CN200985094Y - Power increasing device for ground effect aircraft - Google Patents
Power increasing device for ground effect aircraft Download PDFInfo
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- CN200985094Y CN200985094Y CN 200620016726 CN200620016726U CN200985094Y CN 200985094 Y CN200985094 Y CN 200985094Y CN 200620016726 CN200620016726 CN 200620016726 CN 200620016726 U CN200620016726 U CN 200620016726U CN 200985094 Y CN200985094 Y CN 200985094Y
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- thruseer
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- 230000000694 effects Effects 0.000 title claims abstract description 27
- 230000003028 elevating effect Effects 0.000 claims description 7
- 230000008676 import Effects 0.000 claims description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 abstract description 8
- 238000000034 method Methods 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 230000002706 hydrostatic effect Effects 0.000 description 1
- 238000011112 process operation Methods 0.000 description 1
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Abstract
The utility model discloses a power increasing device of a wing in surface crafts which aims at solving the problem of providing a power increasing device of the wing in surface crafts which can increase the lift force and reduce resistance when taking off through rational power distribution according to the characteristics of the airflow. The utility model adopts the technical proposal to solve the problem: a power increasing device comprises an airframe, wings, an empennage and boosters arranged at the two sides of the head of the airframe; the airframe and the wings are provided with increasing air cavities at the beneath; the booster is provided with a direction changing nozzle to guide the cascade generated by the booster to the increasing air cavities. The utility model guides the high energy airflow generated by the booster to the increasing air cavity, changes the kinetic energy of the airflow to pressure energy, produces hovering force to the wings so as to lift the crafts when taking off thereby reducing the sliding resistance to make the crafts depart from the water to get the effect of increasing and lifting. The maximum taking off weight of the maritime passenger and cargo transportation of the utility model can reach 390 ton.
Description
Technical field
The utility model relates to a kind of ground effect vehicle, especially a kind of power-boosting device of ground effect vehicle.
Background technology
Ground effect vehicle takes off from the sea, is quickened to slide by low speed water skiing state, produces the lift that rises up to wing and progressively is increased to the process that whole aircraft is lifted away from the water surface, need overcome the large drag forces of water.Solve if adopt to strengthen the way of engine power, then needed engine power required power when aircraft cruises, such power configuration obviously is irrational.Therefore, adopting the power-boosting device of reasonable disposition, obtain big additional lift when making the aircraft takeoff water skiing, make its rapid lifting to reduce the resistance of water, is very necessary to ground effect vehicle by the state that water takeoff carries out the transition to cruising flight.Open day be the Chinese utility model patent 02227332.8 on April 2nd, 2003 disclosed a kind of take-off weight that adopts screw propeller to drive only be inland lake, inland river about 5 tons with the power-boosting device of low-speed small ground effect vehicle, but be not suitable for the large high-speed ground effect vehicle that adopts high-power jet power unit.
Summary of the invention
The purpose of this utility model is to provide a kind of power-boosting device of ground effect vehicle, and its technical matters that will solve is according to the ground effect region flow feature, and lift increase, resistance reduce when by rational power configuration ground effect vehicle being taken off.
For addressing the above problem the utility model by the following technical solutions: a kind of power-boosting device of ground effect vehicle, comprise fuselage, wing and device thruseer in the fuselage head both sides, described fuselage and wing below are provided with boosting air cavity, and described thruseer is provided with the spout that turns to that the jet flow that driving engine is produced imports boosting air cavity.
Fuselage described in the utility model is made up of forebody, middle machine body and rear body, and described boosting air cavity is by middle machine body bottom, wing below, the dividing plate at wing two ends and the cavity that the trailing edge wing flap is formed.
Wing flap described in the utility model is provided with and can makes its actuating device around trailing edge deflection, and described forebody is provided with the actuating device that turns to spout deflection that makes thruseer.
Thruseer described in the utility model is four and places the forebody both sides in twos symmetrically with respect to vertical symmetry plane that every side is to settle before and after the tandem arrangement mode.
Front-seat thruseer axis described in the utility model is spent to 11 degree with respect to level reference declivity 9, spend to 22 degree with respect to vertical symmetry plane outer oblique 18, back row's engine axis with respect to level reference declivity 9 degree to 11 degree, with respect to outer oblique 14 degree of vertical symmetry plane to 16 degree.
Front-seat thruseer axis described in the utility model is with respect to level reference declivity 10 degree, and with respect to outer oblique 20 degree of vertical symmetry plane, back row's engine axis is with respect to level reference declivity 10 degree, with respect to outer oblique 15 degree of vertical symmetry plane.
Thruseer described in the utility model turns to the axis of spout to spend the supreme inclined to one side 10 scope intrinsic deflections of spending following inclined to one side 15.
The elevating rudder of horizontal tail trailing edge described in the utility model is provided with the actuating device that makes deflect on it.
Wing flap described in the utility model, thruseer turn to the actuating device of spout and elevating rudder deflection to be separately hydraulic sterring engine, and by the unified control of fly-by-wire.
Wing flap described in the utility model is a rectangle, can be at the scope intrinsic deflection of 0 degree to 20 degree.
The utility model compared with prior art, the high energy air-flow that thruseer is produced imports boosting air cavity, airflow kinetic energy is changed into the pressure energy, wing is produced the lift that hovers, it is lifted aircraft in take-off process, thereby reduce resistance of taxing, make aircraft dried up rapidly, play the effect of lift-rising, the maximum take-off weight that is applied to marine passenger and freight transportation can reach 390 tons.
Description of drawings
Fig. 1 is an integral structure scheme drawing of the present utility model.
Fig. 2 is a working state schematic representation of the present utility model.
Fig. 3 turns to the constructional drawing of spout for the utility model thruseer.
The specific embodiment
The utility model will be further described below in conjunction with accompanying drawing.
As depicted in figs. 1 and 2, the utility model comprises forebody 1, middle machine body 2, rear body 3, wing 5, thruseer 7 and turns to spout 8, thruseer 7 is installed in forebody 1 both sides, described middle machine body 2 is provided with boosting air cavity 9 with wing 5 belows, and described thruseer 7 is provided with the jet flow of its generation to be imported and turns to spout 8 in the boosting air cavity 9.When jet flow is blocked in boosting air cavity, kinetic energy changes the pressure energy into, and the additonal pressure that acts on wing 5 lower surfaces produces the additional lift that hovers, and the lift that hovers can lift aircraft, reduce aircraft and be immersed in part body in the water, thereby reduced the aircraft resistance of taxing.Described boosting air cavity 9 is the cavity of being made up of the dividing plate 6 at middle machine body 2 bottoms, wing 5 belows, wing 5 two ends and wing 5 trailing edge flaps 4, and wherein wing flap 4 is provided with and can makes its actuating device around wing 5 trailing edge deflections.Described forebody 1 is provided with the actuating device that turns to spout 8 deflections that makes thruseer 7.
The utility model wing flap 4 and thruseer 7 turn to spout 8 deflections the time, will cause the variation of full machine longitudinal moment, the elevating rudder 11 that at this moment needs deflection horizontal tail 10 trailing edges is to keep the balance in pitch of full machine.Above-mentioned elevating rudder 11 is provided with the actuating device that makes deflect on it.The actuating device that turns to spout 8 and elevating rudder 11 deflections of wing flap 4 as shown in Figure 3, thruseer 7 is hydraulic sterring engine separately, by the unified control of fly-by-wire, also is that three's deflection is carried out synchronously by chaufeur.
Described wing flap 4 is a rectangle, can be at the scope intrinsic deflection of 0 degree to 20 degree.
Improve air-cushion force with the suitable even angle ground directive air cavity 9 that hovers with highland as far as possible for ease of the tail jet of above-mentioned thruseer 7, the utility model is provided with four thruseers 7, thruseer 7 places forebody 1 both sides in twos symmetrically with respect to vertical symmetry plane, and every side is to settle before and after the tandem arrangement mode.To 11 degree, spend to 22 degree with respect to vertical symmetry plane outer oblique 18, preferred 20 degree by preferred 10 degree with respect to level reference declivity 9 degree for front row thruseer axis.After queue fly engine axis with respect to level reference declivity 9 degree to 11 degree, preferred 10 degree, with respect to outer oblique 14 degree of vertical symmetry plane to 16 degree, preferred 15 degree.Thruseer turns to the axis of spout 8 to spend the supreme inclined to one side 10 scope intrinsic deflections of spending following inclined to one side 15.
The hover performance of the utility model power-boosting device is: the lift that hovers is 2.5 times of thruseer tension level direction component the dried up moment of take-off run in the hydrostatic; Stormy waves increases, and the effect that hovers descends to some extent.Under Pyatyi wave condition, the additional lift that hovers is 1.2 times of thruseer tension level direction component.The utility model power-boosting device can make the successfully dried up cruising condition that carries out the transition to of ground effect vehicle, and whole process operation is easy, and flight attitude is stable.Adopt the passenger-cargo ground effect vehicle in large-scale sea of the present utility model, its take-off weight can reach 390 tons.
Claims (10)
1. the power-boosting device of a ground effect vehicle, comprise fuselage, wing and device thruseer in the fuselage head both sides, described fuselage and wing below are provided with boosting air cavity, it is characterized in that: described thruseer is provided with the spout that turns to that the jet flow that driving engine is produced imports boosting air cavity.
2. according to the power-boosting device of the described ground effect vehicle of claim 1, it is characterized in that:
Described fuselage is made up of forebody, middle machine body and rear body, and described boosting air cavity is by middle machine body bottom, wing below, the dividing plate at wing two ends and the cavity that the trailing edge wing flap is formed.
3. according to the power-boosting device of the described ground effect vehicle of claim 2, it is characterized in that:
Described wing flap is provided with and can makes its actuating device around trailing edge deflection, and described forebody is provided with the actuating device that turns to spout deflection that makes thruseer.
4. according to the power-boosting device of the described ground effect vehicle of claim 3, it is characterized in that:
Described thruseer is four and places the forebody both sides in twos symmetrically with respect to vertical symmetry plane that every side is to settle before and after the tandem arrangement mode.
5. according to the power-boosting device of the described ground effect vehicle of claim 4, it is characterized in that:
Described front-seat thruseer axis with respect to level reference declivity 9 degree to 11 degree, with respect to outer oblique 18 degree of vertical symmetry plane to 22 degree, back row's engine axis with respect to level reference declivity 9 degree to 11 degree, with respect to outer oblique 14 degree of vertical symmetry plane to 16 degree.
6. according to the power-boosting device of the described ground effect vehicle of claim 5, it is characterized in that:
Described front-seat thruseer axis is with respect to level reference declivity 10 degree, and with respect to outer oblique 20 degree of vertical symmetry plane, back row's engine axis is with respect to level reference declivity 10 degree, with respect to outer oblique 15 degree of vertical symmetry plane.
7. according to the power-boosting device of claim 5 or 6 described ground effect vehicles, it is characterized in that: described thruseer turns to the axis of spout to spend the supreme inclined to one side 10 scope intrinsic deflections of spending following inclined to one side 15.
8. according to the power-boosting device of the described ground effect vehicle of claim 1, it is characterized in that:
The elevating rudder of described horizontal tail trailing edge is provided with the actuating device that makes deflect on it.
9. the power-boosting device of described ground effect vehicle according to Claim 8 is characterized in that:
Described wing flap, thruseer turn to the actuating device of spout and elevating rudder deflection to be separately hydraulic sterring engine, and by the unified control of fly-by-wire.
10. according to the power-boosting device of the described ground effect vehicle of claim 9, it is characterized in that:
Described wing flap is a rectangle, can be at the scope intrinsic deflection of 0 degree to 20 degree.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200620016726 CN200985094Y (en) | 2006-12-22 | 2006-12-22 | Power increasing device for ground effect aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200620016726 CN200985094Y (en) | 2006-12-22 | 2006-12-22 | Power increasing device for ground effect aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN200985094Y true CN200985094Y (en) | 2007-12-05 |
Family
ID=38914553
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200620016726 Expired - Lifetime CN200985094Y (en) | 2006-12-22 | 2006-12-22 | Power increasing device for ground effect aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN200985094Y (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104608874A (en) * | 2014-12-15 | 2015-05-13 | 中国特种飞行器研究所 | Hovering type high-performance ground effect ship |
| CN109383789A (en) * | 2018-11-21 | 2019-02-26 | 南京航空航天大学 | High lift device and its application |
-
2006
- 2006-12-22 CN CN 200620016726 patent/CN200985094Y/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104608874A (en) * | 2014-12-15 | 2015-05-13 | 中国特种飞行器研究所 | Hovering type high-performance ground effect ship |
| CN104608874B (en) * | 2014-12-15 | 2017-02-01 | 中国特种飞行器研究所 | Hovering type high-performance ground effect ship |
| CN109383789A (en) * | 2018-11-21 | 2019-02-26 | 南京航空航天大学 | High lift device and its application |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C56 | Change in the name or address of the patentee |
Owner name: CHINA ACADEMY OF SCIENCE + TECHNOLOGY DEVELOPMENT Free format text: FORMER NAME: CHINA SCIENCE + TECHNOLOGY DEVELOPMENT INST. |
|
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 518052, Guangdong, Nanshan District science and Technology Park, Shenzhen science and technology south ten road, research and Development Park, new industry incubator center building, nine floor, East Patentee after: China Science and Technology Development Institute Co Ltd Address before: 518052 Guangdong city of Shenzhen province Nanshan District Gao Xin Road Patentee before: China Science & Technology Development Inst. |
|
| CX01 | Expiry of patent term |
Granted publication date: 20071205 |
|
| EXPY | Termination of patent right or utility model |