CN104443371A - Airplane capable of vertically taking off and landing - Google Patents
Airplane capable of vertically taking off and landing Download PDFInfo
- Publication number
- CN104443371A CN104443371A CN201310420846.6A CN201310420846A CN104443371A CN 104443371 A CN104443371 A CN 104443371A CN 201310420846 A CN201310420846 A CN 201310420846A CN 104443371 A CN104443371 A CN 104443371A
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- fuselage
- airfoils
- landing
- airplane
- rotating shaft
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Abstract
The invention belongs to an improvement of an airplane structure. The invention relates to a common airplane capable of vertically taking off and landing as a helicopter without a wide slide runway, under condition of same horizontal flight performance and flight distance, a structure is simple, complex aeromechanic calculation is not required, and the airplane capable of vertically taking off and landing has the advantages of low cost and strong practicality. The airplane capable of vertically taking off and landing comprises a fuselage, front airfoils are arranged at two sides of forebody of the fuselage, a front blower fan of a front propeller is arranged on the front airfoils; a steering rudder and an empennage are arranged at tail of the fuselage, and the airplane is characterized in that the rear fuselages are arranged at central section of the fuselage, a rear blower fan having a rear propeller is arranged on the rear airfoils, the front airfoils and the rear airfoils are connected to the fuselage through rotating shafts, and the rotating shaft can be connected to a rotation apparatus in the fuselage.
Description
Technical field
the present invention relates to a kind of improvement of aircaft configuration.
Background technology
the AV-8B type produced by MCDONNELL DOUGLAS company at present takes off vertically landing aircraft, and be still on active service at the extra large corps of the U.S., but this takes off vertically, landing aircraft is due to its reasons in structure, in order to adapt to the powerful propulsive force of its deadweight needs; This makes powerful engine become necessity.Further, in order to bear this superpower propulsive force, also need firm body, manufacturing cost is very high; Also therefore, mainly militarily use; If want civil nature, very complicated aeromechanics is needed to calculate.
in other words, do not need complicated calculations, the landing aircraft that takes off vertically that just can be practical does not also have at present; For these reasons, all use pilotless helicopter to work such as the observations of active volcano at present, and helicopter operation is difficult, horizontal flight speed and the bunkerage inferior position that existence is very large compared with conventional airplane, it is very inconvenient to use.
Summary of the invention
the present invention is exactly for the problems referred to above, provide a kind of plane track without the need to broadness, can be taken off vertically the conventional airplane landed as helicopter, under the condition of peer-level airworthiness and flying distance, structure is simple, aeromechanics without the need to complexity calculates, with low cost, the practical landing aircraft that takes off vertically.
for realizing above-mentioned purpose of the present invention, the present invention adopts following technical scheme, the present invention includes fuselage, and fuselage both sides forebody is provided with front wing, front wing is arranged the front blower fan with front propeller; Afterbody is provided with and turns to rudder and empennage, it is characterized in that: waist both sides are provided with rear wing, and rear wing is arranged the rear fan with after screw, described front wing is all connected with fuselage by rotating shaft with rear wing; Rotating shaft is connected with the wheel word in fuselage.
as a preferred embodiment of the present invention, described wheel word comprises drive motor, and the axle drive shaft of drive motor is connected with chain, and chain is connected with the sprocket wheel in rotating shaft.
as another kind of preferred version of the present invention, rotating shaft is provided with pole, pole is provided with spring, the end of spring is connected with fuselage inwall.
beneficial effect of the present invention: the present invention can land in short range running take off, landing of also can taking off vertically, and fuselage weight is light, without the need to the propulsion source of brute force; Can take off in narrow space, and can also fly by Ultra-Low Speed; Good economy performance, practical, not only can use on the unmanned aerial vehicle of wireless remote control, can also adopt on the aircraft having people.The present invention can realize above-mentioned functions completely.
Accompanying drawing explanation
fig. 1 is structural representation of the present invention.
fig. 2 is the structural representation of wing before the present invention.
fig. 3 is the structural representation before the present invention after wing rotation.
fig. 4 is the structural representation of forebody of the present invention.
fig. 5 is the structural representation of wheel word of the present invention.
fig. 6 is using state figure of the present invention.
1 be fuselage in accompanying drawing, 2 be front wing, 3 be rear wing, 4 be empennage, 5 for turning to rudder, 6 to be front propeller, 7 be after screw, 8 be front blower fan, 9 be rear fan, 10 be rotating shaft, 11 be drive motor, 12 be blower fan gear, 13 be drive motor gear, 14 be blower fan chain, 16 be chain, 17 be drive motor, 18 be sprocket wheel, 18 be wheel word, 19 be attachment point, 20 be spring, 21 be pole, 22 for drawing screw propeller, 23 in for front wing end.
Detailed description of the invention
the present invention adopts following technical scheme, the present invention includes fuselage, and fuselage both sides forebody is provided with front wing, front wing is arranged the front blower fan with front propeller; Afterbody is provided with and turns to rudder and empennage, it is characterized in that: waist both sides are provided with rear wing, and rear wing is arranged the rear fan with after screw, described front wing is all connected with fuselage by rotating shaft with rear wing; Rotating shaft is connected with the wheel word in fuselage.
as a preferred embodiment of the present invention, described wheel word comprises drive motor, and the axle drive shaft of drive motor is connected with chain, and chain is connected with the sprocket wheel in rotating shaft.
as another kind of preferred version of the present invention, rotating shaft is provided with pole, pole is provided with spring, the end of spring is connected with fuselage inwall.
Claims (3)
1. take off vertically landing aircraft, comprises fuselage, and fuselage both sides forebody is provided with front wing, front wing arranged the front blower fan with front propeller; Afterbody is provided with and turns to rudder and empennage, it is characterized in that: waist both sides are provided with rear wing, and rear wing is arranged the rear fan with after screw, described front wing is all connected with fuselage by rotating shaft with rear wing; Rotating shaft is connected with the wheel word in fuselage.
2. the landing aircraft that takes off vertically according to claim 1, it is characterized in that described wheel word comprises drive motor, the axle drive shaft of drive motor is connected with chain, and chain is connected with the sprocket wheel in rotating shaft.
3. the landing aircraft that takes off vertically according to claim 2, is characterized in that rotating shaft is provided with pole, pole is provided with spring, and the end of spring is connected with fuselage inwall.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310420846.6A CN104443371A (en) | 2013-09-16 | 2013-09-16 | Airplane capable of vertically taking off and landing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310420846.6A CN104443371A (en) | 2013-09-16 | 2013-09-16 | Airplane capable of vertically taking off and landing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104443371A true CN104443371A (en) | 2015-03-25 |
Family
ID=52890292
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310420846.6A Pending CN104443371A (en) | 2013-09-16 | 2013-09-16 | Airplane capable of vertically taking off and landing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104443371A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104494812A (en) * | 2015-01-08 | 2015-04-08 | 常州大学 | Fixed-wing air vehicle device with screw propeller having tiltable shaft |
| CN105775128A (en) * | 2016-02-22 | 2016-07-20 | 武汉智能鸟无人机有限公司 | Flight vehicle |
| CN106516080A (en) * | 2016-12-06 | 2017-03-22 | 昆山鲲鹏无人机科技有限公司 | Tilting wing unmanned aerial vehicle with aerodynamic layout and tilting mechanisms and method for detecting whether wings get loose or not |
| CN111823797A (en) * | 2020-07-23 | 2020-10-27 | 江苏科技大学 | Duct type water-air amphibious unmanned aircraft capable of tilting |
| CN113165736A (en) * | 2019-01-01 | 2021-07-23 | 株式会社爱隆未来 | Flying object |
-
2013
- 2013-09-16 CN CN201310420846.6A patent/CN104443371A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104494812A (en) * | 2015-01-08 | 2015-04-08 | 常州大学 | Fixed-wing air vehicle device with screw propeller having tiltable shaft |
| CN105775128A (en) * | 2016-02-22 | 2016-07-20 | 武汉智能鸟无人机有限公司 | Flight vehicle |
| CN106516080A (en) * | 2016-12-06 | 2017-03-22 | 昆山鲲鹏无人机科技有限公司 | Tilting wing unmanned aerial vehicle with aerodynamic layout and tilting mechanisms and method for detecting whether wings get loose or not |
| CN106516080B (en) * | 2016-12-06 | 2019-01-11 | 昆山鲲鹏无人机科技有限公司 | A kind of tilting wing unmanned plane with aerodynamic arrangement and inclining rotary mechanism |
| CN113165736A (en) * | 2019-01-01 | 2021-07-23 | 株式会社爱隆未来 | Flying object |
| CN111823797A (en) * | 2020-07-23 | 2020-10-27 | 江苏科技大学 | Duct type water-air amphibious unmanned aircraft capable of tilting |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150325 |
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| WD01 | Invention patent application deemed withdrawn after publication |