CN202728575U - Composite aircraft with fixed wing and electric multi-rotor-wing combined - Google Patents

Composite aircraft with fixed wing and electric multi-rotor-wing combined Download PDF

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Publication number
CN202728575U
CN202728575U CN 201120397886 CN201120397886U CN202728575U CN 202728575 U CN202728575 U CN 202728575U CN 201120397886 CN201120397886 CN 201120397886 CN 201120397886 U CN201120397886 U CN 201120397886U CN 202728575 U CN202728575 U CN 202728575U
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CN
China
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wing
fixed
rotor
power
aircraft
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CN 201120397886
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Chinese (zh)
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田瑜
江文彦
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田瑜
江文彦
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Application filed by 田瑜, 江文彦 filed Critical 田瑜
Priority to CN 201120397886 priority Critical patent/CN202728575U/en
Priority claimed from PCT/CN2011/083305 external-priority patent/WO2013056493A1/en
Priority claimed from US13/704,056 external-priority patent/US20130092799A1/en
Application granted granted Critical
Publication of CN202728575U publication Critical patent/CN202728575U/en

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Abstract

The utility model discloses a composite aircraft with a fixed wing and an electric multi-rotor-wing combined. The composite aircraft comprises a group of electric multi-rotor-wing power systems and a chief controller. A fixed wing power system is independent of the electric multi-rotor-wing power systems in structure. The chief controller comprises a fixed wing control system and an electric multi-rotor-wing control system which is used for controlling the electric multi-rotor-wing power systems to work. The chief controller is also used for controlling the fixed wing control system and the electric multi-rotor-wing control system to work independently or work cooperatively. The rotor wing rotating planes of the electric multi-rotor-wing power systems are parallel with the central axis of an aircraft 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, take-off and landing and flying like a fixed-wing airplane are achieved, but also the mixed working mode of the two power systems during the take-off and landing and flying process can be achieved.

Description

The composite aircraft that fixed-wing and electronic many rotors form
Technical field
The utility model relates to a kind of aircraft, particularly relates to the composite aircraft that a kind of fixed-wing and electronic many rotors 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 Yan " 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 that a kind of fixed-wing and electronic many rotors form, comprise a cover fixed wing aircraft assembly, this assembly comprises fuselage, wing, fixed-wing power system and fixed-wing control system, this fixed-wing control system comprises fixed-wing power control system and fixed-wing rudder surface control system, its characteristics are, this aircraft also comprises one group of electronic many rotors power system and a master controller, described fixed-wing power system and electronic many rotors power system are structurally separate, this master controller comprises this fixed-wing control system and is used for electronic many rotor control systems of this electronic many rotors power system work of control, and this master controller also is used for this fixed-wing control system of control and electronic many rotor control systems and works independently or collaborative work; The rotor wing rotation plane of described electronic many rotors power system and fuselage central axes.
Preferably, these electronic many rotor control systems are used for lifting, attitude and the course of control aircraft.
Preferably, these electronic many rotor control systems are used for the lifting by rotating speed and/or the pitch control aircraft of all rotors of increase and decrease.
Preferably, these electronic many rotor control systems are used for by reducing rotating speed and/or the pitch of rotor 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 rotor after leaning on respect to the center of gravity of aircraft, the attitude of control aircraft.
Preferably, these electronic many rotor control systems are used for turning to by increase and aircraft rotating speed and/or the pitch of reverse rotor, reduce the rotating speed and/or the pitch that turn to rotor in the same way with aircraft, the course of control aircraft.
Preferably, described electronic many rotors power system is at least quadruplet, this system of every cover comprises engine installation and the rotor that is connected with this engine installation, and described each rotor is separately positioned on both sides and the wing front and back side of this fuselage, is symmetrical with respect to this this aircraft center of gravity and places; Perhaps described each electronic many rotors power system integral body is separately positioned on both sides and the wing front and back side of this fuselage, is symmetrical with respect to this aircraft center of gravity and places.
Preferably, the electronic many rotors power system of described every cover or rotor all are connected on this fuselage or the wing by a hold-down arm.
Preferably, described some cover systems or the shared hold-down arm of some cover rotors that respectively overlaps in electronic many rotors power system is connected on this fuselage or the wing.
Preferably, described engine installation is motor.
Preferably, described electronic many rotor control systems comprise a rotor blade position control unit, be used for when electronic many rotors power system is closed, during the unlatching of fixed-wing power system, the rotor blade position of controlling described electronic many rotors power system remains parallel with the aircraft flight direction.To reduce to greatest extent flight resistance, make flight efficiency higher.
Preferably, described master controller comprises one first cooperative work mode controller: be used for being controlled at the switching process from the multirotor helicopter offline mode to the fixed-wing offline mode, by beginning from hovering along with propelling screws produces power, aircraft produces horizontal motion, along with increasing fixed-wing, air speed produces gradually lift, simultaneously thereby many rotors reduce gradually rotating speed and keep the constant until air speed of resultant lift greater than the fixed-wing stalling speed, to finish the multirotor helicopter offline mode to the conversion of fixed-wing offline mode to reduce rotor lift.
Preferably, described master controller comprises one second cooperative work mode controller: be used for being controlled at from the fixed-wing offline mode to multirotor helicopter offline mode switching process, along with reducing horizontal propeller thrust, when air speed during near the fixed-wing stalling speed, many rotors will start generation lift, along with thereby the many rotors of further reduction of air speed will increase rotating speed increase lift with the lift decline of compensation fixed-wing part, thereby it is constant to reach resultant lift, when propelling screws thoroughly stops operating air speed when being reduced to zero, thoroughly convert the multirotor helicopter offline mode to.
Preferably, described master controller comprises one the 3rd cooperative work mode controller: be used for being controlled at whole taking off, fly and the landing process, this fixed-wing control system and the omnidistance collaborative work under the control of master controller of electronic many rotor control systems.
Preferably, the screw propeller of described fixed-wing power system is positioned at fuselage the place ahead, fuselage afterbody or fuselage both sides, and perhaps front and back arrange simultaneously.
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, described fixed-wing power system is electric power system or oil burning power system.
Preferably, the quantity of described fixed-wing power system is single cover or many covers.
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 because have can separate control fixed-wing power system and electronic many rotors power system, so 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, also can in landing and flight course, use the pattern of two power system hybrid workings to realize.
The utility model because adopted can separate control power system, realize again the structure of cyclogyro than in a cover power system, namely realizing fixed wing aircraft, simpler on the utility model structure, do not need very complicated steering structure, can not affect the layout of the interior load of machine and equipment yet.Adopt independent electronic many rotors power system to be conducive to reduce the development risk of power system, by proper arrangement, when sustainer, main engine fault or war damage, lift engine can make aircraft safety make a return voyage, and has realized the power backup.
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.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.
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 is the Flight Vehicle Structure schematic diagram of the utility model the first embodiment.
Fig. 6 is the structural representation of the power control system of aircraft of the present utility model.
Fig. 7-13 is the Flight Vehicle Structure schematic diagram of different empennage types of the present utility model.
Figure 14,15 is the Flight Vehicle Structure schematic diagram of the utility model the second embodiment.
Figure 16 is lifting, attitude and the course control schematic diagram of aircraft of the present utility model.
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 the composite aircraft that a kind of fixed-wing of the present utility model and electronic many rotors form, it comprises a cover fixed wing aircraft assembly, this assembly comprises fuselage 1, main wing 2, empennage 3 and fixed-wing power system 4 (also claiming the fixed wing aircraft power system), is 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, increased the electronic many rotors power system 5 of quadruplet, be the system that the assembly that plays the cyclogyro function provides power, but be not limited to quadruplet, and electronic many rotors power system 5 can adopt the concrete the Nomenclature Composition and Structure of Complexes of existing helicopter, so repeat no more.The rotor wing rotation plane of described electronic many rotors power system is parallel with horizontal surface, parallel comprising close to parallel situation herein, such as the pitch angle of fuselage and horizontal surface in 10 ° scope.The terms such as parallel, the vertical and level that occurs in it will be appreciated by those skilled in the art that in full also comprise the situation close to parallel, vertical and level, are not only to refer to coabsolute parallel, the vertical and level of geometric meaning.And electronic many rotors power system 5 comprises engine installation and rotor, can be separately positioned on rotor both sides and the main wing front and back side of this fuselage, is symmetrical with respect to this fuselage and places, and engine installation is arranged on the fuselage.Perhaps the electronic many rotors power system 5 of the whole series is separately positioned on both sides and the main wing front and back side of this fuselage, is symmetrical with respect to this fuselage 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 rotors power system 5 of every cover integrally or rotor be connected on the main wing 2 by a hold-down arm 6 individually, some cover systems or the shared hold-down arm of rotor that also each can be overlapped in electronic many rotors power system certainly in other embodiments, are connected on fuselage or the wing.
Electronic many rotors 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, from structure fixed-wing power system and the separate setting of electronic many rotors power system, be equipped with a master controller 7 to realize the switching controls between two kinds of patterns.This master controller 7 comprises a fixed-wing control system 71, and this fixed-wing control system comprises the fixed-wing power control system, is used for control fixed-wing power system; And fixed-wing rudder surface control system.Because the fixed-wing control system can adopt the control system structure and composition of existing fixed wing aircraft to realize, do not give unnecessary details so do not do.
This master controller 7 comprises that also one is used for electronic many rotor control systems 72 of these electronic many rotors power system 5 work of control, and this master controller 7 also is used for this fixed-wing control system 71 of control and electronic many rotor control systems 72 and works independently or collaborative work.Here, corresponding when fixed-wing control system 71 works independently is the fixed wing aircraft pattern, electronic many rotor control systems 72 are corresponding when working independently to be helicopter mode, the lifting, attitude and the course that are used for the control aircraft, and be 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 or mixed mode:
1, when the helicopter mode landing, close the fixed-wing power system, open electronic many rotors power system of 4 groups (perhaps more groups), electronic many rotor control systems are by the vertical takeoff and landing of rotating speed and/or the pitch control aircraft of all rotors of increase and decrease.Use the vertical takeoff and landing consumption of power larger, but use electronic many rotors power system time very short, it is little that the landing consumed energy accounts for whole flight energy consumption energy proportion, thus be the main landing pattern of this aircraft, this moment aircraft as the same landing of helicopter.Such as Figure 16,4 rotors all increase or reduce rotating speed during lifting.
2, when the landing of fixed wing aircraft pattern, close 4 groups of (perhaps more groups) electronic many rotors power systems, only open the fixed-wing power system, aircraft just can as the same landing on runway of fixed wing aircraft.
3, when the mixed mode landing, fixed-wing power system and electronic many rotors power system are all opened.Merits and faults is between helicopter mode and fixed wing aircraft pattern.
In the mixed mode take-off process, two kinds of power systems are worked simultaneously, the lift that provides so just is far longer than the independent lift that power system provides, thus field of application is more extensive, the very large situation of Aircraft Load especially.Oil and weaponry when taking off, have been filled such as fighter plane, traditional fighter plane just provides power to realize taking off by deciding wing power system, power is limited, takeoff speed is slow, and electronic many rotors power system of while also provides power in the utility model, then power increases greatly, and takeoff speed is very fast.
In the mixed mode take-off process, also applicable for the situation that landing airdrome length is inadequate.It is 500 meters such as normal landing airdrome length, and some occasion is subject to the restriction of geographical environment, landing airdrome length can't reach 500 meters, on the deck such as the uneven areas such as mountain area or aircraft carrier, for example landing airdrome length only has 250 meters, just can use mixed mode running take off on runway this moment, finally realizes short field take-off.
And flight course also can adopt helicopter mode, fixed wing aircraft pattern and mixed mode:
1, when helicopter mode flies, close the fixed-wing power system, open 4 groups of (or more than) electronic many rotors power systems, 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.Wherein, electronic many rotor control systems are by reducing rotating speed and/or the pitch of rotor 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 rotor after leaning on respect to the center of gravity of aircraft, control the attitude of aircraft.Such as Figure 16, when flying to the left: rotor 5a, 5c speedup, rotor 5,5b slow down.When flying to the right: rotor 5,5b speedup, rotor 5a, 5c slow down.
Electronic many rotor control systems reduce the rotating speed and/or the pitch that turn to rotor in the same way with aircraft by increasing rotating speed and/or the pitch that turns to reverse rotor with aircraft, the course of control aircraft.Such as Figure 16, during left steering: rotor 5,5c speedup, rotor 5a, 5b slow down; During right steering: rotor 5a, 5b speedup, rotor 5,5c slow down; Before fly: rotor 5b, 5c speedup, rotor 5,5a slow down; After fly: rotor 5,5a speedup, rotor 5b, 5c slow down.
Specifically, make exactly the wherein rotor clockwise direction rotation of half, second half rotor anticlockwise direction rotation under helicopter mode, can utilize the rotating speed of 4 rotors of electronic gyroscope control, forms a stable heligyro flying platform.By changing gyroplane rotate speed, change lift and the moment of torsion of 4 rotors, 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, close 4 groups of (perhaps more groups) rotors, only open the fixed-wing 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, this moment aircraft as fixed wing aircraft equally fly.
3, when mixed mode flies, fixed-wing power system and electronic many rotors power system are all opened.Merits and faults is between helicopter mode and fixed wing aircraft pattern.
In mixed mode, in order to guarantee to keep parallel with the aircraft flight direction after rotor partly stops operating, to reduce to greatest extent flight resistance, make flight efficiency higher.Also can in electronic many rotor control systems, add a rotor blade position control unit 721, be used for when electronic many rotors power system is closed, during the unlatching of fixed-wing power system, the rotor blade position of controlling described electronic many rotors power system remains parallel with the aircraft flight direction.
In mixed mode, a kind of situation of aforementioned two power system collaborative works is: the switching process of fixed-wing pattern flight that flies from helicopter mode, by beginning from hovering along with propelling screws produces power, aircraft produces horizontal motion, along with increasing fixed-wing, air speed produces gradually lift, simultaneously thereby many rotors reduce gradually rotating speed and keep the constant until air speed of resultant lift greater than the fixed-wing stalling speed to reduce rotor lift, to finish the fly conversion of fixed-wing pattern flight of helicopter mode.
In mixed mode, the another kind of situation of aforementioned two power system collaborative works is: the switching process of helicopter mode flight that flies from the fixed-wing pattern, along with reducing horizontal propeller thrust, when air speed during near the fixed-wing stalling speed, many rotors will start generation lift, along with thereby the many rotors of further reduction of air speed will increase rotating speed increase lift with the lift decline of compensation fixed-wing part, thereby it is constant to reach resultant lift, when propelling screws thoroughly stops operating air speed when being reduced to zero, thoroughly convert helicopter mode flight to.Another situation of collaborative work is: whole take off, fly and the landing process in, this fixed-wing control system and the omnidistance collaborative work under the control of master controller of electronic many rotor control systems.Above three kinds of situations can realize by three cooperative work mode controllers respectively.
The concrete making of above-mentioned master controller, each control system and each control unit all can realize by existing electronic control mode or software mode with realization, not do at this and give unnecessary details.
Shown in Fig. 7-13, 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 Figure 14,15, the difference of the present embodiment and the first embodiment mainly is: the electronic many rotors power system of 6 covers is arranged in the present embodiment, and wherein 4 covers are installed on the main wing, and other two covers are installed in the position of close empennage on the fuselage.Airplane tail group among Figure 15 is equipped with air jet system 8, can fly forward as power advances aircraft take jet.Remainder and the first embodiment are basic identical.
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 (13)

1. the composite aircraft that forms of a fixed-wing and electronic many rotors, comprise a cover fixed wing aircraft assembly, this assembly comprises fuselage, wing, fixed-wing power system and fixed-wing control system, this fixed-wing control system comprises fixed-wing power control system and fixed-wing rudder surface control system, it is characterized in that, this aircraft also comprises one group of electronic many rotors power system and a master controller, described fixed-wing power system and electronic many rotors power system are structurally separate, this master controller comprises this fixed-wing control system and is used for electronic many rotor control systems of this electronic many rotors power system work of control, and this master controller also is used for this fixed-wing control system of control and electronic many rotor control systems and works independently or collaborative work; The rotor wing rotation plane of described electronic many rotors power system and fuselage central axes.
2. the composite aircraft that forms of fixed-wing as claimed in claim 1 and electronic many rotor, it is characterized in that, described electronic many rotors power system is at least quadruplet, this system of every cover comprises engine installation and the rotor that is connected with this engine installation, described each rotor is separately positioned on both sides and the wing front and back side of this fuselage, is symmetrical with respect to this this aircraft center of gravity and places; Perhaps described each electronic many rotors power system integral body is separately positioned on both sides and the wing front and back side of this fuselage, is symmetrical with respect to this aircraft center of gravity and places.
3. the composite aircraft of fixed-wing as claimed in claim 2 and electronic many rotor compositions is characterized in that, the electronic many rotors power system of described every cover or rotor all are connected on this fuselage or the wing by a hold-down arm.
4. the composite aircraft of fixed-wing as claimed in claim 2 and electronic many rotor compositions is characterized in that, described some cover systems or the shared hold-down arm of some cover rotors that respectively overlaps in electronic many rotors power system is connected on this fuselage or the wing.
5. the composite aircraft of fixed-wing as claimed in claim 2 and electronic many rotor compositions is characterized in that, described engine installation is motor.
6. the composite aircraft that forms of fixed-wing as claimed in claim 1 and electronic many rotor, it is characterized in that, described electronic many rotor control systems comprise a rotor blade position control unit, be used for when electronic many rotors power system is closed, during the unlatching of fixed-wing power system, the rotor blade position of controlling described electronic many rotors power system remains parallel with the aircraft flight direction.
7. the composite aircraft that forms of fixed-wing as claimed in claim 1 and electronic many rotor, 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 the multirotor helicopter offline mode to the fixed-wing offline mode, by beginning from hovering along with propelling screws produces power, aircraft produces horizontal motion, along with increasing fixed-wing, air speed produces gradually lift, simultaneously thereby many rotors reduce gradually rotating speed and keep the constant until air speed of resultant lift greater than the fixed-wing stalling speed, to finish the multirotor helicopter offline mode to the conversion of fixed-wing offline mode to reduce rotor lift.
8. the composite aircraft that forms of fixed-wing as claimed in claim 1 and electronic many rotor, 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 multirotor helicopter offline mode switching process, along with reducing horizontal propeller thrust, when air speed during near the fixed-wing stalling speed, many rotors will start generation lift, along with thereby the many rotors of further reduction of air speed will increase rotating speed increase lift with the lift decline of compensation fixed-wing part, thereby it is constant to reach resultant lift, when propelling screws thoroughly stops operating air speed when being reduced to zero, thoroughly convert the multirotor helicopter offline mode to.
9. the composite aircraft that forms of fixed-wing as claimed in claim 1 and electronic many rotor, it is characterized in that, described master controller comprises one the 3rd cooperative work mode controller: be used for being controlled at whole taking off, fly and the landing process, this fixed-wing control system and the omnidistance collaborative work under the control of master controller of electronic many rotor control systems.
10. the composite aircraft of fixed-wing as claimed in claim 1 and electronic many rotor compositions is characterized in that, the screw propeller of described fixed-wing power system is positioned at fuselage the place ahead, fuselage afterbody or fuselage both sides, and perhaps front and back arrange simultaneously.
11. the composite aircraft that fixed-wing as claimed in claim 1 and electronic many rotor form 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.
12. the composite aircraft that fixed-wing as claimed in claim 1 and electronic many rotors form is characterized in that described fixed-wing power system is electric power system or oil burning power system.
13. the composite aircraft such as the described fixed-wing of claim 1-12 any one and electronic many rotor compositions is characterized in that, the quantity of described fixed-wing power system is single cover or many covers.
CN 201120397886 2011-10-17 2011-10-17 Composite aircraft with fixed wing and electric multi-rotor-wing combined CN202728575U (en)

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CN 201120397886 CN202728575U (en) 2011-10-17 2011-10-17 Composite aircraft with fixed wing and electric multi-rotor-wing combined
PCT/CN2011/083305 WO2013056493A1 (en) 2011-10-17 2011-12-01 Composite aircraft consisting of fixed-wing and electrically driven propellers
EP11870167.1A EP2604519A4 (en) 2011-10-17 2011-12-01 Composite aircraft consisting of fixed-wing and electrically driven propellers
US13/704,056 US20130092799A1 (en) 2011-10-17 2011-12-01 Fixed-wing and electric multi-rotor composite aircraft
JP2014534913A JP2014528382A (en) 2011-10-17 2011-12-01 Aircraft combining fixed wing and electric multi-rotor

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* Cited by examiner, † Cited by third party
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CN103043212A (en) * 2011-10-17 2013-04-17 田瑜 Combined aircraft composed of fixed wing and electric multi-rotor wing
US20130092799A1 (en) * 2011-10-17 2013-04-18 Yu Tian Fixed-wing and electric multi-rotor composite aircraft
CN104816824A (en) * 2015-05-19 2015-08-05 江苏数字鹰科技发展有限公司 Fixed structure type vertical takeoff and landing aircraft based on dual-flight control system and control method for fixed structure type vertical takeoff and landing aircraft
CN105129081A (en) * 2015-08-12 2015-12-09 江阴市翔诺电子科技有限公司 Novel multiaxial rotor aircraft and steering control method of the same under hovering state
CN105270614A (en) * 2015-10-30 2016-01-27 佛山市神风航空科技有限公司 Symmetric eight-axle aircraft
CN105438463A (en) * 2015-11-30 2016-03-30 珞石(北京)科技有限公司 Quad tilt-rotor aircraft
CN105683041A (en) * 2013-08-29 2016-06-15 空中客车防卫和太空有限责任公司 Aircraft capable of vertical take-off
WO2016201661A1 (en) * 2015-06-18 2016-12-22 罗春晖 Lift force device for airplane, and takeoff method using device
CN106275458A (en) * 2015-06-23 2017-01-04 张怡月 A kind of equipment not hindering aircraft
CN107826243A (en) * 2017-09-27 2018-03-23 中国民航大学 A kind of combined type aircraft
CN108572655A (en) * 2018-04-25 2018-09-25 重庆市亿飞智联科技有限公司 Flight control method and relevant apparatus
CN110239709A (en) * 2019-05-20 2019-09-17 邓欣奇 A kind of composite wing aviation aircraft and its flight control method
CN111152920A (en) * 2020-01-08 2020-05-15 北京建筑大学 Unmanned aerial vehicle capable of vertically taking off and landing

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103043212B (en) * 2011-10-17 2016-06-08 优利科技有限公司 The composite aircraft that fixed-wing forms with electronic many rotors
US20130092799A1 (en) * 2011-10-17 2013-04-18 Yu Tian Fixed-wing and electric multi-rotor composite aircraft
CN103043212A (en) * 2011-10-17 2013-04-17 田瑜 Combined aircraft composed of fixed wing and electric multi-rotor wing
CN105683041A (en) * 2013-08-29 2016-06-15 空中客车防卫和太空有限责任公司 Aircraft capable of vertical take-off
CN104816824A (en) * 2015-05-19 2015-08-05 江苏数字鹰科技发展有限公司 Fixed structure type vertical takeoff and landing aircraft based on dual-flight control system and control method for fixed structure type vertical takeoff and landing aircraft
US10279904B2 (en) 2015-05-19 2019-05-07 Jiangsu Digital Eagle Technology Co., Ltd. Fixed structure type vertical take-off and landing aircraft based on dual flying control systems and control method therefor
WO2016184358A1 (en) * 2015-05-19 2016-11-24 江苏数字鹰科技发展有限公司 Fixed structure type vertical take-off and landing aircraft based on dual flying control systems and control method therefor
WO2016201661A1 (en) * 2015-06-18 2016-12-22 罗春晖 Lift force device for airplane, and takeoff method using device
CN106275458A (en) * 2015-06-23 2017-01-04 张怡月 A kind of equipment not hindering aircraft
CN105129081A (en) * 2015-08-12 2015-12-09 江阴市翔诺电子科技有限公司 Novel multiaxial rotor aircraft and steering control method of the same under hovering state
CN105270614A (en) * 2015-10-30 2016-01-27 佛山市神风航空科技有限公司 Symmetric eight-axle aircraft
CN105438463A (en) * 2015-11-30 2016-03-30 珞石(北京)科技有限公司 Quad tilt-rotor aircraft
CN107826243A (en) * 2017-09-27 2018-03-23 中国民航大学 A kind of combined type aircraft
CN108572655A (en) * 2018-04-25 2018-09-25 重庆市亿飞智联科技有限公司 Flight control method and relevant apparatus
CN110239709A (en) * 2019-05-20 2019-09-17 邓欣奇 A kind of composite wing aviation aircraft and its flight control method
CN111152920A (en) * 2020-01-08 2020-05-15 北京建筑大学 Unmanned aerial vehicle capable of vertically taking off and landing

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