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 |
| CN105752345A (en) * | 2016-03-18 | 2016-07-13 | 西安交通大学 | Large load long duration multifunctional aircraft for operation |
| CN106155085A (en) * | 2016-08-05 | 2016-11-23 | 武汉捷特航空科技有限公司 | A kind of unmanned plane assisting in flying control method, system and unmanned plane |
| CN106314809A (en) * | 2016-09-19 | 2017-01-11 | 中电科芜湖钻石飞机设计研究院有限公司 | Fixed wing type hybrid power motorplane |
| CN106927030A (en) * | 2017-03-15 | 2017-07-07 | 西北工业大学 | A kind of oil electric mixed dynamic multi-rotor aerocraft and its flight control method |
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2015
- 2015-04-10 CN CN201520215508.3U patent/CN204527630U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104843181A (en) * | 2015-04-10 | 2015-08-19 | 桂林航龙科讯电子技术有限公司 | Petrol-electric hybrid power fixed wing vertical take-off and landing unmanned plane system |
| 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 |
| CN105752345A (en) * | 2016-03-18 | 2016-07-13 | 西安交通大学 | Large load long duration multifunctional aircraft for operation |
| CN106155085A (en) * | 2016-08-05 | 2016-11-23 | 武汉捷特航空科技有限公司 | A kind of unmanned plane assisting in flying control method, system and unmanned plane |
| CN106314809A (en) * | 2016-09-19 | 2017-01-11 | 中电科芜湖钻石飞机设计研究院有限公司 | Fixed wing type hybrid power motorplane |
| CN106927030A (en) * | 2017-03-15 | 2017-07-07 | 西北工业大学 | A kind of oil electric mixed dynamic multi-rotor aerocraft and its flight control method |
| CN106927030B (en) * | 2017-03-15 | 2023-04-07 | 西北工业大学 | Oil-electricity hybrid power multi-rotor aircraft and flight control method thereof |
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| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150805 Termination date: 20180410 |