CN107672786A - The aircraft and its change flying method of a kind of fixed-wing and rotor change - Google Patents
The aircraft and its change flying method of a kind of fixed-wing and rotor change Download PDFInfo
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- CN107672786A CN107672786A CN201711061621.0A CN201711061621A CN107672786A CN 107672786 A CN107672786 A CN 107672786A CN 201711061621 A CN201711061621 A CN 201711061621A CN 107672786 A CN107672786 A CN 107672786A
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- 230000007246 mechanism Effects 0.000 claims description 19
- 230000005484 gravity Effects 0.000 claims description 10
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
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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
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
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Abstract
The invention discloses a kind of fixed-wing and the aircraft and its change flying method of rotor change, including：Fuselage, wing, change assembly, propeller, empennage；Waist sets change assembly, and change assembly both sides connect wing, and propeller, afterbody installation empennage are installed on wing.It is X-axis to define fuselage axis, and wing spar axis is Y-axis, and Z axis crosses X-axis, Y-axis intersection point perpendicular to X-axis, Y-axis plane；The effect of change assembly 3 is to allow wing and assembly to rotate around X-axis；Wing can rotate around Y-axis, wing angle of attack continuous variable in Y-axis, Z axis plane.The advantage of the invention is that：The wing of fixed-wing can be controlled to be rotated around fuselage datum, it can be changed simultaneously with control machine wing incidence in the surfaces of revolution, the translation of wing during fixed-wing flight is converted to and rotated when rotor takes off vertically around aircraft longitudinal axis, dynamic equilibrium can be kept when rotating at a high speed, realize flight and the control mode of rotor.
Description
Technical field
The present invention relates to vehicle technology field, aircraft and its change of more particularly to a kind of fixed-wing and rotor change
Flying method.
Background technology
At present, Fixed Wing AirVehicle pneumatic efficiency is high, and applicable ceiling scope is wide, and mission payload is various, but to landing site
Require higher with mode.
Conventional Fixed Wing AirVehicle is by the flat vertical fin motor mechanism of fuselage wing into wing peace vertical fin stabilization rigidly connects
Fuselage is connected to, driven by engine propeller provides the power of flight forward to overcome flight resistance, and control system controls rudder face inclined
Turn, torque change of flight device posture is provided by air flow power；Because engine is rigidly secured to body or wing, and it is to provide
Power forward, therefore, such aircraft must rely on sliding race either ejection or accelerated take-off, can not accomplish economic and reliable all the time
Take off vertically.
Rotor requires low to landing site, but its payload is smaller, and cruising time is multiple far away from fixed-wing, mechanical structure
Miscellaneous fault rate is high.Conventional gyroplane uses single rotor tailing rotor, either coaxial or row, file, and its gravity is produced by rotor
Raw lift balances, and the resistance of advance overcomes by the component of lift.Driven by multi-stage speed reducer conversion and passing power
Rotor rotational.Aircraft landing and posture are controlled by adjusting rotor rotating speed and pitch.Rotor directly overcomes the mode of gravity
It is required that engine power is big, therefore payload and voyage, far away from fixed-wing, ceiling is low compared with fixed-wing, flight speed
Spend low.
Fixed-wing adds the composite mode of rotor, with the obvious advantage in landing site and load, but its rotor partial power
Source is single, and transmission and control system are complicated, take mass efficient load.Fixed-wing adds the composite mode of rotor, be exactly
Multiple rotors are installed on conventional fixed-wing platform additional to realize fixed-wing VTOL.The chief is respectively taken, respectively to shortage.Rotor is only rising
Depression of order section provides lift and overcomes gravity, and under average flight state, rotor part-structure will take significant portion payload, and increase
Add flight resistance.This addition composite construction weight increase, the gravity that landing stage rotor need to overcome increases, therefore rotor power
The partial weight of itself and power are intended to accordingly increase.The energy of consumption sharply increases, therefore efficiency is low, and payload is small.
It is related to control and transmission, the power of more rotors can only be provided by electric power.
Tilting rotor be it is a kind of change the direction of pulling force around wing rotation by rotor, reach and offset gravity and advance side
To the aircraft (such as U.S. army active service V2) of air drag.Tilting rotor needs complicated mechanical structure to control rotor to vert completion
The direction change of power, failure rate of machinery are high.And flight state is extremely unstable in power direction transfer process, probability out of control
Greatly, economy is bad.
The content of the invention
The defects of present invention is directed to prior art, there is provided a kind of aircraft of fixed-wing and rotor change and its change fly
Row method, can effectively solve the problem that the above-mentioned problems of the prior art.
In order to realize above goal of the invention, the technical scheme that the present invention takes is as follows：
A kind of aircraft of fixed-wing and rotor change, including：Fuselage 1, wing 2, change assembly 3, propeller 4, empennage
5；The middle part of fuselage 1 sets change assembly 3, and the both sides of change assembly 3 connect wing 2, propeller 4, the afterbody of fuselage 1 are installed on wing 2
Empennage 5 is installed.
The change assembly 3 includes：Fuselage connecting circular tube 6, lockable mechanism 7, cross connecting piece 8, servomotor 9, wing
Pipe beam 11, turbo tooth 12, housing 14, clutch shaft bearing 10, second bearing 13,3rd bearing 15, fourth bearing 16,5th bearing
18 and 6th bearing 19；
Fuselage connecting circular tube 6 connects front and rear fuselage, is cased with 3rd bearing 15 and fourth bearing 16, wing pipe beam outside it
11 are arranged on the both sides of fuselage connecting circular tube 6, and for the wing 2 that is connected, wing pipe beam 11 passes through clutch shaft bearing 10 and second
Bearing 13, clutch shaft bearing 10 and the outer wall of second bearing 13 are fixed with the inwall of cross connecting piece 8；3rd bearing 15 and fourth bearing 16
Outer wall is fixed with the inwall of cross connecting piece 8, and cross connecting piece 8 is rotated freely around fuselage connecting circular tube 6 and axial restraint.
Wing pipe beam 11 can be rotated freely around change assembly 3 and axial restraint.
The rotational angle of wing 2 is rigidly connected by the servomotor 9 for being rigidly connected in cross connecting piece 8 by scroll bar control
Controlled in the turbo tooth 12 on wingbar.
Lockable mechanism 7 is fixed on fuselage, controls change assembly 3 to rotate by automatically controlled lock pin.
Housing 14 is covering, and it is round and smooth excessively with the outer wall of fuselage 1 and the outer wall of wing 2.
Further, it is X-axis to define fuselage axis, and wing spar axis is Y-axis, and Z axis crosses X perpendicular to X-axis, Y-axis plane
Axle, Y-axis intersection point；The effect of change assembly 3 is to allow wing and assembly to rotate around X-axis；Wing can rotate around Y-axis, machine
Wing angle of attack continuous variable in Y, Z plane.Angle of attack angle passes through scroll bar by the servomotor 9 for being rigidly connected in cross connecting piece 8
The turbo tooth 12 being rigidly connected on wingbar is controlled to control；Make full use of the self-locking performance of worm and gear passing power and unidirectional
Property.
A kind of flying method based on above-mentioned aircraft, including following pattern：
Fixed wing slip runs landing pattern：
Change assembly 3 is locked by lockable mechanism 7 with fuselage, and aircraft now is provided pulling force forward by propeller 4
Offset resistance.Servomotor 9 controls the angle of attack of all-moving wing 2, and the lift for changing two half wings 2 realizes aircraft rolling, lifts
Rudder and vertical fin rudder face control pitching and the direction of aircraft respectively, realize normal flight；Vertical fin is equipped with the wheel rotated with rudder face,
Tail wheel and main landing gear form tail wheel type landing gear；
Rotor VTOL pattern：
On aircraft X axis uprightly and ground, four wheels support aircraft of flat vertical fin wing tip is upright；Two wings are differential
Rotate 90 degree, work as propeller rotational, produce the pulling force to the direction of arrow, wing is in the presence of torque, it will around X-axis Y-axis,
Z axis Plane Rotation, symmetrical another wing similarly rotate；Though wing now has cut air, symmetrical airfoil upper and lower surface
Have no pressure difference；When wing is under the driving of Servo-controller, with Y-axis, Z axis planar row into angle a, the wing now rotated produces the string of a musical instrument
Raw lift principle is identical with the propeller of helicopter, produces the power of phase X-direction and the resistance opposite with wing rotation direction, resistance
Offset, fuselage can't be produced anti-twisted by propeller pulling force.Attitude of flight vehicle during VTOL is controlled by flat vertical fin rudder face,
The downwash flow of main rotor acts on aerofoil, and the deflection of rudder face produces corresponding moment loading in aircraft center of gravity, realizes posture
Holding and change；
Rotor turns fixed-wing pattern：
Aircraft vertical takes off, and reaches safe altitude, translates into fixed-wing mode flight.It is by flat vertical fin rudder first
The angle of the posture of face change of flight device, X-axis and horizontal plane progressively diminishes, and with the increase of flying speed, wing helical angle is gradual
Increase, propeller pulling force taper into the component of Y-axis, Z axis plane, and wing assembly is around X-axis spin down and stops, locking machine
Structure 7 is locked, and assembly is rigidly connected with fuselage；Servo-controller control all-moving wing realizes roll attitude control, realizes fixed-wing mould
Formula is flown.
Fixed-wing switch rotor pattern：
Aircraft needs vertical landing or stagnant space-time, need to be converted to rotor mode from fixed-wing；This pattern be divided into head to
Lower and tail down two ways, can be selected according to load condition；Aircraft is reached near level point, and lockable mechanism 7 unlocks, and watches
Take motor 9 and control wing helical angle, under the pulling force effect of inertia and propeller 4, assembly accelerates to rotate around X-axis, machine now
Wing Plane of rotation helps aircraft is horizontal to slow down；Horizontal tail control fuselage X-axis increases with horizontal plane angle and keeps fuselage upright, most
Whole rotor lift and gravitational equilibrium, reduce rotor rotating speed and helical angle, aircraft and slowly decline, during close to ground, pass through distance
Sensor measures ground clearance, and flight control system control rotor rotating speed and helical angle change at a slow speed, landing of finally contacting to earth；
Head falls downward mode：Aircraft is reached near level point, and lockable mechanism 7 unlocks, Servo-controller control wing
Helical angle, under the pulling force effect of inertia and propeller, assembly accelerates to rotate around X-axis, and wing Plane of rotation now provides liter
Dynamic balance aircraft gravity.But flow through flat vertical fin without enough air-flows, it is necessary to there is certain decrease speed to keep gas
Flow the effect to flat vertical fin；When aircraft is to approach ground, ground clearance, flight control system control rotation are measured by range sensor
Wing rotating speed and helical angle change at a slow speed, quickly increase lift, make aircraft down and slowly contact to earth.Such a mode presses load
Matter is selected, it is necessary to install preposition undercarriage additional.
Compared with prior art the advantage of the invention is that：The wing of fixed-wing can be controlled to be rotated around fuselage datum, together
When can with control machine wing incidence the surfaces of revolution change, by the translation of wing during fixed-wing flight be converted to when rotor takes off vertically around
Aircraft longitudinal axis rotates.
Nose-high, now around the wing that fuselage rotates as the rotor of helicopter, suitable rotating speed and the angle of attack can produce
Raw appropriate lift, flat vertical fin rudder face are in rotor downwash, Torque Control fuselage posture caused by control surface deflection.
The power of driving wing rotation is come to fuselage, then has reaction force acts in fuselage, it is necessary to which other mechanisms support
Disappear.Wing revolving force in the present invention is come to the two engine-driven propellers installed on wing.Rotation assembly and fuselage
Between be to be connected by bearing, therefore the reaction force of fuselage is only the kinetic force of friction of bearing.Wing uses symmetrical airfoil, structure weight
Measure it is full symmetric, make its high speed rotate when keep dynamic equilibrium.
After rotor mode lift-off, aircraft will progressively be converted into fixed-wing pattern, the engine and propeller on wing
Line of pull is parallel with aircraft longitudinal axis, there is provided the pulling force that aircraft advances.It is locked around fuselage rotation assembly after completing conversion, but wing
The angle of attack it is still controlled, wing now has both the function of aileron and wing flap, realizes flight and the control mode of fixed-wing.
Brief description of the drawings
Fig. 1 is the upward view of aircraft of the embodiment of the present invention；
Fig. 2 is the structural representation of change assembly of the embodiment of the present invention；
Fig. 3 is aircraft wing change schematic diagram of the embodiment of the present invention.
Embodiment
For the objects, technical solutions and advantages of the present invention are more clearly understood, develop simultaneously embodiment referring to the drawings, right
The present invention is described in further details.
As shown in figure 1, aircraft including fuselage 1, wing 2, change assembly 3, the spiral of a kind of fixed-wing and rotor change
Oar 4, empennage 5；The middle part of fuselage 1 sets change assembly 3, and the both sides of change assembly 3 connect wing 2, propeller 4, machine are installed on wing 2
The afterbody of body 1 installs empennage 5.
As shown in Fig. 2 the change assembly 3 includes：Fuselage connecting circular tube 6, lockable mechanism 7, cross connecting piece 8, servo
Motor 9, wing pipe beam 11, turbo tooth 12, housing 14, clutch shaft bearing 10, second bearing 13,3rd bearing 15, fourth bearing
16th, 5th bearing 18 and 6th bearing 19；
Fuselage connecting circular tube 6 connects front and rear fuselage, is cased with 3rd bearing 15 and fourth bearing 16, wing pipe beam outside it
11 are arranged on the both sides of fuselage connecting circular tube 6, and for the wing 2 that is connected, wing pipe beam 11 passes through clutch shaft bearing 10 and second
Bearing 13, clutch shaft bearing 10 and the outer wall of second bearing 13 are fixed with the inwall of cross connecting piece 8；3rd bearing 15 and fourth bearing 16
Outer wall is fixed with the inwall of cross connecting piece 8, and cross connecting piece 8 is rotated freely around fuselage connecting circular tube 6 and axial restraint.
Wing pipe beam 11 can be rotated freely around change assembly 3 and axial restraint.
The rotational angle of wing 2 is rigidly connected by the servomotor 9 for being rigidly connected in cross connecting piece 8 by scroll bar control
Controlled in the turbo tooth 12 on wingbar.
Lockable mechanism 7 is fixed on fuselage, controls change assembly 3 to rotate by automatically controlled lock pin.
Housing 14 is covering, and it is round and smooth excessively with the outer wall of fuselage 1 and the outer wall of wing 2.
As shown in figure 3, it is X-axis to define fuselage axis, wing spar axis is Y-axis, and Z axis crosses X perpendicular to X-axis, Y-axis plane
Axle, Y-axis intersection point.The effect of change assembly 3 is to allow wing and assembly to rotate around X-axis；Wing can rotate around Y-axis, machine
Wing angle of attack continuous variable in Y, Z plane.Angle of attack angle passes through scroll bar by the servomotor 9 for being rigidly connected in cross connecting piece 8
The turbo tooth 12 being rigidly connected on wingbar is controlled to control.Make full use of the self-locking performance of worm and gear passing power and unidirectional
Property.
The offline mode of aircraft is various, including following pattern：
Fixed wing slip runs landing pattern：
Change assembly 3 is locked by lockable mechanism 7 with fuselage, and aircraft now is provided pulling force forward by propeller 4
Offset resistance.Servomotor 9 controls the angle of attack of all-moving wing 2, and the lift for changing two half wings 2 realizes aircraft rolling, lifts
Rudder and vertical fin rudder face control pitching and the direction of aircraft respectively, realize normal flight.Vertical fin is equipped with the wheel rotated with rudder face,
Tail wheel and main landing gear form tail wheel type landing gear.
Rotor VTOL pattern：
On aircraft X axis uprightly and ground, four wheels support aircraft of flat vertical fin wing tip is upright.Two wings are differential
90 degree are rotated, aircraft enters VTOL pattern.Work as propeller rotational, produce the pulling force to the direction of arrow, wing is in torque
In the presence of, it will similarly rotated in YZ Plane Rotations, symmetrical another wing around X-axis.Though wing now has cut air,
But symmetrical airfoil upper and lower surface has no pressure difference.When wing is under the driving of Servo-controller, the string of a musical instrument and YZ planar rows into angle a, this
Shi Xuanzhuan wing produces that lift principle is identical with the propeller of helicopter, produce phase X-direction power and with wing rotation direction
Opposite resistance, resistance are offset by propeller pulling force, fuselage can't be produced anti-twisted.Attitude of flight vehicle during VTOL by
Flat vertical fin rudder face control, the downwash flow of main rotor act on aerofoil, and the deflection of rudder face produces corresponding moment loading in flight
Think highly of the heart, realize the holding and change of posture.
Rotor turns fixed-wing pattern：
Aircraft vertical takes off, and reaches safe altitude, translates into fixed-wing mode flight.It is by flat vertical fin rudder first
The angle of the posture of face change of flight device, X-axis and horizontal plane progressively diminishes, and with the increase of flying speed, wing helical angle is (with rotation
The angle a) for turning plane gradually increases, and propeller pulling force tapers into the component of YZ planes, and wing assembly is around X-axis spin down
And stop, lockable mechanism 7 is locked, and assembly is rigidly connected with fuselage.Servo-controller control all-moving wing realizes roll attitude control,
Realize fixed-wing mode flight.
Fixed-wing switch rotor pattern：
Aircraft needs vertical landing or stagnant space-time, need to be converted to rotor mode from fixed-wing.This pattern be divided into head to
Lower and tail down two ways, can be selected according to load condition.Aircraft is reached near level point, and lockable mechanism 7 unlocks, and watches
Take motor 9 and control wing helical angle, under the pulling force effect of inertia and propeller 4, assembly accelerates to rotate around X-axis, machine now
Wing Plane of rotation helps aircraft is horizontal to slow down.Horizontal tail control fuselage X-axis increases with horizontal plane angle and keeps fuselage upright, most
Whole rotor lift and gravitational equilibrium, reduce rotor rotating speed and helical angle, aircraft and slowly decline, during close to ground, pass through distance
Sensor measures ground clearance, and flight control system control rotor rotating speed and helical angle change at a slow speed, landing of finally contacting to earth.
Head falls downward mode：Aircraft is reached near level point, while lockable mechanism 7 unlocks, Servo-controller control
Wing helical angle, under the pulling force effect of inertia and propeller, assembly accelerates to rotate around X-axis, and wing Plane of rotation now carries
Aircraft gravity is balanced for lift.But flow through flat vertical fin without enough air-flows, it is necessary to there is certain decrease speed to protect
Hold effect of the air-flow to flat vertical fin；When aircraft is to approach ground, ground clearance, flight control system control are measured by range sensor
Rotor rotating speed processed and helical angle change at a slow speed, quickly increase lift, make aircraft down and slowly contact to earth.Such a mode is by load
Lotus property is selected, it is necessary to install preposition undercarriage additional.
One of ordinary skill in the art will be appreciated that embodiment described here is to aid in reader and understands this hair
Bright implementation, it should be understood that protection scope of the present invention is not limited to such especially statement and embodiment.Ability
The those of ordinary skill in domain can be made according to these technical inspirations disclosed by the invention it is various do not depart from essence of the invention its
Its various specific deformations and combination, these deformations and combination are still within the scope of the present invention.
Claims (3)
1. a kind of fixed-wing and the aircraft of rotor change, it is characterised in that including：Fuselage (1), wing (2), change assembly
(3), propeller (4), empennage (5)；Change assembly (3) is set in the middle part of fuselage (1), change assembly (3) both sides connect wing (2),
Propeller (4), fuselage (1) afterbody installation empennage (5) are installed on wing (2)；
The change assembly (3) includes：Fuselage connecting circular tube (6), lockable mechanism (7), cross connecting piece (8), servomotor
(9), wing pipe beam (11), turbo tooth (12), housing (14), clutch shaft bearing (10), second bearing (13), 3rd bearing
(15), fourth bearing (16), 5th bearing (18) and 6th bearing (19)；
Fuselage before and after fuselage connecting circular tube (6) connection, is cased with 3rd bearing (15) and fourth bearing (16), wing pipe outside it
Beam (11) is arranged on fuselage connecting circular tube (6) both sides, and for the wing that is connected (2), wing pipe beam (11) passes through first axle
(10) and second bearing (13) are held, clutch shaft bearing (10) and second bearing (13) outer wall are fixed with cross connecting piece (8) inwall；The
Three bearings (15) and fourth bearing (16) outer wall are fixed with cross connecting piece (8) inwall, and cross connecting piece (8) connects around fuselage to be justified
Pipe (6) rotates freely and axial restraint；
Wing pipe beam (11) can be rotated freely around change assembly (3) and axial restraint；
The rotational angle of wing (2) is connected by the servomotor (9) for being rigidly connected in cross connecting piece (8) by scroll bar control rigidity
Turbo tooth (12) control being connected on wingbar；
Lockable mechanism (7) is fixed on fuselage, controls change assembly (3) to rotate by automatically controlled lock pin；
Housing (14) is covering, and it is round and smooth excessively with fuselage (1) outer wall and wing (2) outer wall.
2. a kind of fixed-wing according to claim 1 and the aircraft of rotor change, it is characterised in that：Define fuselage axis
For X-axis, wing spar axis is Y-axis, and Z axis is perpendicular to X-axis, Y-axis plane and crosses X-axis, Y-axis intersection point；The effect of change assembly (3)
It is wing and assembly is rotated around X-axis；Wing can rotate around Y-axis, and wing (2) angle of attack in Y-axis, Z axis plane connects
It is continuous variable；Angle of attack angle is rigidly connected in machine by the servomotor (9) for being rigidly connected in cross connecting piece (8) by scroll bar control
Turbo tooth (12) control on spar；Make full use of the self-locking performance and one-way of worm and gear passing power.
3. the flying method of a kind of fixed-wing according to claim 2 and the aircraft of rotor change, it is characterised in that bag
Include following pattern：
Fixed wing slip runs landing pattern：
Change assembly (3) is locked by lockable mechanism (7) with fuselage, drawing of the aircraft by propeller (4) offer forward now
Power offset resistance；The angle of attack of servomotor (9) control all-moving wing (2), the lift for changing two half wings (2) realize that aircraft rolls
Turn, elevator and vertical fin rudder face control pitching and the direction of aircraft respectively, realize normal flight；Vertical fin is equipped with and rotated with rudder face
Wheel, tail wheel and main landing gear form tail wheel type landing gear；
Rotor VTOL pattern：
On aircraft X axis uprightly and ground, four wheels support aircraft of flat vertical fin wing tip is upright；The differential rotation of two wings
90 degree, work as propeller rotational, produce the pulling force to the direction of arrow, wing is in the presence of torque, it will around X-axis in Y-axis, Z axis
Plane Rotation, symmetrical another wing similarly rotate；Though wing now has cut air, symmetrical airfoil upper and lower surface has no
Pressure difference；When wing is under the driving of Servo-controller, with Y-axis, Z axis planar row into angle a, the wing now rotated produces to be risen the string of a musical instrument
Power principle is identical with the propeller of helicopter, produces the lift of same X-direction and the resistance opposite with wing rotation direction, resistance by
Propeller pulling force is offset, and fuselage can't be produced anti-twisted；Attitude of flight vehicle during VTOL is controlled by flat vertical fin rudder face, main
The downwash flow of rotor acts on aerofoil, and the deflection of rudder face produces corresponding moment loading in aircraft center of gravity, realizes posture
Keep and change；
Rotor turns fixed-wing pattern：
Aircraft vertical takes off, and reaches safe altitude, translates into fixed-wing mode flight；It is to be changed by flat vertical fin rudder face first
The angle of the posture of change aircraft, X-axis and horizontal plane progressively diminishes, and with the increase of flying speed, wing helical angle gradually increases,
Propeller pulling force tapers into the component of Y-axis, Z axis plane, and wing assembly is around X-axis spin down and stops, lockable mechanism (7)
Locked, assembly is rigidly connected with fuselage；Servo-controller control all-moving wing realizes roll attitude control, realizes that fixed-wing pattern flies
OK；
Fixed-wing switch rotor pattern：
Aircraft needs vertical landing or stagnant space-time, need to be converted to rotor mode from fixed-wing；This pattern be divided into head downwards and
Tail down two ways, it can be selected according to load condition；Aircraft is reached near level point, lockable mechanism (7) unblock, servo
Motor (9) controls wing helical angle, and under the pulling force effect of inertia and propeller (4), assembly accelerates to rotate around X-axis, now
Wing Plane of rotation helps aircraft is horizontal to slow down；Horizontal tail control fuselage X-axis increases with horizontal plane angle and keeps fuselage upright,
Final rotor lift and gravitational equilibrium.Rotor rotating speed and helical angle, aircraft is reduced slowly to decline, during close to ground, by away from
Ground clearance is measured from sensor, flight control system control rotor rotating speed and helical angle change at a slow speed, landing of finally contacting to earth.
Head falls downward mode：Aircraft is reached near level point, lockable mechanism (7) unblock, Servo-controller control wing spiral shell
Swing angle, under the pulling force effect of inertia and propeller, assembly accelerates to rotate around X-axis, and wing Plane of rotation now provides lift
Balance aircraft gravity；But flow through flat vertical fin without enough air-flows, it is necessary to there is certain decrease speed to keep air-flow
Effect to flat vertical fin；When aircraft is to approach ground, ground clearance, flight control system control rotor are measured by range sensor
Rotating speed and helical angle change at a slow speed, quickly increase lift, make aircraft down and slowly contact to earth；Such a mode presses load character
Selection is, it is necessary to install preposition undercarriage additional.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711061621.0A CN107672786A (en) | 2017-11-02 | 2017-11-02 | The aircraft and its change flying method of a kind of fixed-wing and rotor change |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711061621.0A CN107672786A (en) | 2017-11-02 | 2017-11-02 | The aircraft and its change flying method of a kind of fixed-wing and rotor change |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109131866A (en) * | 2018-09-30 | 2019-01-04 | 深圳市旗客智能技术有限公司 | The compound unmanned plane of multiaxis fixed-wing and its flight control method |
| CN112009674A (en) * | 2020-09-04 | 2020-12-01 | 深圳技术大学 | Tilt wing mechanism and have unmanned aerial vehicle of tilt wing mechanism |
| CN114252262A (en) * | 2021-12-09 | 2022-03-29 | 中国船舶重工集团公司第七0三研究所 | Helicopter main reducer propeller hub load simulation loading device considering balance static deadweight |
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| CN112009674A (en) * | 2020-09-04 | 2020-12-01 | 深圳技术大学 | Tilt wing mechanism and have unmanned aerial vehicle of tilt wing mechanism |
| CN114252262A (en) * | 2021-12-09 | 2022-03-29 | 中国船舶重工集团公司第七0三研究所 | Helicopter main reducer propeller hub load simulation loading device considering balance static deadweight |
| CN114252262B (en) * | 2021-12-09 | 2023-12-08 | 中国船舶重工集团公司第七0三研究所 | Helicopter main reducer hub load simulation loading device considering balanced static dead weight |
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