CN2542561Y - Ground surface effect aircraft having dynamic augment - Google Patents
Ground surface effect aircraft having dynamic augment Download PDFInfo
- Publication number
- CN2542561Y CN2542561Y CN 02227332 CN02227332U CN2542561Y CN 2542561 Y CN2542561 Y CN 2542561Y CN 02227332 CN02227332 CN 02227332 CN 02227332 U CN02227332 U CN 02227332U CN 2542561 Y CN2542561 Y CN 2542561Y
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- wing
- propeller
- boosting
- cavity
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Abstract
A ground-effect vehicle with power augmentation comprises an airframe, a wing, a motor and a propeller driven by the motor. The motor and the propeller are arranged in the front of the wing, and an augmentation cavity is arranged under the airframe and the wing, and the propeller is a duct propeller, the back of which is provided with a flow fence which can guide the air current generated by the duct propeller into the augmentation cavity. Because the high-energy air current generated by the duct propeller is guided into the augmentation cavity formed by the wing, the airframe, the wing flap, the end plate and the water surface, when the air current is hindered in the cavity, the kinetic energy of the air current changes to pressure energy, and the pressure acting on the below of the wing can generate the cushion lift force. When the vehicle takes off, the sliding resistance can be reduced with the help of the cushion life force, and the vehicle leaves water rapidly, achieving the effect of augmentation. Moreover, when the vehicle lands, the cushion life force in the augmentation cavity generates a certain counter pressure, reducing the impact with water and ensuring steadier landing on the water.
Description
Technical field
The utility model relates to a kind of aircraft, particularly a kind of ground effect vehicle with power-boosting system.
Background technology
Rely on the ground effect vehicle of water surface landing, because the density ratio air of water is big more than 800 times, so aircraft need overcome very big resistance and just can take off, solve and address this problem the common way that needs employing to strengthen engine power, power this moment required power when aircraft cruises, such power preparation obviously is irrational, disclosed a kind of " ground effect vehicle of also able to fly " in the Chinese patent 99122366.7, these proprietary design main points are to meet on the basis of general structural principle at ground effect vehicle, how the aircraft of research and design with the function of soaring emphatically overcomes to original ground effect vehicle that the big problem of resistance does not have when taking off
Relate to And
Summary of the invention
It is a kind of according to the ground effect region flow feature that the purpose of this utility model is to provide, and makes by rational power configuration that lift increases when taking off, the ground effect vehicle with power-boosting that resistance reduces.
The utility model comprises the screw propeller of fuselage, wing, driving engine and drive thereof, driving engine and propeller arrangement are at the leading edge of a wing, described fuselage and wing below are provided with boosting air cavity, described screw propeller is a shrouded propeller, and this shrouded propeller rear portion is provided with the flow deflector in the air-flow importing boosting air cavity that the shrouded propeller rotation can be produced.
The utility model is owing to high energy air-flow behind the shrouded propeller being imported the boosting air cavity that is made of wing, fuselage, wing flap, end plate and the water surface, after air-flow is obstructed in the chamber, airflow kinetic energy changes the pressure energy into, the pressure that acts on below the wing can produce the lift that hovers, make it in take-off process, can be by the lift divergence resistance of taxing that hovers, dried up rapidly, play the effect of lift-rising, in addition, when landing, the cushion lift in the boosting air cavity also produces certain back-pressure, make the bump of its minimizing and water, it is more stable water.
Description of drawings
Fig. 1 is an overall layout chart of the present utility model;
Fig. 2 is a front view of the present utility model.
Fig. 3 is the utility model power-boosting system architecture scheme drawing.
The specific embodiment
Comprise fuselage 1, wing 2, driving engine 4 and the screw propeller that drives thereof as Fig. 1 Fig. 2 the utility model shown in Figure 3, driving engine 4 is installed in wing 2 leading edges, screw propeller links to each other with driving engine by transmission shaft, described fuselage 1 is provided with boosting air cavity 3 with wing 2 belows, described screw propeller is a shrouded propeller 6, and these shrouded propeller 6 rear portions are provided with the flow deflector 5 in the air-flow importing boosting air cavity 3 that shrouded propeller 6 rotations can be produced.When air-flow is blocked in the chamber, kinetic energy changes the pressure energy into, and the additonal pressure that acts on wing 2 lower surfaces produces the additional lift that hovers, and the lift that hovers can lift aircraft, reduce the area that aircraft contacts with water, thereby reduced the aircraft resistance of taxing.Above-mentioned boosting air cavity 3 is the cavity of being made up of the end plate 7 at fuselage 1 bottom, wing 2 belows, wing 2 two ends and wing 2 trailing edge flaps 8, and wherein wing flap 8 is provided with and can makes its actuating device around wing 2 trailing edge deflections.Above-mentioned flow deflector 5 by some movable wings of unequal length that are along shrouded propeller 6 duct trailing edge horizontally sets, be provided with the mechanism that can make its work coordinate deflection between each flow deflector (5), above-mentioned flow deflector (5) is provided with the actuating device around the deflection of shrouded propeller (6) duct trailing edge.Above-mentioned
DriveThe hydraulic control system of device for handling synchronously wing flap 8 and flow deflector 5, above-mentioned wing flap 8 and flow deflector 5 are respectively equipped with the operating bar of being handled by hydraulic control system.Described hydraulic control system is made up of electric hydraulic pump, solenoid directional control valve, reducing valve, hydraulic actuating cylinder, described hydraulic ram is arranged at wing 2 trailing edges and shrouded propeller 6 sides respectively, described operating bar one end links to each other with piston in the hydraulic actuating cylinder, and the other end joins with wing flap 8 and flow deflector 5 respectively.Described flow deflector 5 hydraulic control systems and the same hydraulic power source of wing flap 8 hydraulic control systems make flow deflector 5 and wing flap 8 can carry out synchronous manipulation.Flight test confirms that wing flap 8 deflections 5 degree, flow deflector 5 deflections 20 degree are packed up in dried up back 15 seconds simultaneously when taking off, and can make ground effect vehicle successfully dried up and carry out the transition to cruising condition, and whole process operation is easy, flight attitude stable.Above-mentioned wing flap (8) is a rectangle, its pivot angle be 0～30 ° adjustable.Be provided with transmission shaft (14) between above-mentioned driving engine and the shrouded propeller, transmission shaft (14) two ends be provided with for driving engine and shrouded propeller (6) between the elastic coupling that connects.
Claims (6)
1, a kind of ground effect vehicle with power-boosting, comprise fuselage (1), wing (2), driving engine (4) and the screw propeller that drives thereof, driving engine (4) and propeller arrangement are in wing (2) leading edge, it is characterized in that described fuselage (1) and wing (2) below are provided with boosting air cavity (3), described screw propeller is shrouded propeller (6), and this shrouded propeller rear portion is provided with the air-flow that shrouded propeller (6) rotation can be produced and imports the interior flow deflector of boosting air cavity (3).
2, the ground effect vehicle with power-boosting according to claim 1, it is characterized in that above-mentioned boosting air cavity (4) is that wherein wing flap (8) is provided with and can makes its actuating device around wing (2) trailing edge deflection by fuselage (1) bottom, wing (2) below, the end plate (7) at wing (2) two ends and the cavity that wing (2) trailing edge flap (8) is formed.
3, the ground effect vehicle with power-boosting according to claim 1, it is characterized in that above-mentioned flow deflector (5) by some movable wings of unequal length that are along shrouded propeller (6) duct back cavity horizontally set, be provided with the mechanism that can make its work coordinate deflection between each flow deflector (5), above-mentioned flow deflector (5) is provided with the actuating device around the deflection of shrouded propeller (6) duct trailing edge.
4, according to the ground effect vehicle of claim 2 or the 3 described power-boostings that have, it is characterized in that the hydraulic control system of above-mentioned actuating device for handling synchronously wing flap and flow deflector, above-mentioned wing flap (8) and flow deflector (5) are respectively equipped with the operating bar by the hydraulic control system manipulation.
5,, it is characterized in that above-mentioned wing flap (8) angle of inclination are 0～30 degree according to the ground effect vehicle of the described power-boosting that has of claim 2.
6, the ground effect vehicle with power-boosting according to claim 1, it is characterized in that being provided with transmission shaft (14) between above-mentioned driving engine (4) and the shrouded propeller (6), this transmission shaft (14) two ends be provided with for driving engine and shrouded propeller between the elastic coupling that connects.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 02227332 CN2542561Y (en) | 2002-04-30 | 2002-04-30 | Ground surface effect aircraft having dynamic augment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 02227332 CN2542561Y (en) | 2002-04-30 | 2002-04-30 | Ground surface effect aircraft having dynamic augment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2542561Y true CN2542561Y (en) | 2003-04-02 |
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ID=33704137
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 02227332 Expired - Fee Related CN2542561Y (en) | 2002-04-30 | 2002-04-30 | Ground surface effect aircraft having dynamic augment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2542561Y (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009111916A1 (en) * | 2008-03-13 | 2009-09-17 | Tian Yu | Remote control model aircraft |
| CN106585959A (en) * | 2016-09-30 | 2017-04-26 | 朱晓义 | High-speed aerobat for generating great lift force |
| US10464668B2 (en) | 2015-09-02 | 2019-11-05 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| US10875658B2 (en) | 2015-09-02 | 2020-12-29 | Jetoptera, Inc. | Ejector and airfoil configurations |
| US11001378B2 (en) | 2016-08-08 | 2021-05-11 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| US11148801B2 (en) | 2017-06-27 | 2021-10-19 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| CN113665823A (en) * | 2021-08-16 | 2021-11-19 | 航天时代飞鹏有限公司 | Hybrid type freight unmanned aerial vehicle and cargo transportation method |
-
2002
- 2002-04-30 CN CN 02227332 patent/CN2542561Y/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009111916A1 (en) * | 2008-03-13 | 2009-09-17 | Tian Yu | Remote control model aircraft |
| US10464668B2 (en) | 2015-09-02 | 2019-11-05 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| US10875658B2 (en) | 2015-09-02 | 2020-12-29 | Jetoptera, Inc. | Ejector and airfoil configurations |
| US11001378B2 (en) | 2016-08-08 | 2021-05-11 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| CN106585959A (en) * | 2016-09-30 | 2017-04-26 | 朱晓义 | High-speed aerobat for generating great lift force |
| US11148801B2 (en) | 2017-06-27 | 2021-10-19 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| CN113665823A (en) * | 2021-08-16 | 2021-11-19 | 航天时代飞鹏有限公司 | Hybrid type freight unmanned aerial vehicle and cargo transportation method |
| CN113665823B (en) * | 2021-08-16 | 2024-05-10 | 航天时代飞鹏有限公司 | Hybrid freight unmanned aerial vehicle and freight transportation method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20030402 Termination date: 20110430 |