CN110254705A - Blade with fixed-wing can turn Horizontal single-wheel formula and move rotor aircraft - Google Patents
Blade with fixed-wing can turn Horizontal single-wheel formula and move rotor aircraft Download PDFInfo
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- CN110254705A CN110254705A CN201910656172.7A CN201910656172A CN110254705A CN 110254705 A CN110254705 A CN 110254705A CN 201910656172 A CN201910656172 A CN 201910656172A CN 110254705 A CN110254705 A CN 110254705A
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- blade
- wing
- cam
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- axis
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/0009—Aerodynamic aspects
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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
- B64C39/00—Aircraft not otherwise provided for
- B64C39/003—Aircraft not otherwise provided for with wings, paddle wheels, bladed wheels, moving or rotating in relation to the fuselage
- B64C39/005—Aircraft not otherwise provided for with wings, paddle wheels, bladed wheels, moving or rotating in relation to the fuselage about a horizontal transversal axis
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
It can turn Horizontal single-wheel formula the invention discloses a kind of blade with fixed-wing and move rotor aircraft, including the wheeled dynamic wing, transmission mechanism, cam, rotary shaft, retarder, motor, fuselage ring, fixed-wing, steering engine and counterweight, it is arranged in after the motor on fuselage ring is slowed down by retarder and drives rotary shaft continuous rotation, rotating shaft axis direction is vertical with the longitudinally asymmetric face of aircraft, the wheeled dynamic wing is fixedly connected on the rotary shaft, the cam that transmission mechanism connects the wheeled dynamic wing and is arranged on fuselage ring, the wheeled dynamic wing includes rotating frame, and it is mounted on the rotatable blade in rotating frame, cam and transmission mechanism are used to control the rotation and reset of blade, fixed-wing is provided on fuselage ring for generating lift, fuselage ring is provided with steering engine for controlling heading, fuselage ring, which is provided with to match, is reused in holding machine Body left-right balance.It the composite can be widely applied in all kinds of small aircrafts of low reynolds number flight.
Description
Technical field
The present invention relates to movable rotor aircraft and flying robot field, especially a kind of blade with fixed-wing can turn
Horizontal single-wheel formula moves rotor aircraft.
Background technique
Aircraft flight mode has three kinds of fixed-wing, rotor and flapping wing type of flight, and rotor and flapping wing belong to movable wing.
Flapping flight is the flying method that nature flying creature uses, and mainly flutters while generating using the upper and lower of dipteron
Lift and thrust are mainly characterized by lifting, hover and propulsion functions are based on one, while having very strong mobility and spirit
Activity, more suitable for executing the flight of cut-through object etc..For the aircraft of small size and low-speed condition, belong to low thunder
It flies under promise number, the unsteady lift that flapping wing generates is more much bigger than the steady lift of fixed-wing；In terms of thrust, flapping wing is pushed away
It is higher than propeller propulsive efficiency into efficiency.At present flapping wing aircraft research be concentrated mainly on simulation the Nature in flying creature fly
Row posture designs various flapping wing mechanisms.But the common issue of these flapping wing mechanisms is that overall pneumatic efficiency is relatively low, even lower than together
The fixed-wing minute vehicle of scale.It is simple mostly that the main reason for flapping wing aircraft overall efficiency is low, which is in current research,
Imitation birds or insect wing shape and flutter movement, be but difficult to realize utilization during flying creature flapping wing is fluttered up and down
The change of wing itself posture and structure reduces air drag and generates unsteady aerodynamic force, and resulting pneumatic efficiency is lower
Problem seriously constrains the popularization and application of flapping-wing type aircraft.
Rotor flying is to provide the lift of aircraft, the advance pulling force of aircraft with the pulling force of rotor (including propeller)
Horizontal component caused by small angle deflection derived from rotor vector.The posture of the more rotor small aircrafts quickly grown at present
Control and horizontal movement are that the differential pull of more rotors is leaned on to realize.The characteristics of rotor craft is with VTOL and sky
Middle hovering function, and there is the ability flown in smaller region.But since the rotor of rotor craft is relative to its rotation
Wing central axis is motionless, therefore advance resistance is larger, so energy consumption is big, pneumatic efficiency is relatively low, and large power long endurance flies
Row is more difficult.
Summary of the invention
The object of the present invention is to provide a kind of reduction flapping wing type of highly significant and rotor type aircraft flight resistances greatly, mentions
The blade with fixed-wing for rising pneumatic efficiency can turn Horizontal single-wheel formula and move rotor aircraft, to solve on existing in the prior art
State problem.
Realizing the technical solution of the object of the invention is: Horizontal single-wheel formula can be turned by providing a kind of blade with fixed-wing
Dynamic rotor aircraft, including the wheeled dynamic wing, transmission mechanism, cam, rotary shaft, retarder, motor, fuselage ring, fixed-wing, rudder
Machine and counterweight, the motor being arranged on the fuselage ring pass through the retarder being arranged on the fuselage ring
The rotary shaft continuous rotation is driven after deceleration, the rotating shaft axis direction is vertical with the longitudinally asymmetric face of aircraft, the wheel
Formula is moved the wing and is fixedly connected in the rotary shaft, and the transmission mechanism connects the wheeled dynamic wing and is arranged in the fuselage ring
On the cam；The wheeled dynamic wing includes rotating frame, and the rotatable blade being mounted in the rotating frame,
The cam and the transmission mechanism are used to control the rotation and reset of the blade；It is provided on the fuselage ring described solid
The wing is determined for generating lift；The fuselage ring rear end is provided with steering engine for controlling aircraft direction；The fuselage ring is set
Match to be reused in described in being equipped with and keeps aircraft left-right balance.
Further, centre bore and straight beam are provided on the rotating frame, the direction of the straight beam and the center
The axis in hole is parallel, and blade mounting hole, the axis of the blade mounting hole and the axis of the centre bore are provided on the straight beam
It is orthogonal；The blade includes that the blade windward side being oppositely arranged, blade leeward and the blade being arranged on the blade turn
Axis, the blade windward side are parallel with the blade leeward and all parallel with the axis of the blade rotor；The blade turns
Axis is inserted into the blade mounting hole and can be rotated；Centre bore described in the rotation axis connection and the retarder, the electricity
The output shaft of motivation is mounted in the retarder input hole.
Further, the transmission mechanism includes pull ring, push rod and idler wheel；Push rod is provided on the rotating frame
Hole, the axis of the push-rod hole are parallel with the axis of the centre bore；Blade rotor hole and slotted hole are provided on pull ring；Push rod
On be provided with push rod cylinder, tenon cylinder and idler wheel mounting hole, the axis of the axis of the tenon cylinder and the idler wheel mounting hole
Axis vertical take-off of the line all with the push rod cylinder, the blade rotor inserting are fixed in blade rotor hole；It is provided on idler wheel
Coaxial idler wheel cylinder and rolling wheel installing shaft；Cam cylindrical surface, the cam cylindrical surface and the rotary shaft are provided on cam
Coaxially, the cam curve slot around the cam cylindrical surface connection in one week is provided on the cam cylindrical surface；The push rod circle
Column is inserted into the push-rod hole and meets and is slidably matched, the tenon cylinder inserting in the oblong hole and slidably, institute
It states rolling wheel installing shaft inserting to be fixed in the idler wheel mounting hole, the idler wheel cylinder is inserted into cam curve slot and can slide
It is dynamic.
Further, the cam curve slot is by work operating condition straight trough, standby operating conditions straight trough, the first helicla flute and second
One end of helicla flute composition, one end of the work operating condition straight trough and the standby operating conditions straight trough is connected by first helicla flute
Logical, the other end of the work operating condition straight trough is connected to the other end of the standby operating conditions straight trough by second helicla flute.
Further, the two sides of the work operating condition straight trough are plane and all hang down with the axis on the cam cylindrical surface
Directly, the distance between two sides of the work operating condition straight trough are equal with the diameter of the idler wheel cylinder, and the standby operating conditions are straight
The two sides of slot are plane and all vertical with the axis on the cam cylindrical surface, between the two sides of the standby operating conditions straight trough
Distance is equal with the diameter of the idler wheel cylinder, and the two sides of the two sides of first helicla flute and second helicla flute are equal
For spiral camber.
Further, the cam is one symmetrical three-dimensional, the plane of symmetry of the cam is working standard face, described
The axis on cam cylindrical surface is in the working standard face, and the work operating condition straight trough is symmetrical about the working standard face, institute
It is vertical with direction of advance of aircraft when flat winged to state working standard face.
Further, described make the aircraft center of gravity in the longitudinally asymmetric face of the aircraft with Beijing South Maxpower Technology Co. Ltd.
Further, further including at least one of outer reinforcement curved beam and interior reinforcement curved beam on the rotating frame, use
In the intensity for reinforcing the rotating frame.
Further, the straight beam, the outer reinforcement curved beam and the interior reinforcement curved beam are hollow structure；
And/or
The straight beam, the outer reinforcement curved beam and the interior reinforcement curved beam are engineering plastics material；
And/or
The straight beam, the outer reinforcement curved beam and the interior reinforcement curved beam are carbon fiber material.
Further, the straight beam and the push-rod hole are all circumferentially uniformly distributed in the centre bore, the straight beam
Quantity is greater than 1, and the quantity of the push-rod hole is identical as the quantity of the straight beam；The blade mounting hole is straight on the straight beam
Line is uniformly distributed, and the quantity of the blade mounting hole on each straight beam is greater than 1.
A kind of blade with fixed-wing can turn Horizontal single-wheel formula and move rotor aircraft, it is characterised in that including rotating frame,
Blade, pull ring, push rod, idler wheel, cam, rotary shaft, retarder, motor, fuselage ring, fixed-wing, steering engine and counterweight, rotation
There are centre bore, straight beam and push-rod hole on frame, the direction of straight beam and the axis of centre bore are parallel, and blade installation is provided on straight beam
Hole, push-rod hole are circumferentially uniformly distributed in centre bore, the axis of blade mounting hole and the axis vertical take-off of centre bore, the axis of push-rod hole
It is parallel with the axis of centre bore, there are blade windward side, blade rotor and blade leeward on blade, has blade rotor hole on pull ring
And slotted hole, there are push rod cylinder, tenon cylinder and idler wheel mounting hole, the axis of tenon cylinder and the axis of push rod cylinder on push rod
Orthogonal, the axis vertical take-off of the axis of idler wheel mounting hole and push rod cylinder has coaxial idler wheel cylinder and rolling wheel installing shaft on idler wheel,
There is cam cylindrical surface on cam, the cam curve slot around the connection in one week of cam cylindrical surface is provided on cam cylindrical surface, cam is bent
Wire casing is made of work operating condition straight trough, standby operating conditions straight trough, the first spiral groove and the second spiral groove, the two sides for the operating condition straight trough that works
Face is plane and all vertical with the axis on cam cylindrical surface, the two sides of standby operating conditions straight trough be plane and all with cam cylindrical surface
Axis it is vertical, work operating condition straight trough one end be connected to one end of standby operating conditions straight trough by the first helicla flute, work operating condition
The other end of straight trough is connected to the other end of standby operating conditions straight trough by the second helicla flute, cam, retarder, motor, fixation
The wing and counterweight are all fixed on fuselage ring, and steering engine is mounted on fixed-wing rear end, and rotary shaft inserting is fixed in centre bore,
Rotating shaft axis direction is vertical with the longitudinally asymmetric face of aircraft, and cam cylindrical surface and concentric rotation axis, rotary shaft are mounted on deceleration
On the output shaft of device, the output shaft of motor is mounted in retarder input hole, idler wheel cylinder be inserted into cam curve slot and
It can be slided in cam curve slot, rolling wheel installing shaft inserting is fixed in idler wheel mounting hole, and tenon cylinder is inserted into slotted hole
And slidably, push rod cylinder is inserted into push-rod hole and meets and is slidably matched, and blade rotor inserting is fixed in blade rotor hole,
Blade rotor is inserted into blade mounting hole and can be rotated, the distance between two sides for the operating condition straight trough that works and idler wheel cylinder
Diameter is equal, and the distance between two sides of standby operating conditions straight trough are equal with the diameter of idler wheel cylinder, the two sides of the first helicla flute
Face and the two sides of the second helicla flute are spiral camber, make aircraft center of gravity in the longitudinally asymmetric face of aircraft with Beijing South Maxpower Technology Co. Ltd, convex
Wheel is one symmetrical three-dimensional, and the plane of symmetry of cam is working standard face, and work operating condition straight trough is symmetrical about working standard face, work
The direction of advance made when datum level and aircraft are flat to fly is vertical, there is outer reinforcement curved beam and interior reinforcement curved beam on rotating frame, straight beam,
Outer reinforcement curved beam and interior reinforcement curved beam all use hollow structure and use the light materials such as engineering plastics, carbon fibre.
The working principle of the invention is: after motor start-up, rotary shaft, rotating frame are driven after retarder slows down
Frame, blade, pull ring, push rod and idler wheel continuous rotation, when idler wheel slides in standby operating conditions straight trough, push rod is in rotating shaft axis
Direction cannot move, and the blade windward side on blade is parallel with direction of rotation, i.e., parallel with relative wind direction, on blade by
Air resistance it is minimum, be at this time standby operating conditions, when idler wheel turns in the second helicla flute, push rod is revolved synchronous with rotary shaft
Start positive movement relative to rotating shaft axis direction while turning, the axial movement of tenon cylinder is so that positive turn occurs for pull ring
Dynamic, so that blade rotor be driven to rotate forward, when idler wheel turns in work operating condition straight trough, push rod is relative to rotating shaft axis
Direction no longer moves, and blade rotor just rotates forward 90 degree, and blade windward side is vertical with airflow direction, due to the operating condition that works
The working standard face of straight trough is vertical with direction of advance, thus air-flow act directly on blade windward side make blade obtain it is maximum
Forward propulsion, and do not generate lift substantially, it is at this time the operating condition that works, the thrust generated on blade transports no aircraft forward
It is dynamic, and fixed-wing will generate lift at this time, and steering engine then can adjust the heading of aircraft；When idler wheel turns to the first spiral
When in slot, push rod starts to move backward while with rotary shaft synchronous rotary relative to rotating shaft axis direction, tenon cylinder
Pull ring is rotated backward, so that blade rotor is driven to rotate backward, when idler wheel turns in standby operating conditions straight trough, blade
Shaft rotates backward 90 degree, and blade windward side is returned to parallel with airflow direction, returns to standby mode.The present invention and existing skill
Art is compared, and remarkable advantage is:
1. the blade of the present invention with fixed-wing, which can turn Horizontal single-wheel formula, moves rotor aircraft, by by the wheeled dynamic wing
The advantages of middle blade is set as continuous rotation, maintains rotor continuous rotation overcomes the weakness that flapping wing needs to move back and forth.
2. the blade of the present invention with fixed-wing, which can turn Horizontal single-wheel formula, moves rotor aircraft, is controlled and connected by cam
The blade of continuous rotation is also rotatable relative to rotary shaft, so that blade is moved acquisition windward with maximum area in working condition maximum
Air-flow propulsive thrust, and it is parallel with airflow direction to which resistance substantially reduces in standby mode, reach the mesh for improving pneumatic efficiency
, pneumatic efficiency is much higher than existing flapping wing and rotor craft, and biggish thrust can be provided for aircraft.
3. the blade of the present invention with fixed-wing can turn Horizontal single-wheel formula move rotor aircraft, can rotating vane piece working
Switching between state and standby mode is automatically performed under cam control, and complicated electronic control system, knot are not needed
The simple and reliable property of structure is preferable.
4. the blade of the present invention with fixed-wing, which can turn Horizontal single-wheel formula, moves rotor aircraft, by the wheeled dynamic wing and admittedly
Determine the wing to combine, the wheeled dynamic wing generates thrust, and lift is generated by fixed-wing, therefore aircraft puts down and flies more to save energy when state
Amount, further increases energy utilization efficiency, achievees the purpose that long endurance.
5. the blade of the present invention with fixed-wing, which can turn Horizontal single-wheel formula, moves rotor aircraft, structure is simple, processing
Good manufacturability, production cost are low.
Detailed description of the invention
It, below will be to specific in order to illustrate more clearly of the specific embodiment of the invention or technical solution in the prior art
Embodiment or attached drawing needed to be used in the description of the prior art be briefly described, it should be apparent that, it is described below
Attached drawing is some embodiments of the present invention, for those of ordinary skill in the art, before not making the creative labor
It puts, is also possible to obtain other drawings based on these drawings.
Fig. 1 is that the blade with fixed-wing of the embodiment of the present invention 1 can turn the whole knot that Horizontal single-wheel formula moves rotor aircraft
Structure schematic diagram.
Fig. 2 is that the blade with fixed-wing of the embodiment of the present invention 1 can turn the detailed knot that Horizontal single-wheel formula moves rotor aircraft
Structure schematic diagram.
Fig. 3 is that the blade with fixed-wing of the embodiment of the present invention 1 can turn the wheeled dynamic of the dynamic rotor aircraft of Horizontal single-wheel formula
Wing standby mode detailed construction schematic diagram.
Fig. 4 is that the blade with fixed-wing of the embodiment of the present invention 1 can turn the wheeled dynamic of the dynamic rotor aircraft of Horizontal single-wheel formula
Detailed construction schematic diagram of the wing standby mode into working condition handoff procedure.
Fig. 5 is that the blade with fixed-wing of the embodiment of the present invention 1 can turn the wheeled dynamic of the dynamic rotor aircraft of Horizontal single-wheel formula
Wing working condition detailed construction schematic diagram.
Fig. 6 is that the blade with fixed-wing of the embodiment of the present invention 1 can turn the rotating frame that Horizontal single-wheel formula moves rotor aircraft
The structural schematic diagram of frame.
Fig. 7 is that the blade with fixed-wing of the embodiment of the present invention 1 can turn the blade that Horizontal single-wheel formula moves rotor aircraft
Structural schematic diagram.
Fig. 8 is that the blade with fixed-wing of the embodiment of the present invention 1 can turn the pull ring wheel that Horizontal single-wheel formula moves rotor aircraft
Structural schematic diagram
Fig. 9 is that the blade with fixed-wing of the embodiment of the present invention 1 can turn the push rod that Horizontal single-wheel formula moves rotor aircraft
Structural schematic diagram.
Figure 10 is that the blade with fixed-wing of the embodiment of the present invention 1 can turn the idler wheel that Horizontal single-wheel formula moves rotor aircraft
Structural schematic diagram.
Figure 11 is that the blade with fixed-wing of the embodiment of the present invention 1 can turn the cam that Horizontal single-wheel formula moves rotor aircraft
Structural schematic diagram.
Figure 12 be the embodiment of the present invention 1 the blade with fixed-wing can turn Horizontal single-wheel formula move rotor aircraft cam cut open
Structural schematic diagram after cutting.
Figure 13 be the embodiment of the present invention 1 the blade with fixed-wing can turn Horizontal single-wheel formula move rotor aircraft cam cut open
End on projection figure after cutting.
Specific embodiment
In order to make the object, technical scheme and advantages of the embodiment of the invention clearer, below in conjunction with the embodiment of the present invention
In attached drawing, technical scheme in the embodiment of the invention is clearly and completely described, it is clear that described embodiment is
A part of the embodiment of the present invention, instead of all the embodiments.Based on the embodiments of the present invention, those skilled in the art are not having
Every other embodiment obtained under the premise of creative work is made, shall fall within the protection scope of the present invention.
The invention will be further described below in conjunction with the accompanying drawings, but do not limit the invention in any way.
Embodiment 1:
In conjunction with Fig. 1, Fig. 2, Fig. 3, Fig. 4, Fig. 5, Fig. 6, Fig. 7, Fig. 8, Fig. 9, Figure 10, Figure 11, Figure 12 and Figure 13, using having
The blade of fixed-wing can turn the agricultural plant protection unmanned plane that Horizontal single-wheel formula moves rotor aircraft.Including rotating frame 1, blade 2, pull ring
3, push rod 4, idler wheel 5, cam 6, rotary shaft 7, retarder 8, motor 9, fuselage ring 10, fixed-wing 11, steering engine 12 and counterweight
13, there are centre bore 101, straight beam 102 and push-rod hole 104 on rotating frame 1, the direction of straight beam 102 and the axis of centre bore 101 are flat
Row, circumferential equally distributed 102 quantity of straight beam of centre bore 101 is 3, is provided with blade mounting hole 103, straight beam 102 on straight beam 102
The quantity of upper equally distributed blade mounting hole 103 is 4, and push-rod hole 104 is circumferentially uniformly distributed in centre bore 101, push-rod hole
104 quantity is identical as the quantity of straight beam 102, the axis of blade mounting hole 103 and the axis vertical take-off of centre bore 101, push-rod hole
104 axis is parallel with the axis of centre bore 101, there is blade windward side 201, blade rotor 202 and blade leeward on blade 2
203, there are blade rotor hole 301 and slotted hole 302 on pull ring 3, there is push rod cylinder 401, tenon cylinder 402 and idler wheel on push rod 4
Mounting hole 403, the axis of tenon cylinder 402 and the axis vertical take-off of push rod cylinder 401, the axis and push rod of idler wheel mounting hole 403
The axis vertical take-off of cylinder 401 has coaxial idler wheel cylinder 501 and rolling wheel installing shaft 502 on idler wheel 5, has cam cylinder on cam 6
Face 601 is provided with the cam curve slot 602 around the connection in 601 1 weeks of cam cylindrical surface, cam curve slot on cam cylindrical surface 601
602 are made of work operating condition straight trough 603, standby operating conditions straight trough 604, the first helicla flute 605 and the second helicla flute 606, and work work
The two sides of condition straight trough 603 are plane and all vertical with the axis on cam cylindrical surface 601, the two sides of standby operating conditions straight trough 604
It is for plane and all vertical with the axis on cam cylindrical surface 601, one end and the standby operating conditions straight trough 604 of the operating condition straight trough 603 that works
One end is connected to by the first helicla flute 605, and the other end for the operating condition straight trough 603 that works and the other end of standby operating conditions straight trough 604 are logical
The connection of the second helicla flute 606 is crossed, cam 6, retarder 8, motor 9, fixed-wing 11 and counterweight 13 are all fixed on fuselage frame
On frame 10, steering engine 12 is mounted on 11 rear end of fixed-wing, and the inserting of rotary shaft 7 is fixed in centre bore 101,7 axis direction of rotary shaft
Vertical with the longitudinally asymmetric face of aircraft, cam cylindrical surface 601 and rotary shaft 7 are coaxial, and rotary shaft 7 is mounted on the output of retarder 8
On axis, the output shaft of motor 9 is mounted in 8 input hole of retarder, idler wheel cylinder 501 be inserted into cam curve slot 602 and
It can be slided in cam curve slot 602, the inserting of rolling wheel installing shaft 502 is fixed in idler wheel mounting hole 403, and tenon cylinder 402 is inserted
In slotted hole 302 and slidably, push rod cylinder 401 is inserted into push-rod hole 104 and meets and is slidably matched, blade rotor
202 insertings are fixed in blade rotor hole 301, and blade rotor 202 is inserted into blade mounting hole 103 and can be rotated, and work work
The distance between two sides of condition straight trough 603 are equal with the diameter of idler wheel cylinder 501, the two sides of standby operating conditions straight trough 604 it
Between distance it is equal with the diameter of idler wheel cylinder 501, the two sides of the two sides of the first helicla flute 605 and the second helicla flute 606
It is spiral camber, counterweight 13 can make aircraft center of gravity in the longitudinally asymmetric face of aircraft, and cam 6 is one symmetrical three-dimensional,
The plane of symmetry of cam 6 be working standard face F, work operating condition straight trough 603 it is symmetrical about working standard face F, working standard face F and fly
The direction of advance that row device is flat when flying is vertical, there is outer reinforcements curved beam 105 and interior reinforcement curved beam 106 on rotating frame 1, straight beam 102, outside
Reinforce curved beam 105 and interior reinforcement curved beam 106 all using hollow structure and using carbon fiber material.Agricultural plant protection unmanned plane uses
After the present invention can turn the dynamic rotor aircraft of Horizontal single-wheel formula with the blade of fixed-wing, since wheeled dynamic wing drag is small, pneumatic efficiency
Height, can complete sowing fertilizers, spray pulvis, and the multiplicity function such as supple-mentary pollination is answered, and cruise duration is long, relative to rotor wing unmanned aerial vehicle,
In identical service load, the flight time increases by 20%, realizes longer endurance work.
Embodiment 2:
The present embodiment 2 provides a kind of high-rise For Use Only in Case of Fire unmanned plane, structure with embodiment 1, unlike: centre bore
101 circumferential equally distributed 102 quantity of straight beam are 2, and the quantity of equally distributed blade mounting hole 103 is 5 on straight beam 102
A, straight beam 102, outer reinforcement curved beam 105 and interior reinforcement curved beam 106 all use engineering plastics.It can using the blade with fixed-wing
Turn high-rise For Use Only in Case of Fire the unmanned plane that Horizontal single-wheel formula moves rotor aircraft, including rotating frame 1, blade 2, pull ring 3, push rod 4, rolling
Wheel 5, cam 6, rotary shaft 7, retarder 8, motor 9, fuselage ring 10, fixed-wing 11, steering engine 12 and counterweight 13, rotating frame
There are centre bore 101, straight beam 102 and push-rod hole 104 on 1, the direction of straight beam 102 is parallel with the axis of centre bore 101, centre bore
101 circumferential equally distributed 102 quantity of straight beam are 2, are provided with blade mounting hole 103 on straight beam 102, uniformly divide on straight beam 102
The quantity of the blade mounting hole 103 of cloth is 5, and push-rod hole 104 is circumferentially uniformly distributed in centre bore 101, the quantity of push-rod hole 104
It is identical as the quantity of straight beam 102, the axis of blade mounting hole 103 and the axis vertical take-off of centre bore 101, the axis of push-rod hole 104
It is parallel with the axis of centre bore 101, there are blade windward side 201, blade rotor 202 and blade leeward 203, pull ring 3 on blade 2
On have blade rotor hole 301 and slotted hole 302, have push rod cylinder 401, tenon cylinder 402 and idler wheel mounting hole 403 on push rod 4,
The axis of tenon cylinder 402 and the axis vertical take-off of push rod cylinder 401, the axis of idler wheel mounting hole 403 and the axis of push rod cylinder 401
Line is orthogonal, has coaxial idler wheel cylinder 501 and rolling wheel installing shaft 502 on idler wheel 5, has cam cylindrical surface 601, cam on cam 6
The cam curve slot 602 around the connection in 601 1 weeks of cam cylindrical surface is provided on cylindrical surface 601, cam curve slot 602 is by work work
Condition straight trough 603, standby operating conditions straight trough 604, the first helicla flute 605 and the second helicla flute 606 composition, work operating condition straight trough 603
Two sides are plane and all vertical with the axis on cam cylindrical surface 601, the two sides of standby operating conditions straight trough 604 be plane and all with
The axis on cam cylindrical surface 601 is vertical, and the one end for the operating condition straight trough 603 that works and one end of standby operating conditions straight trough 604 pass through first
Helicla flute 605 is connected to, and the other end for the operating condition straight trough 603 that works and the other end of standby operating conditions straight trough 604 pass through the second helicla flute
606 connections, cam 6, retarder 8, motor 9, fixed-wing 11 and counterweight 13 are all fixed on fuselage ring 10, steering engine 12
It is mounted on 11 rear end of fixed-wing, the inserting of rotary shaft 7 is fixed in centre bore 101, and 7 axis direction of rotary shaft and aircraft are longitudinally right
Title face is vertical, and cam cylindrical surface 601 and rotary shaft 7 are coaxial, and rotary shaft 7 is mounted on the output shaft of retarder 8, motor 9
Output shaft is mounted in 8 input hole of retarder, and idler wheel cylinder 501 is inserted into cam curve slot 602 and can be in cam curve slot
Sliding in 602, the inserting of rolling wheel installing shaft 502 are fixed in idler wheel mounting hole 403, and tenon cylinder 402 is inserted into slotted hole 302
And slidably, push rod cylinder 401 is inserted into push-rod hole 104 and meets and is slidably matched, and the inserting of blade rotor 202 is fixed on blade
In shaft hole 301, blade rotor 202 is inserted into blade mounting hole 103 and can be rotated, the two sides for the operating condition straight trough 603 that works
The distance between, two sides of standby operating conditions straight trough 604 the distance between and idler wheel cylinder equal with the diameter of idler wheel cylinder 501
501 diameter is equal, and the two sides of the two sides of the first helicla flute 605 and the second helicla flute 606 are spiral camber, counterweight 13
It can make aircraft center of gravity in the longitudinally asymmetric face of aircraft, cam 6 is one symmetrical three-dimensional, and the plane of symmetry of cam 6 is work
Datum level F, work operating condition straight trough 603 is symmetrical about working standard face F, and working standard face F and aircraft put down advance side when flying
To vertical, there are outer reinforcement curved beam 105 and interior reinforcement curved beam 106, straight beam 102, outer reinforcement curved beam 105 and Nei Jia on rotating frame 1
Strong curved beam 106 all using hollow structure and uses engineering plastics.High-rise For Use Only in Case of Fire unmanned plane has fixed-wing using the present invention
Blade can turn Horizontal single-wheel formula move rotor aircraft after, since wheeled dynamic wing impulse stroke thrust is big, resistance is small, pneumatic efficiency
Height, therefore have stronger mobility, the emergency of energy quick response high level, rapid flight to high level, which is caught fire, a little puts out a fire.
Embodiment 3:
The present embodiment 3 provides a kind of forest fire protection fire-fighting dedicated unmanned machine, structure with embodiment 1, unlike: center
Circumferential equally distributed 102 quantity of straight beam in hole 101 is 4, and the quantity of equally distributed blade mounting hole 103 is 6 on straight beam 102
A, straight beam 102, outer reinforcement curved beam 105 and interior reinforcement curved beam 106 all use engineering plastics.It can using the blade with fixed-wing
Turn the forest fire protection fire-fighting dedicated unmanned machine that Horizontal single-wheel formula moves rotor aircraft, including rotating frame 1, blade 2, pull ring 3, push rod
4, idler wheel 5, cam 6, rotary shaft 7, retarder 8, motor 9, fuselage ring 10, fixed-wing 11, steering engine 12 and counterweight 13, rotation
There are centre bore 101, straight beam 102 and push-rod hole 104 on frame 1, the direction of straight beam 102 is parallel with the axis of centre bore 101, center
Circumferential equally distributed 102 quantity of straight beam in hole 101 is 4, is provided with blade mounting hole 103 on straight beam 102, on straight beam 102 uniformly
The quantity of the blade mounting hole 103 of distribution is 6, and push-rod hole 104 is circumferentially uniformly distributed in centre bore 101, the number of push-rod hole 104
Measure, the axis of blade mounting hole 103 and the axis vertical take-off of centre bore 101 identical as the quantity of straight beam 102, the axis of push-rod hole 104
Line is parallel with the axis of centre bore 101, there is blade windward side 201, blade rotor 202 and blade leeward 203 on blade 2, draws
There are blade rotor hole 301 and slotted hole 302 on ring 3, there is push rod cylinder 401, tenon cylinder 402 and idler wheel mounting hole on push rod 4
403, the axis vertical take-off of the axis and push rod cylinder 401 of tenon cylinder 402, the axis and push rod cylinder 401 of idler wheel mounting hole 403
Axis vertical take-off, have coaxial idler wheel cylinder 501 and rolling wheel installing shaft 502 on idler wheel 5, have cam cylindrical surface 601 on cam 6,
The cam curve slot 602 around the connection in 601 1 weeks of cam cylindrical surface is provided on cam cylindrical surface 601, cam curve slot 602 is by work
Make operating condition straight trough 603, standby operating conditions straight trough 604, the first helicla flute 605 and the second helicla flute 606 composition, work operating condition straight trough
603 two sides are plane and all vertical with the axis on cam cylindrical surface 601, and the two sides of standby operating conditions straight trough 604 are plane
And it is all vertical with the axis on cam cylindrical surface 601, the one end for the operating condition straight trough 603 that works and one end of standby operating conditions straight trough 604 are logical
The connection of the first helicla flute 605 is crossed, the other end for the operating condition straight trough 603 that works and the other end of standby operating conditions straight trough 604 pass through second
Helicla flute 606 is connected to, and cam 6, retarder 8, motor 9, fixed-wing 11 and counterweight 13 are all fixed on fuselage ring 10,
Steering engine 12 is mounted on 11 rear end of fixed-wing, and the inserting of rotary shaft 7 is fixed in centre bore 101,7 axis direction of rotary shaft and aircraft
Longitudinally asymmetric face is vertical, and cam cylindrical surface 601 and rotary shaft 7 are coaxial, and rotary shaft 7 is mounted on the output shaft of retarder 8, electronic
The output shaft of machine 9 is mounted in 8 input hole of retarder, and idler wheel cylinder 501 is inserted into cam curve slot 602 and can be in cam song
Sliding in wire casing 602, the inserting of rolling wheel installing shaft 502 are fixed in idler wheel mounting hole 403, and tenon cylinder 402 is inserted into slotted hole
In 302 and slidably, push rod cylinder 401 is inserted into push-rod hole 104 and meets and is slidably matched, and the inserting of blade rotor 202 is fixed
In blade rotor hole 301, blade rotor 202 is inserted into blade mounting hole 103 and can be rotated, work operating condition straight trough 603
The distance between two sides are equal with the diameter of idler wheel cylinder 501, the distance between two sides of standby operating conditions straight trough 604 and rolling
The diameter for taking turns cylinder 501 is equal, and the two sides of the two sides of the first helicla flute 605 and the second helicla flute 606 are spiral camber,
Counterweight 13 can make aircraft center of gravity in the longitudinally asymmetric face of aircraft, and cam 6 is one symmetrical three-dimensional, the plane of symmetry of cam 6
For working standard face F, the operating condition straight trough 603 that works is symmetrical about working standard face F, and working standard face F and aircraft are put down when flying
Direction of advance is vertical, there is outer reinforcement curved beam 105 and interior reinforcement curved beam 106, straight beam 102, outer reinforcement curved beam 105 on rotating frame 1
All using hollow structure and engineering plastics are used with interior reinforcement curved beam 106.Forest fire protection fire-fighting dedicated unmanned machine is using the present invention
Blade with fixed-wing can turn Horizontal single-wheel formula move rotor aircraft after, due to wheeled dynamic wing impulse stroke thrust is big, resistance is small,
Pneumatic efficiency is high, therefore has stronger mobility, energy quick response forest fire situation, quickly carries out forest inspection and flight is lost
Fire point is put out a fire.
Although being described in conjunction with the accompanying the embodiment of the present invention, those skilled in the art can not depart from the present invention
Spirit and scope in the case where various modifications and variations can be made, such modifications and variations are each fallen within by appended claims institute
Within the scope of restriction.
Claims (10)
1. the blade with fixed-wing, which can turn Horizontal single-wheel formula, moves rotor aircraft, it is characterised in that: including the wheeled dynamic wing, driver
Structure, cam (6), rotary shaft (7), retarder (8), motor (9), fuselage ring (10), fixed-wing (11), steering engine (12) and match
Weight (13), setting is in the motor (9) on the fuselage ring (10) by being arranged on the fuselage ring (10)
The retarder (8) drives the rotary shaft (7) continuous rotation after slowing down, rotary shaft (7) axis direction and aircraft are vertical
Vertical to the plane of symmetry, the wheeled dynamic wing is fixedly connected on the rotary shaft (7), and the transmission mechanism connection is described wheeled dynamic
The wing and the cam (6) being arranged on the fuselage ring (10)；The wheeled dynamic wing includes rotating frame (1), Yi Jian
Rotatable blade (2) in the rotating frame (1), the cam (6) and the transmission mechanism are described for controlling
The rotation and reset of blade (2)；The fixed-wing (11) are provided on the fuselage ring (10) for generating lift；The machine
Body frame (10) rear end is provided with steering engine (12) for controlling aircraft direction；The fuselage ring (10) is provided with the counterweight
(13) for keeping aircraft left-right balance.
2. the blade according to claim 1 with fixed-wing, which can turn Horizontal single-wheel formula, moves rotor aircraft, it is characterised in that:
Centre bore (101) and straight beam (102), the direction of the straight beam (102) and the centre bore are provided on the rotating frame (1)
(101) axis is parallel, is provided with blade mounting hole (103) on the straight beam (102), the axis of the blade mounting hole (103)
With the axis vertical take-off of the centre bore (101)；The blade (2) includes that the blade windward side (201) being oppositely arranged, blade are leeward
Face (203) and the blade rotor (202) being arranged on the blade (2), the blade windward side (201) and the blade are carried on the back
Wind face (203) is parallel and all parallel with the axis of the blade rotor (202)；The blade rotor (202) is inserted into the leaf
In piece mounting hole (103) and it can be rotated；The rotary shaft (7) connects the centre bore (101) and the retarder (8), described
The output shaft of motor (9) is mounted in the retarder (8) input hole.
3. the blade according to claim 1 or 2 with fixed-wing, which can turn Horizontal single-wheel formula, moves rotor aircraft, feature exists
In: the transmission mechanism includes pull ring (3), push rod (4) and idler wheel (5)；Push-rod hole is provided on the rotating frame (1)
(104), the axis of the push-rod hole (104) is parallel with the axis of the centre bore (101)；Blade is provided on pull ring (3) to turn
Axis hole (301) and slotted hole (302)；Push rod cylinder (401), tenon cylinder (402) and idler wheel mounting hole are provided on push rod (4)
(403), the axis of the axis and the idler wheel mounting hole (403) of the tenon cylinder (402) all with the push rod cylinder (401)
Axis vertical take-off, the blade rotor (202) inserting is fixed in blade rotor hole (301)；It is provided on idler wheel (5) coaxial
Idler wheel cylinder (501) and rolling wheel installing shaft (502)；It is provided on cam (6) cam cylindrical surface (601), the cam cylindrical surface
(601) coaxially with the rotary shaft (7), it is provided on the cam cylindrical surface (601) around the cam cylindrical surface (601) one weeks
Connection cam curve slot (602)；The push rod cylinder (401), which is inserted into the push-rod hole (104) and meets sliding, matches
It closes, the tenon cylinder (402) is inserted into the slotted hole (302) and slidably, and rolling wheel installing shaft (502) inserting is solid
It is scheduled in the idler wheel mounting hole (403), the idler wheel cylinder (501) is inserted into cam curve slot (602) and slidably.
4. the blade according to claim 3 with fixed-wing, which can turn Horizontal single-wheel formula, moves rotor aircraft, it is characterised in that:
The cam curve slot (602) is by work operating condition straight trough (603), standby operating conditions straight trough (604), the first helicla flute (605) and
One end of two helicla flutes (606) composition, one end of the work operating condition straight trough (603) and the standby operating conditions straight trough (604) is logical
Cross the first helicla flute (605) connection, the other end and the standby operating conditions straight trough of the work operating condition straight trough (603)
(604) the other end is connected to by second helicla flute (606).
5. the blade according to claim 4 with fixed-wing, which can turn Horizontal single-wheel formula, moves rotor aircraft, it is characterised in that:
The two sides of the work operating condition straight trough (603) are plane and all vertical with the axis of the cam cylindrical surface (601), the work
It is equal with the diameter of the idler wheel cylinder (501) to make the distance between two sides of operating condition straight trough (603), the standby operating conditions are straight
The two sides of slot (604) are plane and all vertical with the axis of the cam cylindrical surface (601), the standby operating conditions straight trough
(604) the distance between two sides are equal with the diameter of the idler wheel cylinder (501), and the two of first helicla flute (605)
Side and the two sides of second helicla flute (606) are spiral camber.
6. the blade according to claim 4 with fixed-wing, which can turn Horizontal single-wheel formula, moves rotor aircraft, it is characterised in that:
The cam (6) is one symmetrical three-dimensional, and the plane of symmetry of the cam (6) is working standard face (F), the cam cylindrical surface
(601) for axis in the working standard face (F), the work operating condition straight trough (603) is right about the working standard face (F)
Claim, the working standard face (F) is vertical with direction of advance of aircraft when flat winged.
7. the blade according to claim 1 with fixed-wing, which can turn Horizontal single-wheel formula, moves rotor aircraft, it is characterised in that:
The counterweight (13) can make the aircraft center of gravity in the longitudinally asymmetric face of the aircraft.
8. the blade according to claim 2 with fixed-wing, which can turn Horizontal single-wheel formula, moves rotor aircraft, it is characterised in that:
It further include at least one of outer reinforcement curved beam (105) and interior reinforcement curved beam (106) on the rotating frame (1), for reinforcing
The intensity of the rotating frame (1).
9. the blade according to claim 8 with fixed-wing, which can turn Horizontal single-wheel formula, moves rotor aircraft, it is characterised in that:
The straight beam (102), the outer reinforcement curved beam (105) and the interior reinforcement curved beam (106) are hollow structure；
And/or
The straight beam (102), the outer reinforcement curved beam (105) and the interior reinforcement curved beam (106) are engineering plastics material；
And/or
The straight beam (102), the outer reinforcement curved beam (105) and the interior reinforcement curved beam (106) are carbon fiber material.
10. the blade according to claim 3 with fixed-wing, which can turn Horizontal single-wheel formula, moves rotor aircraft, feature exists
In: the straight beam (102) and the push-rod hole (104) are all circumferentially uniformly distributed in the centre bore (101), the straight beam
(102) quantity is greater than 1, and the quantity of the push-rod hole (104) is identical as the quantity of the straight beam (102)；The blade peace
It fills hole (103) straight uniform on the straight beam (102) to be distributed, the blade mounting hole on each straight beam (102)
(103) quantity is greater than 1.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910656172.7A CN110254705B (en) | 2019-07-19 | 2019-07-19 | Single-wheel type moving-wing aircraft with rotatable and horizontal blades and fixed wings |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910656172.7A CN110254705B (en) | 2019-07-19 | 2019-07-19 | Single-wheel type moving-wing aircraft with rotatable and horizontal blades and fixed wings |
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| CN110254705A true CN110254705A (en) | 2019-09-20 |
| CN110254705B CN110254705B (en) | 2020-12-08 |
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| Application Number | Title | Priority Date | Filing Date |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113911335A (en) * | 2021-11-17 | 2022-01-11 | 苏州高博软件技术职业学院 | Two-curtain driving energy-adjustable rotary wing aircraft with fixed wings |
| CN113911351A (en) * | 2021-11-17 | 2022-01-11 | 苏州高博软件技术职业学院 | Automatic curtain-pulling type driving energy-adjustable continuous rotating wing device |
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| FR2324513A1 (en) * | 1975-09-17 | 1977-04-15 | Jourdan Joannes | Flapping wing flying machine - has cam acting on bicycle wheel mounted in slots of supports with motion transmitted by rod to wing inner ends |
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| CN113911351A (en) * | 2021-11-17 | 2022-01-11 | 苏州高博软件技术职业学院 | Automatic curtain-pulling type driving energy-adjustable continuous rotating wing device |
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|---|---|
| CN110254705B (en) | 2020-12-08 |
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