CN202728574U - Composite aircraft with fixed wing and electric multiple propellers combined and with helicopter function - Google Patents
Composite aircraft with fixed wing and electric multiple propellers combined and with helicopter function Download PDFInfo
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- CN202728574U CN202728574U CN 201120397882 CN201120397882U CN202728574U CN 202728574 U CN202728574 U CN 202728574U CN 201120397882 CN201120397882 CN 201120397882 CN 201120397882 U CN201120397882 U CN 201120397882U CN 202728574 U CN202728574 U CN 202728574U
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
- B64C29/0025—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being fixed relative to the fuselage
Abstract
The utility model discloses a composite aircraft with a fixed wing and electric multiple propellers combined and with a helicopter function. The composite aircraft comprises a set of fixed-wing airplane components which comprise an airplane body, airplane wings and a fixed-wing plane control system. The aircraft further comprises a group of electric multi-propeller power systems and a chief controller which comprises a fixed-wing plane control system and an electric multi-propeller control system which is used for controlling the electric multi-propeller power systems to work. The chief controller is also used for controlling the fixed-wing plane control system and the electric multi-propeller control system to work independently or work cooperatively. The paddle rotating planes of the electric multi-propeller power systems are perpendicular to the central axis of the airplane body. The aircraft can achieve free switching between the two flying modes, not only are vertical take-off and landing and flying like a helicopter achieved, take-off and landing and flying like a fixed-wing airplane achieved, but also the aircraft can switch to the fixed-wing mode to fly after taking off in the helicopter mode, and then land switching to the helicopter mode.
Description
Technical field
The utility model relates to a kind of aircraft, particularly relates to the composite aircraft with helicopter function that a kind of fixed-wing and electronic many oars form.
Background technology
At the common fixed wing aircraft of aviation field, because main by wing generation lift balance airplane weight, power system is mainly used to overcome the aircraft flight resistance, and therefore the power (push-pull effort) much smaller than aircraft weight just can allow fixed wing aircraft lift off.Its flying speed is fast, and voyage and cruise time are long, but the landing distance requires the special quality runway, has had a strong impact on and hindered fixed wing aircraft in remote application without the special machine Performance Area.
At the common heligyro of aviation field, can solve the problem in the narrow and small place vertical takeoff and landing.In known rotor craft, except common single-rotor helicopter, also have many oars helicopter, many oars helicopter generally is to come the change of flight attitude by the rotating speed that changes oar.Such as 4 oar heligyroes, 4 oars are placed with respect to Central Symmetry, and it is clickwises that 2 oars are wherein arranged, and also having 2 oars is anticlockwise direction rotations.When aircraft needs toward a directional steering, increase the wherein rotating speed of 2 cw/conter clockwise oars as long as change, the rotating speed that reduces other 2 conter clockwises/cw oar just can change course.When needing heeling, as long as reduce the rotating speed of the oar on the heading, the rotating speed that increases the oar of symmetric position just can be by the poor direction flight to appointment of lift.
But the rotor efficient that directly links to each other with power system can not show a candle to the wing of fixed wing aircraft, so power consumption is large.Again because its speed of advance component that mainly inclination by tilting frame produces by rotor oar dish provides, the resistance of helicopter forward flight is also than large many of fixed wing aircraft simultaneously.Therefore its flying speed all is not so good as fixed wing aircraft in distance and cruise duration.The technical personnel of aviation field is being looked for the aircraft that can have fixed wing aircraft and helicopter advantage concurrently always for this reason.
Independent lift engine is simple in design, and lift engine is not worked when cruising, and takies again the machine inner volume, and this is deadweight.Reducing or eliminating deadweight is urgent problem of omniplane.Lift and cruising engine are united two into one, certainly just eliminated the deadweight of special-purpose lift engine.Cruise and the most direct method that unites two into one of lift engine, no more than the jet engine that verts, driving engine directly facing to the ground top blast, is just produced direct lift certainly.So simple reason, why not is the first-selection of omniplane? at first, the driving engine that verts brings very large restriction to driving engine position aboard, not only the position of wing, driving engine must be consistent with the center of gravity of aircraft, also basically only have under the wing or tip location, like this, in case part lift engine fault or momentary output are not enough, asymmetric lift easily causes catastrophic accident.Tilting rotor addresses this problem with synchronizing shaft, and the jet engine that verts just can not when a side power failure, be compensated by the opposite side driving engine substantially.Say, driving engine itself is very heavy again, and inclining rotary mechanism is easier said than done.Also have, driving engine is very high to the requirement of air inlet, otherwise the engine efficiency straight line descends, but driving engine is in the process of verting, and the condition of air inlet is difficult to guarantee.In addition, vertical takeoff and landing (VTOL) requires to produce at short notice a large amount of thrust, cruise require longevity of service but thrust far away otherwise so much, be difficult in design between the two coordinate.By the engine direct living lift of practicing midwifery, cannot resort to trickery to serve oneself.From extreme case, rolling start, produce lift with wing, only need thrust seldom; But take off vertically with jet power, need at least 1: 1 thrust-weight ratio, power requires much higher.
But have the vertical takeoff and landing function and have in the aircraft of fixed wing aircraft function known, roughly be divided into following a few class.One, such as Fig. 1, the scheme that ducted fan and advancing blade 11 are combined.Such as the unmanned plane Mariner of Xi Kesiji, the XV-5 of General Corporation etc.The shortcoming of this aircraft is that duct has increased heavier weight, increases more frontal resistance, has hindered simultaneously the layout of the interior load of machine and equipment, has perhaps reduced the effective lift area of wing.
Two, the power that verts is realized the fixed wing aircraft of vertical takeoff and landing.Such as V22 among Fig. 2 etc., wherein screw propeller is 12.This class aircraft (drawing) power that pushes away vertical ground of engine installation when taking off makes aircraft vertically liftoff, then makes gradually (drawing) power that pushes away of engine installation aloft, turns to the aircraft working direction, makes aircraft forward flight as conventional fixed wing aircraft.But its steering hardware is complicated, and cost is expensive, poor reliability, and when advancing speed (aircraft without) stability and the road-holding property when special power system turns to is puzzlement aeronautical technology personnel's a difficult problem always.
Three, the rotor wing shares aircraft." dragonfly " aircraft such as Boeing among Fig. 3 a-3c.This class aircraft wing 13 can become rotor to be used, and can realize vertical takeoff and landing.The same with the power aerial vehicle that verts, also there is complex structure, cost is expensive, the problems such as poor reliability.
The scheme of four, such as bottom among Fig. 4 a-4c lift engine 14 being installed.This class aircraft all is in order to solve the problem of fixed wing aircraft vertical takeoff and landing, and lift engine is the lift when realizing vertical takeoff and landing or double as a part of direction control just, does not possess completely helicopter flight pattern, such as aircrafts such as many Neils DO.231.
Five, the Ya Ke of the former Soviet Union-38 opportunity of combat only has two lift engines and a lift-cruising engine, and the lift engine in the body has also reduced single-shot and lost efficacy to the threat of safety.But lift engine is installed in the body, and its problem is also arranged.At first, red-hot jet inner engine inlet port is very near, easily causes jet resorption problem.The second, high speed jet on the downward ground of body to two side flow, and body top near the lift engine admission port, air is relatively static, causes the effect that body is adsorbed earthward, i.e. so-called suck down.In addition, because its above deck vertical takeoff and landing (VTOL), the high-temperature gas of its ejection downwards is also quite serious to the ablation on deck, so this opportunity of combat is very impracticable.
Therefore aeronautical chart is in the urgent need to seeking a kind of aircraft that has fixed wing aircraft and heligyro performance concurrently and can freely change at any time of simple in structure, dependable performance between two kinds of offline mode.
The utility model content
The technical problems to be solved in the utility model is in order to overcome defects of the prior art, and a kind of aircraft that has fixed wing aircraft and heligyro performance concurrently and can freely change at any time between two kinds of offline mode of simple in structure, dependable performance is provided.
The utility model solves above-mentioned technical matters by following technical proposals:
The composite aircraft with helicopter function that a kind of fixed-wing and electronic many oars form, comprise a cover fixed wing aircraft assembly, this assembly comprises fuselage, wing and fixed-wing rudder surface control system, its characteristics are, this aircraft also comprises one group of electronic many oars power system and a master controller, this master controller comprises this fixed-wing rudder surface control system and for electronic many blade control systems of controlling the work of described electronic many oars power system, this master controller also is used for this fixed-wing rudder surface control system of control and electronic many blade control systems and works independently or collaborative work; The blade plane of rotation of described electronic many oars power system is vertical with the fuselage center shaft.
Preferably, these electronic many blade control systems are used for lifting, attitude and the course of control aircraft.
Preferably, these electronic many blade control systems are used for the lifting by rotating speed and/or the pitch control aircraft of all blades of increase and decrease.
Preferably, these electronic many blade control systems are used for by reducing rotating speed and/or the pitch of blade forward with respect to the center of gravity of aircraft on heading, be increased in simultaneously on the heading rotating speed and/or the pitch of the blade after leaning on respect to the center of gravity of aircraft, the attitude of control aircraft.
Preferably, these electronic many blade control systems are used for turning to by increase and aircraft rotating speed and/or the pitch of reverse blade, reduce the rotating speed and/or the pitch that turn to blade in the same way with aircraft, the course of control aircraft.
Preferably, described electronic many oars power system is at least quadruplet, and described each oar is in the same plane, and this plane is vertical with the fuselage line of centers.
Preferably, described each oar is separately positioned on both sides and the wing upper and lower sides of this fuselage, is symmetrical with respect to the center of gravity of this aircraft and places.
Preferably, the electronic many oars power system of described every cover or oar all are connected on described fuselage or the wing by a hold-down arm.
Preferably, described some cover systems or the shared hold-down arm of some cover oars that respectively overlaps in electronic many oars power system is connected on this fuselage or the wing.
Preferably, the engine installation of described electronic many oars power system is motor.
Preferably, described master controller comprises one first cooperative work mode controller: be used for being controlled at the switching process from many oars helicopter flight pattern to the fixed-wing offline mode, aircraft is by beginning from hovering by the increase of control body upper blade rotating speed, the below rotating speed reduces, the aircraft flight direction is gradually from vertical direction steering horizontal direction, aircraft progressively turns to the mode of fixed wing aircraft horizontal motion, after the air speed of corresponding fuselage direction is greater than stalling speed, the rotating speed of each oar becomes identical, the fixed-wing rudder surface control system is controlled rudder face simultaneously, has just finished the conversion of many oars helicopter flight pattern and fixed-wing offline mode.
Preferably, described master controller comprises one second cooperative work mode controller: be used for being controlled at from the fixed-wing offline mode to many oars helicopter flight pattern switching process, aircraft is begun by horizontal motion, control fuselage below blade rotating speed increases first, top blade rotating speed progressively increases after reaching certain angle of attack, the aircraft flight direction is climbed rear steering perpendicular to ground from level gradually, and the air speed vanishing realizes that the fixed-wing offline mode is to the conversion of many oars helicopter flight pattern.
Preferably, described angle of attack angle is 10 °-30 °.
Preferably, the tail structure of described aircraft for not with the flying wing type of empennage,
Shape, " T " font, " V " shape or " Λ " shape.
Preferably, this aircraft also comprises the alighting gear that one group of vertical takeoff and landing that additionally is arranged at afterbody is used.
Preferably, described oar is collapsible oar.
Preferably, described aircraft comprises a fixed-wing power system.
Preferably, described fixed-wing power system is electronic or fuel power.
Positive progressive effect of the present utility model is:
Composite aircraft of the present utility model not only has the performance of fixed wing aircraft and heligyro concurrently, and can between these two kinds of offline mode, change freely, both can vertical takeoff and landing and flight as helicopter, can landing and flight as fixed wing aircraft.
The utility model is because employing is electronic, so the weight increase is very light, thereby the deadweight that increases when making the fixed wing aircraft pattern (weight of heligyro part) seldom.Simultaneously owing to being electric-powered scheme, whole Aircraft noise is very little, and heligyro is to the air-flow of blowing down without high temperature, than the more environmental protection of other aircraft with conventional engines.In addition, adopt motor as engine installation, the weight control that can make electronic many rotors power system whole aircraft 20% in, traditional power system is gently a lot of than adopting, thereby makes aircraft more be easy to control, saves energy.
The utility model is structurally simpler, does not need very complicated steering structure, also can not affect the layout of the interior load of machine and equipment.At last, the utility model is widely used, and comprises civil aviaton field and military field, and be not only applicable to the model of an airplane and be applicable to robot airplane, and manned aircraft etc.
Description of drawings
Fig. 1 is the existing Flight Vehicle Structure schematic diagram that ducted fan and advancing blade are combined.
Fig. 2 is the Flight Vehicle Structure schematic diagram that the existing power that verts is realized vertical takeoff and landing.
Fig. 3 a-3c is the Flight Vehicle Structure schematic diagram that existing rotor wing shares.
Fig. 4 a-4c is the Flight Vehicle Structure schematic diagram that lift engine is installed in existing bottom.
Fig. 5 a-5c is respectively birds-eye view, front elevation and the lateral plan of the aircraft of the utility model the first embodiment.
Fig. 6 is the structural representation of flight control of the present utility model.
Fig. 7 a, 7b are respectively front elevation and the birds-eye view of the aircraft of the utility model the second embodiment.
The specific embodiment
Provide the utility model preferred embodiment below in conjunction with accompanying drawing, to describe the technical solution of the utility model in detail.
The first embodiment
Be illustrated in figure 5 as a kind of composite aircraft of the present utility model, it comprises a cover fixed wing aircraft assembly, and this assembly comprises fuselage 1, main wing 2, empennage 3.Also can be according to circumstances and Dingan County's dress fixed-wing power system (also claiming the fixed wing aircraft power system), be the system that the fixed wing aircraft assembly provides power.The main wing and the fixed-wing that occur in it will be appreciated by those skilled in the art that in full refer to same parts, are called fixed-wing with respect to rotor; Being called main wing, is to form from the structure of aircraft, with respect to empennage.On the basis of this fixed wing aircraft assembly, increase the electronic many oars power system 4 of quadruplet, but be not limited to quadruplet, also can be six covers or eight covers etc., and electronic many oars power system 4 can adopt existing concrete the Nomenclature Composition and Structure of Complexes to realize, so repeat no more.
And electronic many oars power system 4 comprises engine installation and oar, and described each oar can be arranged in the same plane, and this plane is vertical with the fuselage line of centers, namely is centered around the fuselage center shaft and becomes the approximate radial distribution of isogonism on every side.Particularly, can be separately positioned on oar both sides and the main wing upper and lower sides of this fuselage, be symmetrical with respect to the center of gravity of this aircraft and place, engine installation is arranged on the fuselage.Perhaps the electronic many oars power system 4 of the whole series is separately positioned on both sides and the main wing upper and lower sides of this fuselage, is symmetrical with respect to the center of gravity of this aircraft and places.Arranging like this guaranteed that the whole center of gravity of aircraft is on the line of centers of fuselage, makes aircraft remain balance in landing and flight course, do not affect its mode of operation.Certainly, also can adopt other position to arrange, all can as long as can reach the set-up mode of aforementioned effect.In the present embodiment, the electronic many oars power system 4 of every cover integrally or oar be connected on the main wing 2 by a hold-down arm 5 individually, some cover systems or the shared hold-down arm of oar that also each can be overlapped in electronic many oars power system certainly in other embodiments, are connected on fuselage or the wing.
Electronic many oars power system in the present embodiment adopts electric-powered system, comprises motor and the rotor that is connected with this motor, can determine whether to add change speed gear box according to actual conditions.Because adopt electronicly, so the weight increase is very light, thereby the deadweight that increases when making the fixed wing aircraft pattern (heligyro part weight) seldom.Simultaneously owing to being electric-powered scheme, whole Aircraft noise is very little, and heligyro is to the air-flow of blowing down without high temperature, than the more environmental protection of other aircraft with conventional engines.And the power of fixed-wing power system also can adopt electronic or other power.The quantity of fixed-wing power system can be single cover or many covers, and the screw propeller of fixed-wing power system is positioned at fuselage the place ahead, fuselage afterbody or fuselage both sides, and perhaps front and back arrange simultaneously and all can.
For guarantee that aircraft of the present utility model switches freely between two kinds of patterns, be equipped with a master controller 6 to realize the switching controls between two kinds of patterns.This master controller 6 comprises fixed-wing rudder surface control system 61 and for electronic many blade control systems 62 of controlling the work of described electronic many oars power system, this master controller also is used for this fixed-wing rudder surface control system 61 of control and electronic many blade control systems 62 and works independently or collaborative work.Because fixed-wing rudder surface control system 61 can adopt the control system structure and composition of existing fixed wing aircraft to realize, do not give unnecessary details so do not do at this.Here, when fixed-wing rudder surface control system 61 works independently, cooperate the rotating speed of each oar identical, corresponding is the fixed wing aircraft pattern; Electronic many blade control systems 62 are corresponding when working independently to be helicopter mode, is used for lifting, attitude and the course of control aircraft, and is referred to as fixed wing aircraft helicopter mixed mode during two system synergistic workings.
For ease of those skilled in the art's understanding, the specific works principle that the below describes these three kinds of patterns in detail from landing process and the flight course of whole aircraft.It should be explicitly made clear at this point, flight course refers to the horizontal flight process of aircraft before landing after taking off, and lifting process refers to the process taking off and land.
Wherein landing process can adopt helicopter mode, fixed wing aircraft pattern:
1, when the helicopter mode landing, aircraft is placed perpendicular to ground, be the fuselage line of centers perpendicular to ground, and the plane of rotation of blade is parallel to ground, thus electronic many blade control systems 62 of realizing 4 groups (perhaps) fly according to helicopter mode fully.Use the vertical takeoff and landing consumption of power larger, but use the rotor jacking system time very short, it is little that the landing consumed energy accounts for whole flight energy consumption energy proportion, thus this mode main landing pattern that is this aircraft, this moment aircraft as the same landing of helicopter.This landing mode not only is applicable to the model of an airplane and unmanned plane, and is applicable to manned aircraft, and existing suspension gear is set in manned aircraft, and when making aircraft no matter be lifting or horizontal flight, human body can both keep normal state, can not tilt.
2, when the landing of fixed wing aircraft pattern, the aircraft level places ground, be that the fuselage line of centers is parallel to ground, and the plane of rotation of blade is approximately perpendicular to ground, each oar rotating speed is identical, thereby makes 4 groups (perhaps) electronic many blade control systems 62 as fixed wing aircraft power system group.Aircraft as the same landing on runway of fixed wing aircraft.
And offline mode can be divided into helicopter mode, fixed wing aircraft pattern:
1, when helicopter mode flies, 4 groups (perhaps) electronic many blade control systems 62 fly according to helicopter mode fully, aircraft can be finished the function of all helicopters, thus can finish take photo by plane, the task such as fixed position investigation, this moment aircraft as helicopter equally fly.When this kind mode was flown, the fuselage line of centers was perpendicular to ground, and the plane of rotation of blade is parallel to ground.Wherein, electronic many blade control systems are by reducing rotating speed and/or the pitch of oar forward with respect to the center of gravity of aircraft on heading, be increased in simultaneously on the heading rotating speed and/or the pitch of the oar after leaning on respect to the center of gravity of aircraft, control the attitude of aircraft.Electronic many blade control systems reduce the rotating speed and/or the pitch that turn to oar in the same way with aircraft by increasing rotating speed and/or the pitch that turns to reverse oar with aircraft, the course of control aircraft.
Specifically, make exactly the wherein oar clockwise direction rotation of half, second half oar anticlockwise direction rotation under helicopter mode, can utilize the rotating speed of 4 oars of electronic gyroscope control, forms a stable heligyro flying platform.By changing the oar rotating speed, change lift and the moment of torsion of 4 oars, thereby the control heligyro is to the flight of all directions and turn to.Wherein electronic gyroscope is this area device commonly used, and technical personnel can be selected its type according to concrete needs oneself.
2, when the fixed wing aircraft pattern is flown, 4 groups (perhaps) electronic many blade control systems 62 are as the fixed-wing aircraft power system.Can finish the function of all fixed wing aircrafts.Advantage is that power consumption is little, and flying distance and time are long.This pattern is the main offline mode of this aircraft.Owing to not needing so large power, so can only drive part oar wherein, other oars can fold to reduce the flight resistance under the fixed wing aircraft pattern after converting the fixed-wing aircraft pattern to.
When fixed-wing rudder surface control system 61 and electronic many blade control system 62 collaborative works, the switching process of fixed-wing pattern flight that flies from many oars helicopter mode, aircraft is by beginning from hovering by the increase of control body upper blade rotating speed, the below rotating speed reduces, the aircraft flight direction is gradually from vertical direction steering horizontal direction, aircraft progressively turns to the mode of fixed wing aircraft horizontal motion, after the air speed of corresponding fuselage direction is greater than stalling speed, the rotating speed of each oar becomes identical, the fixed-wing rudder surface control system is controlled rudder face simultaneously, has just finished the conversion of many oars helicopter mode flight with the flight of fixed-wing pattern.When that is to say helicopter mode lifting or flight, oar is the function that plays lifting airscrew; And when being transformed into the fixed-wing pattern, each oar rotating speed is identical, and what this moment, oar played is the effect that fixed wing aircraft advances oar.
Many oars helicopter mode flight switching process that flies from the fixed-wing pattern, aircraft is begun by horizontal motion, control fuselage below blade rotating speed increases first, top blade rotating speed progressively increases after aircraft reaches certain angle of attack (between such as 10 °-30 °), the aircraft flight direction is climbed rear steering perpendicular to ground from level gradually, the air speed vanishing, those skilled in the art are to be understood that situation about also comprising close to zero, realize the fly conversion of many oars helicopter mode flight of fixed-wing pattern.Above two kinds of situations can realize by two cooperative work mode controllers respectively.
Sum up, in other words in whole helicopter mode, the fuselage line of centers all is perpendicular to ground, and certainly this vertically is be similar to vertical, and those skilled in the art are to be understood that.
The concrete making of above-mentioned master controller, each control system all can realize by existing electronic control mode or software mode with realization, not do at this and give unnecessary details.
In other embodiments, the tail structure of fixed-wing aircraft assembly of the present utility model can also be other types, as not with the flying wing type of empennage,
Shape,
" T " font, " V " shape or " Λ " shape etc.
The second embodiment
Such as Fig. 7 a, 7b, the difference of the present embodiment and the first embodiment mainly is: the electronic many oars power system of 6 covers is arranged in the present embodiment, be the radial position that is installed in close main wing on the fuselage.Remainder and the first embodiment are basic identical.
Among the figure, 6 oars all increase or reduce rotating speed during lifting.When flying to the left: oar 73,74 speedups, oar 71,76 slows down.When flying to the right: oar 71,76 speedups, oar 73,74 slows down.During left steering: oar 71,73,75 speedups, oar 72,74,76 slows down; During right steering: oar 72,74,76 speedups, oar 71,73,75 slows down; Before fly: oar 74,76 speedups, oar 71,73 slows down; After fly: oar 71,73 speedups, oar 74,76 slows down.
Although more than described the specific embodiment of the present utility model, it will be understood by those of skill in the art that these only are casehistorys, protection domain of the present utility model is limited by appended claims.Those skilled in the art can make various changes or modifications to these embodiments under the prerequisite that does not deviate from principle of the present utility model and essence, but these changes and modification all fall into protection domain of the present utility model.
Claims (14)
1. the composite aircraft with helicopter function that forms of a fixed-wing and electronic many oars, comprise a cover fixed wing aircraft assembly, this assembly comprises fuselage, wing and fixed-wing rudder surface control system, it is characterized in that, this aircraft also comprises one group of electronic many oars power system and a master controller, this master controller comprises this fixed-wing rudder surface control system and for electronic many blade control systems of controlling the work of described electronic many oars power system, this master controller also is used for this fixed-wing rudder surface control system of control and electronic many blade control systems and works independently or collaborative work; The blade plane of rotation of described electronic many oars power system is vertical with the fuselage center shaft.
2. the composite aircraft with helicopter function of fixed-wing as claimed in claim 1 and electronic many oar compositions is characterized in that, described electronic many oars power system is at least quadruplet, and described each oar is in the same plane, and this plane is vertical with the fuselage line of centers.
3. the composite aircraft with helicopter function that forms of fixed-wing as claimed in claim 2 and electronic many oar is characterized in that, described each oar is separately positioned on both sides and the wing upper and lower sides of this fuselage, is symmetrical with respect to the center of gravity of this aircraft and places.
4. the composite aircraft with helicopter function of fixed-wing as claimed in claim 2 and electronic many oar compositions is characterized in that, the electronic many oars power system of described every cover or oar all are connected on described fuselage or the wing by a hold-down arm.
5. the composite aircraft with helicopter function that forms of fixed-wing as claimed in claim 2 and electronic many oar, it is characterized in that, described some cover systems or the shared hold-down arm of some cover oars that respectively overlaps in electronic many oars power system is connected on this fuselage or the wing.
6. the composite aircraft with helicopter function of fixed-wing as claimed in claim 1 and electronic many oar compositions is characterized in that, the engine installation of described electronic many oars power system is motor.
7. the composite aircraft with helicopter function that forms of fixed-wing as claimed in claim 1 and electronic many oar, it is characterized in that, described master controller comprises one first cooperative work mode controller: be used for being controlled at the switching process from many oars helicopter flight pattern to the fixed-wing offline mode, aircraft is by beginning from hovering by the increase of control body upper blade rotating speed, the below rotating speed reduces, the aircraft flight direction is gradually from vertical direction steering horizontal direction, aircraft progressively turns to the mode of fixed wing aircraft horizontal motion, after the air speed of corresponding fuselage direction is greater than stalling speed, the rotating speed of each oar becomes identical, the fixed-wing rudder surface control system is controlled rudder face simultaneously, has just finished the conversion of many oars helicopter flight pattern and fixed-wing offline mode.
8. the composite aircraft with helicopter function that forms of fixed-wing as claimed in claim 1 and electronic many oar, it is characterized in that, described master controller comprises one second cooperative work mode controller: be used for being controlled at from the fixed-wing offline mode to many oars helicopter flight pattern switching process, aircraft is begun by horizontal motion, control fuselage below blade rotating speed increases first, top blade rotating speed progressively increases after aircraft reaches certain angle of attack, the aircraft flight direction is climbed rear steering perpendicular to ground from level gradually, the air speed vanishing realizes that the fixed-wing offline mode is to the conversion of many oars helicopter flight pattern.
9. the composite aircraft with helicopter function of fixed-wing as claimed in claim 8 and electronic many oar compositions is characterized in that, described angle of attack angle is 10 °-30 °.
10. the composite aircraft with helicopter function that forms of fixed-wing as claimed in claim 1 and electronic many oar is characterized in that, the tail structure of described aircraft for not with the flying wing type of empennage,
Shape, " T " font, " V " shape or " Λ " shape.
11. the composite aircraft with helicopter function that fixed-wing as claimed in claim 1 and electronic many oar form is characterized in that, this aircraft also comprises the alighting gear that one group of vertical takeoff and landing that additionally is arranged at afterbody is used.
12. the composite aircraft with helicopter function such as the described fixed-wing of claim 1-11 any one and electronic many oar compositions is characterized in that described oar is collapsible oar.
13. the composite aircraft with helicopter function that fixed-wing as claimed in claim 12 and electronic many oars form is characterized in that described aircraft comprises a fixed-wing power system.
14. the composite aircraft with helicopter function that fixed-wing as claimed in claim 13 and electronic many oars form is characterized in that described fixed-wing power system is electronic or fuel power.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120397882 CN202728574U (en) | 2011-10-17 | 2011-10-17 | Composite aircraft with fixed wing and electric multiple propellers combined and with helicopter function |
| PCT/CN2011/083301 WO2013056492A1 (en) | 2011-10-17 | 2011-12-01 | Composite aircraft consisting of fixed-wing and electrically driven propellers and having helicopter functions |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120397882 CN202728574U (en) | 2011-10-17 | 2011-10-17 | Composite aircraft with fixed wing and electric multiple propellers combined and with helicopter function |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202728574U true CN202728574U (en) | 2013-02-13 |
Family
ID=47654301
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201120397882 Expired - Lifetime CN202728574U (en) | 2011-10-17 | 2011-10-17 | Composite aircraft with fixed wing and electric multiple propellers combined and with helicopter function |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN202728574U (en) |
| WO (1) | WO2013056492A1 (en) |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103640690A (en) * | 2013-09-02 | 2014-03-19 | 张更生 | Method for vertical takeoff and landing and rapid flight through change of aircraft engines |
| CN105173076A (en) * | 2015-09-29 | 2015-12-23 | 上海圣尧智能科技有限公司 | VTOL (vertical take-off and landing) UAV (unmanned aerial vehicle) |
| CN105346725A (en) * | 2015-09-29 | 2016-02-24 | 上海圣尧智能科技有限公司 | Vertical take-off and landing unmanned aerial vehicle |
| CN106114854A (en) * | 2016-08-09 | 2016-11-16 | 烟台中飞海装科技有限公司 | A kind of push-button aircraft |
| CN106114853A (en) * | 2016-08-09 | 2016-11-16 | 烟台中飞海装科技有限公司 | A kind of push-button aircraft |
| CN107021219A (en) * | 2017-04-07 | 2017-08-08 | 南昌航空大学 | Fixed-wing unmanned plane and its control method |
| CN108860582A (en) * | 2017-05-08 | 2018-11-23 | 品尼高维斯塔有限责任公司 | More rotor lifting body aircraft with tail portion propeller |
| CN109305356A (en) * | 2017-08-29 | 2019-02-05 | 陕西安康领航智能股份有限公司 | A kind of tilting type vertical take-off and landing drone |
| CN110203387A (en) * | 2019-05-09 | 2019-09-06 | 深圳市禾启智能科技有限公司 | VTOL Fixed Wing AirVehicle |
| JP6609760B1 (en) * | 2018-09-22 | 2019-11-27 | 株式会社エアロネクスト | Flying object |
| JP2020147286A (en) * | 2020-06-18 | 2020-09-17 | 株式会社エアロネクスト | Flying body |
| CN112849403A (en) * | 2019-11-26 | 2021-05-28 | 上海峰飞航空科技有限公司 | Unmanned aerial vehicle and control method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ES2015827A6 (en) * | 1989-10-10 | 1990-09-01 | Del Campo Aguilera Juan | Remote-controlled equipment-carrying aircraft |
| CN101549754B (en) * | 2009-04-29 | 2012-05-23 | 北京航空航天大学 | A composite rotating fixed-wing aircraft and its design method |
| CN201923320U (en) * | 2011-01-13 | 2011-08-10 | 杨苡 | Twin-engine vertical take-off and landing fixed-wing unmanned aerial vehicle |
| CN102133926B (en) * | 2011-03-08 | 2013-05-08 | 上海大学 | Tailstock type vertical take-off and landing unmanned aerial vehicle |
-
2011
- 2011-10-17 CN CN 201120397882 patent/CN202728574U/en not_active Expired - Lifetime
- 2011-12-01 WO PCT/CN2011/083301 patent/WO2013056492A1/en active Application Filing
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103640690A (en) * | 2013-09-02 | 2014-03-19 | 张更生 | Method for vertical takeoff and landing and rapid flight through change of aircraft engines |
| CN105173076A (en) * | 2015-09-29 | 2015-12-23 | 上海圣尧智能科技有限公司 | VTOL (vertical take-off and landing) UAV (unmanned aerial vehicle) |
| CN105346725A (en) * | 2015-09-29 | 2016-02-24 | 上海圣尧智能科技有限公司 | Vertical take-off and landing unmanned aerial vehicle |
| CN106114853B (en) * | 2016-08-09 | 2019-05-10 | 烟台中飞海装科技有限公司 | A kind of push-button aircraft |
| CN106114853A (en) * | 2016-08-09 | 2016-11-16 | 烟台中飞海装科技有限公司 | A kind of push-button aircraft |
| CN106114854A (en) * | 2016-08-09 | 2016-11-16 | 烟台中飞海装科技有限公司 | A kind of push-button aircraft |
| CN106114854B (en) * | 2016-08-09 | 2019-06-25 | 烟台中飞海装科技有限公司 | A kind of push-button aircraft |
| CN107021219A (en) * | 2017-04-07 | 2017-08-08 | 南昌航空大学 | Fixed-wing unmanned plane and its control method |
| CN107021219B (en) * | 2017-04-07 | 2020-06-09 | 南昌航空大学 | Fixed-wing unmanned aerial vehicle and control method thereof |
| CN108860582A (en) * | 2017-05-08 | 2018-11-23 | 品尼高维斯塔有限责任公司 | More rotor lifting body aircraft with tail portion propeller |
| CN109305356A (en) * | 2017-08-29 | 2019-02-05 | 陕西安康领航智能股份有限公司 | A kind of tilting type vertical take-off and landing drone |
| JP6609760B1 (en) * | 2018-09-22 | 2019-11-27 | 株式会社エアロネクスト | Flying object |
| CN110203387A (en) * | 2019-05-09 | 2019-09-06 | 深圳市禾启智能科技有限公司 | VTOL Fixed Wing AirVehicle |
| CN112849403A (en) * | 2019-11-26 | 2021-05-28 | 上海峰飞航空科技有限公司 | Unmanned aerial vehicle and control method thereof |
| CN112849403B (en) * | 2019-11-26 | 2023-09-29 | 上海峰飞航空科技有限公司 | Unmanned aerial vehicle and control method thereof |
| JP2020147286A (en) * | 2020-06-18 | 2020-09-17 | 株式会社エアロネクスト | Flying body |
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| Publication number | Publication date |
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| WO2013056492A1 (en) | 2013-04-25 |
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Owner name: YUNEEC INTERNATIONAL CO.,LTD. Free format text: FORMER OWNER: TIAN YU Effective date: 20150708 Free format text: FORMER OWNER: JIANG WENYAN Effective date: 20150708 |
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Effective date of registration: 20160315 Address after: Hongkong Hongguang Road, Kowloon Bay China billion centre 10 floor Patentee after: You Li Science and Technology Ltd. Address before: Jinxi town Wei Road in Kunshan city Suzhou city Jiangsu province 215324 No. 388 Patentee before: Yuneec International co.,Ltd. |
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