CN106081097A - A kind of jet changement of aircraft - Google Patents
A kind of jet changement of aircraft Download PDFInfo
- Publication number
- CN106081097A CN106081097A CN201610485576.0A CN201610485576A CN106081097A CN 106081097 A CN106081097 A CN 106081097A CN 201610485576 A CN201610485576 A CN 201610485576A CN 106081097 A CN106081097 A CN 106081097A
- Authority
- CN
- China
- Prior art keywords
- deflector
- changement
- inverting seat
- aircraft
- fulcrum
- 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
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C15/00—Attitude, flight direction, or altitude control by jet reaction
- B64C15/02—Attitude, flight direction, or altitude control by jet reaction the jets being propulsion jets
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Toys (AREA)
Abstract
The present invention relates to the jet changement of a kind of aircraft, this aircraft fuselage is provided with one or more sets changements；Described changement includes inverting seat, several deflectors, and each deflector is each provided with fulcrum, and is arranged on below the airintake direction mouth of inverting seat by fulcrum, connects with connecting rod each deflector is linked between each deflector；Being provided with propeller at the airintake direction mouth of this inverting seat, lower section and the afterbody of inverting seat are respectively provided with nozzle.The invention have the benefit that 1, changement simple and reliable, it is achieved cost is the lowest；2, commutation angular range is wide, can reach 180 degree in theory；3, commutating speed is adjustable, can meet the demand of quickly commutation, and actual measurement commutation 90 degree can complete within 0.5 second；4, the torque requiremnt needed for commutation is the least, the whole series changement just can be made to need not extra power and maintain as long as ensureing that conjunctions of the projected area of all deflector fulcrum the right and lefts is identical in theory.
Description
Technical field
The invention belongs to jet changement technical field, particularly relate to a kind of on the equipment such as model plane or unmanned plane
The jet changement of aircraft.
Background technology
Current main flow aircraft particularly unmanned plane industry is broadly divided into many rotors and fixed-wing two kinds.
The advantage of many rotors without runway can more arbitrarily close to the local landing of level, but its flight theory is certainly
It is short to have determined this its flight time of aircraft inefficiency, and radius of action is little.
The efficiency of Fixed Wing AirVehicle be far above many rotors, but have to runway through row landing, this significantly limit
The scope of application of this kind of flight.
Summary of the invention
It is an object of the invention to the deficiency overcoming prior art to exist, and the jet reversing machine of a kind of aircraft is provided
Structure, so that many rotors are perfectly combined with fixed-wing, has both advantages simultaneously.
It is an object of the invention to complete by following technical solution, the jet changement of this aircraft, this flies
On row device fuselage, one or more sets changements are installed；Described changement includes inverting seat, several deflectors, each
Deflector is each provided with fulcrum, and is arranged on below the airintake direction mouth of inverting seat by fulcrum, with even between each deflector
Bar connection makes each deflector link；Propeller is installed at the airintake direction mouth of this inverting seat, the lower section of inverting seat and tail
Portion is respectively provided with nozzle.
As preferably, the rotating range of described deflector can be 0 to 180 °, when deflector is all turned on, now
Air-flow sprays after entering inverting seat vertically downward；When deflector Close All, toward nozzle after now air-flow enters inverting seat
Direction sprays.
The invention have the benefit that
1, changement is simple and reliable, it is achieved cost is the lowest；
2, commutation angular range is wide, can reach 180 degree in theory；
3, commutating speed is adjustable, can meet the demand of quickly commutation, and actual measurement commutation 90 degree can be complete within 0.5 second
Become；
4, the torque requiremnt needed for commutation is the least, as long as ensureing the perspective plane of all deflector fulcrum the right and lefts in theory
Long-pending conjunctions be identical just can be made the whole series changement need not extra power to maintain.
Accompanying drawing explanation
Fig. 1 is the changement mounting structure schematic diagram of the present invention.
Fig. 2 is the A-A cross-sectional view of Fig. 1.
Fig. 3 is the deflector full open position structural representation of the present invention.
Fig. 4 is the deflector fully closed condition structural representation of the present invention.
Label in accompanying drawing is respectively as follows: 1, aircraft fuselage；2, changement；3, propeller；21, inverting seat；22, water conservancy diversion
Plate；23, fulcrum；24, airintake direction mouth；25, connecting rod；26, nozzle.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention done detailed introduction: as shown in accompanying drawing 1,2, this aircraft fuselage 1 is installed
Having one or more sets changements 2, changement 2 is positioned at the surface of aircraft 1, and this changement 2 can be on aircraft 1
Arbitrarily angled installation；Described changement 2 includes inverting seat 21, several deflectors 22, each each self installation of deflector 22
There is fulcrum 23, can rotate around respective fulcrum 23, and be arranged on the airintake direction mouth 24 of inverting seat 21 by fulcrum 23
Lower section, connects with connecting rod 25 between each deflector 22 and each deflector 22 is linked；Airintake direction mouth 24 at this inverting seat 21
Place is provided with propeller 3, and the lower section of inverting seat 21 and afterbody are respectively provided with nozzle 26.Power part can use motor or
Internal-combustion engine drives propeller can also use other power such as jet engine to produce air-flow.
The opening angle of described deflector 22 can the most identical can also be different to adapt to the entirety of diverter
Profile, the length being regulated each deflector 22 arm of force by regulations and parameters principle can make deflector 22 realize can keeping vertical angle simultaneously
Degree also can be closed with different angles simultaneously.Rotate deflector 22 to have only to use the device drives such as servomechanism or steering wheel any
One deflector 22, other all deflectors 22 can and then linkage automatically.
As shown in accompanying drawing 3,4, the rotating range of described deflector 22 is 0 to 180 °, when deflector 22 is all turned on,
Now air-flow sprays after entering air inlet 24 vertically downward；When deflector 22 Close All, now air-flow enters air inlet 24
After along deflector 22 to nozzle 26 direction flow.
The using method of the present invention is: when propeller rotational, and air-flow can be come in from the airintake direction mouth 24 of inverting seat 21,
When all of deflector 22 rotates to vertical state, air-flow sprays straight down along deflector 22, forms counteracting force, control
The size of air-flow processed can make aircraft takeoff, landing, hovering；Gradually rotating flow guidance plate 22 can change the emission direction of air-flow
For controlling athletic posture and the direction of aircraft；When all of deflector 22 rotate to closed mode air-flow can be from nozzle 26
Direction sprays.This jet changement can allow aircraft with the flying method VTOL of many rotors or slowly move, again
Can fly with the flying method of fixed-wing.State of flight can also be the most freely switched under any state.
It is understood that it will be understood by those skilled in the art that to technical scheme and inventive concept in addition etc.
The protection domain of appended claims of the invention all should be belonged to replacement or change.
Claims (2)
1. the jet changement of an aircraft, it is characterised in that: on this aircraft fuselage (1), one or more sets are installed and change
To mechanism (2)；Described changement (2) includes inverting seat (21), several deflectors (22), and each deflector (22) is respective
Fulcrum (23) is installed, and is arranged on by fulcrum (23) below the airintake direction mouth (24) of inverting seat (21), each deflector
(22) connecting with connecting rod (25) between makes each deflector (22) link；Pacify at airintake direction mouth (24) place of this inverting seat (21)
Equipped with propeller (3), the lower section of inverting seat (21) and afterbody are respectively provided with nozzle (26).
The jet changement of aircraft the most according to claim 1, it is characterised in that: the rotation of described deflector (22)
Turning and may range from 0 to 180 °, when deflector (22) is all turned on, now air-flow sprays after entering inverting seat (21) vertically downward
Go out；When deflector (22) Close All, now air-flow enters inverting seat (21) afterwards toward the ejection of nozzle (26) direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610485576.0A CN106081097A (en) | 2016-06-24 | 2016-06-24 | A kind of jet changement of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610485576.0A CN106081097A (en) | 2016-06-24 | 2016-06-24 | A kind of jet changement of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106081097A true CN106081097A (en) | 2016-11-09 |
Family
ID=57213974
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610485576.0A Pending CN106081097A (en) | 2016-06-24 | 2016-06-24 | A kind of jet changement of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106081097A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107010180A (en) * | 2017-03-15 | 2017-08-04 | 王金海 | Naval vessel, vehicle, aircraft autobalance propeller |
| CN108945484A (en) * | 2018-07-02 | 2018-12-07 | 山东理工大学 | A kind of two-way air injection aerial vehicle |
| CN109204850A (en) * | 2018-09-07 | 2019-01-15 | 佛山皖和新能源科技有限公司 | A kind of unmanned vehicle engine progress air-flow rectification mechanism |
| CN109305346A (en) * | 2018-11-27 | 2019-02-05 | 歌尔股份有限公司 | A kind of unmanned plane during flying device |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5890441A (en) * | 1995-09-07 | 1999-04-06 | Swinson Johnny | Horizontal and vertical take off and landing unmanned aerial vehicle |
| JP2007203008A (en) * | 2006-01-31 | 2007-08-16 | Shinzo Tanaka | Vertical taking off and landing airplane |
| JP2008075582A (en) * | 2006-09-22 | 2008-04-03 | Japan Aerospace Exploration Agency | Propelling system for v/stol aircraft |
| CN101437720A (en) * | 2006-03-24 | 2009-05-20 | 国际航空补给I.A.S.有限公司 | Convertible aircraft |
| DE102009048201A1 (en) * | 2009-10-05 | 2011-04-28 | Eads Deutschland Gmbh | Drive mechanism for e.g. fixed wing aircraft, has lifting drive turbine actuated by exhaust gas stream of radiation jet engine, and device increasing exhaust gas temperature of burners and arranged in section of exhaust gas channel |
| CN104908942A (en) * | 2014-03-14 | 2015-09-16 | 顾乃健 | Vertical take-off and landing light airplane |
| CN205770145U (en) * | 2016-06-24 | 2016-12-07 | 张奕嘉 | The jet changement of aircraft |
-
2016
- 2016-06-24 CN CN201610485576.0A patent/CN106081097A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5890441A (en) * | 1995-09-07 | 1999-04-06 | Swinson Johnny | Horizontal and vertical take off and landing unmanned aerial vehicle |
| JP2007203008A (en) * | 2006-01-31 | 2007-08-16 | Shinzo Tanaka | Vertical taking off and landing airplane |
| CN101437720A (en) * | 2006-03-24 | 2009-05-20 | 国际航空补给I.A.S.有限公司 | Convertible aircraft |
| JP2008075582A (en) * | 2006-09-22 | 2008-04-03 | Japan Aerospace Exploration Agency | Propelling system for v/stol aircraft |
| DE102009048201A1 (en) * | 2009-10-05 | 2011-04-28 | Eads Deutschland Gmbh | Drive mechanism for e.g. fixed wing aircraft, has lifting drive turbine actuated by exhaust gas stream of radiation jet engine, and device increasing exhaust gas temperature of burners and arranged in section of exhaust gas channel |
| CN104908942A (en) * | 2014-03-14 | 2015-09-16 | 顾乃健 | Vertical take-off and landing light airplane |
| CN205770145U (en) * | 2016-06-24 | 2016-12-07 | 张奕嘉 | The jet changement of aircraft |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107010180A (en) * | 2017-03-15 | 2017-08-04 | 王金海 | Naval vessel, vehicle, aircraft autobalance propeller |
| CN108945484A (en) * | 2018-07-02 | 2018-12-07 | 山东理工大学 | A kind of two-way air injection aerial vehicle |
| CN109204850A (en) * | 2018-09-07 | 2019-01-15 | 佛山皖和新能源科技有限公司 | A kind of unmanned vehicle engine progress air-flow rectification mechanism |
| CN109204850B (en) * | 2018-09-07 | 2020-11-06 | 观典防务技术股份有限公司 | Unmanned aerial vehicle engine carries out air current rectification mechanism |
| CN109305346A (en) * | 2018-11-27 | 2019-02-05 | 歌尔股份有限公司 | A kind of unmanned plane during flying device |
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| Date | Code | Title | Description |
|---|---|---|---|
| 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: 20161109 |
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| RJ01 | Rejection of invention patent application after publication |