CN105346719B - Vertically taking off and landing flyer - Google Patents
Vertically taking off and landing flyer Download PDFInfo
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- CN105346719B CN105346719B CN201510794978.4A CN201510794978A CN105346719B CN 105346719 B CN105346719 B CN 105346719B CN 201510794978 A CN201510794978 A CN 201510794978A CN 105346719 B CN105346719 B CN 105346719B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
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Abstract
The present invention relates to a kind of vertically taking off and landing flyer, it includes fuselage, wing, empennage, undercarriage and the first rotor power unit and the second rotor power unit that are located at fuselage both sides respectively being arranged on wing, first rotor power unit and the second rotor power unit are symmetrically distributed in the both sides of fuselage, the rotation axis of the rotation axis of first rotor power unit and the second rotor power unit points to the back lower place of fuselage, 3rd rotor power unit, is arranged on the middle part of empennage width in which can vert.The balance of the aircraft is good, mobility strong, environment Ying Xingqiang, and Posture exchange reliability is high and saves.
Description
Technical field
The present invention relates to aircraft, more particularly to a kind of vertically taking off and landing flyer, and in particular to one kind has rotor power
The vertically taking off and landing flyer of unit.
Background technology
1991, U.S. V22 " osprey " tiltrotor once obtained that American National aviation association issues " great aviation is entered
Step prize ", simultaneously because tiltrotor major accident is frequent, development cost is high, technical sophistication and difficulty big, the lead time is long,
Also people are caused greatly to dispute on.
" osprey " includes fuselage, wing, empennage, undercarriage, engine and tilting rotor unit.Pair is provided with wing
Elevator and rudder are provided with the wing, empennage, engine is located in fuselage, and tilting rotor unit is located at the two ends of wing.Incline
When the rotation axis of the rotor of switch rotor unit is vertical, rotor provides the power of VTOL；The rotor of tilting rotor unit
During rotation axis level, rotor provides the power of horizontal flight, and wing provides lift, and empennage provides pitching and yaw adjustment power
Square.
Because " osprey " only has a pair of rotors, the barycenter of the machine is located at the perpendicular where tilting rotor unit tiliting axis
It is interior, keep fuselage steady during so as to VTOL, during vertical landing, empennage can not provide pitching and yaw adjustment torque, lose
The effect of motor-driven regulation fuselage balance, therefore " osprey " requires high to the weather environment of VTOL, if entering to strong wind or strong
Convection weather, is just difficult to VTOL.Again because the power of " osprey " is all from the rotor positioned at two ends of wing, one
Denier has while break down, and is just difficult to as fixed-wing aircraft only to keep balance by the engine on one side and air crash, accident frequency
Hair.
Certainly being arranged on the elevator of empennage can also be substituted by the preposition wing being arranged on fuselage.
The empennage of osprey is respectively by elevator and rudder regulation pitching and yaw maneuver.Also have at present using V-type tail
The wing (abbreviation V tails) carries out flight attitude adjustment, such as U.S. army's global hawk.V tails by two it is with rudder face, mutually about into 120 degree of the wing
Piece is constituted.Being mainly characterized by for V tails is simple in construction, can save 10%-30% tail structure weight.Additionally, due to its V-arrangement
Structure, has been effectively shielded from the influence of wing or propeller sinuous flow, flight stability is increased.Therefore, it is long leave a blank with
And be used widely in the model of an airplane of especially exquisite weight, such as aerodone, electric airplane, indoor aircraft.V tails are one
The tail structure of application compensation principle is planted, the aerofoil for passing through two relative tilts produces the effect of horizontal and vertical stabilization；With
The suitable dynamic and differential control for realizing aircraft pitch and driftage of two rudder faces.
Multi-axis aircraft provides vertical lift using the rotor of approximate horizontal installation, passes through the control flight appearance of rotor rotating speed
State.Referring to Fig. 1 and Fig. 2, aircraft 001 is the six axle aircraft of " Y6 " pattern, and aircraft 001 has 3 horns 011, each
The both sides up and down of the end of horn 011, which are respectively fixed with a motor, the rotating shaft of each motor, is provided with a rotor, each
Two rotors of the end of horn 011 are a pair of positive and negative rotors, i.e. a pair with identical paddle type but the opposite rotor of propeller pitch angle.Often
Two rotors up and down of the individual end of horn 011 have identical rotating speed, and the air reaction torque of generation is cancelled out each other, so as to prevent from flying
Row device 001 spins.Coaxial arrangement, which can lift pulling force and have, above and below rotor can effectively control aircraft volume.But, multiaxis flight
The pulling force that the rotor of device is produced is mainly used in the gravity for overcoming Multi-axis aircraft to be subject to, and cruising time is extremely short.
The content of the invention
Present invention aims at providing, a kind of balance is good, mobility strong, environment Ying Xingqiang, Posture exchange reliability it is high and
The vertically taking off and landing flyer of energy-conservation.
The vertically taking off and landing flyer of the present invention, including fuselage, wing, empennage, undercarriage and the difference being arranged on wing
The first rotor power unit and the second rotor power unit positioned at fuselage both sides, the first rotor power unit and the second rotor are moved
Power unit is symmetrically distributed in the both sides of fuselage, the rotation of the rotation axis of the first rotor power unit and the second rotor power unit
Shaft axis point to the back lower place of fuselage, and the 3rd rotor power unit is arranged on the middle part of empennage width in which can vert.
From such scheme, power unit of the invention can be by the middle downside of air-flow intensively directive fuselage, effectively
Pressure below ground increase fuselage, improves the pressure difference between fuselage upper and lower sides, so as to improve take off vertically speed and the saving energy.
The first rotor power unit, the second rotor power unit and the 3rd rotor power unit composition being symmetrically arranged on wing etc.
Lumbar triangle shape, provides stable motive power point for complete machine, the 3rd rotor power unit that the rotation axis of rotor can vert
Vector air-flow can be provided in fuselage middle vertical plane, it is ensured that complete machine, which possesses good self-balancing ability and mobility, can overcome multiple
Miscellaneous weather environment, environmental suitability is strong.Can by simultaneously start the first rotor power unit, the second rotor power unit and
3rd rotor power unit puts down winged power as high speed, can now pass through the power unit rotation axis of horizontal the 3rd and reduction
First rotor power unit, the rotating speed of the second rotor power unit realize energy-conservation to improve dynamic efficiency；The can also only be started
One rotor power unit, the second rotor power unit as the flat power power that flies, the 3rd rotor power unit as generator or
Idle running；The 3rd rotor power unit can also only be started as flat fly power, the first rotor power unit, the second rotor power list
Member is as generator or dallies to save.The 3rd rotor power unit that the rotation axis of rotor can vert can be in fuselage
Vector air-flow is provided in vertical plane, after taking off vertically, the 3rd rotor power unit adjusts the air-flow towards fuselage inner underside to water
Put down backward or close the switching that can be achieved to take off vertically to horizontal flight posture.When flat winged at a high speed, by the 3rd rotor power list
First horizontally toward rear air-flow transposition can be achieved quickly to brake in the air forward towards fuselage inner underside or level, realize efficient
Mobility is controlled and the flight attitude of high reliability switches.
Further scheme is, the first rotor power unit, the second rotor power unit and the 3rd rotor power unit etc.
Away from distribution；In fuselage short transverse, the first rotor power unit, the second rotor power unit and the 3rd rotor power unit are big
Cause is distributed in sustained height.The equilibrium degree of the stability of aircraft in machine and transverse direction can so be improved.
Another further scheme is, the rotation of the rotation axis of the first rotor power unit and the second rotor power unit
The angle perseverance of straight line where the length direction of axis and fuselage is 45 °.The angle can both provide horizontal thrust, can provide vertical again
Go straight up to power, the rotation axis of the rotation axis of the first rotor power unit and the second rotor power unit need not vert, and improve
The reliability of flight attitude switching between VTOL and flat winged and hovering.
Further scheme is to be respectively arranged with the outside of the first rotor power unit and the second rotor power unit along machine
The preceding ventilating duct of body length direction extension, preceding ventilating duct is sweptback beveling cylinder, and preceding ventilating duct is not only advantageous to stabilization
Air-flow, also helps the effective bearing area of increase wing, increases the lift of wing, and preceding ventilating duct is sweptback beveling circle
Cylinder advantageously reduce air-flow to the fuselage back lower place flow when resistance.
Another further scheme is that rear ventilating duct is provided with the outside of the 3rd rotor power unit, rear ventilating duct be to
The beveling cylinder of top rake.Ventilating duct is not only advantageous to steady air flow afterwards, also helps the effective bearing area of increase wing, increases
Plus the lift of wing, rear ventilating duct be the beveling cylinder turned forward advantageously reduce air-flow to fuselage front lower place flow when resistance
Power.
Further scheme is again, and a pair of avoidance openings are provided with the inside of beveling cylinder.So be conducive to further
When ventilating duct is sweptback beveling cylinder before reducing, air-flow to the fuselage back lower place flow when resistance, and further subtract
When ventilating duct is the beveling cylinder turned forward after few, air-flow to fuselage front lower place flow when resistance.
Further, preceding ventilating duct is embedded in and is fixed on wing.Aircraft altitude is advantageously reduced, aircraft is improved
Intensity, mitigates aircraft weight.Further, on the width of wing, wing where the first rotor power cell distance
The distance of the end of side is about the distance of wing end where 1/6th of wing span, the second rotor power cell distance
About 1/6th of wing span, are conducive to strengthening wing structure intensity and ensure that fuselage laterally balances control.
It is another further, the ratio between the horizontal projected area of the aileron of wing and the horizontal projected area of wing are 35%
To between 45%.When taking off vertically, by the aileron bottom, gas-flow resistance when taking off vertically is advantageously reduced., will during vertical landing
Aileron is flattened, and is conducive to increasing the gas-flow resistance being subject to when aircraft declines, is improved landing stationarity.
Another further first drives camera, is arranged on the front upper place of fuselage, second drives camera, sets
In the bottom of fuselage.So it is easy to that advance and lifting running environment image can be obtained at any time, improves the reliability of flight control.
Further further, the rotor of the 3rd rotor power unit is displacement rotor.Power unit without verting completely
The reverse of air-flow can be achieved.Air-flow deflecting switching is rapid, and reliability is high, improves the mobility of aircraft.
Brief description of the drawings
Fig. 1 is the stereogram of existing aircraft；
Fig. 2 is the rearview of existing aircraft；
Fig. 3 is the top view of aircraft of the present invention；
Fig. 4 is the first stereogram of aircraft of the present invention；
Fig. 5 is the rearview of aircraft of the present invention；
Fig. 6 is Fig. 5 A-A sectional views；
Fig. 7 is the partial enlarged view of the omission commutator segment at Fig. 5 B；
Second stereogram of Fig. 8 aircraft of the present invention；
Fig. 9 is the partial enlarged view of Fig. 3 tail part；
Figure 10 is the steering wheel aileron system of the wing of aircraft of the present invention；
Figure 11 is the nose-gear of aircraft of the present invention；
Air-flow trend graph when Figure 12 is the VTOL of aircraft of the present invention;
Figure 13 is the top view of the displacement rotor system of aircraft of the present invention；
Figure 14 is Figure 13 C-C sectional views；
Figure 15 is confined explosion's stereogram of the displacement rotor system of aircraft of the present invention.
Embodiment
The vertically taking off and landing flyer of the present invention（Hereinafter referred to as aircraft）VTOL and horizontal high-speed flight can be realized.
The width W of aircraft is the width of fuselage, wing, empennage and each power unit, the length of aircraft
Direction L is the width of fuselage, wing, empennage and each power unit, and the short transverse H of aircraft is fuselage, wing, empennage
With the short transverse of each power unit.
Embodiment one
As shown in Fig. 3, Fig. 4 and Fig. 5, aircraft 100 of the invention has fuselage 110, wing 120, empennage 130, by preceding
The undercarriage 180 that foot stool 181 and rear leg 182 are constituted, is symmetrically distributed in the first rotor power unit of the both sides of fuselage 110
140 and the second rotor power unit 150, it is arranged on the 3rd rotor power at the middle part of the width of empennage 130 with can verting
Unit 160.The rotation axis of the rotation axis of first rotor power unit 140 and the second rotor power unit 150 points to fuselage
110 back lower place.It is preferred that, the first rotor power unit 140, the second rotor power unit 150 and the 3rd rotor power unit
160 are equally spaced, i.e. the first rotor power unit 140, the second rotor power unit 150 and the 3rd rotor power unit 160
Central distribution is in the fixed point of equilateral triangle.Further, in short transverse H, the first rotor power unit 140, second
The rotor power unit 160 of rotor power unit 150 and the 3rd is centrally located at sustained height.
First rotor power unit 140, the second rotor power unit 150 and the 3rd rotor power unit 160 are using altogether
The self-balancing of air reaction torque can be achieved in the double oar layouts of axle, each power unit.It is preferred that, the rotor of each power unit by
Carbon fiber is made, and the inside of blade is filled with foam, the light weight of this oar, intensity foot, moreover it is possible to absorb the vibrations of rotor.Empennage
A pair of commutator segments 131 are provided with 130.
Along fuselage length direction L, the rotor of ventilating duct 141 and second is moved before the outside of the first rotor power unit 140 is provided with
Ventilating duct 151 before the outside of power unit 150 is provided with, preceding ventilating duct 141,151 is sweptback beveling cylinder；3rd rotor is moved
The outside of power unit 160 is provided with rear ventilating duct 161, and rear ventilating duct 161 is the beveling cylinder turned forward.Chamfer the interior of cylinder
Side is provided with a pair of avoidance openings for being used to reduce gas-flow resistance, i.e. the preceding inner side of ventilating duct 141 is provided with avoidance 142 Hes of opening
143, the preceding inner side of ventilating duct 151 is provided with avoidance opening 152 and 153, and the preceding inner side of ventilating duct 161 is provided with avoidance 162 Hes of opening
163.Preceding ventilating duct 151 and rear ventilating duct 161 can play a part of supercharging and water conservancy diversion with rotor collocation, be conducive to improving pneumatic effect
Rate and power.
Preceding ventilating duct 141,151 is embedded in and is fixed on wing 120.It is preferred that, preceding ventilating duct 141,151 is molded over wing
On 120.Before first rotor power unit 140 and the second rotor power unit 150 are arranged on by three connecting rods 126 respectively
In ventilating duct 141,151, connecting rod 126 it is inner respectively with the first rotor power unit 140 and the second rotor power unit 150
Mounting disc connection, inwall of the outer end respectively with preceding ventilating duct 141,151 be connected.Preceding ventilating duct 141 is connected with two in it
Bar tie point is connected respectively close to wing 120 and two tie points of preceding ventilating duct 141, preceding ventilating duct 151 with two in it
The tie point of bar can so improve the entirety of wing 120 respectively close to wing 120 and two tie points of preceding ventilating duct 151
Intensity.Further, on the width of wing 120, rotation axis and the wing 120 of the first rotor power unit 140 are leaned on
The distance of the end of the nearly side of first rotor power unit 140 is about 1/6th of the span of wing 120；Second rotor is moved
The rotation axis of power unit 150 and distance of the wing 120 close to the end of the side of the first rotor power unit 150 are about machine
/ 6th of the span of the wing 120.
The ratio between the horizontal projected area of the aileron 121 of wing 120 and the horizontal projected area of wing are between 35% to 45%.
When taking off vertically, by the aileron bottom, gas-flow resistance when taking off vertically is advantageously reduced.During vertical landing, aileron is flattened, had
The gas-flow resistance being subject to when declining beneficial to increase aircraft, improves landing stationarity.
It is preferred that, the ratio between the horizontal projected area of the aileron 121 of wing 120 and the horizontal projected area of wing 120 are 35%
To between 45%.When taking off vertically, by the bottom of aileron 121, gas-flow resistance when taking off vertically is advantageously reduced.During vertical landing,
Aileron 121 is flattened, is conducive to increasing the gas-flow resistance being subject to when aircraft declines, improves landing stationarity.
The front upper place of fuselage 110 is provided with printing opacity deep bead 171, is provided with it towards the first of front and drives camera
（It is not shown）.
As shown in Figure 6, it is preferred that the rotation axis 154 of the second rotor power unit 150 and the length direction L of fuselage 110
Angle perseverance is 45 ° formed by the straight line at place；Likewise, the rotation axis and the length of fuselage of the first rotor power unit 140
It is 45 ° that angle formed by straight line where the L of direction is also permanent.The angle can both provide horizontal thrust, and vertical lift can be provided again, is had
Realize that left-right balance is adjusted beneficial to aircraft, be advantageously implemented the stable low flight of aircraft.
As shown in fig. 7, the 3rd rotor power unit 160 is rotatably installed in rotating shaft 164, motor 165 passes through worm screw
The rotor power unit 160 of gear drive shaft 164 and the 3rd verts.Obviously, motor 165 can also be by toothed belt transmission, even
The mode such as bar transmission or Chain conveyer drives the 3rd rotor power unit 160 to vert.
As shown in figure 8, the lower section of fuselage 110 is provided with printing opacity deep bead 172, second driving downward is provided with it
Sail camera 172.The bottom of wing 120 is provided with the groove position 183 for storing front foot frame 181.
As shown in figure 9, steering wheel 166 controls the variable-distance being arranged on the 3rd rotor power unit 160 to revolve by driving lever 167
The propeller pitch angle of the wing.
As shown in Figure 10, installed on the output shaft of steering wheel 122 on rear arm 123, aileron 121 and torque arm 125, rocking arm are installed
Connected between 123 and torque arm 125 by connecting rod 124.
As shown in figure 11, front foot frame 181 has sleeve 184, slide bar 185, is arranged between sleeve 184 and slide bar 185
Spring（It is not shown）, a pair opposed spacing connecting rods 186 and the wheel 187 positioned at the end of slide bar 185.Opposed spacing connecting rod 186 can be with
Improve the bulk strength of front foot frame 181.
When the aircraft 100 of the present embodiment takes off vertically, the 3rd rotor power unit 160 164 can vert to it around the shaft
The rotation axis of rotor points to the front lower place of fuselage 110, it is preferred that the rotating shaft of the 3rd rotor power unit 160 is respectively with first
The rotation axis of the rotor power unit 150 of rotor power unit 140 and second is vertical.When taking off, air-flow intensively directive fuselage
Middle downside, effectively increase the pressure below fuselage, improve the pressure difference between both sides above and below fuselage, taken off vertically so as to improve
Speed and the saving energy.Take off vertically to after predetermined altitude, the 3rd rotor power unit 160 stops, and around the shaft 164 vert to
The rotation axis of its rotor points to the rear of fuselage 110, restarts, can so reduce the resistance that verts.3rd rotor power list
After the stalling of member 160, aircraft 100 is advanced under the first rotor power unit 140 and the driving of the second rotor power unit 150
Make a concerted effort and move ahead, move ahead when, empennage can provide lift for fuselage afterbody, even if the 3rd rotor power unit 160 stop incline
Turn, fuselage afterbody also will not excessive convergence.When the 3rd rotor power unit 160 164 verts to the rotary shaft of its rotor around the shaft
Line is pointed to behind the rear of fuselage 110, can start the first rotor power unit 140, the second rotor power unit 150 and the simultaneously
Three rotor power units 160 are power winged before aircraft 100 is provided, and can also only lean on the first rotor power unit 140, second
Rotor power unit 150 is power winged before aircraft 100 is provided, and can also only be flight by the 3rd rotor power unit 160
The power winged before providing of device 100.When preceding winged, pass through the 3rd rotor power unit 160 that verts so that the air-flow sprayed backward is perpendicular
Downward shift in straight plane, can be rapidly completed the pitching motion of aircraft 100.When preceding winged, it can be moved by the 3rd rotor that verts
Power unit 160, makes the rotation axis of its rotor point to the front lower place of fuselage, so that brake air flow power is provided for aircraft 100,
Realize aerial emergency brake, when verting the 3rd rotor power unit 160, can first stop, wait vert in place afterwards restart.When winged
When row device 100 needs vertical landing, the 3rd rotor power unit 160 stops, and 164 verts around the shaft to the rotary shaft of its rotor
Line points to the front lower place of fuselage 110, restarts, and can so reduce the resistance that verts, and improves the air pressure of the downside of aircraft 100, just
Landed in aircraft using less power of motor.
Referring to Fig. 9 and Figure 12.It is further preferred that the rotation axis of the 3rd rotor power unit 160 revolves with first respectively
The rotation axis of the rotor power unit 150 of wing power unit 140 and second is vertical.When taking off, air-flow intensively directive fuselage
Middle downside.Take off vertically to after predetermined altitude, the 3rd rotor power unit 160 164 verts to the rotary shaft of its rotor around the shaft
Line points to the front of fuselage 110, during verting, the propeller pitch angle reversion of the control displacement of steering wheel 166 rotor 168, makes air-flow rapid
Change is sprayed backward.The resistance that verts can so be reduced, air-flow deflecting is rapid, the stationarity of flight attitude switching is improved, reliability and
Security.Likewise, during horizontal flight, the first rotor power unit 140, the second rotor power unit 150 can be started simultaneously
Be power winged before aircraft 100 is provided with the 3rd rotor power unit 160, can also only lean on the first rotor power unit 140,
Second rotor power unit 150 is power winged before aircraft 100 is provided, and can also be by the 3rd rotor power unit 160 only
The power winged before providing of aircraft 100.When preceding winged, pass through the 3rd rotor power unit 160 that verts so that the air-flow sprayed backward
The downward shift in perpendicular, can be rapidly completed the pitching motion of aircraft 100.When needing brake, only steering wheel 166 need to be controlled
The propeller pitch angle of displacement rotor 168 is inverted, air-flow is sprayed forward, quick airflow direction switching can be in very short time
The interior aerial brake of realization.When aircraft 100 needs vertical landing, control steering wheel 166 is anti-by the propeller pitch angle of displacement rotor 168
Turn, air-flow is sprayed forward, while controlling the rotation axis of displacement rotor 168 to vert and point to the front lower place of fuselage 110, so
The resistance that verts can be reduced, air-flow deflecting is quickly realized, the air pressure of the downside of aircraft 100 is improved, is easy to aircraft to use smaller
Power of motor landed, further shorten the landing time and improve the safety and reliability of landing.
It is preferred that, the first rotor power unit, the second rotor power unit and the 3rd rotor power unit have one respectively
To the positive and reverse return wing, under such a collocation, during VTOL, can by increase the 3rd rotor power unit rotor rotating speed or oar
Elongation controls the anterior-posterior balance of fuselage.Certainly, the first rotor power unit, the rotor of the second rotor power unit can also be
Single rotor, now, the first rotor power unit, the rotor of the second rotor power unit are a pair of positive and negative rotors, likewise, vertically
During landing, the anterior-posterior balance of fuselage can be controlled by the rotating speed or propeller pitch angle of the rotor for adjusting the 3rd rotor power unit.
The rotor of 3rd rotor power unit can be a pair of coaxial positive and negative rotors；It is single rotor that can also adopt, now the 3rd rotor
Power unit needs can be around the rotation axis rotation along aircraft altitude direction.
The tail of the present invention is not limited to V-type tail, and can also be includes the U-shaped or T-shaped machine of elevator and rudder respectively
Tail.
As shown in Figure 13, Figure 14 and Figure 15, displacement rotor system includes steering wheel 166, driving lever 167, oar seat 191, gland
192, kuppe 193, the displacement rotor 168 with three blades 194, slip cap 195, bearing 196 and bearing 197.Gland 192
It is arranged on by screw on oar seat 191, the outer ring of bearing 196 is pressed between gland 192 and oar seat 191.The root of blade 194
Portion is provided with rotating shaft 194a and rotating shaft 194b, and rotating shaft 194a is arranged in bearing 196, and blade 194 is rotatable by bearing 196
On oar seat 191.Rotating shaft 194b is inserted in the hole 198 of slip cap 195.Slip cap 195 is enclosed on oar with can sliding axially
The outside of seat 191, the one end in the outside of slip cap 195 and the inner ring of bearing 197 are fixed, and outer ring and the driving lever 167 of bearing 197 are consolidated
It is fixed.Steering wheel 166 can control the propeller pitch angle of blade 194 by driving lever 167.
Certain displacement rotor system is not limited to above-mentioned concrete structure, can also be the displacement rotor of the afterbody of similar helicopter
System.
Finally it should be noted that the invention is not restricted to above-mentioned embodiment, through non-on the basis of embodiment of above
The embodiment that creativeness is changed is still within claims hereof protection domain.
Claims (10)
1. vertically taking off and landing flyer, including fuselage, wing, empennage, undercarriage and it is arranged on the wing and is located at institute respectively
State the first rotor power unit and the second rotor power unit of fuselage both sides；
It is characterized in that：
First rotor power unit and the second rotor power unit are symmetrically distributed in the both sides of the fuselage；
The rotation axis of the rotation axis of the first rotor power unit and the second rotor power unit points to the machine
The back lower place of body；
3rd rotor power unit, is arranged on the middle part of the empennage width in which can vert；
When the aircraft vertical takes off, the 3rd rotor power unit can vert to the rotation axis sensing of rotor around the shaft
The front lower place of the fuselage.
2. vertically taking off and landing flyer according to claim 1, it is characterised in that：
First rotor power unit, the second rotor power unit and the 3rd rotor power unit are equally spaced；
In the fuselage short transverse, the first rotor power unit, the second rotor power unit and the described 3rd
Rotor power unit is substantially distributed in sustained height.
3. vertically taking off and landing flyer according to claim 1, it is characterised in that：
The rotation axis of the rotation axis of the first rotor power unit and the second rotor power unit and the fuselage
Length direction where straight line angle perseverance be 45 °.
4. vertically taking off and landing flyer according to claim 3, it is characterised in that：
It is respectively arranged with the outside of the first rotor power unit and the second rotor power unit along the fuselage length side
To the preceding ventilating duct of extension；
The preceding ventilating duct is sweptback beveling cylinder.
5. vertically taking off and landing flyer according to claim 1：It is characterized in that：
Rear ventilating duct is provided with the outside of the 3rd rotor power unit；
The rear ventilating duct is the beveling cylinder turned forward.
6. the vertically taking off and landing flyer according to claim 4 or 5, it is characterised in that：
A pair of avoidance openings are provided with the inside of the beveling cylinder.
7. vertically taking off and landing flyer according to claim 4, it is characterised in that：
The preceding ventilating duct is embedded in and is fixed on the wing.
8. the vertically taking off and landing flyer according to any one of claim 1 to 5, it is characterised in that：
The ratio between the horizontal projected area of the aileron of the wing and the horizontal projected area of the wing are between 35% to 45%.
9. the vertically taking off and landing flyer according to any one of claim 1 to 5, it is characterised in that：
First drives camera, is arranged on the front upper place of the fuselage；
Second drives camera, is arranged on the bottom of the fuselage.
10. the vertically taking off and landing flyer according to any one of claim 1 to 5, it is characterised in that：
The rotor of the 3rd rotor power unit is displacement rotor.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510794978.4A CN105346719B (en) | 2015-11-18 | 2015-11-18 | Vertically taking off and landing flyer |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510794978.4A CN105346719B (en) | 2015-11-18 | 2015-11-18 | Vertically taking off and landing flyer |
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| Publication Number | Publication Date |
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| CN105346719A CN105346719A (en) | 2016-02-24 |
| CN105346719B true CN105346719B (en) | 2017-11-03 |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105857594B (en) * | 2016-05-31 | 2018-11-09 | 聂平利 | Hedgehopping device |
| CN106394886A (en) * | 2016-06-15 | 2017-02-15 | 珠海市磐石电子科技有限公司 | Multi-axis aircraft capable of movably flying, flying assisting platform and flying method |
| CN107757914A (en) * | 2016-08-15 | 2018-03-06 | 南京福尔摩斯智能科技有限公司 | Double dynamical VTOL fixed-wing unmanned plane |
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