CN108313282A

CN108313282A - High motor-driven helicopter

Info

Publication number: CN108313282A
Application number: CN201710027196.7A
Authority: CN
Inventors: 原熙
Original assignee: Individual
Current assignee: Individual
Priority date: 2017-01-16
Filing date: 2017-01-16
Publication date: 2018-07-24

Abstract

A kind of high motor-driven helicopter.It is laid out using single-blade face engine behind front wheel, tail sitting posture landing mode, has the flaperon that two panels can be deflected independently and the vertical tail that one or more rudder faces mutually link.Maneuver under landing, flat winged and floating state is all realized by the deflection and engine output that control rudder face.It can realize VTOL on any flat surfaces, have the mobility for being equivalent to traditional fixed wing aircraft under flat winged state, then have all 6 controllable degree of freedom of gyroplane under floating state.

Description

High motor-driven helicopter

Technical field

It can not only hover the present invention relates to a kind of but also winged aircraft can be put down, can especially fly and hovering pattern flat The motor-driven helicopter of height of the lower whole mobility for realizing fixed wing aircraft and gyroplane respectively.

Background technology

Helicopter, you can with the fixed wing aircraft of VTOL, because greatly relaxing fixed wing aircraft to landing The requirement of condition just becomes one of the developing goal of aeronautical technology at the beginning of being proposed from concept.

Early 20th century aircraft invented after, all lock into and be short of power in a very long time, allow tight to power demand The VTOL of lattice has rested on the conceptual phase.Nonetheless, before nineteen thirty, European Patent Institute has also been accepted simultaneously Have approved the relevant patented technology of several helicopters.

Realize that the prerequisite to take off vertically is engine and must generate the thrust conducted oneself with dignity more than aircraft in vertical direction Or pulling force, and to Fixed Wing AirVehicle VTOL ability, the active demand for the ability that especially takes off vertically is then at second It is generated in world war：Germany in nineteen forty-four on airport in order to, by allied forces bombers is returned in the case of compacting, start to grind The rocket-powered interceptor of Ba349 types processed, and first-fly is realized at the beginning of 1945.Although Ba349 ultimately fails to volume production, initiate Tail sitting posture take off pattern, continued to use by hereafter many fixed wing aircraft VTOL projects.

After cold war starts, heligyro technology starts to popularize, and the aircraft that research and development thrust-weight ratio is more than 1 is no longer to be difficult to exceed Technical barrier more.And cold war both sides also allow fixed-wing fighter plane and the vertical of interceptor to rise the expection of full-scale nuclear war again Winged ability becomes extremely urgent.Since the beginning of the fifties in last century, nearly all country for having aircraft industry is all to this progress Cross research.Among these, the model that the aircraft industry U.S. the most flourishing develops is also most.

The mainstream product in this stage has, first-fly in 1954, vertical by the XFV Salmon of american lockheed company Landing fighter plane；First-fly in 1954, the XFY Pogo vertical take off and landing fighters developed by Kang Weier companies；Nineteen fifty-five first-fly, by The X-13 jet power VTOL aircrafts that Ruian Aeronautical Industrial SA develops.Wherein, XFV uses X-type empennage as undercarriage, XFY Pogo use main wing tip and vertical tail tip and constitute the configuration of undercarriage, these novel designs are influenced at that time It is limited, but become the classical scheme that unmanned tail sitting posture takes off vertically after many decades.

Military type helicopter during cold war is finally with the sparrow hawk formula of Britain and refined gram 38 of the Soviet Union both layout height phase As type finish up, this mode of taking off of tail sitting posture be proved to be not suitable for military operational aircraft.This form of taking off is made no public appearances After half a century, attention is retrieved along with the emergence of unmanned plane finally.

Compared to manned fighter plane and interceptor, the present age light-duty unmanned plane can have easily far surpass the former thrust-weight ratio and Structural strength, and this 2 points of biggest obstacles that exactly fifties, helicopter once faced.Especially in multirotor helicopter After maturation, between nearly 10 years, the helicopter number of applications based on the differential control technology of multirotor helicopter It is rather numerous, while some helicopter patent applications using traditional fixed wing aircraft control principle have also been emerged in large numbers, if or even The design of the dry tiltable blade for introducing single-rotor helicopter.Many schemes therein all use that be just proved to the fifties can Capable tail sitting posture takes off pattern.

However, carefully examine existing tail sitting posture helicopter closely, otherwise the problem of scheme is solved is to allow fixed wing aircraft It realizes VTOL or is that gyroplane is allowed to realize flat fly.This is no doubt relative to the fixed wing aircraft peace for needing runway to slide race It is huge progress for winged slow-paced gyroplane, but not the whole of helicopter concept --- classical fixed-wing flies Machine can realize flexible, i.e. advanced speed variation, rolling, flexion-extension and yaw in 4 controllable degree of freedom, and classical All 6 controllable degree of freedom then may be implemented in heligyro, i.e., move along X, Y, Z axis and rotated around X, Y, Z axis.

Regrettably, in existing tail sitting posture helicopter design, the logical due to operating of control principle is flown based on fixed wing aircraft Road is naturally insufficient, and 6 controllable degree of freedom can not be all realized in hovering；It is then needed with differential mode based on more rotor principles The manipulation degree of freedom of fixed wing aircraft is simulated, not only puts down the incomparable traditional fixed wing aircraft of speed and motor-driven when flying, also The high-stability that aerodynamic arrangement must not depended on maintains to equal winged stability, further sacrifices mobility.

The ideal helicopter of one frame, the 4 controllable degree of freedom that should be provided simultaneously under flat winged state and hovering shape 6 controllable degree of freedom under state, and its implementation must efficiently, simply, directly, to reduce the loss of pneumatic efficiency. The advantages of only having the helicopter of such characteristic, could combining fixed wing aircraft and gyroplane to the maximum extent, allows straight The scope of application for rising aircraft is more extensive.

Invention content

For 6 for overcoming existing helicopter high efficiency realization flat 4 winged controllable degree of freedom and hovering The problem of controllable degree of freedom, the present invention provide a kind of high motor-driven helicopter, the helicopter can not only take off vertically and Landing, is also provided simultaneously with the controllable degree of freedom of whole and operating flexibility of fixed wing aircraft and gyroplane.

The technical solution adopted by the present invention to solve the technical problems is：It is laid out using single-blade face, main plane root or so Respectively have it is a piece of can independent activities flaperon；It is vertical that After-Body is disposed with one or more pieces axial symmetry arrangement, rudder face links The all moving fin integrally deflected may be used in empennage, can also be the fixation vertical fin for having rudder face；Main wing tip and vertical tail Tip collectively forms undercarriage during take-off and landing, and helicopter can be stablized in such a way that tail is sat and is positioned in plane；Propeller pushes away It is located at body front end into device, the maximum thrust that propeller can generate is more than the maximum take-off weight of helicopter；Propeller can Can also be the multi-thruster that axial symmetry is laid out to be centrally arranged single propeller, layout principles are vertical fin rudder face and two The air-flow that flaperon must have propeller to generate at any time passes through, and to ensure under arbitrary state of flight, rudder face can have enough Steerage；When single vertical fin cannot meet this condition, then it should increase the vertical fin quantity that rudder face mutually links to ensure vertical fin rudder face Steerage；To avoid the visual field or road is launched towards ventral in space in the middle part of main wing surface rear end for installing the load such as camera, opening Diameter is shielded.

The advantageous effect of the present invention compared with the prior art is, can on any flatly face takeoff and landing, flying It can fly freely to convert between two kinds of state of flights of hovering flat according to actual needs in the process；Under flat winged state, have solid Determine the high speed of wing aircraft and long endurance feature, and whole maneuvers of typical fixed wing aircraft can be completed, that is, changes Rate, rolling, flexion-extension in direction of advance and yaw, the similar traditional fixed wing aircraft of manipulation flexibility；Under floating state, tool All 6 controllable degree of freedom of standby typical case's gyroplane.

Description of the drawings

Attached drawing show a kind of three-view diagram of possible specific embodiment of the present invention.Shown scheme uses single-shot all-wing aircraft Formula is laid out, and moves vertical tail entirely, drives two blade propeller to promote by gasoline engine.

Fig. 1 is the vertical view of the present invention.

Fig. 2 is the side view of the present invention.

Fig. 3 is the front view of the present invention.

Arrow meaning is the definition of reference axis in attached drawing.Wherein, X-axis is parallel to two tip lines of aircraft main wing Straight line, the straight line of plane where Y-axis is perpendicular to aircraft main plane, Z axis is the straight line where aircraft central axes.

Parts title in attached drawing：

1. propeller, 2. main planes, 3. move vertical tail, 4. flaperons, 5. load installation positions entirely.

Specific implementation mode

Invention is further explained with reference to the accompanying drawings of the specification.Embodiment only represents of the invention a kind of possible Embodiment, it is not as a limitation of the invention.

Before taking off, aircraft need to be positioned over tail sitting posture state on flat surfaces, at this time main plane（2）Two tips and complete Dynamic vertical fin（3）Tip form triangular support face, keep fuselage to stablize.

Start engine and increase output power, due to the propeller of driven by engine（1）It can generate more than aircraft The thrust of maximum take-off weight, aircraft vertical leaves ground, and stablizes and accelerate, at this time flaperon（4）And all moving fin（3）By Flight control system is controlled to keep flight attitude to stablize.

When the flying speed of aircraft in vertical direction is more than minimum level speed, two panels flaperon（4）While to Ventral direction deflects, and allows aircraft to be gradually transferred to horizontal flight, while engine output is reduced to and is enough to maintain required flat The level rapidly spent.

Under flat winged state, 4 manipulation degree of freedom of fixed wing aircraft are realized using following methods：

1. by changing the rate of propeller output power change of flight device in a forward direction, i.e. motion state on Z axis；

2. passing through two panels flaperon（4）Reverse deflection realizes rolling, i.e., moves about the z axis；

3. passing through two panels flaperon（4）Deflection, which is realized, in the same direction pitches, i.e., is moved around X-axis；

4. passing through vertical tail（3）Deflection realize yaw, i.e., around Y-axis move.

When needing to be changed into floating state from flat winged state, two panels flaperon（4）It deflects, allows winged to machine back of the body direction simultaneously Row device direction gradually becomes posture straight up.The appropriate engine output that increases is to make up main plane（2）Lift damage It loses.At this moment, although row device has come into hovering posture, but still maintains the horizontal velocity towards ventral direction, but by In flaperon at this time（4）Deflection angle Vehicle nose can be allowed to be tilted to away from the direction of horizontal movement direction, propeller pushes away The component of power in the horizontal direction can allow aircraft down.When the speed in horizontal direction is close to 0, flight control system adjusts two panels For the deflection angle of flaperon (4) to restore posture, aircraft enters floating state.

Under floating state, the present invention realizes 6 controllable degree of freedom of gyroplane using following methods：

1. changing height by changing propeller output power, i.e., moved along Z axis；

2. passing through two panels flaperon（4）Reverse deflection realization moves about the z axis；

3. passing through two panels flaperon（4）Yaw tilt fuselage in the same direction, realizes and is moved around X-axis；

4. passing through vertical tail（3）Yaw tilt fuselage, realize around Y-axis move；

5. in two panels flaperon（4）Deflection in the same direction, in the case of fuselage is inclined, keeps this posture, is caused using fuselage inclination Propeller tilt realize horizontal direction on movement, i.e., moved along Y-axis；

6. on vertical tail（3）Deflection, in the case of fuselage is inclined, is kept this posture, is pushed away caused by being tilted using fuselage The movement realized in another horizontal direction is tilted into device, i.e., is moved along X-axis；

The process for being changed into flat winged state from floating state is similar with take-off process.

Claims

1. a kind of high motor-driven helicopter is directed toward by engine driving one or more and is fixed using tail sitting posture state VTOL Propeller provide hovering lift peace fly propulsive force, it is characterized in that：Have 2 flaperons that can independently deflect, has simultaneously The vertical tail rudder face of one or more standby linkages, flight control system all only pass through transmission under landing, flat winged and floating state Left flaperon, right flaperon, vertical tail rudder face, engine export this 4 control signals and realize gesture stability and maneuver.

2. the motor-driven helicopter of height according to claim 1, it is characterized in that：Any one control rudder face in landing, flat fly Pass through to ensure steerage with the air-flow for thering is propeller to push under floating state.

3. the motor-driven helicopter of height according to claim 1, it is characterized in that：It is being positioned over flat surfaces with tail sitting posture state When, main wing tip and all vertical tail tips collectively form undercarriage.

4. the motor-driven helicopter of height according to claim 1, it is characterized in that：Under floating state, by flaperon and hang down The deflection of straight tail rudder face allows fuselage to tilt, and is realized by the component of airscrew thrust under lateral attitude in the horizontal direction Movement in horizontal direction.