CN109229355A - A kind of more rotor manned aircraft - Google Patents

A kind of more rotor manned aircraft Download PDF

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Publication number
CN109229355A
CN109229355A CN201811274756.XA CN201811274756A CN109229355A CN 109229355 A CN109229355 A CN 109229355A CN 201811274756 A CN201811274756 A CN 201811274756A CN 109229355 A CN109229355 A CN 109229355A
Authority
CN
China
Prior art keywords
rotor
blade
fuselage
connect
rocker arm
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
CN201811274756.XA
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Chinese (zh)
Inventor
王鹏飞
王志成
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Foshan Shenfeng Aviation Technology Co Ltd
Original Assignee
Foshan Shenfeng Aviation Technology Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Foshan Shenfeng Aviation Technology Co Ltd filed Critical Foshan Shenfeng Aviation Technology Co Ltd
Priority to CN201811274756.XA priority Critical patent/CN109229355A/en
Publication of CN109229355A publication Critical patent/CN109229355A/en
Withdrawn legal-status Critical Current

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Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/04Helicopters
    • B64C27/08Helicopters with two or more rotors
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
    • B64D27/02Aircraft characterised by the type or position of power plant
    • B64D27/16Aircraft characterised by the type or position of power plant of jet type
    • B64D27/20Aircraft characterised by the type or position of power plant of jet type within or attached to fuselage
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D31/00Power plant control; Arrangement thereof

Abstract

The invention discloses a kind of more rotor manned aircraft, including fuselage and undercarriage, undercarriage is installed on fuselage bottom, and fuselage periphery two sides are equipped with propulsion device;Fuselage interior is equipped with cockpit, main rotor portion is installed on fuselage top plan, main rotor portion includes six the first rotors and 12 the second rotors, first rotor passes through first connecting rod and is welded on fuselage top plan, each first rotor is connect with first electric-motor drive, first rotor passes through the second connecting rod and connect with the second rotor, and the second rotor passes through retarder and connect with the second electric-motor drive, is connected between the second rotor by third connecting rod;There are four third rotors for installation in the plane of fuselage bottom end, each third rotor is connect with a third electric-motor drive, according to the technical solution of the present invention, is capable of providing very big lift and thrust, the dual guarantee of gesture stability, keeps attitude flight control system more complete.

Description

A kind of more rotor manned aircraft
Technical field
The present invention relates to multi-rotor aerocraft technical field, more particularly to a kind of more rotor manned aircraft.
Background technique
Gyroplane refers to " aircraft " for being provided lift with unpowered rotor, being overweighted air.Existing gyroplane It mainly include fuselage, single layer rotor, empennage, take-off and landing device, power device and cockpit instrument.When advancing air-flow blow rotor and Lift is generated, it cannot take off vertically or hover, and one initial driving force of rotor is often also given when taking off, increases the lift of rotor Add.
Wherein, the function of take-off and landing device, which is to provide aircraft takeoff, landing and ground and parks, is used, and landing can be absorbed in it Impact energy reduces shock loading, improves sliding performance.Generally there are three undercarriage, the main undercarriages of two of them for gyroplane Positioned at the fuselage two sides of immediate vicinity, main supporting role, another undercarriage is in head or tail, if claiming if tail For rear bikini, it is more suitable for advancing on coarse road face, if being known as first three point type in head, being adopted by most of gyroplanes With, and the front-wheel can be controlled by pedals and be deflected, flexibly to turn when ground taxi.Wheel undercarriage is generally set There is damping device, most of landing energy can be absorbed, takeoff and landing can be slided on rigid road surface.
Cockpit instrument is available to pilot's observation and judges state of flight, to make correct manipulation and control.It is general Including engine instruments, such as revolution counter, oil pressure gauge, pneumatic instrument, such as airspeed-indicator, climb meter, electronic instrument, as Level, navigator etc..Different gyroplanes chooses to install different configuration of instrument according to complex degree of structure.But existing gyroplane It cannot fly fully according to the speed of setting, control system ability has to be strengthened.
The major function of fuselage is that mounting structure is provided for other components, and the common materials of fuselage are metal materials and compound Material can make to weld or be bolted, and can also be realized using matched combined mode.But existing gyroplane is negative Weight is smaller, and fuselage often accounts for most weight, on the one hand, is unfavorable for the promotion of flying speed, on the other hand, can disappear significantly Energy consumption.
The major function of single layer rotor is that necessary lift and control ability are provided for gyroplane, and common structure is band paddle The teetering rotor of hub inclination control, that is, two panels blade are rigidly attached together, when a piece of blade moves upwards, Another blade moves downward.But the lift that the rotor structure of this single layer obtains is not big enough, control force is not also strong, continuation of the journey Ability is weaker, and security performance is to be improved.
Empennage is made of vertical tail and tailplane, and major function is considered as gyroplane and provides stability and deflection control. But tail structure also increases the volume of gyroplane without weight bearing is integrally increased suspected of gyroplane.
In addition, an attitude control system is typically only arranged in existing gyroplane, but face the powerful air-flow in high-altitude Or the generation of various contingencies, attitude control system are highly susceptible to destroy, and cause fuselage disequilibrium or can not carry out just The security performance of normal steering, gyroplane can not be guaranteed.
Therefore it provides a kind of flight lift is big and attitude control system completely more rotor manned aircraft are this field skills The problem of art personnel's urgent need to resolve.
Summary of the invention
In view of this, the present invention provides a kind of more rotor manned aircraft, to overcome gyroplane in the prior art to fly Row lift is small, and cruise duration is short, the problem that gesture stability is indifferent and security performance is not high.
To achieve the goals above, the present invention adopts the following technical scheme:
A kind of more rotor manned aircraft, including fuselage and undercarriage, the undercarriage are installed on the fuselage bottom, the machine Body periphery two sides are equipped with propulsion device;The fuselage interior is equipped with cockpit, is equipped with main rotation on the fuselage top plan Alar part, the main rotor portion include six the first rotors and 12 the second rotors, and first rotor passes through the first connection Bar is welded on the fuselage top plan, and each first rotor is connect with first electric-motor drive, and described One rotor passes through the second connecting rod and connect with second rotor, and second rotor passes through retarder and the second motor It is sequentially connected, is connected between second rotor by third connecting rod;There are four thirds for installation in the plane of the fuselage bottom end Rotor, each third rotor are connect with a third electric-motor drive.
By taking above scheme, the beneficial effects of the present invention are:
It is designed by double-deck rotor mechanism, the main rotor portion on upper layer includes the first rotor and the second rotor, the first rotor and the Setting on two rotor positions and connection relationship, ensure that the overall stability of gyroplane, reach the intensity requirement of flight, Wherein, the first rotor is posture master control, for keeping existing posture and posture transformation, the second rotor be mainly used for providing lift and The third rotor of thrust, lower layer is mainly used for spare gesture stability, when the damage of the first rotor, can start third rotation in time The wing controls posture, ensure that the whole-process control of flight attitude;12 the second rotors drive simultaneously, can be rotor Machine provides enough and stable lift, guarantees that gyroplane is maintained at the height and speed of setting.In the first rotor, the second rotor When breaking down, third rotor can provide certain lift and thrust again, enhance cruise duration, meanwhile, ensure rotation Wing machine be capable of safety drop to ground, considerably increase security performance.
Further, first rotor include the first rotor shell, the first rotor shaft, the first propeller hub, the first blade and First blade rocker arm, described first connecting rod one end are connect with the fuselage top plan, outside the other end and first rotor Shell vertically connects, and first rotor shaft is equipped in the first rotor shell, each first rotor shaft is respectively by one First motor drive, first rotor shaft top are equipped with first propeller hub, first propeller hub and described the One blade is connected by the first blade rocker arm.
Further, the number of first blade is two leaves.
Advantageous effects by adopting the above technical scheme are that six the first rotors are arranged symmetrically, each One rotor is the posture master control of rotor craft by individual first motor drive, for keeping aircraft existing Posture or posture transformation.
Further, second rotor include the second rotor shell, the second rotor shaft, the second propeller hub, the second blade and Second blade rocker arm, second connecting rod one end are connect with the first rotor shell vertical, outside the other end and second rotor Shell vertically connects, and the second rotor interior of shell is equipped with second rotor shaft, and second rotor shaft is by described second Motor drives through the retarder, and second rotor shaft top is equipped with second propeller hub, second propeller hub and institute The second blade is stated to connect by the second blade rocker arm.
Further, the number of second blade is two leaves.
Advantageous effects by adopting the above technical scheme are that 12 the second rotors are arranged symmetrically, the second electricity Motivation drives 12 the second rotor shaft rotations simultaneously, and then drives the rotation of the second blade, can provide for gyroplane stable And very big lift.
Further, the third rotor includes third strut, third rotor shaft, third propeller hub, third blade and third Blade rocker arm, third strut one end are connect with fuselage bottom end plane, and the other end is vertical with the third rotor shaft to be connected It connects, each third rotor shaft respectively by a third motor drive, install by third rotor shaft top Third propeller hub is stated, the third propeller hub is connect with the third blade by the third blade rocker arm.
Further, the number of the third blade is four leaves.
Advantageous effects by adopting the above technical scheme are that four third rotors are arranged symmetrically, each Three rotors are by an individual third motor drive.When the damage of the first rotor, four third motor accelerate simultaneously or Slow down, can be realized the raising and lowering movement of gyroplane in vertical direction;Under the conditions of knots modification is consistent, one of them Third motor speed rises, therewith symmetrical third motor speed decline, and remaining third motor is made to keep original Revolving speed, since a third rotor lift becomes larger, symmetrical third rotor lift becomes smaller therewith, generate unbalanced torque, It is pivoted fuselage, similarly, gyroplane can be realized roll motion, pitching movement, move forward and backward and lateral movement, also can Stable control flight attitude is emergency back-up flight posture, ensure that the control of gyroplane flight attitude;It is met simultaneously in the second rotor When to failure, third rotor equally can also play the effect of the second rotor, provide lift and thrust, enhance cruising ability, protect Card gyroplane be capable of safety drop to ground, increase security performance.
Further, the propulsion device is jet engine, is equipped with injection pump, institute inside the jet engine It states jet engine and electron speed regulator is electrically connected.
Advantageous effects by adopting the above technical scheme are that jet engine can provide enough for gyroplane Thrust, and it is high-efficient, oil consumption is low, air mileage is remote.
Further, the electron speed regulator includes controller, revolving speed adjustment potentiometer, sensor and actuator, described One end of controller and power positive cathode are electrically connected, and the other end adjusts electricity with the revolving speed for setting flight revolving speed respectively Position device, the sensor and the actuator are electrically connected, wherein the sensor is mounted on inside the jet engine Turbine on, the revolving speed of the turbine collected is transferred to the controller, and the controller controls the actuator hair Lively to make, the actuator is connect with the injection pump.
Further, the actuator includes direct current generator, output shaft rocker arm and feedback element;The direct current generator driving The output shaft rocker arm rotation, the output shaft rocker arm are connect by adjusting connecting rod with the ratch of the injection pump, the feedback The working condition of the actuator is passed to the controller to form closed-loop control system by component.
Advantageous effects by adopting the above technical scheme are that the revolving speed needed with revolving speed adjustment potentiometer setting passes Sensor measures engine speed actual value by the gear ring on turbine, and is sent to controller, in the controller, actual value with Setting value compares, and the difference compared drives actuator output shaft rocker arm, pass through adjusting through controlling the arrangement of route, amplification Connecting rod pulls injection pump ratch, carries out the adjusting of fuel delivery, is able to maintain setting speed.
It can be seen via above technical scheme that compared with prior art, the present disclosure provides a kind of more rotor manneds Aircraft, rotor double-layer structure design, is capable of providing very big lift and thrust, the dual guarantee of gesture stability makes flight appearance State control system is more complete, by the design of electron speed regulator, is able to maintain setting speed flight, has reached cruising ability By force, control ability is strong, and security performance is high, the advantageous effects that have wide range of applications.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this The embodiment of invention for those of ordinary skill in the art without creative efforts, can also basis The attached drawing of offer obtains other attached drawings.
Fig. 1 attached drawing is a kind of overall structure diagram of more rotor manned aircraft provided by the invention;
Fig. 2 attached drawing is a kind of overlooking structure diagram of more rotor manned aircraft provided by the invention.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other Embodiment shall fall within the protection scope of the present invention.
As shown in Figs. 1-2, the embodiment of the invention discloses a kind of more rotor manned aircraft, including fuselage 1 and undercarriage 2, undercarriage 2 is installed on 1 bottom of fuselage, and the peripheral two sides of fuselage 1 are equipped with propulsion device 3;Cockpit 4, machine are equipped with inside fuselage 1 Main rotor portion is installed, main rotor portion includes six first the second rotors of rotor 5 and 12 6, the first rotation on 1 top plan of body The wing 5 is welded on 1 top plan of fuselage by first connecting rod 7, each first rotor 5 with first electric-motor drive Connection, the first rotor 5 are connect by the second connecting rod 8 with the second rotor 6, and the second rotor 6 is by retarder and the second electricity Motivation is sequentially connected, and is connected between the second rotor 6 by third connecting rod 9;There are four thirds to revolve for installation in 1 bottom end plane of fuselage The wing 10, each third rotor 10 are connect with a third electric-motor drive.It is designed by double-deck rotor mechanism, the master on upper layer Rotary-Wing Department includes the first rotor 5 and the second rotor 6, the setting on the first rotor 5 and 6 position of the second rotor and connection relationship, The overall stability that ensure that gyroplane has reached the intensity requirement of flight, wherein the first rotor 5 is posture master control, for protecting Existing posture and posture transformation are held, the second rotor 6 is mainly used for providing lift and thrust, the third rotor 10 of lower layer are mainly used for Spare gesture stability can start third rotor 10 in time, control posture, ensure that winged when the damage of the first rotor 5 The whole-process control of row posture;12 the second rotors 6 drive simultaneously, and enough and stable lift can be provided for gyroplane, Guarantee that gyroplane is maintained at the height and speed of setting.When the first rotor 5, the second rotor 6 break down, third rotor 10 can provide certain lift and thrust again, enhance cruise duration, meanwhile, ensured gyroplane be capable of safety drop to ground Face considerably increases security performance.
Specifically, the first rotor 5 includes the first rotor shell, the first rotor shaft, the first propeller hub, the first blade and the first paddle Leaf rocker arm, 7 one end of first connecting rod are connect with 1 top plan of fuselage, and the other end is connect with the first rotor shell vertical, the first rotation The first rotor shaft is equipped in wing shell, each first rotor shaft is respectively by first motor drive, the first rotor shaft top First propeller hub is installed, the first propeller hub is connect with the first blade by the first blade rocker arm.
Specifically, the number of the first blade is two leaves.
Specifically, the second rotor 6 includes the second rotor shell, the second rotor shaft, the second propeller hub, the second blade and the second paddle Leaf rocker arm, 8 one end of the second connecting rod are connect with the first rotor shell vertical, and the other end is connect with the second rotor shell vertical, the Two rotor interior of shells are equipped with the second rotor shaft, and the second rotor shaft is driven by the second motor through retarder, the second rotor shaft Top is equipped with the second propeller hub, and the second propeller hub is connect with the second blade by the second blade rocker arm.
Specifically, the number of the second blade is two leaves.
Specifically, third rotor 10 includes third strut, third rotor shaft, third propeller hub, third blade and third blade Rocker arm, third strut one end are connect with fuselage bottom end plane, and the other end is vertical with third rotor shaft to be connect, each third rotor shaft Respectively by a third motor drive, third rotor shaft top is equipped with third propeller hub, and third propeller hub passes through with third blade The connection of third blade rocker arm.
Specifically, the number of third blade is four leaves.
Specifically, propulsion device 3 is jet engine, injection pump is equipped with inside jet engine, it is jet-propelled to start Machine and electron speed regulator are electrically connected.
Specifically, actuator includes direct current generator, output shaft rocker arm and feedback element;Direct current generator drives output shaft rocker arm Rotation, output shaft rocker arm are connected by adjusting the ratch of connecting rod and injection pump, and the working condition of actuator is passed to by feedback element Controller is to form closed-loop control system.
The foregoing description of the disclosed embodiments enables those skilled in the art to implement or use the present invention. A variety of modifications of embodiment will be readily apparent to those skilled in the art, it is as defined herein general Principle can be realized in other embodiments without departing from the spirit or scope of the present invention.Therefore, the present invention will not It can be restricted to embodiment illustrated herein, and be to fit to consistent with the principles and novel features disclosed in this article most wide Range.

Claims (10)

1. a kind of more rotor manned aircraft, including fuselage and undercarriage, the undercarriage is installed on the fuselage bottom, described Fuselage periphery two sides are equipped with propulsion device;The fuselage interior is equipped with cockpit, which is characterized in that the fuselage top plan On main rotor portion is installed, the main rotor portion includes six the first rotors and 12 the second rotors, and first rotor is equal Be welded on the fuselage top plan by first connecting rod, each first rotor with first electric-motor drive Connection, first rotor pass through the second connecting rod and connect with second rotor, and second rotor passes through retarder It connect with the second electric-motor drive, is connected between second rotor by third connecting rod;Pacify in the plane of the fuselage bottom end There are four third rotor, each third rotors to connect with a third electric-motor drive for dress.
2. a kind of more rotor manned aircraft according to claim 1, which is characterized in that first rotor includes first Rotor shell, the first rotor shaft, the first propeller hub, the first blade and the first blade rocker arm, described first connecting rod one end with it is described The connection of fuselage top plan, the other end are connect with the first rotor shell vertical, are equipped in the first rotor shell described First rotor shaft, each first rotor shaft is respectively by first motor drive, first rotor shaft top First propeller hub is installed, first propeller hub is connect with first blade by the first blade rocker arm.
3. a kind of more rotor manned aircraft according to claim 2, which is characterized in that the number of first blade is Two leaves.
4. a kind of more rotor manned aircraft according to claim 1, which is characterized in that second rotor includes second Rotor shell, the second rotor shaft, the second propeller hub, the second blade and the second blade rocker arm, second connecting rod one end and first The connection of rotor shell vertical, the other end are connect with the second rotor shell vertical, and the second rotor interior of shell is equipped with institute The second rotor shaft is stated, second rotor shaft is driven by second motor through the retarder, second rotor shaft Top is equipped with second propeller hub, and second propeller hub is connect with second blade by the second blade rocker arm.
5. a kind of more rotor manned aircraft according to claim 4, which is characterized in that the number of second blade is Two leaves.
6. a kind of more rotor manned aircraft according to claim 1, which is characterized in that the third rotor includes third Strut, third rotor shaft, third propeller hub, third blade and third blade rocker arm, third strut one end and the fuselage bottom Transverse plane connection, the other end is vertical with the third rotor shaft to be connect, and each third rotor shaft is respectively by one described the Three-motor driving, third rotor shaft top are equipped with the third propeller hub, the third propeller hub and the third blade It is connected by the third blade rocker arm.
7. a kind of more rotor manned aircraft according to claim 6, which is characterized in that the number of the third blade is Four leaves.
8. a kind of more rotor manned aircraft according to claim 1, which is characterized in that the propulsion device is jet-propelled Engine, the jet engine inside are equipped with injection pump, and the jet engine and electron speed regulator are electrically connected.
9. a kind of more rotor manned aircraft according to claim 8, which is characterized in that the electron speed regulator includes control Device, revolving speed adjustment potentiometer, sensor and actuator processed, the input terminal and power positive cathode of the controller are electrically connected, defeated Outlet electrically connects with revolving speed adjustment potentiometer, the sensor and the actuator for setting flight revolving speed respectively It connects, wherein the sensor is mounted on the turbine inside the jet engine, the revolving speed of the turbine collected It is transferred to the controller, the controller controls the actuator and acts, and the actuator is connect with the injection pump.
10. a kind of more rotor manned aircraft according to claim 9, which is characterized in that the actuator includes direct current Motor, output shaft rocker arm and feedback element;The direct current generator drives the output shaft rocker arm rotation, and the output shaft rocker arm is logical It overregulates connecting rod to connect with the ratch of the injection pump, the working condition of the actuator is passed to the control by the feedback element Device processed is to form closed-loop control system.
CN201811274756.XA 2018-10-30 2018-10-30 A kind of more rotor manned aircraft Withdrawn CN109229355A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201811274756.XA CN109229355A (en) 2018-10-30 2018-10-30 A kind of more rotor manned aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201811274756.XA CN109229355A (en) 2018-10-30 2018-10-30 A kind of more rotor manned aircraft

Publications (1)

Publication Number Publication Date
CN109229355A true CN109229355A (en) 2019-01-18

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
CN201811274756.XA Withdrawn CN109229355A (en) 2018-10-30 2018-10-30 A kind of more rotor manned aircraft

Country Status (1)

Country Link
CN (1) CN109229355A (en)

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Application publication date: 20190118