CN110282125A - It can turn vertical dicycly based on blade and move the aircraft that the wing pushes - Google Patents
It can turn vertical dicycly based on blade and move the aircraft that the wing pushes Download PDFInfo
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- CN110282125A CN110282125A CN201910655295.9A CN201910655295A CN110282125A CN 110282125 A CN110282125 A CN 110282125A CN 201910655295 A CN201910655295 A CN 201910655295A CN 110282125 A CN110282125 A CN 110282125A
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- blade
- wing
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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
- B64C39/006—Aircraft not otherwise provided for with wings, paddle wheels, bladed wheels, moving or rotating in relation to the fuselage about a vertical 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)
- Turbine Rotor Nozzle Sealing (AREA)
- Transmission Devices (AREA)
Abstract
It can turn the aircraft that vertical dicycly moves wing promotion based on blade the invention discloses a kind of, it is characterized by comprising the wheeled dynamic wings, transmission mechanism, cam, rotary shaft, retarder, motor, fuselage ring and fixed-wing, fuselage ring is monosymmetric to be mounted with two cams, there are two the rotary shafts of vertical direction for the monosymmetric arrangement of fuselage ring, two motor being arranged on fuselage ring pass through respectively after two retarders being arranged on fuselage ring slow down drives two rotary shaft continuous rotations respectively, the rotation direction of two rotary shafts is opposite, two wheeled dynamic wings are respectively fixedly connected in two rotary shafts, two sets of transmission mechanism are separately connected two wheeled dynamic wings and two cams, the wheeled dynamic wing includes rotating frame, and it is mounted on the rotatable blade in rotating frame, cam and transmission mechanism are for controlling leaf The rotation and reset of piece are provided with fixed-wing on fuselage ring for generating lift.
Description
Technical field
The present invention relates to movable rotor aircrafts and flying robot field, especially a kind of to turn vertical two-wheel based on blade
Formula moves the aircraft that the wing pushes.
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
Rising pneumatic efficiency, aerodynamic arrangement reasonably can turn the aircraft that vertical dicycly moves wing promotion based on blade, to solve existing skill
The above problem present in art.
Realizing the technical solution of the object of the invention is: the dynamic wing promotion of vertical dicycly can be turned by providing one kind based on blade
Aircraft, including the wheeled dynamic wing, transmission mechanism, cam, rotary shaft, retarder, motor, fuselage ring and fixed-wing, institute
State that fuselage ring is monosymmetric to be mounted with two cams, there are two perpendicular for the monosymmetric arrangement of fuselage ring
Histogram to the rotary shaft, two motor being arranged on the fuselage ring pass through respectively be arranged in the fuselage
Two retarders on frame drive two rotary shaft continuous rotations, turn of two rotary shafts respectively after slowing down
Move contrary, two wheeled dynamic wings are respectively fixedly connected in two rotary shafts, two sets of transmission mechanisms point
It Lian Jie not two wheeled dynamic wings and two cams；The wheeled dynamic wing includes rotating frame, and is mounted on described
Rotatable blade in rotating frame, the cam and the transmission mechanism are used to control the rotation and reset of the blade；
The fixed-wing is provided on the fuselage ring for generating lift.
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；Two rotary shafts are separately connected two centre bores and two institutes
Retarder is stated, the output shaft of two motor is separately mounted in two retarder input holes.
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；It is provided with cam cylindrical surface on cam, two cam cylindrical surfaces are respectively with two
A concentric rotation axis is provided with the cam curve around the cam cylindrical surface connection in one week on the cam cylindrical surface
Slot；The idler wheel cylinder is inserted into the cam curve slot and slidably, and the push rod cylinder is inserted into the push-rod hole
And meet and be slidably matched, in the oblong hole and slidably, the rolling wheel installing shaft inserting is fixed for tenon cylinder inserting
In the idler wheel mounting hole.
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, 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.
It is a kind of to turn the aircraft that vertical dicycly moves wing promotion based on blade, it is characterised in that including rotating frame, leaf
Piece, pull ring, push rod, idler wheel, cam, rotary shaft, retarder, motor, fuselage ring and fixed-wing have center on rotating frame
Hole, straight beam and push-rod hole, the direction of straight beam and the axis of centre bore are parallel, blade mounting hole are provided on straight beam, push-rod hole is in
Heart hole is circumferentially uniformly distributed, the axis of blade mounting hole and the axis vertical take-off of centre bore, the axis of push-rod hole and the axis of centre bore
Line is parallel, has blade windward side, blade rotor and blade leeward on blade, has blade rotor hole and slotted hole on pull ring, push away
There are push rod cylinder, tenon cylinder and idler wheel mounting hole, the axis of tenon cylinder and the axis vertical take-off of push rod cylinder, idler wheel peace on bar
The axis in hole and the axis vertical take-off of push rod cylinder are filled, has coaxial idler wheel cylinder and rolling wheel installing shaft on idler wheel, has on cam convex
Cylindrical surface is taken turns, is provided with the cam curve slot around the connection in one week of cam cylindrical surface on cam cylindrical surface, cam curve slot is by working
Operating condition straight trough, standby operating conditions straight trough, the first spiral groove and the second spiral groove composition, work operating condition straight trough two sides be plane and
All vertical with the axis on cam cylindrical surface, the two sides of standby operating conditions straight trough are plane and all hang down with the axis on cam cylindrical surface
Directly, one end of work operating condition straight trough is connected to one end of standby operating conditions straight trough by the first helicla flute, and work the another of operating condition straight trough
One end is connected to the other end of standby operating conditions straight trough by the second helicla flute, and fuselage ring is monosymmetric to be mounted with two
Cam, there are two the rotary shaft of vertical direction, two cam cylindrical surfaces to revolve respectively with two for the monosymmetric arrangement of fuselage ring
Shaft is coaxial, and two rotary shafts are separately mounted on the output shaft of two retarders, and the output shaft of two motor is installed respectively
In two retarder input holes, retarder, motor and fixed-wing counterweight are all fixed on fuselage ring, two rotations
Frame is set in two rotary shafts again by centre bore, and idler wheel cylinder is inserted into cam curve slot and can be in cam curve
Sliding in slot, rolling wheel installing shaft inserting are 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 inserting
In blade mounting hole and can be rotated, the distance between two sides for the operating condition straight trough that works are equal with the diameter of idler wheel cylinder, to
The distance between the two sides of machine operating condition straight trough are equal with the diameter of idler wheel cylinder, the two sides of the first helicla flute and the second spiral
The two sides of slot are spiral camber, and the rotation direction of two rotary shafts is on the contrary, cam is a symmetrical solid, pair of cam
Face is referred to as working standard face F, and the axis on cam cylindrical surface is in the F of working standard face, and the operating condition straight trough that works is about working standard face F
Symmetrically, working standard face F is vertical with direction of advance of aircraft when flat winged, has outer reinforcement curved beam and interior reinforcement bent on rotating frame
Beam, straight beam, outer reinforcement curved beam and interior reinforcement curved beam all use hollow structure and use the lightweights material such as engineering plastics, carbon fibre
Material.
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；When idler wheel turns in the first helicla flute, push rod with rotary shaft synchronous rotary
Start to move backward relative to rotating shaft axis direction simultaneously, tenon cylinder rotates backward pull ring, thus with movable vane piece
Shaft rotates backward, and when idler wheel turns in standby operating conditions straight trough, blade rotor rotates backward 90 degree, and blade windward side is again
It returns to parallel with airflow direction, returns to standby mode.When two motor speeds are identical, what the wheeled dynamic wing of the left and right sides generated
Thrust is the same, therefore flies before aircraft, and the torque that the wheeled dynamic wing in two sides generates is equal in magnitude, contrary, therefore flies
Device entirety torque is balance, and gas layout is quite reasonable, and when two motor speeds are not identical, the wheeled dynamic wing of the left and right sides is produced
Raw thrust is different, then turn function may be implemented in aircraft.
Compared with prior art, the present invention its remarkable advantage is:
It vertical dicycly can be turned based on blade moves the aircraft that the wing pushes 1. of the present invention, by will be in the wheeled dynamic wing
The advantages of blade is set as continuous rotation, maintains rotor continuous rotation overcomes the weakness that flapping wing needs to move back and forth.
2. of the present invention can turn the aircraft that vertical dicycly moves wing promotion based on blade, controlled by cam continuous
The blade of rotation is also rotatable relative to rotary shaft, moves blade windward with maximum area in working condition and obtains most atmosphere
Power, and it is parallel with airflow direction to which resistance substantially reduces in standby mode, achieve the purpose that improve pneumatic efficiency, gas
Efficiency of movement is much higher than existing flapping wing and rotor craft, and biggish thrust can be provided for aircraft.
3. it is of the present invention based on blade can turn vertical dicycly move the wing push aircraft, can rotating vane piece work shape
Switching between state and standby mode is automatically performed under cam control, and complicated electronic control system, structure are not needed
Simple and reliable property is preferable.
4. of the present invention can turn the aircraft that vertical dicycly moves wing promotion based on blade, it is configured with two symmetrically
The vertical wheeled dynamic wing, not only thrust is bigger, do not have to use steering engine transfer, and it is preceding winged when fuselage body force square self-balancing,
Other balancing devices, more compact structure are not needed；Fixed-wing generates lift, can save energy when aircraft is flat to fly, reach long
The purpose of endurance.
5. of the present invention can turn the aircraft that vertical dicycly moves wing promotion based on blade, structure is simple, processes work
Skill is good, and production cost is 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 the overall structure that can turn the aircraft that the dynamic wing of vertical dicycly pushes based on blade of the embodiment of the present invention 1
Schematic diagram.
Fig. 2 is the detailed construction that can turn the aircraft that the dynamic wing of vertical dicycly pushes based on blade of the embodiment of the present invention 1
Schematic diagram.
Fig. 3 is the wheeled dynamic wing that can turn the aircraft that the dynamic wing of vertical dicycly pushes based on blade of the embodiment of the present invention 1
Standby mode detailed construction schematic diagram.
Fig. 4 is the wheeled dynamic wing that can turn the aircraft that the dynamic wing of vertical dicycly pushes based on blade of the embodiment of the present invention 1
Detailed construction schematic diagram of the standby mode into working condition handoff procedure.
Fig. 5 is the wheeled dynamic wing that can turn the aircraft that the dynamic wing of vertical dicycly pushes based on blade of the embodiment of the present invention 1
Working condition detailed construction schematic diagram.
Fig. 6 is the rotating frame that can turn the aircraft that the dynamic wing of vertical dicycly pushes based on blade of the embodiment of the present invention 1
Structural schematic diagram.
Fig. 7 is the knot of the blade that can turn the aircraft that the dynamic wing of vertical dicycly pushes based on blade of the embodiment of the present invention 1
Structure schematic diagram.
Fig. 8 is the pull ring wheel that can turn the aircraft that the dynamic wing of vertical dicycly pushes based on blade of the embodiment of the present invention 1
Structural schematic diagram
Fig. 9 is the knot of the push rod that can turn the aircraft that the dynamic wing of vertical dicycly pushes based on blade of the embodiment of the present invention 1
Structure schematic diagram.
Figure 10 is the knot of the idler wheel that can turn the aircraft that the dynamic wing of vertical dicycly pushes based on blade of the embodiment of the present invention 1
Structure schematic diagram.
Figure 11 is the knot of the cam that can turn the aircraft that the dynamic wing of vertical dicycly pushes based on blade of the embodiment of the present invention 1
Structure schematic diagram.
Figure 12 is the cam cutting that can turn the aircraft that the dynamic wing of vertical dicycly pushes based on blade of the embodiment of the present invention 1
Structural schematic diagram afterwards.
Figure 13 is the cam cutting that can turn the aircraft that the dynamic wing of vertical dicycly pushes based on blade of the embodiment of the present invention 1
End on projection figure afterwards.
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 being based on
Blade can turn the agricultural plant protection unmanned plane that vertical dicycly moves the aircraft that the wing pushes.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 and fixed-wing 11 have on rotating frame 1
The direction of centre bore 101, straight beam 102 and push-rod hole 104, straight beam 102 is parallel with the axis of centre bore 101, and centre bore 101 is circumferential
Equally distributed 102 quantity of straight beam is 3, is provided with blade mounting hole 103, equally distributed blade on straight beam 102 on straight beam 102
The quantity of mounting hole 103 is 4, and push-rod hole 104 is circumferentially uniformly distributed in centre bore 101, the quantity and straight beam of push-rod hole 104
102 quantity is identical, the axis of blade mounting hole 103 and the axis vertical take-off of centre bore 101, the axis of push-rod hole 104 and center
The axis in hole 101 is parallel, has blade windward side 201, blade rotor 202 and blade leeward 203 on blade 2, has leaf on pull ring 3
Piece shaft hole 301 and slotted hole 302 have push rod cylinder 401, tenon cylinder 402 and idler wheel mounting hole 403, tenon circle on push rod 4
The axis of the axis vertical take-off of the axis of column 402 and push rod cylinder 401, the axis of idler wheel mounting hole 403 and push rod cylinder 401 is just
It hands over, has coaxial idler wheel cylinder 501 and rolling wheel installing shaft 502 on idler wheel 5, have cam cylindrical surface 601, cam cylinder on cam 6
The cam curve slot 602 around the connection in 601 1 weeks of cam cylindrical surface is provided on face 601, cam curve slot 602 is straight by work operating condition
Slot 603, standby operating conditions straight trough 604, the first helicla flute 605 and the second helicla flute 606 composition, the two sides for the operating condition straight trough 603 that works
Face is 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 cam
The axis on 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 the first spiral
Slot 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 are connected by the second helicla flute 606
Logical, fuselage ring 10 is monosymmetric to be mounted with two cams 6, and there are two vertical for the monosymmetric arrangement of fuselage ring 10
The rotary shaft 7 in direction, two cam cylindrical surfaces 601 are coaxial with two rotary shafts 7 respectively, and two rotary shafts 7 are separately mounted to two
On the output shaft of a retarder 8, the output shaft of two motor 9 is separately mounted in two 8 input holes of retarder, retarder 8,
Motor 9 and 11 counterweight 13 of fixed-wing are all fixed on fuselage ring 10, and two rotating frames 1 are divided by centre bore 101
It is not set in two rotary shafts 7 again, idler wheel cylinder 501 is inserted into cam curve slot 602 and can slide in cam curve slot 602
Dynamic, the inserting of rolling wheel installing shaft 502 is fixed in idler wheel mounting hole 403, and tenon cylinder 402 is inserted into slotted hole 302 and can slide
Dynamic, 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 rotor hole
In 301, blade rotor 202 is inserted into blade mounting hole 103 and can be rotated, between the two sides of operating condition straight trough 603 that work
Distance is equal with the diameter of idler wheel cylinder 501, the distance between two sides of standby operating conditions straight trough 604 and idler wheel cylinder 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, two rotary shafts 7
Rotation direction on the contrary, cam 6 is one symmetrical three-dimensional, the plane of symmetry of cam 6 is working standard face F, cam cylindrical surface 601
Axis in the F of working standard face, work operating condition straight trough 603 it is symmetrical about working standard face F, working standard face F and aircraft
Direction of advance when flat winged is vertical, there is outer reinforcement curved beam 105 and interior reinforcement curved beam 106, straight beam 102, outer reinforcement on rotating frame 1
Curved beam 105 and interior reinforcement curved beam 106 all using hollow structure and use carbon fiber material.Agricultural plant protection unmanned plane uses this hair
It, can be complete since wheeled dynamic wing drag is small, pneumatic efficiency is high after the bright aircraft that can turn the dynamic wing promotion of vertical dicycly based on blade
At sowing fertilizers, pulvis is sprayed, the multiplicity function such as supple-mentary pollination is answered, and cruise duration is long, relative to rotor wing unmanned aerial vehicle, identical
When 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 turn vertical double using based on blade
High-rise For Use Only in Case of Fire the unmanned plane for the aircraft that the wheeled dynamic wing pushes.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 and fixed-wing 11, have on rotating frame 1 centre bore 101,
The direction of straight beam 102 and push-rod hole 104, straight beam 102 is parallel with the axis of centre bore 101, and centre bore 101 is circumferential equally distributed
102 quantity of straight beam is 2, is provided with blade mounting hole 103, equally distributed blade mounting hole 103 on straight beam 102 on straight beam 102
Quantity be 5, push-rod hole 104 is uniformly distributed centre bore 101 is circumferential, the quantity and the quantity phase of straight beam 102 of push-rod hole 104
Together, the axis vertical take-off of the axis of blade mounting hole 103 and centre bore 101, the axis of push-rod hole 104 and the axis of centre bore 101
In parallel, there are blade windward side 201, blade rotor 202 and blade leeward 203 on blade 2, have blade rotor hole 301 on pull ring 3
With slotted hole 302, there are push rod cylinder 401, tenon cylinder 402 and idler wheel mounting hole 403, the axis of tenon cylinder 402 on push rod 4
With the axis vertical take-off of push rod cylinder 401, the axis vertical take-off of the axis of idler wheel mounting hole 403 and push rod cylinder 401 has on idler wheel 5
Coaxial idler wheel cylinder 501 and rolling wheel installing shaft 502 has cam cylindrical surface 601 on cam 6, be provided on cam cylindrical surface 601 around
The cam curve slot 602 of cam cylindrical surface connection in 601 1 weeks, cam curve slot 602 is by work operating condition straight trough 603, standby work
Condition straight trough 604, the first helicla flute 605 and the second helicla flute 606 composition, the two sides of work operating condition straight trough 603 are plane and all
It is vertical with the axis on cam cylindrical surface 601, the two sides of standby operating conditions straight trough 604 be plane and all with cam cylindrical surface 601
Axis is vertical, and the one end for the operating condition straight trough 603 that works is connected to one end of standby operating conditions straight trough 604 by the first helicla flute 605, work
The other end for making operating condition straight trough 603 is connected to the other end of standby operating conditions straight trough 604 by the second helicla flute 606, fuselage ring
10 it is monosymmetric be mounted with two cams 6, there are two the rotations of vertical direction for the monosymmetric arrangement of fuselage ring 10
Axis 7, two cam cylindrical surfaces 601 are coaxial with two rotary shafts 7 respectively, and two rotary shafts 7 are separately mounted to two retarders 8
On output shaft, the output shaft of two motor 9 is separately mounted in two 8 input holes of retarder, retarder 8, motor 9 and solid
Determine 11 counterweight 13 of the wing to be all fixed on fuselage ring 10, two rotating frames 1 are set with two again by centre bore 101
In rotary shaft 7, idler wheel cylinder 501 is inserted into cam curve slot 602 and can slide in cam curve slot 602, idler wheel installation
The inserting of axis 502 is fixed in idler wheel mounting hole 403, and tenon cylinder 402 is inserted into slotted hole 302 and slidably, push rod cylinder
401 are inserted into push-rod hole 104 and meet and are slidably matched, and the inserting of blade rotor 202 is fixed in blade rotor hole 301, blade
Shaft 202 is inserted into blade mounting hole 103 and can be rotated, the distance between two sides for the operating condition straight trough 603 that works and idler wheel
The diameter of cylinder 501 is equal, and the distance between two sides of standby operating conditions straight trough 604 are equal with the diameter of idler wheel cylinder 501, the
The two sides of one helicla flute 605 and the two sides of the second helicla flute 606 are spiral camber, the rotation direction of two rotary shafts 7
On the contrary, cam 6 is one symmetrical three-dimensional, the plane of symmetry of cam 6 is working standard face F, and the axis on cam cylindrical surface 601 is in work
Make in datum level F, work operating condition straight trough 603 is symmetrical about working standard face F, before working standard face F is put down with aircraft when flying
It is vertical into direction, there are outer reinforcement curved beam 105 and interior reinforcement curved beam 106, straight beam 102, outer 105 and of reinforcement curved beam on rotating frame 1
Interior reinforcement curved beam 106 all using hollow structure and uses engineering plastics.High-rise For Use Only in Case of Fire unmanned plane is using the present invention is based on leaves
After piece can turn the aircraft that vertical dicycly moves wing promotion, 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 turn vertical double using based on blade
The forest fire protection fire-fighting dedicated unmanned machine for the aircraft that the wheeled dynamic wing pushes.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 and fixed-wing 11 have centre bore on rotating frame 1
101, the direction of straight beam 102 and push-rod hole 104, straight beam 102 is parallel with the axis of centre bore 101, and centre bore 101 is circumferential uniformly to be divided
102 quantity of straight beam of cloth is 4, is provided with blade mounting hole 103, equally distributed blade mounting hole on straight beam 102 on straight beam 102
103 quantity is 6, and push-rod hole 104 is circumferentially uniformly distributed in centre bore 101, the quantity of push-rod hole 104 and the number of straight beam 102
Measure identical, the axis of blade mounting hole 103 and the axis vertical take-off of centre bore 101, axis and the centre bore 101 of push-rod hole 104
Axis is parallel, has blade windward side 201, blade rotor 202 and blade leeward 203 on blade 2, has blade rotor on pull ring 3
Hole 301 and slotted hole 302 have push rod cylinder 401, tenon cylinder 402 and idler wheel mounting hole 403, tenon cylinder 402 on push rod 4
Axis and push rod cylinder 401 axis vertical take-off, the axis vertical take-off of the axis of idler wheel mounting hole 403 and push rod cylinder 401, idler wheel
There are coaxial idler wheel cylinder 501 and rolling wheel installing shaft 502 on 5, there is cam cylindrical surface 601 on cam 6, on cam cylindrical surface 601
Be provided with the cam curve slot 602 around the connection in 601 1 weeks of cam cylindrical surface, cam curve slot 602 by work operating condition straight trough 603,
Standby operating conditions straight trough 604, the first helicla flute 605 and the second helicla flute 606 composition, the two sides of work operating condition straight trough 603 are flat
Face 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 cam cylindrical surface
601 axis 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 are connected by the first helicla flute 605
Logical, the other end for the operating condition straight trough 603 that works is connected to the other end of standby operating conditions straight trough 604 by the second helicla flute 606, fuselage
Frame 10 is monosymmetric to be mounted with two cams 6, and there are two vertical directions for the monosymmetric arrangement of fuselage ring 10
Rotary shaft 7, two cam cylindrical surfaces 601 are coaxial with two rotary shafts 7 respectively, and two rotary shafts 7 are separately mounted to two decelerations
On the output shaft of device 8, the output shaft of two motor 9 is separately mounted in two 8 input holes of retarder, retarder 8, motor
9 and 11 counterweight 13 of fixed-wing be all fixed on fuselage ring 10, two rotating frames 1 are set with by centre bore 101
Again in two rotary shafts 7, idler wheel cylinder 501 is inserted into cam curve slot 602 and can slide in cam curve slot 602, rolls
The wheel inserting of installation axle 502 is fixed in idler wheel mounting hole 403, and tenon cylinder 402 is inserted into slotted hole 302 and slidably, is pushed away
Bar 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 rotor hole 301
Interior, blade rotor 202 is inserted into blade mounting hole 103 and can be rotated, the distance between the two sides for the operating condition straight trough 603 that works
It is equal with the diameter of idler wheel cylinder 501, the diameter of the distance between two sides of standby operating conditions straight trough 604 and idler wheel cylinder 501
Equal, the two sides of the two sides of the first helicla flute 605 and the second helicla flute 606 are spiral camber, turn of two rotary shafts 7
Move contrary, cam 6 is one symmetrical three-dimensional, and the plane of symmetry of cam 6 is working standard face F, the axis on cam cylindrical surface 601
For line in the F of working standard face, work operating condition straight trough 603 is symmetrical about working standard face F, and working standard face F and aircraft are flat winged
When direction of advance it is vertical, have outer reinforcement curved beam 105 and interior reinforcement curved beam 106, straight beam 102, outer reinforcement curved beam on rotating frame 1
105 and interior reinforcement curved beam 106 all using hollow structure and use engineering plastics.Forest fire protection fire-fighting dedicated unmanned machine uses this hair
It is bright based on blade can turn vertical dicycly move the wing push aircraft after, due to wheeled dynamic wing impulse stroke thrust is big, resistance is small,
Thrust is big, pneumatic efficiency is high, therefore has stronger mobility, and energy quick response forest fire situation quickly carries out forest inspection
It catches fire with flight and a little puts 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 (9)
1. can turn vertical dicycly based on blade moves the aircraft that the wing pushes, it is characterised in that: including the wheeled dynamic wing, driver
Structure, cam (6), rotary shaft (7), retarder (8), motor (9), fuselage ring (10) and fixed-wing (11), the fuselage frame
Frame (10) is monosymmetric to be mounted with two cams (6), and the fuselage ring (10) is monosymmetric to be disposed with two
The rotary shaft (7) of a vertical direction, two motor (9) being arranged on the fuselage ring (10) pass through respectively
It is arranged after two on the fuselage ring (10) retarders (8) are slowed down and drives two rotary shafts (7) respectively even
Continuous rotation, the rotation directions of two rotary shafts (7) is on the contrary, two wheeled dynamic wings are respectively fixedly connected with described in two
In rotary shaft (7), two sets of transmission mechanisms are separately connected two wheeled dynamic wings and two cams (6)；The wheel
It includes rotating frame (1) that formula, which moves the wing, and the rotatable blade (2) being mounted in the rotating frame (1), the cam
(6) and the transmission mechanism is for controlling the rotation and reset of the blade (2)；It is provided on the fuselage ring (10) described
Fixed-wing (11) is for generating lift.
2. according to claim 1 can turn the aircraft that vertical dicycly moves wing promotion based on blade, it is characterised in that: institute
It states and is provided with centre bore (101) and straight beam (102) on rotating frame (1), the direction of the straight beam (102) and the centre bore
(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；Two rotary shafts (7) are separately connected two centre bores (101) and two institutes
It states retarder (8), the output shaft of two motor (9) is separately mounted in two retarder (8) input holes.
3. according to claim 1 or 2 can turn the aircraft that vertical dicycly moves wing promotion based on blade, 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), two cam circles
Cylinder (601) respectively with two rotary shafts (7) coaxially, be provided on the cam cylindrical surface (601) around the cam circle
The cam curve slot (602) of cylinder connection in (601) one weeks；The idler wheel cylinder (501) is inserted into the cam curve slot
(602) in and slidably, the push rod cylinder (401) is inserted into the push-rod hole (104) and meets and is slidably matched, the tenon
Head cylinder (402) is inserted into the slotted hole (302) and slidably, and rolling wheel installing shaft (502) inserting is fixed on described
In idler wheel mounting hole (403).
4. according to claim 3 can turn the aircraft that vertical dicycly moves wing promotion based on blade, it is characterised in that: institute
Cam curve slot (602) is stated by work operating condition straight trough (603), standby operating conditions straight trough (604), the first helicla flute (605) and second
Helicla flute (606) composition, one end of the work operating condition straight trough (603) and one end of the standby operating conditions straight trough (604) pass through
First helicla flute (605) connection, the other end of the work operating condition straight trough (603) and the standby operating conditions straight trough (604)
The other end pass through second helicla flute (606) be connected to.
5. according to claim 4 can turn the aircraft that vertical dicycly moves wing promotion based on blade, it is characterised in that: institute
The two sides for stating work operating condition straight trough (603) are plane and all vertical with the axis of the cam cylindrical surface (601), the work
The distance between two sides of operating condition straight trough (603) are equal with the diameter of the idler wheel cylinder (501), the standby operating conditions straight trough
(604) two sides 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 it is equal with the diameter of the idler wheel cylinder (501), the two sides of first helicla flute (605) and
The two sides of second helicla flute (606) are spiral camber.
6. according to claim 5 can turn the aircraft that vertical dicycly moves wing promotion based on blade, it is characterised in that: institute
Stating 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. according to claim 2 can turn the aircraft that vertical dicycly moves wing promotion based on blade, it is characterised in that: institute
Stating on rotating frame (1) further includes at least one of outer reinforcement curved beam (105) and interior reinforcement curved beam (106), for reinforcing
State the intensity of rotating frame (1).
8. according to claim 7 can turn the aircraft that vertical dicycly moves wing promotion based on blade, it is characterised in that: institute
Stating straight beam (102), the outer reinforcement curved beam (105) and the interior reinforcement curved beam (106) is 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.
9. according to claim 3 can turn the aircraft that vertical dicycly moves wing promotion based on blade, it is characterised in that: institute
It states straight beam (102) and the push-rod hole (104) to be all circumferentially uniformly distributed in the centre bore (101), the number of the straight beam (102)
Amount 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 mounting hole (103)
Straight uniform is distributed on the straight beam (102), the quantity of the blade mounting hole (103) on each straight beam (102)
Greater than 1.
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| CN201910655295.9A CN110282125B (en) | 2019-07-19 | 2019-07-19 | Aircraft based on blade-rotatable vertical double-wheel type moving wing pushing |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910655295.9A CN110282125B (en) | 2019-07-19 | 2019-07-19 | Aircraft based on blade-rotatable vertical double-wheel type moving wing pushing |
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| CN110282125B CN110282125B (en) | 2020-12-08 |
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Cited By (1)
| 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 |
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| CN109050898A (en) * | 2018-08-16 | 2018-12-21 | 南京壹诺为航空科技有限公司 | Non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula |
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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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| CN105775117A (en) * | 2016-04-19 | 2016-07-20 | 倪德玉 | Helicopter taking off and landing vertically and flying horizontally and application thereof |
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| 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 |
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| CN110282125B (en) | 2020-12-08 |
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