CN108482633A - A kind of thrust vectoring engine - Google Patents
A kind of thrust vectoring engine Download PDFInfo
- Publication number
- CN108482633A CN108482633A CN201810198561.5A CN201810198561A CN108482633A CN 108482633 A CN108482633 A CN 108482633A CN 201810198561 A CN201810198561 A CN 201810198561A CN 108482633 A CN108482633 A CN 108482633A
- Authority
- CN
- China
- Prior art keywords
- engine
- drive beam
- thrust vectoring
- machine frame
- transmission shaft
- 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
- 230000005540 biological transmission Effects 0.000 claims abstract description 41
- 239000007787 solid Substances 0.000 claims 1
- 239000003638 chemical reducing agent Substances 0.000 abstract description 7
- 230000008878 coupling Effects 0.000 abstract description 3
- 238000010168 coupling process Methods 0.000 abstract description 3
- 238000005859 coupling reaction Methods 0.000 abstract description 3
- 230000015556 catabolic process Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 5
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/06—Rigid airships; Semi-rigid airships
- B64B1/24—Arrangement of propulsion plant
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/02—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions specially adapted for specific power plants
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/08—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission being driven by a plurality of power plants
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Wind Motors (AREA)
Abstract
The invention discloses a kind of thrust vectoring engines, and in the deviation pattern of thrust vectoring, the driving of transmission device makes drive beam rotate, and airscrew reduction device connected to it reaches required angle, this provides minimum aerodynamic resistance；When engine breakdown, connector disconnects gearing speed-reducer and engine, and mechanical wear loss will reduce, and engine only understands rotating screw, provides part tractive force, reaches balance and protects the controllability of equipment；All components of the equipment are placed on to the high-precision for being conducive to axis connection on machine frame, simplify design, alleviate weight, engine and retarder are not necessarily to additional shaft coupling；It can mitigate intensity with the drive beam run together with engine, mitigate weight, reduce the load of holder；Fairshaped profile provides minimum aerodynamic resistance in symmetrical section, because cross section always turns along any flows at angles of engine；Allow to work using multiple engines, increases the safety of equipment.
Description
Technical field
The present invention relates to technical field of engines, specifically a kind of thrust vectoring engine.
Background technology
Known modern times dirigible power plant can be convenient for up-and-down maneuver by vectored thrust take-off and landing.Known tool
There is variable thrust vector engine, by one or more cluster engines at including one is started machine frame.But its design have with
Under defect：1, need to overcome the gyroscopic matrix of air, the thrust vectoring that engine is generated in rotation can increase the work(of driver
Rate and weight；The complexity that engine performance is ensured when 2, turning, needs to provide special fuel oil and fuel supply for engine
System.
Invention content
The purpose of the present invention is to provide a kind of thrust vectoring engines, to solve mentioned above in the background art ask
Topic.
To achieve the above object, the present invention provides the following technical solutions：
A kind of thrust vectoring engine, including machine frame, several engines in machine frame and transmission device, transmission shaft and
Drive beam is equipped with the transmission shaft extended outside machine frame in the machine frame, and engine passes through gearing speed-reducer and transmission shaft phase
Connection, the outside of the machine frame are provided with airscrew reduction device, and the output end of airscrew reduction device is mutually fixedly connected with transmission shaft,
The input terminal of the transmission device is connected with transmission shaft, and the output end of transmission device is mutually fixedly connected with drive beam, the machine
The lower part of frame is equipped with holder, and drive beam rotates with holder to be connect and be mutually fixedly connected with airscrew reduction device, and propeller subtracts
The output end of fast device is equipped with propeller, and punch components, the transmission shaft and drive beam are equipped on the airscrew reduction device
In punch components.
As a further solution of the present invention：The engine is at least one.
As further scheme of the invention：Connector is provided on the transmission shaft, the reducing gear in gearing speed-reducer
Wheel is mounted on connector.
As further scheme of the invention：The drive beam is arranged in hollow state and transmission shaft in drive beam
Portion, the drive beam and the concentric setting of transmission shaft.
As further scheme of the invention：The punch components have symmetrical sweep outline in cross-section.
As further scheme of the invention：The sweep outline is the one of symmetrical wing shape or drop shape
Kind.
Compared with prior art, the beneficial effects of the invention are as follows：
1, in the deviation pattern of thrust vectoring, the driving of transmission device makes drive beam rotate, airscrew reduction connected to it
Device reaches required angle, this provides minimum aerodynamic resistance；
2, when engine breakdown, connector disconnects gearing speed-reducer and engine, and mechanical wear loss will reduce, engine
Only meeting rotating screw, provides part tractive force, reaches balance and protects the controllability of equipment；
3, all components of the equipment are placed on to the high-precision for being conducive to axis connection on machine frame, simplify design, alleviate weight
Amount, engine and retarder are not necessarily to additional shaft coupling；
4, the drive beam run together with engine can mitigate intensity, mitigate weight, reduce the load of holder；
5, fairshaped profile provides minimum aerodynamic resistance in symmetrical section, because always edge is started for cross section
Any flows at angles of machine turns；
6, allow to work using multiple engines, increase the safety of equipment, each engine can also be coordinated according to consumption
Work, in power failure reduce propeller thrust loss, keep the controllability and balance of equipment.
Description of the drawings
Fig. 1 is a kind of structural schematic diagram of thrust vectoring engine；
Fig. 2 is the structural schematic diagram of coaxial thrust vectoring engine；
Fig. 3 is the structural schematic diagram of two thrust vectoring engines；
Fig. 4 is the structural schematic diagram of two coaxial thrust vectoring engines；
Fig. 5 is the A of Fig. 1 to schematic diagram；
Fig. 6 is the schematic cross-sectional view of the line B-B in Fig. 1；
Fig. 7 is the schematic top plan view of Fig. 1.
Specific implementation mode
The technical solution of this patent is described in more detail With reference to embodiment.
Please refer to Fig.1-7, a kind of thrust vectoring engine, including machine frame 1, several engines 2 in machine frame 1
With transmission device 3, transmission shaft 4 and drive beam 5, the transmission shaft 4 extended outside machine frame 1, engine are installed in the machine frame 1
2 are connected by gearing speed-reducer 9 with transmission shaft 4, and the outside of the machine frame 1 is provided with airscrew reduction device 7, airscrew reduction
The output end of device 7 is fixedly connected with 4 phase of transmission shaft, and the input terminal of the transmission device 3 is connected with transmission shaft 4, transmission device 3
Output end be fixedly connected with 5 phase of drive beam, the lower part of the machine frame 1 is equipped with holder 6, drive beam 5 and 6 company of rotating of holder
It connects and is fixedly connected with 7 phase of airscrew reduction device, the output end of airscrew reduction device 7 is equipped with propeller 11, the propeller
Punch components 8 are installed, the transmission shaft 4 and drive beam 5 are mounted in punch components 8 on retarder 7.
The engine 2 is at least one.
Connector 10 is provided on the transmission shaft 4, the reduction gearing in gearing speed-reducer 9 is mounted on connector 10.
The drive beam 5 is arranged in hollow state and transmission shaft 4 in the inside of drive beam 5, the drive beam 5 and transmission shaft
4 concentric settings.
The punch components 8 have symmetrical sweep outline in cross-section.
The sweep outline is symmetrical wing shape or one kind of drop shape.
The present invention operation principle be：It is transmitted by the gearing speed-reducer 9 and connector 10 of the motor 2 on machine frame 1
It to transmission shaft 4, is then transmitted on transmission shaft 4 by airscrew reduction device 7, to the longitudinal traction needed for generation device movement
Power；In the deviation pattern of thrust vectoring, the driving of transmission device 3 makes drive beam 5 rotate, airscrew reduction device connected to it
7 reach required angle, this provides minimum aerodynamic resistance；When engine 2 breaks down, connector 10 disconnects transmission
Retarder 9 and engine 2, mechanical wear loss will reduce, 2, engine can rotating screw 11, part tractive force is provided, is reached
To the controllability for balancing and protecting equipment；
All components of the equipment are placed on to the high-precision for being conducive to axis connection on machine frame 1, simplify design, alleviate weight
Amount, engine 2 and retarder are not necessarily to additional shaft coupling；The drive beam 5 run together with engine 2 can mitigate intensity, subtract
Light weight reduces the load of holder 6；Fairshaped profile provides minimum aerodynamic resistance in symmetrical section, because
Always turn along any flows at angles of engine 2 for cross section；Allow to work using multiple engines 2, increases the safety of equipment
Property, the work of each engine 2 can also be coordinated according to consumption, the loss of propeller thrust is reduced when engine 2 fails,
Keep the controllability and balance of equipment.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " setting ", " phase
Even " and " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or be integrally connected；
It can be directly connected, can also can be indirectly connected through an intermediary the connection inside two elements.For this field
Those of ordinary skill for, the concrete meaning of above-mentioned term in the present invention can be understood with concrete condition.
It is obvious to a person skilled in the art that invention is not limited to the details of the above exemplary embodiments, Er Qie
In the case of without departing substantially from spirit or essential attributes of the invention, the present invention can be realized in other specific forms.Therefore, no matter
From the point of view of which point, the present embodiments are to be considered as illustrative and not restrictive, and the scope of the present invention is by appended power
Profit requires rather than above description limits, it is intended that all by what is fallen within the meaning and scope of the equivalent requirements of the claims
Variation is included within the present invention.Any reference signs in the claims should not be construed as limiting the involved claims.
In addition, it should be understood that although this specification is described in terms of embodiments, but not each embodiment is only wrapped
Containing an independent technical solution, this description of the specification is merely for the sake of clarity, and those skilled in the art should
It considers the specification as a whole, the technical solutions in the various embodiments may also be suitably combined, forms those skilled in the art
The other embodiment being appreciated that.
Claims (6)
1. a kind of thrust vectoring engine, including machine frame, several engines in machine frame and transmission device, transmission shaft
And drive beam, which is characterized in that the transmission shaft extended outside machine frame is equipped in the machine frame, engine passes through gear reduction
Device is connected with transmission shaft, and the outside of the machine frame is provided with airscrew reduction device, the output end of airscrew reduction device and transmission
Axis is mutually fixedly connected, and the input terminal of the transmission device is connected with transmission shaft, and the output end and drive beam of transmission device are mutually solid
Fixed connection, the lower part of the machine frame are equipped with holder, and drive beam rotates with holder to be connect and mutually fixed with airscrew reduction device
Connection, the output end of airscrew reduction device are equipped with propeller, punch components, the biography are equipped on the airscrew reduction device
Moving axis and drive beam are mounted in punch components.
2. thrust vectoring engine according to claim 1, which is characterized in that the engine is at least one.
3. thrust vectoring engine according to claim 1, which is characterized in that be provided with connector on the transmission shaft, pass
Reduction gearing in dynamic retarder is mounted on connector.
4. thrust vectoring engine according to claim 1, which is characterized in that the drive beam is in hollow state and transmission
Axis is arranged in the inside of drive beam, the drive beam and the concentric setting of transmission shaft.
5. thrust vectoring engine according to claim 1, which is characterized in that the punch components have in cross-section
Symmetrical sweep outline.
6. thrust vectoring engine according to claim 5, which is characterized in that the sweep outline is symmetrical wing
One kind of shape or drop shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810198561.5A CN108482633A (en) | 2018-03-12 | 2018-03-12 | A kind of thrust vectoring engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810198561.5A CN108482633A (en) | 2018-03-12 | 2018-03-12 | A kind of thrust vectoring engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108482633A true CN108482633A (en) | 2018-09-04 |
Family
ID=63338360
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810198561.5A Pending CN108482633A (en) | 2018-03-12 | 2018-03-12 | A kind of thrust vectoring engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108482633A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2583971A (en) * | 2019-05-16 | 2020-11-18 | Autonomous Devices Ltd | Control arrangement for fluid borne vehicles |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2014168511A1 (en) * | 2013-04-12 | 2014-10-16 | Общество с ограниченной ответственностью ОКБ "АТЛАНТ" | Power plant with a variable thrust vector |
| US20150007550A1 (en) * | 2006-12-18 | 2015-01-08 | Aerojet Rocketdyne, Inc. | Combined Cycle Integrated Combustor and Nozzle System |
| CN104590535A (en) * | 2014-08-19 | 2015-05-06 | 中国特种飞行器研究所 | Propelling device for airship power device |
| RU2570743C2 (en) * | 2014-04-17 | 2015-12-10 | Открытое Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка" | Control over aircraft equipped with engine with jet nozzles |
-
2018
- 2018-03-12 CN CN201810198561.5A patent/CN108482633A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150007550A1 (en) * | 2006-12-18 | 2015-01-08 | Aerojet Rocketdyne, Inc. | Combined Cycle Integrated Combustor and Nozzle System |
| WO2014168511A1 (en) * | 2013-04-12 | 2014-10-16 | Общество с ограниченной ответственностью ОКБ "АТЛАНТ" | Power plant with a variable thrust vector |
| RU2570743C2 (en) * | 2014-04-17 | 2015-12-10 | Открытое Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка" | Control over aircraft equipped with engine with jet nozzles |
| CN104590535A (en) * | 2014-08-19 | 2015-05-06 | 中国特种飞行器研究所 | Propelling device for airship power device |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2583971A (en) * | 2019-05-16 | 2020-11-18 | Autonomous Devices Ltd | Control arrangement for fluid borne vehicles |
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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: 20180904 |