CN106143901A - The unmanned plane wing that a kind of active force can be verted - Google Patents
The unmanned plane wing that a kind of active force can be verted Download PDFInfo
- Publication number
- CN106143901A CN106143901A CN201610641341.6A CN201610641341A CN106143901A CN 106143901 A CN106143901 A CN 106143901A CN 201610641341 A CN201610641341 A CN 201610641341A CN 106143901 A CN106143901 A CN 106143901A
- Authority
- CN
- China
- Prior art keywords
- face
- power motor
- wing
- unmanned plane
- mounting seat
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
Abstract
The invention discloses the unmanned plane wing that a kind of active force can be verted, it is characterized in that, including: constitute the wing end face of framework, strengthen end face and support end face, and driving steering wheel, electricity is adjusted, power motor mounting seat, drive transmission component, power motor and propeller, wherein, two drive steering wheel be separately mounted to wing end face and strengthen on end face, electricity mediation power motor mounting seat is installed in wing end face and strengthens between end face, rotary shaft is had in power motor mounting seat, steering wheel is driven to drive, by the transmission component that drives of left and right, the pitch motion that power motor mounting seat carries out 90 °, power motor integral installation is in power motor mounting seat, propeller is arranged on power motor.The invention have benefit that: active force support can either be provided for the VTOL of aircraft, advance pulling force support can be provided for the flat journey of flying over of aircraft again, make the use of unmanned plane can not be limited by place, reduce the threshold that unmanned plane uses.
Description
Technical field
The present invention relates to a kind of unmanned plane wing, be specifically related to the unmanned plane wing that a kind of active force can be verted, belong to
Unmanned air vehicle technique field.
Background technology
The thrust that current fixed-wing unmanned plane, pulling force that its power provides for head or tail provide.Either which
A kind of power, all can produce propellerslip effect, affect the layout of propeller.
Additionally, the most any power, all can not realize verting, it is impossible to complete the vertical and landing takeoff of aircraft, make
The range of aircraft is greatly limited.
Summary of the invention
For solving the deficiencies in the prior art, it is an object of the invention to provide the unmanned plane machine that a kind of active force can be verted
The wing, it can either provide the active force of unmanned plane VTOL process, unmanned plane can be provided again to put down the advance pulling force flying over journey,
Reduce the harsh threshold that unmanned plane uses, make the use of unmanned plane can not be limited by place.
In order to realize above-mentioned target, the present invention adopts the following technical scheme that:
The unmanned plane wing that a kind of active force can be verted, it is characterised in that including: wing end face (9), reinforcement end face
(11), support end face (2), drive steering wheel (7), electricity to adjust (8), power motor mounting seat (4), drive transmission component (6), power current
Machine (3) and propeller (1), wherein,
Wing end face (9), reinforcement end face (11) and support end face (2) connect and compose firm rigid frame, drive steering wheel
(7) about employing, the layout type of each is separately mounted to wing end face (9) and strengthens on end face (11), and electricity is adjusted (8) and moves
Force motor mounting seat (4) is installed in wing end face (9) and strengthens between end face (11), and electricity adjusts (8) to be positioned in rigid frame
Portion, power motor mounting seat (4) is positioned at the front end of rigid frame, and power motor mounting seat (4) has rotary shaft, drives steering wheel
(7) the driving transmission component (6) driving power motor mounting seat (4) by left and right carries out the pitch motion of 90 °, power motor
(3) integral installation is in power motor mounting seat (4), and propeller (1) is arranged on power motor (3).
The unmanned plane wing that aforesaid active force can be verted, it is characterised in that aforementioned wing end face (9), reinforcement end face
(11) and support end face (2) all use modularized design.
The unmanned plane wing that aforesaid active force can be verted, it is characterised in that also include: fuselage front-axle beam (12) and fuselage
The back rest (13), the two is arranged on the rear portion of rigid frame, and rigid frame is by both being connected on fuselage.
The unmanned plane wing that aforesaid active force can be verted, it is characterised in that after aforementioned fuselage front-axle beam (12) and fuselage
Beam (13) all uses modularized design.
The unmanned plane wing that aforesaid active force can be verted, it is characterised in that also include: electricity adjusts fin (10), electricity
Adjust (8) to adjust fin (10) to carry out pretension by aforementioned electricity to fix.
The unmanned plane wing that aforesaid active force can be verted, it is characterised in that also include: protective cover (5), aforementioned protection
Cover (5) is arranged on wing end face (9) and strengthens on end face (11), blocks driving transmission component (6).
The invention have benefit that: " drive steering wheel to be driven by the driving transmission component of left and right dynamic owing to have employed
Force motor mounting seat carries out the pitch motion of 90 ° " such design, institute is so that aircraft achieves active force and verts, so
Active force support can either be provided for the VTOL of aircraft, advance pulling force support can be provided for the flat journey of flying over of aircraft again, make
The use of unmanned plane can not be limited by place, reduces the harsh threshold that unmanned plane uses.
Accompanying drawing explanation
Fig. 1 is the structural representation of a specific embodiment of the unmanned plane wing that the active force of the present invention can be verted.
The implication of reference in figure: 1-propeller, 2-support end face, 3-power motor, 4-power motor mounting seat, 5-
Protective cover, 6-drive transmission component, 7-drive steering wheel, 8-electricity tunes, 9-wing end face, 10-electricity adjust fin, 11-reinforcement end face,
12-fuselage front-axle beam, the 13-fuselage back rest.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the present invention made concrete introduction.
With reference to Fig. 1, the unmanned plane wing that the active force of the present invention can be verted includes: wing end face 9, strengthen end face 11,
Support end face 2, drive steering wheel 7, fuselage front-axle beam 12, the fuselage back rest 13, electricity tune 8, power motor mounting seat 4, driving transmission component
6, power motor 3 and propeller 1.
Wing end face 9, reinforcement end face 11 and support end face 2 all use modularized design, and three is attached by screw,
Finally constitute firm rigid frame.
Fuselage front-axle beam 12 and the fuselage back rest 13 are also adopted by modularized design, and the two is arranged on the rear portion of rigid frame, passes through
Screw fastens, and rigid frame is by both being connected on fuselage.
Modularity is installed and both can have been improved installation rate, can reduce error with precise positioning, also ensure that structure simultaneously again
Compacter, weight more lightweight, so that aircraft can perform, more difficult task is more diversified with execution to fly
Row index.
The layout type of each one about steering wheel 7 employing is driven to be separately mounted to wing end face 9 and strengthen on end face 11, both
Can ensure that the concordance of installation, sufficiently large driving torsion can be provided again simultaneously, reduce space accounting.
Electricity tune 8 and power motor mounting seat 4 are installed in wing end face 9 and strengthen between end face 11, and wherein, electricity adjusts 8
In the middle part of rigid frame, and adjusting fin 10 to carry out pretension and fix by electricity, precise positioning can be heat while installing
Derive to outside；Power motor mounting seat 4 is positioned at the front end of rigid frame.
There is rotary shaft in power motor mounting seat 4, drive steering wheel 7 to drive power current by the driving transmission component 6 of left and right
Machine mounting seat 4 carries out the pitch motion of 90 °.The outside driving transmission component 6 is provided with protective cover 5, and protective cover 5 is pacified by screw
It is contained in wing end face 9 and strengthens on end face 11, both to driving transmission component 6 to be blocked, maintaining again good concordance
Beautify with outward appearance.
Power motor 3 integral installation threadably is in power motor mounting seat 4, and propeller 1 passes through pretension
Screw is arranged on power motor 3.
As can be seen here, in the present invention, owing to have employed, " the driving transmission component 6 driving steering wheel 7 to pass through left and right drives dynamic
Force motor mounting seat 4 carries out the pitch motion of 90 ° " such design, institute is so that aircraft achieves active force and verts, so
Active force support can either be provided for the VTOL of aircraft, the support that journey offer advance pulling force is provided can be put down again for aircraft,
The use making unmanned plane can not be limited by place, reduces the harsh threshold that unmanned plane uses.
Additionally, due to active force is distributed on wing, so the wing of the present invention can reduce propellerslip to aircraft
Impact, reduce lift loss, improve rolling stability.
Become it should be noted that above-described embodiment limits the present invention, all employing equivalents or equivalence the most in any form
The technical scheme that the mode changed is obtained, all falls within protection scope of the present invention.
Claims (6)
1. the unmanned plane wing that an active force can be verted, it is characterised in that including: wing end face (9), reinforcement end face
(11), support end face (2), drive steering wheel (7), electricity to adjust (8), power motor mounting seat (4), drive transmission component (6), power current
Machine (3) and propeller (1), wherein,
Wing end face (9), reinforcement end face (11) and support end face (2) connect and compose firm rigid frame, drive steering wheel (7) to adopt
Being separately mounted to wing end face (9) with the layout type of each one of left and right and strengthen on end face (11), electricity adjusts (8) and power motor
Mounting seat (4) is installed in wing end face (9) and strengthens between end face (11), and electricity adjusts (8) to be positioned at the middle part of rigid frame, power
Motor mount (4) is positioned at the front end of rigid frame, and power motor mounting seat (4) has rotary shaft, drives steering wheel (7) by a left side
Right driving transmission component (6) drives the pitch motion that power motor mounting seat (4) carries out 90 °, power motor (3) integral installation
In power motor mounting seat (4), propeller (1) is arranged on power motor (3).
The unmanned plane wing that active force the most according to claim 1 can be verted, it is characterised in that described wing end face
(9), strengthen end face (11) and support end face (2) all uses modularized design.
The unmanned plane wing that active force the most according to claim 1 can be verted, it is characterised in that also include: before fuselage
Beam (12) and the fuselage back rest (13), the two is arranged on the rear portion of rigid frame, and rigid frame is by both being connected on fuselage.
The unmanned plane wing that active force the most according to claim 3 can be verted, it is characterised in that described fuselage front-axle beam
And the fuselage back rest (13) all uses modularized design (12).
The unmanned plane wing that active force the most according to claim 1 can be verted, it is characterised in that also include: electricity is adjusted and dissipated
Backing (10), electricity is adjusted (8) to adjust fin (10) to carry out pretension by described electricity and is fixed.
The unmanned plane wing that active force the most according to claim 1 can be verted, it is characterised in that also include: protective cover
(5), described protective cover (5) is arranged on wing end face (9) and strengthens on end face (11), blocks driving transmission component (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610641341.6A CN106143901A (en) | 2016-08-05 | 2016-08-05 | The unmanned plane wing that a kind of active force can be verted |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610641341.6A CN106143901A (en) | 2016-08-05 | 2016-08-05 | The unmanned plane wing that a kind of active force can be verted |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106143901A true CN106143901A (en) | 2016-11-23 |
Family
ID=57329363
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610641341.6A Pending CN106143901A (en) | 2016-08-05 | 2016-08-05 | The unmanned plane wing that a kind of active force can be verted |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106143901A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106379544A (en) * | 2016-11-29 | 2017-02-08 | 北京奇正数元科技股份有限公司 | Modularized and detachable type power nacelle of unmanned aerial vehicle |
| CN108313264A (en) * | 2018-01-26 | 2018-07-24 | 易瓦特科技股份公司 | Adjustable rotor engine body system for fixed-wing unmanned plane |
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|---|---|---|---|---|
| CN102765477A (en) * | 2012-08-10 | 2012-11-07 | 南昌航空大学 | Airplane capable of performing fixed wing flight and vertical take-off and landing based on three-axle flight control panel |
| US20130105620A1 (en) * | 2011-10-31 | 2013-05-02 | King Abdullah II Design and Development Bureau | Sided performance coaxial vertical takeoff and landing (vtol) uav and pitch stability technique using oblique active tilting (oat) |
| US20140008498A1 (en) * | 2010-09-17 | 2014-01-09 | Johannes Reiter | Tilt Wing Rotor VTOL |
| CN104210655A (en) * | 2014-09-03 | 2014-12-17 | 西北农林科技大学 | Double-rotor-wing unmanned plane |
| CN204489181U (en) * | 2015-03-10 | 2015-07-22 | 广州天翔航空科技有限公司 | Variable motor angle four axle vertical takeoff and landing fixed-wing compound unmanned plane |
| CN205854496U (en) * | 2016-08-05 | 2017-01-04 | 北京奇正数元科技股份有限公司 | The unmanned plane wing that a kind of active force can be verted |
-
2016
- 2016-08-05 CN CN201610641341.6A patent/CN106143901A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140008498A1 (en) * | 2010-09-17 | 2014-01-09 | Johannes Reiter | Tilt Wing Rotor VTOL |
| US20130105620A1 (en) * | 2011-10-31 | 2013-05-02 | King Abdullah II Design and Development Bureau | Sided performance coaxial vertical takeoff and landing (vtol) uav and pitch stability technique using oblique active tilting (oat) |
| CN102765477A (en) * | 2012-08-10 | 2012-11-07 | 南昌航空大学 | Airplane capable of performing fixed wing flight and vertical take-off and landing based on three-axle flight control panel |
| CN104210655A (en) * | 2014-09-03 | 2014-12-17 | 西北农林科技大学 | Double-rotor-wing unmanned plane |
| CN204489181U (en) * | 2015-03-10 | 2015-07-22 | 广州天翔航空科技有限公司 | Variable motor angle four axle vertical takeoff and landing fixed-wing compound unmanned plane |
| CN205854496U (en) * | 2016-08-05 | 2017-01-04 | 北京奇正数元科技股份有限公司 | The unmanned plane wing that a kind of active force can be verted |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106379544A (en) * | 2016-11-29 | 2017-02-08 | 北京奇正数元科技股份有限公司 | Modularized and detachable type power nacelle of unmanned aerial vehicle |
| CN108313264A (en) * | 2018-01-26 | 2018-07-24 | 易瓦特科技股份公司 | Adjustable rotor engine body system for fixed-wing unmanned plane |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20161123 |
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| RJ01 | Rejection of invention patent application after publication |