CN103192989A - Land ground effect aircraft - Google Patents
Land ground effect aircraft Download PDFInfo
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- CN103192989A CN103192989A CN2013101194067A CN201310119406A CN103192989A CN 103192989 A CN103192989 A CN 103192989A CN 2013101194067 A CN2013101194067 A CN 2013101194067A CN 201310119406 A CN201310119406 A CN 201310119406A CN 103192989 A CN103192989 A CN 103192989A
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Abstract
The invention relates to the field of aircrafts, and in particular relates to a land ground effect aircraft. The land ground effect aircraft comprises a propelling device, an engine, a main aerofoil, an undercarriage, a tail wing and an aircraft body; the aircraft body is provided with the engine which is connected with the propelling device through a rotary shaft and is used for driving the propelling device so as to provide power for the aircraft; the main aerofoil is fixed at two sides of the aircraft body, and connecting lines of tail tips at two ends of the main aerofoil are in parallel to a cross shaft of the aircraft; the tail wing is fixedly connected with the tail part of the aircraft body; the bottom of the aircraft body is provided with the undercarriage; the aircraft body and the lower surface of the main aerofoil form a semi-sealed cavity body which is a lift augmentation air cavity; high-speed air steams flow into the lift augmentation air cavity for generating a greater pad lift force. The land ground effect aircraft provided by the invention can take off and land for being provided with the undercarriage, and requirements of material quality, structure and power system of the aircraft are low, so the production cost is reduced.
Description
Technical field
The present invention relates to the aircraft field, in particular to the land ground effect vehicle.
Background technology
Ground effect vehicle is also referred to as wing ground effect machine, is a kind of aircraft that utilizes the effect flight of wing ground, is a kind of novel high speed aircraft between aircraft, naval vessel and air cushion vehicle.Ground effect vehicle is mainly at ground effect region flight, just ground proximity, water surface flying.When aircraft ground proximity or water surface flying, air flow stream can flow to the back lower place after crossing wing, at this moment ground or the water surface will produce one antagonistic force, when aircraft when ground effect region flies, the difference of pressure up and down of whole machine body increases, lift can suddenly increase, and resistance reduces, and stops the aircraft wing tenesmus.
In the prior art, ground effect vehicle generally can only take off and lands at the water surface, can not take off on land and land.Because the speed of aircraft takeoff or landing is very fast, the application force of body and the water surface is very big, and is high to material, structure and the power system requirement of aircraft, so the productive costs height.
Summary of the invention
The object of the present invention is to provide the land ground effect vehicle, to solve the above problems.
The land ground effect vehicle is provided in an embodiment of the present invention, has comprised: propelling unit, driving engine, host wing, alighting gear, empennage and fuselage; Described fuselage is provided with described driving engine, and described driving engine is connected with described propelling unit by rotating shaft, is used for driving propelling unit, for aircraft provides power; Described host wing is fixed on the both sides of described fuselage, the line of its two ends tip and aircraft transverse axis; Described empennage is captiveed joint with the afterbody of described fuselage; The bottom of described fuselage is provided with described alighting gear; The semi-enclosed cavity that the lower surface of described fuselage and described host wing constitutes is boosting air cavity, and high velocity air flows into described boosting air cavity, for generation of bigger air-cushion force.
The land ground effect vehicle of the above embodiment of the present invention because this land ground effect vehicle is provided with alighting gear, can take off and land on the ground, and is lower to material, structure and the power system requirement of aircraft, reduced productive costs.
Description of drawings
Fig. 1 shows the front view of land of the present invention ground effect vehicle;
Fig. 2 shows the lateral plan of land of the present invention ground effect vehicle;
Fig. 3 shows the lateral plan of the twin vertical fin wing among the present invention.
Among the figure: 1 screw propeller, 2 driving engines, 3 host wings
4 little wing 5 ailerons 6 wing flaps
7 tailplanes, 8 elevating rudders, 9 alighting gears
10 vertical tails, 11 fuselages, 12 end plates
The specific embodiment
Also by reference to the accompanying drawings the present invention is described in further detail below by specific embodiment.
As depicted in figs. 1 and 2, land provided by the invention ground effect vehicle aircraft comprises: propelling unit, driving engine 2, host wing 3, empennage, alighting gear 9 and fuselage 11; Fuselage 11 is provided with driving engine 2, and the position of driving engine 2 can be arranged on any position of fuselage 11, and it can fixedly mount, also can whole deflection.Driving engine 2 is connected with propelling unit by rotating shaft, and driving engine 2 drives propelling unit and rotates, and is used for propelling unit, and for aircraft provides power, wherein propelling unit can be screw propeller 1, also can be ducted fan.Screw propeller 1 can adopt fixed angle to install, but also can adopt deflection to install.Host wing 3 is fixed on the both sides of fuselage 11, the line of its two ends tip and aircraft transverse axis.Empennage is captiveed joint with the afterbody of fuselage 11.Empennage can be vee tail, also can be the T type tail, can also be the twin vertical fin wing.The T type tail comprises tailplane 7 and vertical tail 10, vertical tail 10 is connected with the afterbody vertical fixing of fuselage 11, tailplane 7 is fixed on the vertical tail 10, tailplane 7 is "T"-shaped with the longitudinal cross-section of vertical tail 10, tailplane 7 both can be integrative-structure, also can adopt the branch body structure, in an embodiment preferred split design, it comprises horizontal stabilizer and elevating rudder 8, and horizontal stabilizer is fixed on the vertical tail 10; Elevating rudder 8 is connected with the horizontal stabilizer axle, and adapter shaft is vertical mutually with the face at vertical tail 10 places; Elevating rudder 8 can be with respect to horizontal stabilizer deflection up and down.The bottom of fuselage 11 is provided with alighting gear 9; Fuselage 11 is boosting air cavity with the semi-enclosed cavity of the lower surface formation of host wing 3, and high velocity air flows into boosting air cavity, for generation of bigger air-cushion force.To sum up, owing to be provided with alighting gear 9, the land ground effect vehicle can take off and land on land, the great force of having avoided ground effect vehicle of the prior art to take off in water and to land and to produce, material and structural requirement to integral body 11 are low, reduce production costs.In addition, take off and land in the sea because existing ground effect vehicle is everlasting, seawater is had relatively high expectations to the resistance to corrosion of aircraft material, and land provided by the invention ground effect vehicle takes off on land and lands, so require also lower to the resistance to corrosion of whole aircraft material.
As shown in figures 1 and 3, this installs the optional twin vertical fin wing and comprises vertical tail 10 and 7, two vertical tails 10 of tailplane line centered by the fuselage 11, is fixed on the two sides of tail of fuselage 11, with the angle of level be acute angle; Tailplane 7 is fixed on two vertical tails 10; Tailplane 7 comprises horizontal stabilizer and elevating rudder 8, and horizontal stabilizer is captiveed joint with two vertical tails 10, and elevating rudder 8 is connected with the horizontal stabilizer axle; Elevating rudder 8 can be with respect to horizontal stabilizer deflection up and down.
As shown in Figure 2, the alighting gear in this device can be wheel undercarriage, float landing gears, skid formula alighting gear; Consider that aircraft only rises and falls on land, the mode of rising and falling is single, and purposes can be limited to, so alighting gear 9 can also be floating drum wheel undercarriage or floating drum skid formula alighting gear.Described floating drum wheel undercarriage can rise and fall in water, also can rise and fall on land, and wheel both had been installed on the alighting gear 9, and floating drum also is installed; Described floating drum skid formula alighting gear can rise and fall in water, also can rise and fall at snowfield or meadow, and skid both had been installed on the alighting gear 9, and floating drum also is installed.The alighting gear 9 of dual mode can be changed accordingly according to user demand.
As shown in Figure 1, this device also comprises end plate 12, host wing 3 is in the right-angled trapezium that is projected as on ground, wherein host wing 3 is captiveed joint with fuselage 11 than a side on long base, a side on short base is captiveed joint with end plate 12, the face at end plate 12 places is vertical mutually with the face at host wing 3 places, and its longitudinal cross-section is
Shape.At this moment, boosting air cavity is the semi-enclosed cavity of lower surface, fuselage 11 and end plate 12 compositions of host wing 3.This device can also comprise wing flap 6, and the leading edge of host wing 3 or trailing edge are provided with wing flap 6; Wing flap 6 is connected with 3 of host wings, can be with respect to host wing deflection about in the of 3.Wing flap 6 can actv. increases the lift of aircraft.At this moment, boosting air cavity is the semi-enclosed cavity of lower surface, fuselage 11, end plate 12 and wing flap 6 compositions of host wing 3.By the boosting air cavity that this specific mechanism forms, the high velocity air that produces during aircraft takeoff flows into boosting air cavity, can produce bigger air-cushion force.
As depicted in figs. 1 and 2, this device can also comprise little wing 4, and little wing 4 is captiveed joint with host wing 3 shorter bases one side, and the angle of little wing 4 and horizontal surface is acute angle.Little wing 4 can promote the lift of Fetion device.In addition, can also comprise aileron 5 on little wing 4, aileron 5 is connected with 4 on little wing, and it can be with respect to the deflection about in the of 4 of described little wing.It is motor-driven that the rolling moment that aileron 5 differential deflections in the pilot guidance left and right sides produce can make aircraft do roll.
The above is the preferred embodiments of the present invention only, is not limited to the present invention, and for a person skilled in the art, the present invention can have various changes and variation.Within the spirit and principles in the present invention all, any modification of doing, be equal to replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (10)
1. a land ground effect vehicle is characterized in that, comprising: propelling unit, driving engine, host wing, alighting gear, empennage, fuselage; Described fuselage is provided with described driving engine, and described driving engine is connected with described propelling unit by rotating shaft, is used for driving propelling unit, for aircraft provides power; Described host wing is fixed on the both sides of described fuselage, the line of its two ends tip and aircraft transverse axis; Described empennage is captiveed joint with the afterbody of described fuselage; The bottom of described fuselage is provided with described alighting gear; The semi-enclosed cavity that the lower surface of described fuselage and described host wing constitutes is boosting air cavity, and high velocity air flows into described boosting air cavity, for generation of bigger air-cushion force.
2. land according to claim 1 ground effect vehicle is characterized in that described propelling unit is screw propeller or ducted fan.
3. land according to claim 1 ground effect vehicle is characterized in that, described empennage be following any one: T type tail or the twin vertical fin wing.
4. land according to claim 3 ground effect vehicle, it is characterized in that, described T type tail comprises tailplane and vertical tail, described vertical tail is connected with the afterbody vertical fixing of described fuselage, described tailplane is fixed on the described vertical tail, and the longitudinal cross-section of described tailplane and described vertical tail is "T"-shaped; Described tailplane comprises horizontal stabilizer and elevating rudder, and described horizontal stabilizer is fixed on the described vertical tail; Described elevating rudder is connected with described horizontal stabilizer axle, and adapter shaft is vertical mutually with the face at described vertical tail place; Described elevating rudder can be with respect to the deflection up and down of described horizontal stabilizer;
Or the described twin vertical fin wing comprises vertical tail and tailplane, and two described vertical tails line centered by the described fuselage is fixed on the two sides of tail of described fuselage, with the angle of level be acute angle; Described tailplane is fixed on two described vertical tails; Described tailplane comprises horizontal stabilizer and elevating rudder, and described horizontal stabilizer is captiveed joint with two described vertical tails, and described elevating rudder is connected with described horizontal stabilizer axle; Described elevating rudder can be with respect to the deflection up and down of described horizontal stabilizer.
5. land according to claim 1 ground effect vehicle is characterized in that, described alighting gear be following any one: wheel undercarriage, float landing gears, skid formula alighting gear, floating drum wheel undercarriage, floating drum skid formula alighting gear.
6. land according to claim 1 ground effect vehicle, it is characterized in that, also comprise end plate, the ground of described host wing is projected as right-angled trapezium, a wherein said host wing side on long base is captiveed joint with described fuselage, a side on short base is captiveed joint with described end plate, and the face at described end plate place is vertical mutually with the face at described host wing place, and its longitudinal cross-section is
Shape.
7. land according to claim 6 ground effect vehicle is characterized in that also comprise wing flap, the leading edge of described host wing or trailing edge are provided with described wing flap; Described wing flap is connected with described host wing axle, can be with respect to the deflection up and down of described host wing.
8. land according to claim 7 ground effect vehicle is characterized in that, described boosting air cavity is the semi-enclosed cavity that the lower surface of described host wing, described fuselage, described end plate and described wing flap are formed.
9. land according to claim 8 ground effect vehicle is characterized in that also comprise little wing, described little wing is captiveed joint with the shorter base of described host wing one side, and the angle of described little wing and horizontal surface is acute angle.
10. land according to claim 9 ground effect vehicle is characterized in that, also comprises aileron, is provided with described aileron at the trailing edge of described little wing; Described aileron is connected with described little wing axis, and it can be with respect to the deflection up and down of described little wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310119406.7A CN103192989B (en) | 2013-04-08 | 2013-04-08 | Land ground effect vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310119406.7A CN103192989B (en) | 2013-04-08 | 2013-04-08 | Land ground effect vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103192989A true CN103192989A (en) | 2013-07-10 |
| CN103192989B CN103192989B (en) | 2016-08-24 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310119406.7A Expired - Fee Related CN103192989B (en) | 2013-04-08 | 2013-04-08 | Land ground effect vehicle |
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| Country | Link |
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| CN (1) | CN103192989B (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108430871A (en) * | 2015-12-31 | 2018-08-21 | 空中客车西班牙运营有限责任公司 | Aircraft with rear engine |
| CN109131867A (en) * | 2018-07-18 | 2019-01-04 | 深圳筋斗云智能科技有限公司 | Aircraft |
| US10464668B2 (en) | 2015-09-02 | 2019-11-05 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| CN110901906A (en) * | 2019-12-04 | 2020-03-24 | 中国直升机设计研究所 | Ground effect rotor craft and flight mode switching method |
| 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 |
| CN117262214A (en) * | 2023-10-11 | 2023-12-22 | 哈尔滨工业大学 | Amphibious short-distance take-off and landing ground effect aircraft |
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| CN2525038Y (en) * | 2001-07-30 | 2002-12-11 | 罗专予 | Land effect air craft with take-off and landing wheel |
| US20040050602A1 (en) * | 2002-09-17 | 2004-03-18 | William Larry Jones | Ground effect vehicle using a frontal ram air stream and aerodynamic lift |
| CN201010045Y (en) * | 2006-12-15 | 2008-01-23 | 中国科技开发院 | Ground-effect aircraft |
| CN201023656Y (en) * | 2007-03-02 | 2008-02-20 | 广州天象地效飞行器股份有限公司 | Ground effect aircraft |
| US8152095B2 (en) * | 2007-07-26 | 2012-04-10 | Airbus France | Aircraft having a reduced acoustic signature |
| CN202244080U (en) * | 2011-01-12 | 2012-05-30 | 中国高科集团有限公司 | Ground effect aircraft |
| CN203222111U (en) * | 2013-04-08 | 2013-10-02 | 孙亮 | Terrestrial ground effect aircraft |
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2013
- 2013-04-08 CN CN201310119406.7A patent/CN103192989B/en not_active Expired - Fee Related
Patent Citations (7)
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| CN2525038Y (en) * | 2001-07-30 | 2002-12-11 | 罗专予 | Land effect air craft with take-off and landing wheel |
| US20040050602A1 (en) * | 2002-09-17 | 2004-03-18 | William Larry Jones | Ground effect vehicle using a frontal ram air stream and aerodynamic lift |
| CN201010045Y (en) * | 2006-12-15 | 2008-01-23 | 中国科技开发院 | Ground-effect aircraft |
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| US8152095B2 (en) * | 2007-07-26 | 2012-04-10 | Airbus France | Aircraft having a reduced acoustic signature |
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| CN203222111U (en) * | 2013-04-08 | 2013-10-02 | 孙亮 | Terrestrial ground effect aircraft |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN108430871A (en) * | 2015-12-31 | 2018-08-21 | 空中客车西班牙运营有限责任公司 | Aircraft with rear engine |
| 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 |
| CN109131867A (en) * | 2018-07-18 | 2019-01-04 | 深圳筋斗云智能科技有限公司 | Aircraft |
| CN109131867B (en) * | 2018-07-18 | 2023-10-27 | 深圳筋斗云智能科技有限公司 | Aircraft with a plurality of aircraft body |
| CN110901906A (en) * | 2019-12-04 | 2020-03-24 | 中国直升机设计研究所 | Ground effect rotor craft and flight mode switching method |
| CN117262214A (en) * | 2023-10-11 | 2023-12-22 | 哈尔滨工业大学 | Amphibious short-distance take-off and landing ground effect aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103192989B (en) | 2016-08-24 |
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Granted publication date: 20160824 Termination date: 20180408 |