CN102745332A - Pneumatic type power augmenting device - Google Patents
Pneumatic type power augmenting device Download PDFInfo
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- CN102745332A CN102745332A CN2012102619337A CN201210261933A CN102745332A CN 102745332 A CN102745332 A CN 102745332A CN 2012102619337 A CN2012102619337 A CN 2012102619337A CN 201210261933 A CN201210261933 A CN 201210261933A CN 102745332 A CN102745332 A CN 102745332A
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- augmenting
- type power
- pneumatic type
- drainage system
- drainage device
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Abstract
The invention relates to a pneumatic type power augmenting device, which solves the technical problem that current augmenting devices are undesirable in augmenting effect in varying degrees and are hard to implement due to complex mechanisms. The invention provides the pneumatic type power augmenting device which consists of a drainage device, an adjusting device and an engine nozzle. The drainage device is located at a jet flow opening of an engine. Both ends of a flow guide plate of the drainage device are fixed near the center of gravity of a device body through a rotary shaft. The flow guide plate of the drainage device is controlled by the adjusting device to form an airflow angle of attack by rotation on the rotary shaft. The invention has the beneficial effects and advantages that the device is simple in structure, and remarkable in augmenting effect. The device is applied so that short take-off and landing and vertical take-off and landing technologies are more easily realized. An additional lift force can be provided by the drainage device and the thrust is affected minimally. Position of the drainage device is controlled by the adjusting device to achieve the purpose of controlling the lift force. If the device generates an unexpected pitch moment while augmenting, the pitch moment is eliminated by a jet vane installed behind the flow guide plate, thus achieving an effect of balancing.
Description
Technical field:
The present invention relates to a kind of aircraft high lift device, relate in particular to a kind of pneumatic type power-boosting device.Belong to field of aerospace technology.
Background technology:
The aircraft high lift device can be divided into aerodynamic force high lift device, jet flow high lift device and power-boosting device substantially at present.During the aerodynamic force high lift device has been widely used in airplane design and has made such as aircraft flap; The jet flow high lift device Journal of Sex Research that experimentizes at present, increasing extra jet flow through wing, to make lower aerofoil produce speed poor, adds lift thereby produce; The current driving force high lift device is to turn to through increase barrier or engine nozzle to change the jet cutting car flow direction, such as 90 degree, thereby realizes the thrust lift-rising.
Above-mentioned high lift device or lift-rising effect are limited, or mechanism is complicated, are difficult to realize.
Summary of the invention:
The present invention for solve present high lift device in various degree have a lift-rising effect technical matters undesirable and that be difficult to realize owing to mechanism is complicated; A kind of pneumatic type power-boosting device is provided, and this device is made up of drainage system, control apparatus and engine nozzle; Said drainage system is positioned at the flow jeting port place of driving engine, and the deflecting plate two ends of said drainage system are fixed on the body nodal point vicinity through S. A.; And pass through the deflecting plate that said control apparatus is controlled drainage system, on S. A., rotate and form the air-flow angle of attack.
Beneficial effect of the present invention and characteristics: this apparatus structure is simple, and the lift-rising effect is obvious.The application of this device makes STOL and vertical takeoff and landing (VTOL) technology be easy to more realize.Be in particular in:
Through drainage system additional lift can be provided, minimum to the thrust influence simultaneously;
Through control apparatus control drainage system position, play the purpose of control lift size;
If this high lift device produces the pitching moment of not expecting in lift-rising, then eliminate pitching moment through the gas rudder that is installed in behind the deflecting plate, play equilibrium activity.
Description of drawings:
Fig. 1 structural representation of the present invention
The specific embodiment:
Referring to Fig. 1, pneumatic type power-boosting device, this device is made up of the flow jeting port 4 of drainage system 2, control apparatus and driving engine 3; Said drainage system 2 is positioned at flow jeting port 4 places of driving engine 3, and deflecting plate 5 two ends of said drainage system 2 are fixed on fuselage 1 center of gravity (midway location) vicinity through S. A. 6; And through said control apparatus and drainage system 2 control linkages.
Deflecting plate 5 above and belows at said driving engine 3 are clearance envelope, and all not having other device influences air velocity distribution.
The shape of said deflecting plate 5 is supersonic airfoil or subsonic airfoil according to the jet cutting car flow speed selection; Select high temperature material according to the jet flow temperature.
Principle of work: through the jet flow flow field analysis is calculated, the design drainage system is realized power-boosting.Flow through drainage system through jet cutting car flow and produce aerodynamic force, realize additional lift.
Embodiment:
Pneumatic type power-boosting device is installed on the middle part (body center of gravity place) of unmanned aerial vehicle body 1, and this device is made up of the flow jeting port 4 of drainage system 2, control apparatus and driving engine 3; Said drainage system 2 is oppositely arranged with the flow jeting port 4 of driving engine 3, and deflecting plate 5 two ends of drainage system 2 are fixed on the fuselage 1 of both sides through S. A. 6 respectively; This drainage system 2 plays the purpose of control lift size through the position of its deflecting plate 5 of control apparatus control; If this high lift device produces the pitching moment of not expecting in lift-rising, then eliminate pitching moment through the gas rudder that is installed in behind the deflecting plate, play equilibrium activity.Can increase lift through this device, reduction is taken off with sinking speed and is reduced runway distance.
Claims (3)
1. pneumatic type power-boosting device, it comprises nozzle (3), it is characterized in that: this device also comprises drainage system (2) and control apparatus; Said drainage system (2) is positioned at the flow jeting port (4) of nozzle (3) to be located, and deflecting plate (5) two ends of said drainage system (2) are fixed near fuselage (1) center of gravity through S. A. (6); And pass through the deflecting plate (5) that said control apparatus is controlled drainage system (2), go up at S. A. (6) and rotate the formation air-flow angle of attack.
2. a kind of pneumatic type power-boosting device according to claim 1 is characterized in that: deflecting plate (5) above and below in said driving engine (3) is a clearance envelope, and all not having other device influences air velocity distribution.
3. a kind of pneumatic type power-boosting device according to claim 1 is characterized in that: the shape of said deflecting plate (5) is supersonic airfoil or subsonic airfoil according to the jet cutting car flow speed selection; Select high temperature material according to the jet flow temperature.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210261933.7A CN102745332B (en) | 2012-07-26 | 2012-07-26 | Pneumatic type power augmenting device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210261933.7A CN102745332B (en) | 2012-07-26 | 2012-07-26 | Pneumatic type power augmenting device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102745332A true CN102745332A (en) | 2012-10-24 |
| CN102745332B CN102745332B (en) | 2014-11-05 |
Family
ID=47025931
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210261933.7A Active CN102745332B (en) | 2012-07-26 | 2012-07-26 | Pneumatic type power augmenting device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102745332B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116793690A (en) * | 2023-08-29 | 2023-09-22 | 绵阳亿丰达智能装备有限公司 | Automatic overturning water pouring equipment for engine |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1289705A (en) * | 2000-11-10 | 2001-04-04 | 贾龙 | Flying method and equipment |
| CN1074373C (en) * | 1995-09-29 | 2001-11-07 | 克里斯蒂安·奥德纳松工程公司 | Aircraft with jet flap propulsion |
| CN2542560Y (en) * | 2002-04-30 | 2003-04-02 | 广州天象地效飞行器股份有限公司 | Ground surface effect aircraft having special pneumatic layout |
-
2012
- 2012-07-26 CN CN201210261933.7A patent/CN102745332B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1074373C (en) * | 1995-09-29 | 2001-11-07 | 克里斯蒂安·奥德纳松工程公司 | Aircraft with jet flap propulsion |
| CN1289705A (en) * | 2000-11-10 | 2001-04-04 | 贾龙 | Flying method and equipment |
| CN2542560Y (en) * | 2002-04-30 | 2003-04-02 | 广州天象地效飞行器股份有限公司 | Ground surface effect aircraft having special pneumatic layout |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116793690A (en) * | 2023-08-29 | 2023-09-22 | 绵阳亿丰达智能装备有限公司 | Automatic overturning water pouring equipment for engine |
| CN116793690B (en) * | 2023-08-29 | 2023-11-03 | 绵阳亿丰达智能装备有限公司 | Automatic overturning water pouring equipment for engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102745332B (en) | 2014-11-05 |
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| C06 | Publication | ||
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| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
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| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of invention: Pneumatic type power augmenting device Effective date of registration: 20170411 Granted publication date: 20141105 Pledgee: Shengjing bank Limited by Share Ltd Shenyang Tianhe branch Pledgor: Shenyang Shenlan Aviation Technology Co., Ltd. Registration number: 2017210000009 |
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| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20180608 Granted publication date: 20141105 Pledgee: Shengjing bank Limited by Share Ltd Shenyang Tianhe branch Pledgor: Shenyang Shenlan Aviation Technology Co., Ltd. Registration number: 2017210000009 |