CN107176292A - A kind of aircraft air propeller - Google Patents
A kind of aircraft air propeller Download PDFInfo
- Publication number
- CN107176292A CN107176292A CN201710457546.3A CN201710457546A CN107176292A CN 107176292 A CN107176292 A CN 107176292A CN 201710457546 A CN201710457546 A CN 201710457546A CN 107176292 A CN107176292 A CN 107176292A
- Authority
- CN
- China
- Prior art keywords
- fuselage
- screw mechanism
- propeller
- push away
- control
- 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
Links
- 238000005183 dynamical system Methods 0.000 claims abstract description 18
- 229910000838 Al alloy Inorganic materials 0.000 claims description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims 1
- 229910052799 carbon Inorganic materials 0.000 claims 1
- 230000005611 electricity Effects 0.000 claims 1
- 238000005516 engineering process Methods 0.000 description 4
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000012549 training Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
-
- 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
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/11—Propulsion using internal combustion piston engines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/13—Propulsion using external fans or propellers
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of aircraft air propeller, including fuselage, above push away screw mechanism, preceding push away screw mechanism, wing and propeller control system.It is described above to push away the rear and front end that screw mechanism is installed in fuselage, it is described before push away the left and right sides that screw mechanism is installed in fuselage, the waist is provided with cabin, and the wing is on fuselage.The propeller control system includes the middle control main frame in cabin and the dynamical system, control module, laser ranging controller and the center dynamic balance system that are electrically connected with middle control main frame, the control module is electrically connected with dynamical system, self balancing device and remote control, the dynamical system is electrically connected with lifting force system and advance propulsion system, the screw mechanism that above pushes away is controlled by the lifting force system, it is described before push away screw mechanism and controlled by the advance propulsion system.A kind of aircraft air propeller of the present invention has simple to operate, the high advantage of easy to use and security performance.
Description
Technical field
The present invention relates to vehicle technology field, and in particular to a kind of aircraft air propeller.
Background technology
The mankind have the ideal flown in the air as birds very early.For a long time, the mankind are most for the fantasy that can fly up into the sky
Various methods.With the continuous development of scientific technology, the dream that the mankind fly in the air becomes reality.It is existing most of
Aircraft is mainly used in scientific research, and cost is sufficiently expensive, is not particularly suited for masses, and needs to stop in the large-scale place such as airport
Put, it is suppressed that the consumption of most people, at the same existing aircraft operation when due to more complicated, it is therefore desirable to Special Training
It could drive, therefore, be badly in need of providing a kind of simple to operate, and the high aircraft of security performance.
The content of the invention
For above-mentioned deficiency, it is an object of the present invention to provide a kind of aircraft air propeller, it has operation letter
It is single, the high advantage of easy to use and security performance.
To achieve the above object, technical scheme provided by the present invention is：
A kind of aircraft air propeller, including fuselage, above push away screw mechanism, preceding push away screw mechanism, wing and propulsion
Device control system.It is described above to push away the rear and front end that screw mechanism is installed in fuselage, it is described before push away screw mechanism and be installed in fuselage
The left and right sides, the waist is provided with cabin, and the wing is on fuselage.The propeller control system includes being located at machine
Middle control main frame in cabin and the dynamical system being electrically connected with middle control main frame, control module, laser ranging controller and in it is aroused in interest
Balance system, the control module is electrically connected with dynamical system, self balancing device and remote control, and the dynamical system is electrical
Be connected with lifting force system and advance propulsion system, the screw mechanism that above pushes away is controlled by the lifting force system, it is described before
Screw mechanism is pushed away to control by the advance propulsion system.
As a further improvement, it is described above push away screw mechanism be arranged at fuselage rear and front end above push away propeller blade.
As a further improvement, it is to be arranged at before fuselage left and right ends to push away propeller blade that screw mechanism is pushed away before described, institute
Stating advance propulsion system includes course changing control module, and realization steering work(is adjusted for pushing away the left and right directions of propeller blade before control
Energy.
As a further improvement, the self balancing device improves aircraft for gyroscope and by control module control
Balanced capacity.
As a further improvement, the fuselage uses carbon fiber and aluminium alloy, it can effectively mitigate fuselage weight.
As a further improvement, the dynamical system is driven using battery electric power.
As a further improvement, the dynamical system is driven using gasoline engine.
Beneficial effects of the present invention are：
Screw mechanism is above pushed away when a kind of aircraft of the present invention is used with air propeller by the control of lifting force system to rotate,
Aircraft, which is risen to after certain altitude, to be controlled advance propulsion system to push away screw mechanism before opening and rotate to realize that aircraft advances, simultaneously
Turning function is realized in the left and right directions regulation that propeller blade is pushed away before being controlled by course changing control module, and operator can be distributed completion
Lifting, advance and steering operation, make the aircraft operation simpler, while the laser ranging controller, center dynamic balancing system
The setting of system and self balancing device, improves the security performance of the present invention.
Below in conjunction with the accompanying drawings with embodiment, the present invention is further described.
Brief description of the drawings
Accompanying drawing is, for providing a further understanding of the present invention, and to constitute a part for specification, with following tool
Body embodiment is used to explain the present invention together, but is not construed as limiting the invention.In the accompanying drawings：
Fig. 1 is a kind of structural representation of aircraft air propeller of the invention.
Fig. 2 is the theory diagram of the propeller control system of the present invention.
Each description of reference numerals is as follows in figure.
Fuselage -1, above push away screw mechanism -2, preceding push away screw mechanism -3, wing -4, cabin -5.
Embodiment
To describe the technology contents of the present invention in detail, feature, the objects and the effects being constructed, below in conjunction with embodiment
And coordinate accompanying drawing to be explained in detail.
Technical scheme is clearly and completely described below in conjunction with accompanying drawing, it is clear that described implementation
Example is a part of embodiment of the invention, rather than whole embodiments.Based on the embodiment in the present invention, ordinary skill
The every other embodiment that personnel are obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.
In the description of the invention, it is necessary to explanation, term " " center ", " on ", " under ", "left", "right", " vertical ", " level ",
The orientation or position relationship of the instructions such as " interior ", " outer " are, based on orientation shown in the drawings or position relationship, to be for only for ease of and retouch
State the present invention and simplify description, rather than indicate or imply that the device or element of meaning there must be specific orientation, with specific
Azimuth configuration and operation, therefore be not considered as limiting the invention.
Refer to Fig. 1 and Fig. 2, a kind of aircraft air propeller, including fuselage 1, above push away screw mechanism 2, preceding push away spiral shell
Revolve mechanism 3, wing 4 and propeller control system.It is described above to push away the rear and front end that screw mechanism 2 is installed in fuselage 1, it is aircraft
Raising and lowering provide power, it is described before push away the left and right sides that screw mechanism 3 is installed in fuselage 1, be that the advance of aircraft is carried
For power.The middle part of fuselage 1 is provided with cabin 5, and operator takes manipulation, and the wing 4 is on fuselage 1.The propeller
Control system includes the middle control main frame in cabin 5 and the dynamical system being electrically connected with middle control main frame, control module, laser
Ranging controller and center dynamic balance system, the control module are electrically connected with dynamical system, self balancing device and remote control dress
Put, the setting of the remote control can make the aircraft of the present invention serve as unmanned plane by remote control control to use.It is described dynamic
Force system is electrically connected with lifting force system and advance propulsion system, and the screw mechanism 2 that above pushes away passes through the lifting force system
Control, it is described before push away screw mechanism 3 and controlled by the advance propulsion system.
In the present embodiment, it is described above push away screw mechanism 2 be arranged at the rear and front end of fuselage 1 above push away propeller blade, and
Above push away propeller blade to drive by motor, and the rotation that i.e. control above pushes away propeller blade is rotated by lifting force system controlled motor
Speed.
In the present embodiment, screw mechanism 3 is pushed away before described to push away propeller blade before being arranged at the left and right ends of fuselage 1, and
Propeller blade is pushed away before this to drive by motor, and it is to push away propeller blade before controlling to be rotated by advance propulsion system controlled motor
Rotating speed.The advance propulsion system includes course changing control module, and the left and right directions for pushing away propeller blade before control adjusts realization
Turning function.
In the present embodiment, the self balancing device improves aircraft for gyroscope and by control module control
Balanced capacity, it is ensured that the security performance of aircraft.
In the present embodiment, the fuselage 1 uses carbon fiber and aluminium alloy, can effectively mitigate fuselage weight.
In the present embodiment, the dynamical system is driven using battery electric power.
In the present embodiment, the dynamical system is driven using gasoline engine.
During present invention work：First, hollow main frame is opened, and dynamical system is opened by control module, passes through lifting force
System control above pushes away screw mechanism 2 and rotated, and aircraft, which is risen to after certain altitude, controls advance propulsion system to push away spiral before opening
Mechanism 3, which is rotated, realizes that aircraft advances, while the left and right directions that propeller blade is pushed away before being controlled by course changing control module is adjusted
Realize turning function.After arriving at, advance propulsion system is closed, and gradually reduced by lifting force system and above push away screw machine
The thrust of structure 2, slowly drops to ground, is then shut off dynamical system.Wherein, the laser ranging controller is used to control to fly
Device is awing not above safe altitude, and then improves the safety coefficient of aircraft, and the center dynamic balance system is adjustable
Whole bottom load-bearing is always maintained at center, improves dynamic balancing ability of the aircraft in running, further improves safety coefficient.
In summary, spiral is above pushed away by the control of lifting force system when a kind of aircraft of the invention is used with air propeller
Mechanism 2 is rotated, and aircraft, which is risen to after certain altitude, controls advance propulsion system to push away the rotation realization flight of screw mechanism 3 before opening
Device advances, while turning function is realized in the left and right directions regulation that propeller blade is pushed away before being controlled by course changing control module, operates
Person can be distributed completion lifting, advance and steering operation, make the aircraft operation simpler, while the laser ranging controller,
The setting of center dynamic balance system and self balancing device, improves the security performance of the present invention.
The announcement and teaching of book according to the above description, those skilled in the art in the invention can also be to above-mentioned embodiment party
Formula is changed and changed.Therefore, the invention is not limited in embodiment disclosed and described above, to the present invention's
Some modifications and changes should also be as falling into the scope of the claims of the present invention.Although in addition, being used in this specification
Some specific terms, but these terms are merely for convenience of description, do not constitute any limitation to the present invention, using with its
Same or analogous other devices, all fall in the scope of protection of the present invention.
Claims (7)
1. a kind of aircraft air propeller, it is characterised in that：Including fuselage (1), above push away screw mechanism (2), preceding push away spiral
Mechanism (3), wing (4) and propeller control system, it is described above to push away the rear and front end that screw mechanism (2) is installed in fuselage (1), institute
Pushed away before stating and be provided with cabin (5), the wing in the middle part of the left and right sides that screw mechanism (3) is installed in fuselage (1), the fuselage (1)
(4) on fuselage (1), the propeller control system includes the middle control main frame in cabin (5) and controls main frame electricity with middle
Property connection dynamical system, control module, laser ranging controller and center dynamic balance system, the control module is electrically connected with
Dynamic system, self balancing device and remote control, the dynamical system, which is electrically connected with lifting force system and advanced, promotes system
System, the screw mechanism (2) that above pushes away control by the lifting force system, it is described before push away screw mechanism (3) and pass through the advance
Propulsion system is controlled.
2. a kind of aircraft air propeller as claimed in claim 1, it is characterised in that：It is described above to push away screw mechanism (2)
Propeller blade is above pushed away for be arranged at fuselage (1) rear and front end.
3. a kind of aircraft air propeller as claimed in claim 1, it is characterised in that：Screw mechanism (3) is pushed away before described
Propeller blade is pushed away to be arranged at before fuselage (1) left and right ends, the advance propulsion system includes course changing control module, for controlling
Turning function is realized in the left and right directions regulation that propeller blade is pushed away before system.
4. a kind of aircraft air propeller as claimed in claim 1, it is characterised in that：The self balancing device is gyro
Instrument and by control module control, improves the balanced capacity of aircraft.
5. a kind of aircraft air propeller as claimed in claim 1, it is characterised in that：The fuselage (1) is fine using carbon
Peacekeeping aluminium alloy, can effectively mitigate fuselage weight.
6. a kind of aircraft air propeller as claimed in claim 1, it is characterised in that：The dynamical system uses battery
Driven by power.
7. a kind of aircraft air propeller as claimed in claim 1, it is characterised in that：The dynamical system uses gasoline
Machine drives.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710457546.3A CN107176292A (en) | 2017-06-16 | 2017-06-16 | A kind of aircraft air propeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710457546.3A CN107176292A (en) | 2017-06-16 | 2017-06-16 | A kind of aircraft air propeller |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107176292A true CN107176292A (en) | 2017-09-19 |
Family
ID=59835443
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710457546.3A Pending CN107176292A (en) | 2017-06-16 | 2017-06-16 | A kind of aircraft air propeller |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107176292A (en) |
Citations (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB567072A (en) * | 1943-04-14 | 1945-01-26 | Arthur Katz | Screw and jet propelled aircraft |
| US5503350A (en) * | 1993-10-28 | 1996-04-02 | Skysat Communications Network Corporation | Microwave-powered aircraft |
| US20040026563A1 (en) * | 2002-02-08 | 2004-02-12 | Moller Paul S. | Vertical take-off and landing vehicles |
| US20040031880A1 (en) * | 2000-05-05 | 2004-02-19 | Reiner Stemme | Aircraft and propulsion system for an aircraft, and operating method |
| US20060226281A1 (en) * | 2004-11-17 | 2006-10-12 | Walton Joh-Paul C | Ducted fan vertical take-off and landing vehicle |
| US20090014580A1 (en) * | 2007-07-11 | 2009-01-15 | Piasecki Aircraft Corporation | Vectored thruster augmented aircraft |
| US20090216392A1 (en) * | 2007-07-11 | 2009-08-27 | Piasecki Aircraft Corporation | Vectored thruster augmented aircraft |
| US20100301168A1 (en) * | 2006-11-02 | 2010-12-02 | Severino Raposo | System and Process of Vector Propulsion with Independent Control of Three Translation and Three Rotation Axis |
| CN102363445A (en) * | 2011-06-21 | 2012-02-29 | 杨朝习 | Tilting dynamic vertical take-off and landing land-air amphibious aircraft |
| CN202219839U (en) * | 2011-08-12 | 2012-05-16 | 余宁晖 | Omnidirectional flying wing structure of vertical lifting aircraft |
| CN102874408A (en) * | 2012-11-02 | 2013-01-16 | 冯小淋 | Double ducted-propeller electric manned aircraft capable of taking off and landing vertically |
| CN103043212A (en) * | 2011-10-17 | 2013-04-17 | 田瑜 | Combined aircraft composed of fixed wing and electric multi-rotor wing |
| US20130206915A1 (en) * | 2010-04-22 | 2013-08-15 | Jean-Marc (Joseph) Desaulniers | Vertical take-off and landing multimodal, multienvironment, gyropendular craft with compensatory propulsion and fluidic gradient collimation |
| CN204355275U (en) * | 2014-08-29 | 2015-05-27 | 深圳市艾特航空科技股份有限公司 | There is the aircraft of safe propulsion system |
| CN106043686A (en) * | 2016-07-18 | 2016-10-26 | 四川傲势乐翼科技有限公司 | Vertical take-off and landing fixed wing aircraft |
| US20170129601A1 (en) * | 2015-11-10 | 2017-05-11 | Parrot Drones | Drone having a coupled propulsion support |
| CN106802659A (en) * | 2017-01-13 | 2017-06-06 | 清华大学 | The control method of feather multi-rotor aerocraft |
| CN206813318U (en) * | 2017-06-16 | 2017-12-29 | 重庆谭工科技有限公司 | A kind of aircraft air propeller |
-
2017
- 2017-06-16 CN CN201710457546.3A patent/CN107176292A/en active Pending
Patent Citations (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB567072A (en) * | 1943-04-14 | 1945-01-26 | Arthur Katz | Screw and jet propelled aircraft |
| US5503350A (en) * | 1993-10-28 | 1996-04-02 | Skysat Communications Network Corporation | Microwave-powered aircraft |
| US20040031880A1 (en) * | 2000-05-05 | 2004-02-19 | Reiner Stemme | Aircraft and propulsion system for an aircraft, and operating method |
| US20040026563A1 (en) * | 2002-02-08 | 2004-02-12 | Moller Paul S. | Vertical take-off and landing vehicles |
| US20060226281A1 (en) * | 2004-11-17 | 2006-10-12 | Walton Joh-Paul C | Ducted fan vertical take-off and landing vehicle |
| US20100301168A1 (en) * | 2006-11-02 | 2010-12-02 | Severino Raposo | System and Process of Vector Propulsion with Independent Control of Three Translation and Three Rotation Axis |
| US20090014580A1 (en) * | 2007-07-11 | 2009-01-15 | Piasecki Aircraft Corporation | Vectored thruster augmented aircraft |
| US20090216392A1 (en) * | 2007-07-11 | 2009-08-27 | Piasecki Aircraft Corporation | Vectored thruster augmented aircraft |
| US20130206915A1 (en) * | 2010-04-22 | 2013-08-15 | Jean-Marc (Joseph) Desaulniers | Vertical take-off and landing multimodal, multienvironment, gyropendular craft with compensatory propulsion and fluidic gradient collimation |
| CN102363445A (en) * | 2011-06-21 | 2012-02-29 | 杨朝习 | Tilting dynamic vertical take-off and landing land-air amphibious aircraft |
| CN202219839U (en) * | 2011-08-12 | 2012-05-16 | 余宁晖 | Omnidirectional flying wing structure of vertical lifting aircraft |
| CN103043212A (en) * | 2011-10-17 | 2013-04-17 | 田瑜 | Combined aircraft composed of fixed wing and electric multi-rotor wing |
| CN102874408A (en) * | 2012-11-02 | 2013-01-16 | 冯小淋 | Double ducted-propeller electric manned aircraft capable of taking off and landing vertically |
| CN204355275U (en) * | 2014-08-29 | 2015-05-27 | 深圳市艾特航空科技股份有限公司 | There is the aircraft of safe propulsion system |
| US20170129601A1 (en) * | 2015-11-10 | 2017-05-11 | Parrot Drones | Drone having a coupled propulsion support |
| CN106043686A (en) * | 2016-07-18 | 2016-10-26 | 四川傲势乐翼科技有限公司 | Vertical take-off and landing fixed wing aircraft |
| CN106802659A (en) * | 2017-01-13 | 2017-06-06 | 清华大学 | The control method of feather multi-rotor aerocraft |
| CN206813318U (en) * | 2017-06-16 | 2017-12-29 | 重庆谭工科技有限公司 | A kind of aircraft air propeller |
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|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170919 |