CN202244080U - Ground effect aircraft - Google Patents
Ground effect aircraft Download PDFInfo
- Publication number
- CN202244080U CN202244080U CN2011202702706U CN201120270270U CN202244080U CN 202244080 U CN202244080 U CN 202244080U CN 2011202702706 U CN2011202702706 U CN 2011202702706U CN 201120270270 U CN201120270270 U CN 201120270270U CN 202244080 U CN202244080 U CN 202244080U
- Authority
- CN
- China
- Prior art keywords
- fuselage
- machine body
- cabin
- wing
- keel
- 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.)
- Expired - Lifetime
Links
- 239000003381 stabilizer Substances 0.000 claims abstract description 9
- 239000011521 glass Substances 0.000 claims abstract description 4
- 238000005452 bending Methods 0.000 claims description 3
- 108010066278 cabin-4 Proteins 0.000 description 2
- 210000000988 bone and bone Anatomy 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000010006 flight Effects 0.000 description 1
- 230000033001 locomotion Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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Abstract
The utility model relates to a ground effect aircraft, which comprises a global machine body, a cabin, two propellers with round shells, a tail fin and cantilever type wings, wherein the rear part of the machine body is protruded, and two floating slide plates are installed below the machine body; the cabin is arranged inside the machine body along the axial line of the machine body, and the upper part of the cabin is sealed by a smooth streamlined glass window; the two propellers with the round shells are respectively installed at two side of the head of the machine body; the tail fin is provided with a keel and a stabilizer located at the position higher than that of the keel; the cantilever type wings can be retracted rearward along two sides of the machine body; the bottom of the cantilever of each cantilever type wing is provided with an extension belt bent like a sea-gull wing shape; the tip end of each cantilever type wing straightly extends downward; lateral ladders on opposite slide plate surfaces are provided with longitudinal stability-augmentation floating buoys; and two sub-wings on the stabilizer are of an upper and lower symmetrical structure. Therefore, the aircraft has excellent esthetic characteristics, and good structural stability, symmetry and integrality.
Description
Technical field
The utility model relates to a kind of vehicle, particularly relates to a kind of ground effect vehicle.
Background technology
The floating slide plate that well-known means of delivery ground effect vehicle has can be packed up along the fuselage side, the cabin is arranged in the Vehicle nose and along the fuselage axis extends, and the front side, cabin has been fixed two screw propellers that are enclosed in the circular housing side by side.There is straight cantilever wing the fuselage both sides, and the T type tail is arranged, (with reference to No. the 42344th, Russ P).
The utility model content
The purpose of the utility model is to provide a kind of later-model ground effect vehicle, and this kind ground effect vehicle has good aesthetic characteristic, good structural stability, symmetry and integraty.
The above-mentioned purpose of the utility model realizes through following technical scheme:
A kind of ground effect vehicle is characterized in that, comprising: the ball-shaped fuselage, and the rear portion of said fuselage is outstanding, and two floating slide plates are installed below said fuselage; The cabin, it is arranged on said fuselage interior, and along the axis setting of said fuselage, top, said cabin is airtight with level and smooth fleetline glass port; Two screw propellers that have circular housing, it is installed in the both sides of said fuselage head respectively; The empennage that has keel, and empennage has and is positioned at the stabiliser that is higher than the keel position; The cantilevered wing, it can be packed up along the fuselage both sides backward, and wherein, the cantilever root of said cantilevered wing has the stretching, extension band of picture sea-gull wing shape bending; The straight downwards exhibition of said cantilevered wing tip; Relatively the horizontal ladder of slide plate face has and increases steady floating drum longitudinally; Two branch wings on the said stabiliser are structure and symmetry up and down up and down.
Description of drawings
Through the description of the utility model exemplary embodiment being done below in conjunction with exemplary and nonrestrictive accompanying drawing, with other feature and advantage of knowing the utility model.In said accompanying drawing,
Fig. 1 is the birds-eye view according to the ground effect vehicle of an embodiment of the utility model;
Fig. 2 is the lateral plan of ground effect vehicle shown in Figure 1;
Fig. 3 is the front elevation of ground effect vehicle shown in Figure 1.
The specific embodiment
The ground effect vehicle of the utility model is different from the general purpose hauling instrument of delivery passenger and goods function, can realize the effect (low-latitude flying) of some face of land flights:, and can and slide along ground motion like the water surface, ice face, marsh, ice and snow area or the like.
In the ground effect vehicle according to the embodiment of the utility model, fuselage 1 is roughly spherical in shape, and outstanding in the center of wing rear side, both sides are equipped with two floating slide plates 2 below fuselage, is provided with several along the slide plate of level and increases steady floating drum 3.Inside at fuselage 1 (for example is provided with cabin 4 along the fuselage axis; Chaufeur and/or passenger storehouse); The upside in cabin 4 is airtight, and said upside comprises level and smooth fleetline skylight 5, and comprises a plurality of glass ports (porthole) 6; The fuselage head both sides are provided with screw propeller 8, and screw propeller 8 is positioned at the inside of circular housing 9.
One continuous line bone 10 is connected to fuselage 1 with the aircraft empennage, and the aircraft empennage has stabiliser 11, and left-right symmetric is equipped with two fin-separatings 12 on stabiliser 11, and each fin-separating 12 is structure and symmetry up and down up and down.
The both sides of fuselage afterbody are installed on cantilevered wing 13, have as the stretching, extension of sea-gull wing shape at the wing root and are with 14, the straight downwards exhibition of wing tip 15.
Whole characteristics of enumerating have confirmed to embody a concentrated reflection of the technical characterictic of aircraft, make technical scheme vivid, and have shown the function purposes.
The technical scheme of the utility model makes aircraft have good aesthetic characteristic, and good structural stability, symmetry and integraty have originality on the technical scheme.
Technical scheme of the utility model and the key distinction of prior art summary are understood fully the difference of technological design scheme and current similar model through feature:
Be provided with the cantilevered wing, the cantilever root has the stretching, extension band of picture sea-gull wing shape bending;
The straight downwards exhibition of wing tip;
Relatively the horizontal ladder of slide plate face has and increases steady floating drum longitudinally;
Two branch wings on the stabiliser are structure and symmetry up and down up and down.
Claims (1)
1. a ground effect vehicle is characterized in that, comprising:
The ball-shaped fuselage, the rear portion of said fuselage is outstanding, and two floating slide plates are installed below said fuselage;
The cabin, it is arranged on said fuselage interior, and along the axis setting of said fuselage, top, said cabin is airtight with level and smooth fleetline glass port;
Two screw propellers that have circular housing, it is installed in the both sides of said fuselage head respectively;
The empennage that has keel, and empennage has and is positioned at the stabiliser that is higher than the keel position; And
The cantilevered wing, it can be packed up along said fuselage both sides backward,
Wherein,
The cantilever root of said cantilevered wing has the stretching, extension band of picture sea-gull wing shape bending;
The straight downwards exhibition of said cantilevered wing tip;
The horizontal ladder of slide plate face is provided with and increases steady floating drum longitudinally relatively;
Two branch wings on the said stabiliser are symmetrical structure up and down separately.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2011500024 | 2011-01-12 | ||
RU2011500024/49(000307) | 2011-01-12 |
Publications (1)
Publication Number | Publication Date |
---|---|
CN202244080U true CN202244080U (en) | 2012-05-30 |
Family
ID=46105365
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN2011202702706U Expired - Lifetime CN202244080U (en) | 2011-01-12 | 2011-07-28 | Ground effect aircraft |
Country Status (1)
Country | Link |
---|---|
CN (1) | CN202244080U (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103192989A (en) * | 2013-04-08 | 2013-07-10 | 孙亮 | Land ground effect aircraft |
WO2021109311A1 (en) * | 2019-12-04 | 2021-06-10 | 中国直升机设计研究所 | Ground effect based rotorcraft and flight mode switching control method |
-
2011
- 2011-07-28 CN CN2011202702706U patent/CN202244080U/en not_active Expired - Lifetime
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103192989A (en) * | 2013-04-08 | 2013-07-10 | 孙亮 | Land ground effect aircraft |
CN103192989B (en) * | 2013-04-08 | 2016-08-24 | 孙亮 | Land ground effect vehicle |
WO2021109311A1 (en) * | 2019-12-04 | 2021-06-10 | 中国直升机设计研究所 | Ground effect based rotorcraft and flight mode switching control method |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
C14 | Grant of patent or utility model | ||
GR01 | Patent grant | ||
C41 | Transfer of patent application or patent right or utility model | ||
TR01 | Transfer of patent right |
Effective date of registration: 20160215 Address after: 571127 No. 351 Ling Gui Avenue, Meilan District, Hainan, Haikou Patentee after: Hainan engga wig manufacturing Co. Ltd. Address before: Room 22, building 213, Hu Zhong building, 2209 Queen's Road East, Wan Chai, Hongkong, China Patentee before: China Hi-Tech Group Co., Ltd. |
|
CX01 | Expiry of patent term | ||
CX01 | Expiry of patent term |
Granted publication date: 20120530 |