CN104290907B - Novel hybrid vertical/short take off and landing unmanned vehicle - Google Patents
Novel hybrid vertical/short take off and landing unmanned vehicle Download PDFInfo
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- CN104290907B CN104290907B CN201410545432.0A CN201410545432A CN104290907B CN 104290907 B CN104290907 B CN 104290907B CN 201410545432 A CN201410545432 A CN 201410545432A CN 104290907 B CN104290907 B CN 104290907B
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Abstract
The invention discloses a kind of novel hybrid vertical/short take off and landing unmanned vehicle, object is to solve complex structure that existing aircraft exists, the problem such as with high costs.It comprises fuselage, host wing, the elevon be arranged on host wing, be arranged on forebody canard, be arranged on fuselage afterbody vertical tail, be arranged on alighting gear, storage battery, control system, power-supply management system etc. below fuselage.The present invention adopts ducted fan to provide lift and auxiliary balance when vertical takeoff and landing, adopt driving engine to make main thrust and independent power generation simultaneously, effective utilization oil electricity is complementary, simultaneously by the design to aircaft configuration and aerodynamic arrangement, realize fuel oil and electric energy reasonable disposition used in combination, realize vertical and short take-off and landing, reduce the control difficulty of aircraft, effectively solve the control difficulty of existing vertical take-off and landing unmanned aerial vehicle and the problem of voyage demilance shield.The present invention can realize vertical short from landing, has the flight advantage such as steady, applied widely flexibly.
Description
Technical field
The present invention relates to space industry, especially a kind of novel hybrid vertical/short take off and landing unmanned vehicle.
Background technology
Unmanned plane due to cost low, safety is good, of many uses, all has huge application potential at military, civil area.At military aspect, unmanned plane can carry out low latitude investigation, communication, electro countermeasure and air-to-ground attack etc.; In civilian, unmanned plane can be used for the supervision and rescue etc. of communication repeating, Environmental Studies, disaster.Therefore, unmanned plane enjoys the concern of people and the attention of the military of various countries in recent years.
For early stage unmanned plane, its cruise duration is short, flying height is low, and reconnaissance and surveillance area is little, can not obtaining information continuously, often causes information " blind area ".And going deep into along with research, unmanned plane performance is also constantly being enhanced.At present, the existing plunderer's unmanned plane reaching 24 hours cruise duration in the world, global hawk unmanned plane during high-altitude heavy load length boat, the faint star unmanned plane etc. that HAE is stealthy.From developed recently situation, the prospect that unmanned plane has it wide.
Domestic existing unmanned plane mainly contains two kinds of flight forms: rotor craft and Fixed Wing AirVehicle.Wherein, rotor craft is mainly based on multi-rotor aerocraft, helicopter, and the principal feature of this class aircraft is: can realize hovering, can standing start, requires low to runway, and flying height promotes fast, launch reclaim simple.But rotor craft also exists that load carrying ability is little, cruise duration is little, cruising speed is low, the shortcomings such as manoevreability is little.Fixed Wing AirVehicle has the advantage that cruise duration is long, manoevreability is higher, but mainly with catapult-assisted take-off with play the parachuting form that falls and reclaim.But this way of recycling exists larger defect, as process is complicated, accessory equipment is many, recovery precision is low, the preparatory period of again taking off is long, particularly cannot use on naval vessel.
Along with science and technology and the develop rapidly of information techenology, the performance of unmanned plane significantly promotes, novel fixed-wing vertically/short take-off and landing (STOL) unmanned vehicle become the Hot spots for development of research.
At present, the existing Fixed Wing AirVehicle that can realize vertical/short take-off and landing (STOL) function is mainly divided into three kinds: rotor verts system flight device, vector spray system flight device, ducted fan system flight device etc.
Rotor system aircraft, one of its representative is U.S. osprey, and major defect is: cruising speed is low and control is complicated.Meanwhile, its structure is comparatively complicated, and Maintenance and Repair work capacity is comparatively large, and use cost is also higher.Affect by himself structural factor, wind loading rating is poor, larger by weather effect.
Vector spray system flight device, one of its representative is Britain's sparrow hawk formula, and major defect is: bullet-loading capacity is little, efficiency of taking off is low (landing oil consumption is large), the hang time is short, and more restive.
Ducted fan system flight device, one of its representative is U.S. F-35, in order to meet vertical takeoff and landing requirement, to devise under lift fan, engine nozzle partially, the vertical takeoff and landing power scheme of posture adjustment jet pipe, lift fan is made up of duct, fan, D shape jet pipe, coupler, movement device and Fu, complex structure, with high costs.
Therefore, at present in the urgent need to a kind of new aircraft, effectively to solve the problem.
Summary of the invention
Goal of the invention of the present invention is: for above-mentioned Problems existing, provides a kind of novel hybrid vertical/short take off and landing unmanned vehicle.The present invention adopts ducted fan to provide lift and auxiliary balance when vertical takeoff and landing, adopt driving engine to make main thrust and independent power generation simultaneously, effective utilization oil electricity is complementary, simultaneously by the design to aircaft configuration and aerodynamic arrangement, realize fuel oil and electric energy reasonable disposition used in combination, realize vertical and short take-off and landing, reduce the control difficulty of aircraft, effectively solve the control difficulty of existing vertical take-off and landing unmanned aerial vehicle and the problem of voyage demilance shield.The present invention can realize vertical and short take-off and landing, has the flight advantage such as steady, applied widely, with low cost flexibly.
To achieve these goals, the present invention adopts following technical scheme:
Novel hybrid vertical/short take off and landing unmanned vehicle, comprise fuselage, the host wing be arranged on fuselage, the elevon be arranged on host wing, be arranged on forebody canard, be arranged on fuselage afterbody vertical tail, be arranged on alighting gear, fuel tank, storage battery, control system, power-supply management system below fuselage;
Described host wing is triangular in shape, described elevon, canard, vertical tail are symmetricly set on the line of centers both sides of fuselage respectively, described fuselage is provided with electric ducted fan, the wingtip of described host wing both sides is symmetrically arranged with electric ducted fan respectively, guiding rudder face is provided with immediately below described electric ducted fan, described electric ducted fan is the distribution of equilateral triangle non-co-planar, and the position of the electric ducted fan place horizontal surface on described fuselage is lower than the position of electric ducted fan place, host wing both sides horizontal surface;
Described fuselage is U-shaped, described fuselage adopts lifting body head, and the middle part of described fuselage is fixedly installed Sloped rotating mechanism, and described Sloped rotating mechanism is provided with driving engine, described driving engine is positioned at the geometric centre of electric ducted fan, and described driving engine is provided with power generating system;
Described fuel tank, storage battery are separately positioned in fuselage, and described power generating system is connected with power-supply management system, and described power-supply management system is connected with control system, storage battery, electric ducted fan respectively.
Described driving engine is the one in turbojet engine, fanjet, the dynamic driving engine of oil.
Relative height between the position of the electric ducted fan place horizontal surface on described fuselage and the position of electric ducted fan place, host wing both sides horizontal surface is poor, for turbojet engine or fanjet diameter 1.5-3 doubly.
Described alighting gear is shock-absorbing alighting gear, and described alighting gear is three.
Described fuel tank is soft capsule fuel tank.
For foregoing problems, the invention provides a kind of novel hybrid vertical/short take off and landing unmanned vehicle.This aircraft comprises fuselage, the host wing be arranged on fuselage, the elevon be arranged on host wing, be arranged on forebody canard, be arranged on fuselage afterbody vertical tail, be arranged on alighting gear, fuel tank, storage battery, control system, power-supply management system below fuselage.
Host wing is triangular in shape, elevon, canard, vertical tail is symmetricly set on the line of centers both sides of fuselage respectively, the head of fuselage is provided with electric ducted fan, the wingtip of host wing both sides is symmetrically arranged with electric ducted fan respectively, guiding rudder face is provided with immediately below electric ducted fan, arrange in equilateral triangle non-co-planar between three groups of electric ducted fans, the position of the electric ducted fan place horizontal surface on head is lower than the position of electric ducted fan place, host wing both sides horizontal surface, diff-H is preferably 1.5-3 times of engine diameters, for turbojet engine, diff-H is preferably 1.5-3 times of turbojet engine diameter, while ensureing the normal air inlet of turbojet engine, the stationarity of effective guarantee aircraft.The U-shaped structure of fuselage, fuselage adopts lifting body head, Die Design is that lifting body and fuselage merge, the middle part of fuselage is fixedly installed Sloped rotating mechanism, Sloped rotating mechanism is provided with driving engine, driving engine is positioned at the geometric centre of electric ducted fan triangular arrangement, and driving engine is provided with power generating system.Fuel tank, storage battery are separately positioned in fuselage, and power generating system is connected with power-supply management system, and power-supply management system is connected with control system, storage battery, electric ducted fan respectively.Driving engine is the one in turbojet engine, fanjet, the dynamic driving engine of oil.Further, alighting gear is shock-absorbing alighting gear, and alighting gear is three, and fuel tank is soft capsule fuel tank.
In the present invention, elevon is with mixing Schema control, and collocation front end canard, obtains actv. pitching trim effect more, realizes high maneuver flight; Meanwhile, on driving engine, configuration is provided with high-speed power generation module, sustainable outside output electric energy, and electric energy is synchronously incorporated to and powers to ducted fan and control system by power-supply management system, or charges a battery; The spout axis of driving engine overlaps with the center of gravity of airplane, and electric ducted fan is equilateral triangle layout and the center of gravity of aircraft is positioned at the triangle centre of form; Meanwhile, by the mix and match of Aviation Fuel and electric energy, utilize oil electricity complementary, realize vertical and short take-off and landing; The relative height difference design of electric ducted fan, can ensure the normal air inlet of driving engine.
Aircraft of the present invention is divided into the vertical takeoff and landing stage peacefully to fly the stage.Wherein, control balance with three electric ducted fans, driving engine vertically operates and makes main thrust, realizes the vertical takeoff and landing stage.Three electric ducted fan level runnings, control flight with each corresponding rudder face, realize putting down flying the stage.
In the present invention, adopt three electric ducted fans of Triangle-Profile, electric ducted fan running is offset with electric ducted fan guiding rudder face, and electric ducted fan operates the anti-twisted power that produces and control driftage, pitching and rolling rely on the different rotating speeds of three electric ducted fans to coordinate.Aircraft is after being vertically raised up to safe altitude, and acceleration level is moved; Be up to the standard movement minimum speed after, close electric ducted fan, vert driving engine, transits to flat to fly the stage.
In the present invention, three axle forms are combined with driving engine, make aircaft configuration and aerodynamic arrangement more reasonable, fuel oil and electric energy used in combination, efficiency reasonable disposition can be realized, vertical and short take-off and landing can be realized, have the advantages that flight is steady, applied widely, with low cost flexibly.
In sum, owing to have employed technique scheme, the invention has the beneficial effects as follows:
1, can take off and land by static vertical
Aircraft of the present invention can vertical and landing takeoff, reduces flying field area: this aircraft can verting by driving engine, completes the conversion of power direction.The power of vertical direction verts for the power in horizontal direction by the present invention, instead of the effect of vector spray, reduces overall aircraft cost, alleviates the deadweight of aircraft, adds the load carrying ability of aircraft.Vertical takeoff and landing function of the present invention, can allow aircraft complete taking off and landing on warship deck or under state of ground complex environment, add the field of application of aircraft.
2, the present invention can avoid the novel long-term R & D flying to control
Present invention, avoiding the novel exploitation flying to control, reduce R&D costs: the present invention adopts fixed-wing to fly control and Multi-axis aircraft flies to control the form combined, because two kinds of research and development flying to control are very ripe, direct employing two kinds flies control and to combine form, greatly R&D costs be can reduce, and stability and the reliability of aircraft increased.The present invention, when horizontal flight, uses fixed-wing to fly control, can improve the stability of flight; When vertical and landing takeoff, adopt multiaxis to fly control, aircraft can be allowed to carry out stable taking off and land.Further, the fixed-wing in the present invention flies control and multiaxis and flies control and do not conflict, as long as turn off electric ducted fan, multiaxis flies control and just no longer has an impact to aircraft.
3, the power supply that the present invention can realize continuing supplies
On driving engine in the present invention, configuration is provided with high-speed power generation module, sustainable outside output electric energy.Electric energy is synchronously incorporated to and powers to ducted fan and control system by power-supply management system, or powers to control system and charge a battery.
4, the present invention can realize hovering, low cruise and high-speed flight
Aircraft of the present invention can change the direction of main thrust by the mode of rotary engine, main thrust direction lockable be horizontal forward angle 0 °, 30 °, 45 °, 60 °, 90 °, 100 °.When engine thrust direction is level angle 0 ° to 90 °, the lift or part lift that overcome aircraft deadweight can be provided, realizes at a high speed to low cruise.When engine thrust direction is level angle 90 ° to 100 °, while the lift overcoming aircraft deadweight can be provided, realize decelerating flight.These are for fixed point investigation and antisubmarinely provide sound assurance, may be used for ground assault and investigate at a high speed.
Accompanying drawing explanation
Examples of the present invention will be described by way of reference to the accompanying drawings, wherein:
Fig. 1 is integral structure schematic diagram of the present invention.
Fig. 2 is the birds-eye view of Fig. 1.
Fig. 3 is Circuits System control chart of the present invention.
Fig. 4 is the flight course realization figure of aircraft of the present invention.
Mark in figure: 1 is fuselage, and 2 is host wing, and 3 is elevon, 4 is canard, and 5 is vertical tail, and 6 is alighting gear, 7 is fuel tank, and 8 is storage battery, and 9 is control system, 10 is power-supply management system, 11 is electric ducted fan, and 12 is guiding rudder face, and 13 is Sloped rotating mechanism, 14 is driving engine, and 15 is power generating system.
Detailed description of the invention
All features disclosed in this specification sheets, or the step in disclosed all methods or process, except mutually exclusive feature and/or step, all can combine by any way.
Arbitrary feature disclosed in this specification sheets, unless specifically stated otherwise, all can be replaced by other equivalences or the alternative features with similar object.That is, unless specifically stated otherwise, each feature is an example in a series of equivalence or similar characteristics.
Embodiment 1
As shown in the figure, the unmanned vehicle of the present embodiment, comprise fuselage, the host wing be arranged on fuselage, the elevon be arranged on host wing, be arranged on forebody canard, be arranged on fuselage afterbody vertical tail, be arranged on alighting gear, fuel tank, storage battery, control system, power-supply management system below fuselage.
Host wing is triangular in shape, elevon, canard, vertical tail are symmetricly set on the line of centers both sides of fuselage respectively, the head of fuselage is provided with electric ducted fan, the wingtip of host wing both sides is symmetrically arranged with electric ducted fan respectively, be provided with guiding rudder face immediately below electric ducted fan, arrange in equilateral triangle non-co-planar between three groups of electric ducted fans.
The U-shaped structure of fuselage adopted implemented by book, fuselage adopts lifting body head, Die Design is that lifting body and fuselage merge, the middle part of fuselage is fixedly installed Sloped rotating mechanism, Sloped rotating mechanism is provided with driving engine, driving engine is positioned at the geometric centre of electric ducted fan triangular arrangement, and driving engine is provided with power generating system.In the present embodiment, driving engine adopts turbojet engine or fanjet.The position of the electric ducted fan place horizontal surface on head is lower than the position of electric ducted fan place, host wing both sides horizontal surface, and diff-H is preferably 1.5-3 times of turbojet engine diameter.Fuel tank, storage battery are separately positioned in fuselage, and power generating system is connected with power-supply management system, and power-supply management system is connected with control system, storage battery, electric ducted fan respectively.Driving engine is the one in turbojet engine, fanjet, the dynamic driving engine of oil.Alighting gear adopts three shock-absorbing alighting gears, is distributed in below fuselage, and fuel tank is soft capsule fuel tank.
The layout of the present embodiment is adopted as equilateral triangle and arranges, is equipped with rotatable whirlpool spray/fanjet, thus realizes the vertical takeoff and landing of unmanned plane.Three groups of electric ducted fans lay respectively on the Handpiece Location of fuselage and the wingtip of host wing both sides, arrange in equilateral triangle, at stage of taking off vertically of unmanned plane, vertical landing stage, hovering stage auxiliary balance unmanned plane.
Be provided with guiding rudder face immediately below electric ducted fan, be responsible for the driftage of adjustment unmanned plane and offset by the reverse torsion produced when electric ducted fan and engine running.Arrange in equilateral triangle non-co-planar between three groups of electric ducted fans, driving engine is positioned at the geometric centre of electric ducted fan, to ensure the auxiliary balance not affecting electric ducted fan.Under the drive of Sloped rotating mechanism, driving engine can do pitch motion with different flight state relative to main machine body.Unmanned plane, in flight course, when driving engine does pitch motion, there will be pitching overbalance, the present invention arranges canard in both sides, main machine body front end, elevon collocation simultaneously regulates, to ensure that unmanned plane is in state of flight switching process, and pitching trim when pitching balance and high maneuver flight.Host wing is triangular in shape, under equalling at unmanned plane the state flown, and can completely with the high-speed flight of fixed-wing form.Fuselage length of the present invention is comparatively large, and therefore adopt two vertical tail layout, vertical tail is responsible for the yawed flight of unmanned plane, to ensure the longitudinal stability of unmanned plane, avoids the tail jet of whirlpool spray/fanjet simultaneously.Fuselage of the present invention adopts lifting body head, and lifting body structure and fuselage combine together, the lift demand effectively during guarantee horizontal flight and balance.The fuel tank of the present embodiment is preferably soft capsule fuel tank, and the soft capsule fuel tank of fuselage heavy cartridges, makes fuselage have maximized year oily space, ensures to fly for a long time.
The flight course of the present embodiment unmanned vehicle is mainly divided into three mission phases: takeoff phase (A stage), mission phase (B-stage), landing phases (C stage).Be divided into two kinds of forms takeoff phase: rolling start, to take off vertically.Mission phase is divided into two kinds of forms: maneuvering flight, hovering.Landing phases is divided into two kinds of forms: slide landing, vertical landing.
The Circuits System of unmanned plane is that oil-fired power generating is to Circuits System supply form.When level cruise is flown, electric ducted fan quits work, and power generating system generates electricity, and is charged in power distribution to the control circuit of control system and to storage battery by power-supply management system.When vertical flight, electric ducted fan work, power generating system generates electricity, and electric energy and storage battery electric energy combined control circuit and electric ducted fan is powered by power-supply management system.
Rolling start, maneuvering flight, slide landing identical with principle with the control form of common fixed wing aircraft.
The present embodiment unmanned vehicle takes off vertically to safe altitude, controls three electric ducted fans and unmanned plane acceleration level is moved, and in this process, flies control and controls unmanned vehicle parallel motion with the mode of Multi-axis aircraft; When reaching setting safe flight speed I, start the driving engine that verts, after driving engine completes and verts, when reaching setting safe flight speed II, close electric ducted fan, fly control simultaneously and switch to fixed-wing master mode, control unmanned plane during flying with the mode of fixed wing aircraft, now unmanned plane completes whole taking off to the flat switching process flown.In the process that unmanned plane was changed to landing phases in the flat stage that flies, whirlpool spray/fanjet starts to vert to vertical direction, adjust the control of elevon simultaneously, the overall camber changing wing, increase the lift of wing, unmanned vehicle reduces speed now flight, when reaching setting safe flight speed III, open electric ducted fan, after whirlpool spray/fanjet completes vert completely, when reaching setting safe flight speed IV, conversion flies control, fly control and control unmanned plane with the mode of Multi-axis aircraft, reach sustained hover, now unmanned plane both can continue hovering, also vertical landing can be realized by safety and precise.
The driving engine of the present embodiment unmanned vehicle also can be the dynamic engine prop form of oil, and its basis and principle are constant, are all that the new layout of hybrid power can vertical take-off and landing unmanned aerial vehicle.
The present invention is not limited to aforesaid detailed description of the invention.The present invention expands to any new feature of disclosing in this manual or any combination newly, and the step of the arbitrary new method disclosed or process or any combination newly.
Claims (6)
1. a hybrid power vertical/short take off and landing unmanned vehicle, it is characterized in that, comprise fuselage, the host wing be arranged on fuselage, the elevon be arranged on host wing, be arranged on forebody canard, be arranged on fuselage afterbody vertical tail, be arranged on alighting gear, fuel tank, storage battery, control system, power-supply management system below fuselage;
Described host wing is triangular in shape, described elevon, canard, vertical tail are symmetricly set on the line of centers both sides of fuselage respectively, described fuselage is provided with electric ducted fan, the wingtip of described host wing both sides is symmetrically arranged with electric ducted fan respectively, guiding rudder face is provided with immediately below three electric ducted fans, three described electric ducted fans are the distribution of equilateral triangle non-co-planar, and the position of the electric ducted fan place horizontal surface on described fuselage is lower than the position of electric ducted fan place, host wing both sides horizontal surface;
Described fuselage is U-shaped, described fuselage adopts lifting body head, and the middle part of described fuselage is fixedly installed Sloped rotating mechanism, and described Sloped rotating mechanism is provided with driving engine, described driving engine is positioned at the geometric centre of three electric ducted fans, and described driving engine is provided with power generating system;
Described fuel tank, storage battery are separately positioned in fuselage, and described power generating system is connected with power-supply management system, and described power-supply management system is connected with control system, storage battery, electric ducted fan respectively.
2. hybrid power vertical/short take off and landing unmanned vehicle according to claim 1, is characterized in that, described driving engine is the dynamic driving engine of oil.
3. hybrid power vertical/short take off and landing unmanned vehicle according to claim 1, it is characterized in that, described driving engine is turbojet engine or fanjet.
4. hybrid power vertical/short take off and landing unmanned vehicle according to claim 3, it is characterized in that, relative height between the position of the electric ducted fan place horizontal surface on described fuselage and the position of electric ducted fan place, host wing both sides horizontal surface is poor, for turbojet engine or fanjet diameter 1.5-3 doubly.
5. hybrid power vertical/short take off and landing unmanned vehicle according to any one of claim 1 ~ 4, is characterized in that, described alighting gear is shock-absorbing alighting gear, and described alighting gear is three.
6. hybrid power vertical/short take off and landing unmanned vehicle according to any one of claim 1 ~ 4, is characterized in that, described fuel tank is soft capsule fuel tank.
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| CN107399432A (en) * | 2017-06-20 | 2017-11-28 | 深圳高科新农技术有限公司 | VTOL fixed-wing unmanned plane structure |
| US10822101B2 (en) * | 2017-07-21 | 2020-11-03 | General Electric Company | Vertical takeoff and landing aircraft having a forward thrust propulsor |
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