CN109131868A - Inclining rotary mechanism and aircraft for aircraft - Google Patents
Inclining rotary mechanism and aircraft for aircraft Download PDFInfo
- Publication number
- CN109131868A CN109131868A CN201811075476.6A CN201811075476A CN109131868A CN 109131868 A CN109131868 A CN 109131868A CN 201811075476 A CN201811075476 A CN 201811075476A CN 109131868 A CN109131868 A CN 109131868A
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- Prior art keywords
- aircraft
- connecting rod
- rotary mechanism
- inclining rotary
- bearing seat
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- 230000007246 mechanism Effects 0.000 title claims abstract description 59
- 239000000463 material Substances 0.000 claims description 8
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 3
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 3
- 239000004917 carbon fiber Substances 0.000 claims description 3
- 239000000839 emulsion Substances 0.000 claims description 3
- 239000003365 glass fiber Substances 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 claims description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 3
- 238000000465 moulding Methods 0.000 claims description 3
- 239000000741 silica gel Substances 0.000 claims description 3
- 229910002027 silica gel Inorganic materials 0.000 claims description 3
- 238000005516 engineering process Methods 0.000 abstract description 4
- 238000010586 diagram Methods 0.000 description 7
- 230000008901 benefit Effects 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 230000004048 modification Effects 0.000 description 5
- 238000012986 modification Methods 0.000 description 5
- 239000002131 composite material Substances 0.000 description 3
- 238000005183 dynamical system Methods 0.000 description 3
- 238000007689 inspection Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 206010039203 Road traffic accident Diseases 0.000 description 1
- 238000010009 beating Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000002386 leaching Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000032258 transport Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Tires In General (AREA)
Abstract
The invention discloses a kind of inclining rotary mechanisms and aircraft for aircraft, belong to vehicle technology field.It includes first bearing seat 22a, second bearing seat 22b, first bearing 23a, second bearing 23b, axle sleeve 28, first connecting rod 24, second connecting rod 25, third connecting rod 26, steering engine 21 and anchor ear 27 that this, which is used for inclining rotary mechanism described in the inclining rotary mechanism of aircraft,.The aircraft includes the inclining rotary mechanism for being used for aircraft.This is in the inclining rotary mechanism of aircraft, first bearing seat 22a, second bearing seat 22b, first bearing 23a, second bearing 23b, axle sleeve 28, first connecting rod 24, second connecting rod 25, third connecting rod 26, steering engine 21 and anchor ear 27 constitute a crank and rocker mechanism, it can apply the geometrical relationship of the crank and rocker mechanism, the accurate adjustment for carrying out tilt angle to tiliting axis according to the flying condition of aircraft, so that the angle of plane locating for propeller and horizontal plane is precisely controlled.
Description
Technical field
The present invention relates to vehicle technology fields, more particularly to a kind of inclining rotary mechanism and aircraft for aircraft.
Background technique
With the fast development of science and technology, in recent years, unmanned plane for various industries application development also increasingly
Extensively, at this stage, the application of unmanned plane has been directed to take photo by plane, agricultural plant protection, geological prospecting, electric inspection process, oil and gas pipeline patrol
It looks into, expressway traffic accident management, forest fire protection inspection, pollute environment prospecting, anti-terrorism stability maintenance police law execution, emergency management and rescue and rescue
The fields applications such as shield, rescue and relief work, coastline inspection.
Above-mentioned industrial application unmanned plane is mostly multi-rotor unmanned aerial vehicle or fixed-wing unmanned plane, both offline mode respectively have it
Many advantages, such as advantage and disadvantage of itself, multi-rotor unmanned aerial vehicle can carry out spot hover, not rely on runway VTOL, but its
Cruising ability is poor, and voyage is shorter.And fixed wing aircraft although voyage with higher, but it can not make multi-rotor unmanned aerial vehicle
Hovering, VTOL working method.For the above, in recent years, all kinds of composite wings are constantly released in unmanned plane market
Unmanned plane.This unmanned plane can either be satisfied with fixed chord endurance flight, and the ability with more rotor working methods.But
Since composite wing unmanned plane not only needs the rotor power system in 3-4 group vertical direction, it is also necessary to independent 1-2 group horizontal direction
On the flat Force system that flies, multiple groups dynamical system makes aircraft empty weight larger, load capacity caused to reduce.Secondly compound
Rotor aircraft does not have the operating condition ability that emergency stop whips, changes back to multiaxis ocean weather station observation mode from fixed-wing cruise mode at it
In the process, unmanned plane has flown out the sizable a distance of observation point, is not suitable for many industries such as police, military.
Summary of the invention
In view of this, flight can be controlled the present invention provides a kind of inclining rotary mechanism and aircraft for aircraft
The rotor of device carries out special angle rotation, so that suitable cruising ability is obtained under the special angle, thus more suitable for reality
With.
In order to reach above-mentioned first purpose, provided by the present invention for aircraft inclining rotary mechanism technical solution such as
Under:
Inclining rotary mechanism provided by the present invention for aircraft include first bearing seat (22a), second bearing seat (22b),
First bearing (23a), second bearing (23b), axle sleeve (28), first connecting rod (24), second connecting rod (25), third connecting rod (26),
Steering engine (21) and anchor ear (27),
One end of the axle sleeve (28) is connected to the first bearing seat (22a) by the first bearing (23a), described
The other end of axle sleeve (28) is connected to the second bearing seat (22b) by the second bearing (23b),
One end of the first connecting rod (24) is fixedly connected on the output shaft (29) of the steering engine (21), the first connecting rod
(24) the other end is articulated with one end of the second connecting rod (25), and the other end of the second connecting rod (25) is articulated with described
The other end of one end of three-link (26), the third connecting rod (26) is fixedly connected on the anchor ear (27), the anchor ear (27)
Tiliting axis (3) fixation with the axle sleeve (28) tight fit, the aircraft is arranged in the axle sleeve (28).
It following technical measures also can be used further realizes provided by the present invention for the inclining rotary mechanism of aircraft.
Preferably, the inclining rotary mechanism for aircraft further includes intermediate medium part, the intermediate medium part setting
Between the anchor ear (27) and the axle sleeve (28) and/or the hinged place of the connecting rod, the intermediate medium part are friction member
Or compressive deformation part.
Preferably, the material of the intermediate medium part is selected from rubber, silica gel or natural emulsion.
Preferably, the first connecting rod (24), second connecting rod (25), third connecting rod (26) composition crank and rocker mechanism,
So that the steering engine (21) is able to drive described when the rotation angle of the output shaft (29) of the steering engine (21) changes
Crank and rocker mechanism controls the rotation angle of the tiliting axis (3) of the aircraft according to the geometrical relationship of the crank and rocker mechanism
Degree.
Preferably, the inclining rotary mechanism for aircraft further includes connector (30),
The first bearing seat (22a) and the second bearing seat (22b) are symmetrical in chirality, and the connector (30) is fixed
It is connected between the first bearing seat (22a) and second bearing seat (22b)；
The first bearing seat (22a) and second bearing seat (22b) are connected to the flight by the connector (30)
The fuselage of device.
Preferably, the radial center of circle of the output shaft (29) of the steering engine (21), the tiliting axis (3) the radial center of circle,
The radial center of circle, the second connecting rod (25) and the third of articulated shaft between the first connecting rod (24) and second connecting rod (25) connect
4 points of the radial center of circle composition parallelogram of articulated shaft between bar (26).
In order to reach above-mentioned second purpose, the technical solution of aircraft provided by the invention is as follows:
Aircraft provided by the invention includes the inclining rotary mechanism provided by the present invention for aircraft.
Aircraft provided by the invention also can be used following technical measures and further realize.
Preferably, the mass percentage for being used to manufacture each component in the material of the aircraft includes: that carbon fiber is pre-
Leaching material: >=35%, glass fibre prepreg: >=30%, Polymethacrylimide: >=20%.
Preferably, the aircraft is an integral molding structure.
Preferably, the aircraft includes the first inclining rotary mechanism and the second inclining rotary mechanism, the tiliting axis includes first
Tiliting axis and the second tiliting axis,
First tiliting axis is connected to the fuselage head of the aircraft by first inclining rotary mechanism, and described first
The both ends of tiliting axis are connected separately with the propeller of the aircraft；
Second tiliting axis is connected to the afterbody of the aircraft by second inclining rotary mechanism, and described second
The both ends of tiliting axis are connected separately with the propeller of the aircraft.
Provided by the present invention in the inclining rotary mechanism of aircraft, first bearing seat 22a, second bearing seat 22b, first axle
23a, second bearing 23b, axle sleeve 28, first connecting rod 24, second connecting rod 25, third connecting rod 26, steering engine 21 and anchor ear 27 is held to constitute
One crank and rocker mechanism can apply the geometrical relationship of the crank and rocker mechanism, be inclined according to flying condition to tiliting axis
The accurate adjustment of gyration, so that the angle of plane locating for propeller and horizontal plane is precisely controlled, it therefore, can
More accurate stress is obtained, during continuation of the journey, the tilt angle that aircraft can use propeller obtains suitable effect
Therefore power can be improved the cruising ability of the aircraft.
Detailed description of the invention
By reading the following detailed description of the preferred embodiment, various other advantages and benefits are common for this field
Technical staff will become clear.The drawings are only for the purpose of illustrating a preferred embodiment, and is not considered as to the present invention
Limitation.And throughout the drawings, the same reference numbers will be used to refer to the same parts.In the accompanying drawings:
Fig. 1 is the perspective view of the inclining rotary mechanism provided in an embodiment of the present invention for aircraft；
Fig. 2 is the schematic diagram in the direction A in Fig. 1；
The schematic diagram of Fig. 3 inclining rotary mechanism provided in an embodiment of the present invention for aircraft and tiliting axis fit applications；
Fig. 4 is the angle of plane and horizontal plane of the aircraft provided in an embodiment of the present invention locating for propeller when being 0 °
Schematic diagram；
Fig. 5 is that the angle of plane and horizontal plane of the aircraft provided in an embodiment of the present invention locating for propeller is to lean forward
Schematic diagram at 45 °；
Fig. 6 is the schematic diagram in the direction B in Fig. 5；
Fig. 7 is that the angle of plane and horizontal plane of the aircraft provided in an embodiment of the present invention locating for propeller is hypsokinesis
Schematic diagram at 35 °；
Fig. 8 is the schematic diagram in the direction C in Fig. 7.
Specific embodiment
The present invention in order to solve the problems existing in the prior art, provide it is a kind of for the inclining rotary mechanism of aircraft, control device,
Computer readable storage medium and terminal device, the rotor that can control aircraft carries out special angle rotation, thus at this
Suitable cruising ability is obtained under special angle, thus more suitable for practical.
It is of the invention to reach the technical means and efficacy that predetermined goal of the invention is taken further to illustrate, below in conjunction with
Attached drawing and preferred embodiment, to it is proposed according to the present invention for the inclining rotary mechanism of aircraft, control device, computer-readable deposit
Storage media and terminal device, specific embodiment, structure, feature and its effect, detailed description is as follows.In the following description,
What different " embodiment " or " embodiment " referred to is not necessarily the same embodiment.In addition, feature in one or more embodiments,
Structure or feature can be combined by any suitable form.
The terms "and/or", only a kind of incidence relation for describing affiliated partner, indicates that there may be three kinds of passes
System, it is specific to understand for example, A and/or B are as follows: it can simultaneously include A and B, can be with individualism A, it can also be with individualism
B can have above-mentioned three kinds of any case.
Embodiment one
Referring to attached drawing 1~3, the inclining rotary mechanism for aircraft that one embodiment of the embodiment of the present invention provides includes first axle
Hold a 22a, second bearing seat 22b, first bearing 23a, second bearing 23b, axle sleeve 28, first connecting rod 24, second connecting rod 25,
Three-link 26, steering engine 21 and anchor ear 27.One end of axle sleeve 28 is connected to first bearing seat 22a, axle sleeve 28 by first bearing 23a
The other end second bearing seat 22b is connected to by second bearing 23b.One end of first connecting rod 24 is fixedly connected on steering engine 21
Output shaft 29, the other end of first connecting rod 24 are articulated with one end of second connecting rod 25, and the other end of second connecting rod 25 is articulated with
One end of three-link 26, the other end of third connecting rod 26 are fixedly connected on anchor ear 27, anchor ear 27 and 28 tight fit of axle sleeve, aircraft
Tiliting axis 3 fixation be arranged in axle sleeve 28.
It wherein, further include intermediate medium part for the inclining rotary mechanism of aircraft.Intermediate medium part is set to anchor ear 27 and axis
Between the set 28 and/or hinged place of connecting rod, intermediate medium part are friction member or compressive deformation part.In this case, pass through
The intermediate medium part, enables to the tight fit between anchor ear 27 and axle sleeve 28 relatively reliable.In the present embodiment, intermediate medium part
Material be selected from rubber, silica gel or natural emulsion.
Wherein, first connecting rod 24, second connecting rod 25, third connecting rod 26 constitute crank and rocker mechanism, so that in steering engine 21
The rotation angle of output shaft 29 when changing, steering engine 21 is able to drive crank and rocker mechanism according to the several of crank and rocker mechanism
The rotation angle of the tiliting axis 3 of what relationship control aircraft.
It wherein, further include connector 30 for the inclining rotary mechanism of aircraft.First bearing seat 22a and second bearing seat 22b
Symmetrical in chirality, connector 30 is fixedly connected between first bearing seat 22a and second bearing seat 22b；First bearing seat 22a and
Second bearing seat 22b is connected to the fuselage of aircraft by connector 30.In this case, inclining rotary mechanism itself constitutes one
A integrated morphology is easily installed, dismantles, packs, transports.
Wherein, the radial center of circle of the output shaft 29 of steering engine 21, the radial center of circle of tiliting axis 3, first connecting rod 24 and second connect
4, the radial center of circle structure of articulated shaft between the radial center of circle of articulated shaft between bar 25, second connecting rod 25 and third connecting rod 26
At parallelogram.In this case, tiliting axis to be made rotates an angle [alpha], it is only necessary to by the output shaft 29 for making steering engine 21
Angle [alpha] is rotated, no longer needs to convert by the geometrical relationship for calculating the crank and rocker mechanism, therefore, can be avoided fortune
Error is calculated, operation time is saved.
Embodiment two
Referring to attached drawing 4~8, aircraft provided by Embodiment 2 of the present invention includes the offer of the embodiment of the present invention one for flying
The inclining rotary mechanism of row device.
Wherein, the mass percentage of each component includes: carbon fiber prepreg in material for manufacturing aircraft: >=
35%, glass fibre prepreg: >=30%, Polymethacrylimide: >=20%.The material has specific strength height, specific stiffness
Also therefore high characteristic can be improved the service life of the aircraft.
Wherein, aircraft is an integral molding structure.It can be avoided at jointing existing for stress concentrate, therefore,
It can be improved the service life of aircraft.
Wherein, aircraft includes the first inclining rotary mechanism and the second inclining rotary mechanism, and tiliting axis includes the first tiliting axis and second
Tiliting axis.First tiliting axis is connected to the fuselage head of aircraft, the both ends difference of the first tiliting axis by the first inclining rotary mechanism
It is connected with the propeller of aircraft；Second tiliting axis is connected to the afterbody of aircraft by the second inclining rotary mechanism, and second inclines
The both ends of shaft are connected separately with the propeller of aircraft.In this case, which has 4 propellers, stress altogether
It is more balanced.
When in running order second embodiment of the present invention provides aircraft, the folder of plane locating for propeller and horizontal plane
Angle mainly includes turning forward 45 ° and to tilt backwards 35 ° of two kinds of operation modes, the folder of plane and horizontal plane locating for the propeller
Angle mainly includes when turning forward 45 °, and aircraft can put down winged mode flight, since the wing of aircraft at this time generates lift, so
Flight efficiency under this mode is higher, so as to realize the purpose of long period cruise；The plane locating for the propeller with
The angle of horizontal plane mainly includes when tilting backwards 35 °, and tiliting axis support arm position can enable aircraft when switching mode
Enough avoid the slip-stream of paddle disk from beating makes aircraft have nose-down pitching moment on wing, therefore, is able to carry out and observes for a long time.The present embodiment
In, any one dynamical system of the dynamical system of aircraft in electronic, oily dynamic or oil electricity three kinds of modes of mixing.
In the present embodiment, aircraft further includes double nacelle or five smooth gondolas 7, and should go out hanging point is general hanging point, can basis
Different task carries out replacement gondola to execute different task.The undercarriage 8 of aircraft is skid landing gear, the aircraft
Undercarriage used is composite material undercarriage, has many advantages, such as that intensity, rigidity are high, light-weight.The aircraft also has binocular
Avoidance equipment 5, holder gondola 6, RTK antenna 11,14 record antenna 16, lower view binocular gondola 15.
Although preferred embodiments of the present invention have been described, it is created once a person skilled in the art knows basic
Property concept, then additional changes and modifications may be made to these embodiments.So it includes excellent that the following claims are intended to be interpreted as
It selects embodiment and falls into all change and modification of the scope of the invention.
Obviously, various changes and modifications can be made to the invention without departing from essence of the invention by those skilled in the art
Mind and range.In this way, if these modifications and changes of the present invention belongs to the range of the claims in the present invention and its equivalent technologies
Within, then the present invention is also intended to include these modifications and variations.
Claims (10)
1. a kind of inclining rotary mechanism for aircraft, which is characterized in that the inclining rotary mechanism includes first bearing seat (22a),
Two bearing bracket (22b), first bearing (23a), second bearing (23b), axle sleeve (28), first connecting rod (24), second connecting rod (25),
Third connecting rod (26), steering engine (21) and anchor ear (27),
One end of the axle sleeve (28) is connected to the first bearing seat (22a), the axle sleeve by the first bearing (23a)
(28) the other end is connected to the second bearing seat (22b) by the second bearing (23b),
One end of the first connecting rod (24) is fixedly connected on the output shaft (29) of the steering engine (21), the first connecting rod (24)
The other end be articulated with one end of the second connecting rod (25), the other end of the second connecting rod (25) is articulated with the third and connects
The other end of one end of bar (26), the third connecting rod (26) is fixedly connected on the anchor ear (27), the anchor ear (27) and institute
Axle sleeve (28) tight fit is stated, tiliting axis (3) fixation of the aircraft is arranged in the axle sleeve (28).
2. the inclining rotary mechanism according to claim 1 for aircraft, which is characterized in that further include intermediate medium part, institute
Intermediate medium part is stated to be set between the anchor ear (27) and the axle sleeve (28) and/or the hinged place of the connecting rod, it is described in
Between medium member be friction member or compressive deformation part.
3. the inclining rotary mechanism according to claim 2 for aircraft, which is characterized in that the material of the intermediate medium part
Selected from rubber, silica gel or natural emulsion.
4. the inclining rotary mechanism according to claim 1 for aircraft, which is characterized in that the first connecting rod (24),
Two connecting rods (25), third connecting rod (26) constitute crank and rocker mechanism, so that the rotation of the output shaft (29) in the steering engine (21)
When gyration changes, the steering engine (21) is able to drive the crank and rocker mechanism according to the several of the crank and rocker mechanism
What relationship controls the rotation angle of the tiliting axis (3) of the aircraft.
5. the inclining rotary mechanism according to claim 1 for aircraft, which is characterized in that it further include connector (30),
The first bearing seat (22a) and the second bearing seat (22b) are symmetrical in chirality, and the connector (30) is fixedly connected
Between the first bearing seat (22a) and second bearing seat (22b)；
The first bearing seat (22a) and second bearing seat (22b) pass through the connector (30) and are connected to the aircraft
Fuselage.
6. the inclining rotary mechanism according to claim 1 for aircraft, which is characterized in that the output shaft of the steering engine (21)
(29) hinge between the radial center of circle in the radial center of circle, the tiliting axis (3), the first connecting rod (24) and second connecting rod (25)
4 points of the radial center of circle of articulated shaft between the radial center of circle of spindle, the second connecting rod (25) and third connecting rod (26) constitutes flat
Row quadrangle.
7. a kind of aircraft, which is characterized in that including the inclining rotary mechanism for aircraft any in claim 1~6.
8. aircraft according to claim 7, which is characterized in that each component in the material for manufacturing the aircraft
Mass percentage includes: carbon fiber prepreg: >=35%, glass fibre prepreg: and >=30%, Polymethacrylimide:
>=20%.
9. aircraft according to claim 7, which is characterized in that the aircraft is an integral molding structure.
10. aircraft according to claim 7, which is characterized in that the aircraft includes the first inclining rotary mechanism and second
Inclining rotary mechanism, the tiliting axis include the first tiliting axis and the second tiliting axis,
First tiliting axis is connected to the fuselage head of the aircraft by first inclining rotary mechanism, and described first verts
The both ends of axis are connected separately with the propeller of the aircraft；
Second tiliting axis is connected to the afterbody of the aircraft by second inclining rotary mechanism, and described second verts
The both ends of axis are connected separately with the propeller of the aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811075476.6A CN109131868A (en) | 2018-09-14 | 2018-09-14 | Inclining rotary mechanism and aircraft for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811075476.6A CN109131868A (en) | 2018-09-14 | 2018-09-14 | Inclining rotary mechanism and aircraft for aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109131868A true CN109131868A (en) | 2019-01-04 |
Family
ID=64825508
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811075476.6A Pending CN109131868A (en) | 2018-09-14 | 2018-09-14 | Inclining rotary mechanism and aircraft for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109131868A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113184177A (en) * | 2021-05-17 | 2021-07-30 | 朱世友 | Tilt-rotor aircraft and power transmission device thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204211908U (en) * | 2014-11-10 | 2015-03-18 | 浙江理工大学 | What a kind of cam path was fixing can covert footpath weft insertion device |
| CN205574273U (en) * | 2016-05-06 | 2016-09-14 | 吉林大学 | Four rotor crafts at adjustable rotor inclination |
| CN106394886A (en) * | 2016-06-15 | 2017-02-15 | 珠海市磐石电子科技有限公司 | Multi-axis aircraft capable of movably flying, flying assisting platform and flying method |
| CN206939066U (en) * | 2017-03-23 | 2018-01-30 | 沈阳无距科技有限公司 | Multiaxis unmanned plane |
| CN207732093U (en) * | 2018-01-31 | 2018-08-14 | 北京星网卫通科技开发有限公司 | Antenna pitching rotating locking apparatus and antenna pitching Rotable Control System |
| CN209097011U (en) * | 2018-09-14 | 2019-07-12 | 沈阳无距科技有限公司 | Inclining rotary mechanism and aircraft for aircraft |
-
2018
- 2018-09-14 CN CN201811075476.6A patent/CN109131868A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204211908U (en) * | 2014-11-10 | 2015-03-18 | 浙江理工大学 | What a kind of cam path was fixing can covert footpath weft insertion device |
| CN205574273U (en) * | 2016-05-06 | 2016-09-14 | 吉林大学 | Four rotor crafts at adjustable rotor inclination |
| CN106394886A (en) * | 2016-06-15 | 2017-02-15 | 珠海市磐石电子科技有限公司 | Multi-axis aircraft capable of movably flying, flying assisting platform and flying method |
| CN206939066U (en) * | 2017-03-23 | 2018-01-30 | 沈阳无距科技有限公司 | Multiaxis unmanned plane |
| CN207732093U (en) * | 2018-01-31 | 2018-08-14 | 北京星网卫通科技开发有限公司 | Antenna pitching rotating locking apparatus and antenna pitching Rotable Control System |
| CN209097011U (en) * | 2018-09-14 | 2019-07-12 | 沈阳无距科技有限公司 | Inclining rotary mechanism and aircraft for aircraft |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113184177A (en) * | 2021-05-17 | 2021-07-30 | 朱世友 | Tilt-rotor aircraft and power transmission device thereof |
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