CN209667364U - Coaxial double-rotary swing device - Google Patents
Coaxial double-rotary swing device Download PDFInfo
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- CN209667364U CN209667364U CN201822213524.5U CN201822213524U CN209667364U CN 209667364 U CN209667364 U CN 209667364U CN 201822213524 U CN201822213524 U CN 201822213524U CN 209667364 U CN209667364 U CN 209667364U
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- rotary swing
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Abstract
The utility model discloses a kind of coaxial double-rotary swing devices, including upper rotor mechanism, lower rotor mechanism, wing drop pitch-changing mechanism and central axis.Upper rotor mechanism and lower rotor mechanism are arranged on central axis, and upper rotor mechanism can be rotated backward with lower rotor mechanism relative to central axis, and upper rotor mechanism and lower rotor mechanism can collapse and be unfolded relative to central axis；On the centrally disposed axis of wing drop pitch-changing mechanism, wing drop pitch-changing mechanism is between upper rotor mechanism and lower rotor mechanism, wing drop pitch-changing mechanism is for changing upper rotor mechanism and expansion amplitude of the lower rotor mechanism relative to central axis, and for changing the distance between upper rotor mechanism and lower rotor mechanism.The coaxial double-rotary swing device of the utility model after aircraft assembly, can be realized lifting, longitudinal and transverse direction movement and the adjustment of flight attitude, while the ability for making aircraft resist wind-force is stronger, ensures the flight stability of aircraft, and easy to carry.
Description
Technical field
The utility model relates to vehicle technology fields, more particularly to a kind of coaxial double-rotary swing device.
Background technique
In recent years, small-sized unmanned aircraft plays remarkable effect in military, civil field.In military field, small in size,
Light-weight small aircraft has very strong stealthy effect in various aspects such as vision, noise and radar reflection sections, can mention significantly
It is horizontal to rise battle field informationization.In civil field, small-sized unmanned aircraft also can be using exploration outdoors, power-line patrolling, fire prison
In the dangerous situations such as survey.
Currently, small-sized unmanned aircraft often shows certain limitation when coping with a variety of different task demands.Example
Such as, conventional Fixed Wing AirVehicle, forward flight speed is fast, task radius is big, but sliding race or ejection is needed to take off, and needs to block
Land, and a hovering investigation can not be carried out away to target；Rotor class aircraft, further as helicopter, more rotors fly
Row device etc., can VTOL, hovering, show excellent low-speed performance, but rotor class aircraft forward flight speed is low, task
Radius is small, can not cope with quick response, remote mission requirements.
In particular, individual soldier and level of platoon leader combat unit are different to the performance requirement of aircraft under different operational environments, for example,
In military operations in urban terrain, have it is vertical rise battle array, ability of hovering unmanned vehicle can between building, on roof, on windowsill observation exist
The enemy in shelter promotes soldier's situation of battlefield sensing capability；In Field Operational, often need flying speed fast, combat radius
Big aircraft is to obtain rapidly the large-scale reconnaissance in periphery.It is limited by load capacity, individual soldier and level of platoon leader combat unit are difficult
Different combat duty demands are coped with to carry a variety of aircraft simultaneously, a kind of flight stability is researched and developed, is not easy to be affected by the wind, it is empty
Between occupy small, be convenient for carrying, be suitble to individual equipment, be able to satisfy friction speed, different combat radiuses, can vertically play the small-sized nothing of battle array
People's aircraft is particularly important.
Utility model content
The purpose of this utility model is to provide a kind of coaxial double-rotary swing device, with solve it is existing in the prior art nobody
Aircraft flight is unstable, the big technical problem of space hold.
To achieve the goals above, the utility model uses following technical scheme:
A kind of coaxial double-rotary swing device provided by the utility model, including upper rotor mechanism, lower rotor mechanism, wing drop
Pitch-changing mechanism and central axis；
The upper rotor mechanism and the lower rotor mechanism are arranged on the central axis, the upper rotor mechanism and institute
Stating lower rotor mechanism can rotate backward relative to the central axis, and the upper rotor mechanism and the lower rotor mechanism are equal
It can collapse and be unfolded relative to the central axis；
The wing drop pitch-changing mechanism is arranged on the central axis, and the wing drop pitch-changing mechanism is located on described
Between rotor mechanism and the lower rotor mechanism, the wing drop pitch-changing mechanism for changing the upper rotor mechanism with it is described
Expansion amplitude of the lower rotor mechanism relative to the central axis, and for changing the upper rotor mechanism and the lower gyroplane
The distance between structure.
Further, the upper rotor mechanism includes propeller hub, blade pose adjustment portion and rotor blade；
The propeller hub is rotatably arranged on the central axis；
The rotor blade is connect by blade pose adjustment portion with the propeller hub.
Further, the upper rotor mechanism further includes rotor connecting rod；
The propeller hub is connect by the rotor connecting rod with the wing drop pitch-changing mechanism.
Further, the upper rotor mechanism further includes brushless motor and motor cabinet；
The motor cabinet is fixed on the central axis；
The stator of the brushless motor is connect with the motor cabinet, and the rotor of the brushless motor is connect with the propeller hub.
Further, blade pose adjustment portion includes limiting fixed seat and rotor holder；
The limiting fixed seat is arranged on the propeller hub；
One end of the rotor holder is arranged on the limiting fixed seat by the connection horizontal axis, the rotor
Holder can be relative to the radial rotating of the propeller hub, and moving radially along the propeller hub.
Further, retaining spring is arranged on the connection horizontal axis；
One end of the retaining spring is connect with the limiting fixed seat, the other end of the retaining spring and the rotor
The connection of paddle holder, the retaining spring are used to limit the relative position of the rotor holder and the limiting fixed seat.
Further, the foldable other end that the rotor holder is set of the rotor blade.
Further, the propeller hub passes through bearing and the center axis connection.
Further, the rotor holder is socketed on the connection horizontal axis by sliding bearing.
Further, the lower rotor mechanism is identical as the upper rotor mechanism structure, and the two is relative to the central axis
Radial symmetric be arranged on the central axis.
Coaxial double-rotary swing device provided by the utility model, upper rotor mechanism and lower rotor mechanism are coaxially disposed, Neng Gou
It is coaxially rotated backward on central axis, after aircraft assembly, can be realized lifting, wing drop pitch-changing mechanism is located at upper rotor
Between mechanism and lower rotor mechanism, upper rotor mechanism and expansion amplitude of the lower rotor mechanism relative to central axis can be changed, with
And the distance between upper rotor mechanism and lower rotor mechanism can be changed, so as to adjust the flight attitude of aircraft, so that
It is mobile that aircraft realizes longitudinal and transverse direction, while the ability for making aircraft resist wind-force is stronger, significantly reduces wind-force pair
The influence of aircraft flight can effectively ensure the flight stability of aircraft, also, upper rotor mechanism and lower rotor mechanism
It can be collapsed relative to central axis, the present apparatus can be reduced to the occupancy in space, improve the portability of aircraft and easy-to-use
Property, solve unstable, the big problem of space hold of existing unmanned vehicle flight.
Detailed description of the invention
It, below will be right in order to illustrate more clearly of specific embodiment of the present invention or technical solution in the prior art
Specific embodiment or attached drawing needed to be used in the description of the prior art are briefly described, it should be apparent that, it is described below
In attached drawing be that some embodiments of the utility model are not paying creativeness for those of ordinary skill in the art
Under the premise of labour, it is also possible to obtain other drawings based on these drawings.
Fig. 1 is a kind of structural schematic diagram for coaxial double-rotary swing device that the utility model embodiment one provides；
Fig. 2 is a kind of structural schematic diagram for coaxial double-rotary swing device that the utility model embodiment one provides；
Fig. 3 is that the structure of the upper rotor mechanism in a kind of coaxial double-rotary swing device that the utility model embodiment one provides is shown
It is intended to；
Fig. 4 is that the structure of the upper rotor mechanism in a kind of coaxial double-rotary swing device that the utility model embodiment one provides is shown
It is intended to；
Fig. 5 is the section view knot of the upper rotor mechanism in a kind of coaxial double-rotary swing device that the utility model embodiment one provides
Structure schematic diagram；
Fig. 6 is the knot in the blade pose adjustment portion in a kind of coaxial double-rotary swing device that the utility model embodiment one provides
Structure schematic diagram；
Fig. 7 is cuing open for the blade pose adjustment portion in a kind of coaxial double-rotary swing device that the utility model embodiment one provides
Depending on structural schematic diagram；
Fig. 8 is a kind of overall structure diagram for portable aircraft that the utility model embodiment two provides；
Fig. 9 is a kind of overall structure diagram for portable aircraft that the utility model embodiment two provides；
Figure 10 is that the structure of the rotor holder in a kind of portable aircraft that the utility model embodiment two provides is shown
It is intended to；
Figure 11 is the wing drop pitch-changing mechanism in a kind of portable aircraft that the utility model embodiment two provides
Structural schematic diagram；
Figure 12 is the wing drop pitch-changing mechanism in a kind of portable aircraft that the utility model embodiment two provides
Structural schematic diagram；
Figure 13 is the wing drop pitch-changing mechanism in a kind of portable aircraft that the utility model embodiment two provides
Schematic cross-sectional view；
Figure 14 is the structure in the upper wing drop portion in a kind of portable aircraft that the utility model embodiment two provides
Schematic diagram；
Figure 15 is the structure of the folding and unfolding take-off and landing device in a kind of portable aircraft that the utility model embodiment two provides
Schematic diagram.
Appended drawing reference:
The upper rotor mechanism of 110-；Rotor mechanism under 120-；130- wing drop pitch-changing mechanism；140- central axis；
111- propeller hub；112- rotor blade；113- blade pose adjustment portion；114- rotor connecting rod；115- brushless motor；
116- motor cabinet；
1131- limiting fixed seat；1132- rotor holder；1133- connection horizontal axis；1134- sliding bearing；1135- positioning
Spring；
000- fuselage；100- coaxial double-rotary swing device；200- folding and unfolding take-off and landing device；
11321- limiting slot；11322- rotating base；11323- position limit arm；
The upper wing drop portion 131-；Wing drop portion under 132-；133- synchronising (connecting) rod；The anti-torsion link assembly of 134-；135-
Leaning device steering engine；136- steering engine kinematic link；137- steering engine driving rocker；138- leaning device steering engine bracket；139- inclination
Portion's connecting rod；
1311- rake inner ring；1312- rake outer ring；
230- buffers foot mechanism；
211- telescoping mechanism steering engine fixing seat；212- telescoping mechanism steering engine；213- sliding connector；214- sliding bearing；
221- first connecting rod；222- second connecting rod；223- third connecting rod；224- fourth link；The 5th connecting rod of 225-；226-
Six-bar linkage.
Specific embodiment
The technical solution of the utility model is clearly and completely described below in conjunction with attached drawing, it is clear that described
Embodiment is the utility model a part of the embodiment, instead of all the embodiments.Based on the embodiments of the present invention, originally
Field those of ordinary skill every other embodiment obtained without making creative work belongs to practical
Novel protected range.
It is in the description of the present invention, it should be noted that term " center ", "upper", "lower", "left", "right", " perpendicular
Directly ", the orientation or positional relationship of the instructions such as "horizontal", "inner", "outside" is to be based on the orientation or positional relationship shown in the drawings, and is only
For ease of description the utility model and simplify description, rather than the device or element of indication or suggestion meaning must have it is specific
Orientation, be constructed and operated in a specific orientation, therefore should not be understood as limiting the present invention.In addition, term " the
One ", " second ", " third " are used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " is pacified
Dress ", " connected ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integrally
Connection；It can be mechanical connection, be also possible to be electrically connected；Can be directly connected, can also indirectly connected through an intermediary,
It can be the connection inside two elements.For the ordinary skill in the art, above-mentioned art can be understood with concrete condition
The concrete meaning of language in the present invention.
Embodiment one:
In the optinal plan of the present embodiment, as shown in Figures 1 to 7, a kind of coaxial double-rotary wing dress provided in this embodiment
It sets, including upper rotor mechanism 110, lower rotor mechanism 120, wing drop pitch-changing mechanism 130 and central axis 140；
Upper rotor mechanism 110 is arranged on central axis 140 with lower rotor mechanism 120, upper rotor mechanism 110 and lower rotor
Mechanism 120 can coaxially be rotated backward relative to central axis 140, and upper rotor mechanism 110 and lower rotor mechanism 120 can be relative to
Central axis 140 collapses and expansion；
On the centrally disposed axis 140 of wing drop pitch-changing mechanism 130, wing drop pitch-changing mechanism 130 is located at upper gyroplane
Between structure 110 and lower rotor mechanism 120, wing drop pitch-changing mechanism 130 is for changing upper rotor mechanism 110 and lower rotor mechanism
The 120 expansion amplitude relative to central axis 140, and for changing between upper rotor mechanism 110 and lower rotor mechanism 120 away from
From.
In the present embodiment, upper rotor mechanism 110 is coaxially disposed with lower rotor mechanism 120, can be enterprising in central axis 140
Row coaxially rotates backward, and after aircraft assembly, can be realized lifting, wing drop pitch-changing mechanism 130 is located at upper rotor mechanism 110
Between lower rotor mechanism 120, upper rotor mechanism 110 and expansion of the lower rotor mechanism 120 relative to central axis 140 can be changed
The distance between amplitude, and upper rotor mechanism 110 and lower rotor mechanism 120 can be changed, so as to adjust aircraft
Flight attitude, so that aircraft realizes longitudinal and transverse direction movement, while the ability for making aircraft resist wind-force is stronger, effectively
Influence of the wind-force to aircraft flight is reduced, can effectively ensure the flight stability of aircraft, also, upper rotor mechanism
110 can collapse with lower rotor mechanism 120 relative to central axis 140, can reduce the present apparatus to the occupancy in space, improve
The portability and ease for use of aircraft.
In the optinal plan of the present embodiment, upper rotor mechanism 110 includes propeller hub 111, blade pose adjustment portion 113 and rotation
Wing blade 112；Propeller hub 111 is rotatably arranged on central axis 140；Rotor blade 112 passes through blade pose adjustment portion 113 and propeller hub
111 connections.
In the optinal plan of the present embodiment, upper rotor mechanism 110 further includes rotor connecting rod 114；Propeller hub 111 passes through rotor
Connecting rod 114 is connect with wing drop pitch-changing mechanism 130.
In the optinal plan of the present embodiment, upper rotor mechanism 110 further includes brushless motor 115 and motor cabinet 116；Motor
Seat 116 is fixed on central axis 140；The stator of brushless motor 115 is connect with motor cabinet 116, the rotor of brushless motor 115
It is connect with propeller hub 111.
In the optinal plan of the present embodiment, blade pose adjustment portion 113 includes that limiting fixed seat 1131 and rotor are pressed from both sides
Seat 1132；Limiting fixed seat 1131 is arranged on propeller hub 111；One end of rotor holder 1132 is arranged by connection horizontal axis 1133
On limiting fixed seat 1131, rotor holder 1132 can be relative to the radial rotating of propeller hub 111, and along the diameter of propeller hub 111
To movement.
In the optinal plan of the present embodiment, connects and be arranged with retaining spring 1135 on horizontal axis 1133；Retaining spring 1135
One end connect with limiting fixed seat 1131, the other end of retaining spring 1135 is connect with rotor holder 1132, retaining spring
1135 for limiting the relative position of rotor holder 1132 Yu limiting fixed seat 1131.
In the present embodiment, rotor blade 112 is unfolded, and adjusts posture, and retaining spring 1135 is matched with sliding bearing 1134
Cooperation is used, and rotor blade 112 and the relative position of limiting fixed seat 1131 are locked, and guaranteeing will not be because of rotor in flight course
112 position of leaf is unstable and safety accident occurs.
In the optinal plan of the present embodiment, the foldable other end that rotor holder 1132 is set of rotor blade 112.
In the present embodiment, for the foldable setting of rotor blade 112 on rotor holder 1132, rotor blade 112 can
Fold, reduce the space hold of the present apparatus when not in use, convenient for storage and transport etc., improve the present apparatus portability and easily
The property used；Rotor blade 112 can lock after being unfolded relative to rotor holder 1132, and the position of rotor blade 112 is reliable, steady
It is fixed, the normal flight of aircraft is not influenced.
In the optinal plan of the present embodiment, propeller hub 111 is connect by bearing with central axis 140.
In the optinal plan of the present embodiment, rotor holder 1132 is socketed in connection horizontal axis by sliding bearing 1134
On 1133, structure is simple, the operation is stable.
In the optinal plan of the present embodiment, lower rotor mechanism 120 is identical as upper 110 structure of rotor mechanism, and the two is opposite
In on the centrally disposed axis 140 of radial symmetric of central axis 140.
Embodiment two:
In the optinal plan of the present embodiment, as shown in Fig. 8 to Figure 15, a kind of portable flight provided in this embodiment
Device, including fuselage 000, folding and unfolding take-off and landing device 200 and the coaxial double-rotary swing device 100 as described in embodiment one:
Wherein, coaxial double-rotary swing device 100 includes upper rotor mechanism 110, lower rotor mechanism 120, wing drop displacement machine
Structure 130 and central axis 140；
Upper rotor mechanism 110 is arranged on fuselage 000 by central axis 140 with lower rotor mechanism 120, upper rotor mechanism
110 can coaxially rotate backward with lower rotor mechanism 120 relative to central axis 140, so that this aircraft can be realized lifting, and on
Rotor mechanism 110 and lower rotor mechanism 120 can collapse and be unfolded, upper rotor mechanism 110, lower gyroplane relative to fuselage 000
Structure 120 can be inserted into the seam of fuselage 000 after collapsing, and improve the portability and ease for use of this aircraft；
On the centrally disposed axis 140 of wing drop pitch-changing mechanism 130, wing drop pitch-changing mechanism 130 is located at upper gyroplane
Between structure 110 and lower rotor mechanism 120, wing drop pitch-changing mechanism 130 is for changing upper rotor mechanism 110 and lower rotor mechanism
The 120 expansion amplitude relative to fuselage 000, and for changing between upper rotor mechanism 110 and lower rotor mechanism 120 away from
From enabling this aircraft to realize in three-dimensional space longitudinally, laterally and vertically and horizontally compound movement, further, it is possible to adjust this
The flight attitude of aircraft is effectively reduced influence of the wind-force to flight, so that the ability that this aircraft resists wind-force is stronger, flies
Row is more steady；
Folding and unfolding take-off and landing device 200 includes telescoping mechanism and buffering foot mechanism 230；The centrally disposed axis in one end of telescoping mechanism
On 140, the other end of telescoping mechanism is arranged in buffering foot mechanism 230, and telescoping mechanism can be unfolded and receive relative to fuselage 000
Hold together.
In the present embodiment, upper rotor mechanism 110 and lower 120 coaxial reverse of rotor mechanism, can eliminate from torque, make
It is more steady to obtain the work of coaxial double-rotary swing device 100, has ensured the flight stability of this aircraft.
In the optinal plan of the present embodiment, upper rotor mechanism 110 includes propeller hub 111, blade pose adjustment portion 113, rotation
Wing blade 112 and rotor connecting rod 114；Propeller hub 111 is rotatably arranged on central axis 140；Rotor blade 112 passes through blade posture tune
Whole 113 connect with propeller hub 111；Propeller hub 111 is connect by rotor connecting rod 114 with wing drop pitch-changing mechanism 130.
Further, the quantity in rotor blade 112 and blade pose adjustment portion 113 is multiple, and the quantity phase of the two
Together, multiple blade pose adjustments portion 113 is uniformly arranged along the circumferential direction of propeller hub 111.
Preferably, propeller hub 111 is connect by bearing with central axis 140.
In the optinal plan of the present embodiment, upper rotor mechanism 110 further includes brushless motor 115 and motor cabinet 116；Motor
Seat 116 is fixed on central axis 140；The stator of brushless motor 115 is connect with motor cabinet 116, the rotor of brushless motor 115
It is connect with propeller hub 111.
In the optinal plan of the present embodiment, blade pose adjustment portion 113 includes that limiting fixed seat 1131 and rotor are pressed from both sides
Seat 1132；Limiting fixed seat 1131 is arranged on propeller hub 111；One end of rotor holder 1132 is arranged by connection horizontal axis 1133
On limiting fixed seat 1131, rotor holder 1132 can be relative to the radial rotating of propeller hub 111, and along the diameter of propeller hub 111
To movement；The foldable other end that rotor holder 1132 is set of rotor blade 112.
In the present embodiment, for the foldable setting of rotor blade 112 on rotor holder 1132, rotor blade 112 can
It is folded relative to fuselage 000, rotor blade 112 is inserted into the seam of fuselage 000 after folding, and reduces this aircraft when not in use
Space hold, convenient for storage and transport etc., improve the portability and ease for use of this aircraft.
Further, rotor holder 1132 is socketed on connection horizontal axis 1133 by sliding bearing 1134, connection structure
Simply, the operation is stable.
Also, retaining spring 1135, one end of retaining spring 1135 and limiting fixed seat are arranged on connection horizontal axis 1133
1131 connections, the other end of retaining spring 1135 are connect with rotor holder 1132, and retaining spring 1135 is for limiting rotor
The relative position of holder 1132 and limiting fixed seat 1131.
Still further, rotor holder 1132 includes rotating base 11322 and limiting slot 11321；Rotating base 11322
One end be socketed on limiting fixed seat 1131；The other end of rotating base 11322 is arranged in limiting slot 11321.Rotating base
11322 are socketed on sliding bearing 1134, and rotating base 11322 can be slided and be rotated relative to limiting fixed seat 1131.
Also, rotor holder 1132 further includes position limit arm 11323；Rotating base 11322 is arranged in position limit arm 11323
One end, position limit arm 11323 is for limiting range of the rotating base 11322 on limiting fixed seat 1131.
Preferably, rotor blade 112 passes through the foldable other end that rotor holder 1132 is arranged in of shaft；Also, it revolves
The quantity of wing blade 112 is preferably 3, i.e., the sum of the blade of this aircraft is 6.
In the present embodiment, rotor blade 112 is unfolded, and adjusts posture, and retaining spring 1135 is matched with sliding bearing 1134
Cooperation is used, and rotor blade 112 and the relative position of limiting fixed seat 1131 are locked, and guaranteeing will not be because of rotor in flight course
112 position of leaf is unstable and safety accident occurs.
It should be noted that lower rotor mechanism 120 is identical as upper 110 structure of rotor mechanism, the diameter relative to central axis 140
To being symmetricly set on central axis 140.
In the optinal plan of the present embodiment, wing drop pitch-changing mechanism 130 includes upper wing drop portion 131, lower automatic
Rake 132 and synchronising (connecting) rod 133；Upper wing drop portion 131 is movably arranged on central axis 140 with lower wing drop portion 132
On, upper wing drop portion 131 can be tilted with lower wing drop portion 132 relative to the axis of central axis 140, and in
The axis direction of mandrel 140 is mobile；Upper wing drop portion 131 is connect with lower wing drop portion 132 by synchronising (connecting) rod 133, on
Wing drop portion 131 and lower wing drop portion 132 can the axis simultaneously relative to central axis 140 tilted, and along center
The axis direction of axis 140 is mobile；Upper rotor mechanism 110 is connect with upper wing drop portion 131, lower rotor mechanism 120 with it is lower automatic
Rake 132 connects.
In the optinal plan of the present embodiment, wing drop pitch-changing mechanism 130 further includes anti-torsion link assembly 134；Down certainly
Dynamic rake 132 is connect by anti-torsion link assembly 134 with central axis 140.
Further, anti-torsion link assembly 134 includes the sequentially connected first anti-torsion connecting rod and the second anti-torsion connecting rod；First
Anti- torsion connecting rod and the second anti-torsion connecting rod are at angle；First anti-torsion connecting rod is connect with the second anti-torsion connecting rod by pin shaft, the axis of pin shaft
Axis of the line perpendicular to central axis 140.
In the optinal plan of the present embodiment, wing drop pitch-changing mechanism 130 further includes leaning device steering engine 135 and inclination
Mechanism steering engine bracket 138；Leaning device steering engine bracket 138 is fixed on central axis 140, and leaning device steering engine 135 is arranged
On leaning device steering engine bracket 138；Upper wing drop portion 131 is passed by sequentially connected steering engine kinematic link 136 and steering engine
Shake arm 137 to connect with leaning device steering engine 135；Upper wing drop portion 131 is located at dumper with lower wing drop portion 132
The two sides up and down of structure steering engine bracket 138.
In the present embodiment, leaning device steering engine 135 is driven by steering engine kinematic link 136 and steering engine driving rocker 137
Axis run-off the straight of the upper wing drop portion 131 relative to central axis 140, and moved along the axis direction of central axis 140, it is real
Existing 100 feathering of coaxial double-rotary swing device, that is, realize feathering between upper rotor mechanism 110 and lower rotor mechanism 120.
Preferably, leaning device steering engine 135 is arranged on leaning device steering engine bracket 138 by bolt.
Wherein, anti-one end for turning round link assembly 134 is connect with lower wing drop portion 132, anti-to turn round the another of link assembly 134
End is connect with leaning device steering engine bracket 138.
In the optinal plan of the present embodiment, upper wing drop portion 131 includes rake inner ring 1311 and rake outer ring
1312；Rake inner ring 1311 is set on central axis 140 by oscillating bearing, and rake inner ring 1311 can be relative to central axis
140 axis is tilted to any direction；Rake outer ring 1312 is set in rake inner ring 1311；Rake inner ring
1311 are connect by steering engine kinematic link 136 with steering engine driving rocker 137；Rake outer ring 1312 and upper rotor mechanism 110 connect
It connects.
In the present embodiment, oscillating bearing can be moved up and down along central axis 140, thus upper wing drop portion 131 and under
Wing drop portion 132 can be moved up and down along central axis 140.
Preferably, rake outer ring 1312 is set in rake inner ring 1311 by ball bearing.
Wherein, rake inner ring 1311 is connect by steering engine kinematic link 136 with steering engine driving rocker 137, so with incline
Oblique mechanism steering engine 135 connects, that is to say, that rake inner ring 1311 is connect with leaning device steering engine 135.
Further, rake connecting rod 139 is provided in rake inner ring 1311；Rake inner ring 1311 passes through rake
Connecting rod 139 is connect with steering engine kinematic link 136.
It should be noted that lower wing drop portion 132 is identical as upper 131 structure of wing drop portion；Upper wing drop portion 131
Rake inner ring 1311 and the rake inner ring 1311 in lower wing drop portion 132 connect by synchronising (connecting) rod 133；On incline automatically
The rake outer ring 1312 of inclined portion 131 is connect by rotor connecting rod 114 with the propeller hub 111 of upper rotor mechanism 110, lower wing drop
The rake outer ring 1312 in portion 132 is connect by rotor connecting rod 114 with the propeller hub 111 of lower rotor mechanism 120.
Also, anti-one end for turning round link assembly 134 is connect with the rake inner ring 1311 in lower wing drop portion 132, anti-torsion
The other end of link assembly 134 is connect with leaning device steering engine bracket 138.
Further, upper wing drop portion 131 further includes bulb mouth.
In the optinal plan of the present embodiment, telescoping mechanism includes sequentially connected second connecting rod 222, third connecting rod 223
And the 5th connecting rod 225；Second connecting rod 222 is connected on central axis 140, second connecting rod 222 can relative to fuselage 000 be unfolded and
It collapses；Buffering foot mechanism 230 is connected on the 5th connecting rod 225；Telescoping mechanism further include first connecting rod 221, fourth link 224 and
Six-bar linkage 226；One end of first connecting rod 221 is connected on second connecting rod 222, and the other end of first connecting rod 221 is connected to
On double leval jib 224, one end of fourth link 224 is connected on third connecting rod 223, and the other end of fourth link 224 is connected to
One end of six-bar linkage 226, the other end of six-bar linkage 226 are connected on the 5th connecting rod 225.
In the present embodiment, six hinged connecting rods constitute two parallelogram stretching structures；Also, it is interconnected
Connecting rod is realized by the structure type of pin shaft and shaft hole matching and is connected.
In the optinal plan of the present embodiment, buffering foot mechanism 230 includes buffering foot prop；Buffering foot prop is rotatably connected on the
On five connecting rods 225.
In the present embodiment, when this aircraft lands, buffering foot prop plays the role of bumper and absorbing shock.
Further, buffering foot prop is connect with the 5th connecting rod 225 by pin shaft；Torque spring, torsion are arranged on pin shaft
One end of spring is connect with buffering foot prop, and the other end of torque spring is connect with the 5th connecting rod 225.
In the present embodiment, buffering foot prop can be rotated relative to the 5th connecting rod 225, and be resetted after rotation.
Still further, folding and unfolding take-off and landing device 200 further includes Power Component, Power Component is used to provide it to telescoping mechanism
The power for being unfolded relative to fuselage 000 and collapsing.
Also, Power Component include telescoping mechanism steering engine 212, telescoping mechanism steering engine fixing seat 211, sliding bearing 214 and
Sliding connector 213；Telescoping mechanism steering engine fixing seat 211 is fixed on central axis 140；The one of telescoping mechanism steering engine 212
End is arranged in telescoping mechanism steering engine fixing seat 211, and telescoping mechanism steering engine 212 can provide the axis side for being parallel to central axis 140
To power；Sliding bearing 214 is set on central axis 140, and sliding bearing 214 is another with telescoping mechanism steering engine 212 simultaneously
End connection, sliding bearing 214 can be under the drives of telescoping mechanism steering engine 212 along the axial direction up and down motion of central axis 140；Sliding connects
One end of fitting 213 is movably arranged on sliding bearing 214, and the other end of sliding connector 213 is connected on telescoping mechanism, sliding
Follower link 213 is moved with sliding bearing 214 to drive telescoping mechanism to be unfolded and collapse relative to fuselage 000.
Wherein, one end of second connecting rod 222 and telescoping mechanism steering engine fixing seat 211 are rotatablely connected, second connecting rod 222 it is another
One end and third connecting rod 223 and first connecting rod 221 are rotatablely connected.
Also, one end of sliding connector 213 and sliding bearing 214 are rotatablely connected, the other end of sliding connector 213 with
First connecting rod 221 is rotatablely connected.
In the present embodiment, sliding bearing 214 is under the drive of telescoping mechanism steering engine 212 in the axial direction of central axis 140
Lower movement, then drive telescoping mechanism to be unfolded and collapse relative to fuselage 000 by sliding connector 213.
After this aircraft takeoff, the telescoping mechanism steering engine 212 of Power Component is moved down, so that sliding connector 213
The slide downward on central axis 140, so that first connecting rod 221 is moved down with sliding connector 213, so that first
Connecting rod 221 rotates, and the other end of first connecting rod 221 moves up, i.e., the other end of first connecting rod 221 tilts, first connecting rod
221 pull the one of one end of second connecting rod 222 and the connection of third connecting rod 223 and fourth link 224 and the connection of the 5th connecting rod 225
End moves up, and the distance that fourth link 224 moves up connects less than the distance that the 5th connecting rod 225 moves up, the 6th
The other end of bar 226 tilts, and in the horizontal direction upwards, first connecting rod 221, second connecting rod 222, third connecting rod the 223, the 4th
Connecting rod 224, the 5th connecting rod 225 are mobile to fuselage 000, and final folding and unfolding take-off and landing device 200 is folded in the seam of fuselage 000,
During aircraft is taken photo by plane, the visual field of taking photo by plane will not be blocked.When the landing of this aircraft, the telescoping mechanism steering engine of Power Component
212 move up, so that the upward sliding on central axis 140 of sliding connector 213, so that first connecting rod 221 and sliding
Connector 213 moves up, so that first connecting rod 221 rotates, and the other end of first connecting rod 221 is moved down, i.e., and the
The other end of one connecting rod 221 is sagging, one end that first connecting rod 221 pulls second connecting rod 222 and third connecting rod 223 to connect and the
One end of double leval jib 224 and the connection of the 5th connecting rod 225 moves down, and the distance that moves down of fourth link 224 is less than the
The distance that five connecting rods 225 move down, six-bar linkage 226 and buffer foot mechanism 230 one end it is sagging, and in the horizontal direction to
On, first connecting rod 221, second connecting rod 222, third connecting rod 223, fourth link 224, the 5th connecting rod 225 are towards far from fuselage 000
Direction it is mobile, buffering foot mechanism 230 becomes the minimum point of aircraft, in aircraft landing with ground face contact, bumper and absorbing shock.
It should be noted that being provided with mission payload, flight control system, smart battery system on fuselage 000；Task carries
Lotus is mounted on the lower end of fuselage 000, and according to the needs of task, mission payload can be changed the outfit as photoelectric nacelle, first-aid medicine packet, be answered
The load such as anxious communication equipment；Flight control system is used to control brushless motor 115, the wing drop of coaxial double-rotary swing device 100
The leaning device steering engine 135 of pitch-changing mechanism 130 and the telescoping mechanism steering engine 212 of folding and unfolding take-off and landing device 200 work；Intelligent battery
The two sides up and down of coaxial double-rotary swing device 100 are set to symmetry system having symmetry, and are connect by central axis 140 with motor cabinet 116, are used
In for the brushless motor 115 of coaxial double-rotary swing device 100, the leaning device steering engine 135 of wing drop pitch-changing mechanism 130 and receive
The telescoping mechanism steering engine 212 for putting take-off and landing device 200 is powered, and smart battery system includes upper battery pack, lower battery pack and cell tube
Family.In addition, this aircraft further includes mission payload installing mechanism, mission payload installing mechanism includes load portion, and load portion is used for
Gondola is mounted, is convenient for quick despatch, also, SOS alarm is installed on mission payload installing mechanism, is sent out when beyond specified counterweight
Sound and optical alert out.
In conclusion the course of work of this portable aircraft is as follows:
Aircraft rises or falls, and folding and unfolding take-off and landing device 200 lands, and fuselage 000 is perpendicular to the ground, coaxial double-rotary wing dress
Two groups of brushless motors 115 for setting 100 drive two groups of coaxial reverse rotations of rotor blade 112, and pushing air to generate thrust flies this
Row device takes off vertically；Change thrust size by adjusting the revolving speed of two groups of brushless motors 115, control aircraft rises or falls
Flight；
Aircraft changes course, and controls two groups of rotor blades 112 by two groups of brushless motors 115 and carries out differential speed rotation,
Yawing, the heading of change of flight device are provided using the reaction torque difference of two groups of rotor blades 112 for this aircraft；
The longitudinal direction of aircraft or/and horizontal flight adjust three steering engine kinematic links by three leaning device steering engines 135
136 relative position, such as a steering engine kinematic link 136 moves downward, other two steering engine kinematic link 136 is transported upwards
It is dynamic, so that upper wing drop portion 131, lower wing drop portion 132 synchronize inclination in the same direction, remain parastate, rotor connecting rod
114 drive upper rotor mechanism 110, lower rotor mechanism 120 therewith, so that the rotor of upper rotor mechanism 110, lower rotor mechanism 120
Blade 112 changes different angle in each swing circle, realizes the longitudinal direction or/and transverse shifting of this aircraft.
Finally, it should be noted that the above various embodiments is only to illustrate the technical solution of the utility model, rather than it is limited
System；Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should
Understand: it is still possible to modify the technical solutions described in the foregoing embodiments, or to some or all of
Technical characteristic is equivalently replaced；And these are modified or replaceed, it does not separate the essence of the corresponding technical solution, and this is practical new
The range of each embodiment technical solution of type.
Claims (10)
1. a kind of coaxial double-rotary swing device, which is characterized in that including upper rotor mechanism (110), lower rotor mechanism (120), automatic
Tilt pitch-changing mechanism (130) and central axis (140)；
The upper rotor mechanism (110) and the lower rotor mechanism (120) are arranged on the central axis (140), it is described on
Rotor mechanism (110) and the lower rotor mechanism (120) can rotate backward relative to the central axis (140) is coaxial, and described
Upper rotor mechanism (110) and the lower rotor mechanism (120) can collapse and be unfolded relative to the central axis (140)；
The wing drop pitch-changing mechanism (130) is arranged on the central axis (140), the wing drop pitch-changing mechanism
(130) between the upper rotor mechanism (110) and the lower rotor mechanism (120), the wing drop pitch-changing mechanism
(130) for changing the upper rotor mechanism (110) and the lower rotor mechanism (120) relative to the central axis (140)
Expansion amplitude, and for changing the distance between the upper rotor mechanism (110) and the lower rotor mechanism (120).
2. coaxial double-rotary swing device according to claim 1, which is characterized in that the upper rotor mechanism (110) includes paddle
Hub (111), blade pose adjustment portion (113) and rotor blade (112)；
The propeller hub (111) is rotatably arranged on the central axis (140)；
The rotor blade (112) is connect by blade pose adjustment portion (113) with the propeller hub (111).
3. coaxial double-rotary swing device according to claim 2, which is characterized in that the upper rotor mechanism (110) further includes
Rotor connecting rod (114)；
The propeller hub (111) is connect by the rotor connecting rod (114) with the wing drop pitch-changing mechanism (130).
4. coaxial double-rotary swing device according to claim 2, which is characterized in that the upper rotor mechanism (110) further includes
Brushless motor (115) and motor cabinet (116)；
The motor cabinet (116) is fixed on the central axis (140)；
The stator of the brushless motor (115) is connect with the motor cabinet (116), the rotor of the brushless motor (115) and institute
State propeller hub (111) connection.
5. coaxial double-rotary swing device according to claim 2, which is characterized in that blade pose adjustment portion (113) packet
Include limiting fixed seat (1131) and rotor holder (1132)；
The limiting fixed seat (1131) is arranged on the propeller hub (111)；
One end of the rotor holder (1132) is arranged on the limiting fixed seat (1131) by connection horizontal axis (1133),
The rotor holder (1132) can be relative to the radial rotating of the propeller hub (111), and the radial direction along the propeller hub (111)
It is mobile.
6. coaxial double-rotary swing device according to claim 5, which is characterized in that be arranged on the connection horizontal axis (1133)
Retaining spring (1135)；
One end of the retaining spring (1135) is connect with the limiting fixed seat (1131), the retaining spring (1135) it is another
One end is connect with the rotor holder (1132), and the retaining spring (1135) is for limiting the rotor holder (1132)
With the relative position of the limiting fixed seat (1131).
7. coaxial double-rotary swing device according to claim 5, which is characterized in that the rotor blade (112) is foldable to be set
Set the other end in the rotor holder (1132).
8. coaxial double-rotary swing device according to claim 2, which is characterized in that the propeller hub (111) passes through bearing and institute
State central axis (140) connection.
9. coaxial double-rotary swing device according to claim 5, which is characterized in that the rotor holder (1132) passes through cunning
Dynamic bearing (1134) is socketed on the connection horizontal axis (1133).
10. coaxial double-rotary swing device according to any one of claims 1 to 9, which is characterized in that the lower rotor mechanism
(120) identical as upper rotor mechanism (110) structure, the two exists relative to the radial symmetric setting of the central axis (140)
On the central axis (140).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822213524.5U CN209667364U (en) | 2018-12-26 | 2018-12-26 | Coaxial double-rotary swing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822213524.5U CN209667364U (en) | 2018-12-26 | 2018-12-26 | Coaxial double-rotary swing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209667364U true CN209667364U (en) | 2019-11-22 |
Family
ID=68563827
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822213524.5U Expired - Fee Related CN209667364U (en) | 2018-12-26 | 2018-12-26 | Coaxial double-rotary swing device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209667364U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117419885A (en) * | 2023-12-19 | 2024-01-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Scissor type tail rotor wind tunnel test bed |
| WO2024093476A1 (en) * | 2022-11-01 | 2024-05-10 | 苏州览众科技有限公司 | Coaxial dual-rotor unmanned aerial vehicle |
-
2018
- 2018-12-26 CN CN201822213524.5U patent/CN209667364U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2024093476A1 (en) * | 2022-11-01 | 2024-05-10 | 苏州览众科技有限公司 | Coaxial dual-rotor unmanned aerial vehicle |
| CN117419885A (en) * | 2023-12-19 | 2024-01-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Scissor type tail rotor wind tunnel test bed |
| CN117419885B (en) * | 2023-12-19 | 2024-03-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Scissor type tail rotor wind tunnel test bed |
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