CN102632991A - Wing full-motion airplane without rudder surface - Google Patents
Wing full-motion airplane without rudder surface Download PDFInfo
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- CN102632991A CN102632991A CN2012100833158A CN201210083315A CN102632991A CN 102632991 A CN102632991 A CN 102632991A CN 2012100833158 A CN2012100833158 A CN 2012100833158A CN 201210083315 A CN201210083315 A CN 201210083315A CN 102632991 A CN102632991 A CN 102632991A
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- wing
- fuselage
- aircraft
- rudder face
- rotating shaft
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Abstract
The invention relates to a wing full-motion airplane without a rudder surface. The wing full-motion airplane comprises wings, a power system and a fuselage, wherein the wings are connected with the fuselage through rotating shaft mechanisms, the power system is positioned in the fuselage, and a driving mechanism connected with the power system is arranged on the fuselage, and connected with leading edges of the wings. The wing full-motion airplane without the rudder surface not only can realize various attitude control of the airplane by wing full-motion, but also can realize short take-off and landing, and is large in fuselage space.
Description
Technical field
The present invention relates to the moving full aircraft of a kind of no rudder face wing, belong to short field aircraft and aviation aircraft design field.
Background technology
At present, along with the enhancing of China's national defense strength, the military attack strength that aircraft carrier has necessitated, and the development of aircraft carrier certainly will require corresponding carrier-borne aircraft technology.Because the aircraft-carrier-deck distance is limited, so require the carrier-borne aircraft STOL.It is less that present stage solves the fixed wing aircraft type of STOL, and cost is high, but the other VTOL aircraft has reduced the performance of aircraft because its mechanism is complicated, and weight is excessive for realizing some equipment that VTOL increases, and cost performance is low excessively.
Summary of the invention
The present invention is directed to the deficiency of the problems referred to above, propose a kind of can STOL, the fuselage space is big and the moving full aircraft of no rudder face wing that moved each attitude control that realizes aircraft by wing entirely.
The present invention is that the technical scheme that solves the problems of the technologies described above proposition is: the moving full aircraft of a kind of no rudder face wing; It is characterized in that: comprise wing, power system and fuselage; Said wing is connected with fuselage through rotating shaft mechanism; And power system is positioned at fuselage, and on fuselage, is provided with the driver train that is connected with power system, and said driver train is connected with the leading edge of a wing.
Preferred again: the girder web of said wing is provided with a rotating shaft axle sleeve, and this axle sleeve and wing are affixed, and the wing girder correspondence position on the said fuselage is fixed with a circular shaft, and this diameter of axle and sleeve diameter form free-running fit.
Further: said fuselage and empennage are an integral body.
Again further: also comprise the wing drive system, this wing drive system realizes that through controlling and driving mechanism wing rotates around the axis.
Preferred more again: said rotating shaft axle sleeve is the square-outside and round-inside type.
During use; The wing drive system realizes that through controlling and driving mechanism wing rotates around the axis; Just; Realize the pitch control of aircraft when realizing that through wing drive system controlling and driving mechanism wing rotates synchronously, realize the turning and the lift-over of aircraft when realizing that through wing drive system controlling and driving mechanism wing is differential.Specifically be that when driver train made two wings differential to the leading edge of a wing application of force, aircraft can be realized turning or lift-over.When driver train rotated two wings to the leading edge of a wing application of force synchronously, aircraft can be realized pitch control, promptly worked as two wings and increased the angle of attack synchronously, and aircraft comes back, and realizes climbing; When two wings reduced the angle of attack synchronously, aircraft was bowed, and realized diving.
The moving full aircraft of no rudder face wing of the present invention; Compare prior art; Has following beneficial effect: be connected with fuselage through rotating shaft mechanism because wing is stated in employing; Therefore driver train and leading edge of a wing bonded assembly are pressed design plan, can STOL, the fuselage space is big and moved each attitude control that realizes aircraft entirely by wing; Select for use rotating shaft axle sleeve and circular shaft to cooperate the rotating shaft mechanism that forms more to help the rotation of wing simultaneously; Adopt the wing drive system, make driver train realize that more easily wing rotates around the axis; The rotating shaft axle sleeve is made as the square-outside and round-inside type, makes that the stability of rotating shaft mechanism and rotation are better.
Description of drawings
Fig. 1: no rudder face wing is the profile three-view diagram of moving aircraft entirely;
Fig. 2: no rudder face wing is the structural representation of moving aircraft entirely;
Fig. 3 is Fig. 2 bottom bracket axle structural representation;
Fig. 4 is a wing pivot structure scheme drawing among Fig. 2;
Fig. 5 is Fig. 2 wing difference structure scheme drawing;
Fig. 6 is the synchronous rotational structure scheme drawing of Fig. 2 wing;
Fig. 7 is the maximum positive incidence structural representation of Fig. 2 starboard wing;
Fig. 8 is Fig. 2 port wing maximum negative angle of attack structural representation;
Fig. 9 is Fig. 2 tail structure scheme drawing;
Wherein: 1-fuselage, 2-wing, 3-empennage, the rotating shaft of 4-wing, 5-driver train, 6-rotating shaft axle sleeve.
The specific embodiment
Accompanying drawing discloses the structural representation of a preferred embodiment of the invention without limitation, below will combine accompanying drawing that technical scheme of the present invention at length is described.
Embodiment
The moving full aircraft of the no rudder face wing of present embodiment is shown in Fig. 1 ~ 8; Comprise wing, power system and fuselage; Said wing is connected with fuselage through rotating shaft mechanism; And power system is positioned at fuselage, and on fuselage, is provided with the driver train that is connected with power system, and said driver train is connected with the leading edge of a wing.
The girder web of said wing is provided with a rotating shaft axle sleeve, and this axle sleeve and wing are affixed, and the wing girder correspondence position on the said fuselage is fixed with a circular shaft, and this diameter of axle and sleeve diameter form free-running fit.
Said fuselage and empennage are an integral body.
Also comprise the wing drive system, this wing drive system realizes that through controlling and driving mechanism wing rotates around the axis.
Said rotating shaft axle sleeve is the square-outside and round-inside type.
During use; The wing drive system realizes that through controlling and driving mechanism wing rotates around the axis; Just; Realize the pitch control of aircraft when realizing that through wing drive system controlling and driving mechanism wing rotates synchronously, realize the turning and the lift-over of aircraft when realizing that through wing drive system controlling and driving mechanism wing is differential.Specifically be that when driver train made two wings differential to the leading edge of a wing application of force, aircraft can be realized turning or lift-over.When driver train rotated two wings to the leading edge of a wing application of force synchronously, aircraft can be realized pitch control, promptly worked as two wings and increased the angle of attack synchronously, and aircraft comes back, and realizes climbing; When two wings reduced the angle of attack synchronously, aircraft was bowed, and realized diving.
Combine the preferred specific embodiment of the described the present invention of accompanying drawing only to be used to explain embodiment of the present invention above; Rather than as restriction to aforementioned goal of the invention and accompanying claims content and scope; Every foundation technical spirit of the present invention all still belongs to the present invention's technology and rights protection category to any simple modification, equivalent variations and modification that above embodiment did.
Claims (6)
1. a no rudder face wing moves aircraft entirely; It is characterized in that: comprise wing, power system and fuselage; Said wing is connected with fuselage through rotating shaft mechanism; And power system is positioned at fuselage, and on fuselage, is provided with the driver train that is connected with power system, and said driver train is connected with the leading edge of a wing.
2. according to the moving full aircraft of the said no rudder face wing of claim 1, it is characterized in that: said driver train is a connecting rod mechanism.
3. according to the moving full aircraft of the said no rudder face wing of claim 2; It is characterized in that: the girder web of said wing is provided with a rotating shaft axle sleeve; This axle sleeve and wing are affixed, and the wing girder correspondence position on the said fuselage is fixed with a circular shaft, and this diameter of axle and sleeve diameter form free-running fit.
4. according to the moving full aircraft of the said no rudder face wing of claim 3, it is characterized in that: said fuselage and empennage are an integral body.
5. according to the moving full aircraft of the said no rudder face wing of claim 4, it is characterized in that: also comprise the wing drive system, this wing drive system realizes that through controlling and driving mechanism wing rotates around the axis.
6. according to the moving full aircraft of the said no rudder face wing of claim 5, it is characterized in that: said rotating shaft axle sleeve is the square-outside and round-inside type.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012100833158A CN102632991A (en) | 2012-03-27 | 2012-03-27 | Wing full-motion airplane without rudder surface |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012100833158A CN102632991A (en) | 2012-03-27 | 2012-03-27 | Wing full-motion airplane without rudder surface |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102632991A true CN102632991A (en) | 2012-08-15 |
Family
ID=46617605
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012100833158A Pending CN102632991A (en) | 2012-03-27 | 2012-03-27 | Wing full-motion airplane without rudder surface |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102632991A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103466074A (en) * | 2013-09-24 | 2013-12-25 | 中国航天空气动力技术研究院 | Ship-based net collision recovery unmanned aerial vehicle |
| CN104477374A (en) * | 2014-12-15 | 2015-04-01 | 佛山市神风航空科技有限公司 | High-lift-wing aircraft |
| CN105667759A (en) * | 2015-12-28 | 2016-06-15 | 武汉蓝天翔航空科技有限公司 | Movable wing large airplane with flexible take-off or landing function |
| CN106314761A (en) * | 2016-08-31 | 2017-01-11 | 北京航空航天大学 | All-moving wing mechanism applied to small compound helicopter |
Citations (7)
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| GB389845A (en) * | 1931-06-23 | 1933-03-23 | Hannibal Choate Ford | Improvements in and relating to aeroplane control |
| CN1118591A (en) * | 1993-01-22 | 1996-03-13 | 自由翼飞机公司 | Stol/vtol free wing aircraft with articulated tail boom |
| CN2395985Y (en) * | 1999-11-01 | 2000-09-13 | 卢伯华 | Wing vibration type small aircraft |
| US20060202083A1 (en) * | 2005-03-14 | 2006-09-14 | Milde Karl F Jr | VTOL personal aircraft |
| CN201010044Y (en) * | 2007-03-05 | 2008-01-23 | 苏小明 | Novel wing structure of bionic aircraft |
| CN102040002A (en) * | 2010-12-02 | 2011-05-04 | 北京航空航天大学 | Curve slide-connecting rod mechanism in high lift device of large aircraft |
| CN202593851U (en) * | 2012-03-27 | 2012-12-12 | 南京航空航天大学 | All-moving wing aircraft without control plane |
-
2012
- 2012-03-27 CN CN2012100833158A patent/CN102632991A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB389845A (en) * | 1931-06-23 | 1933-03-23 | Hannibal Choate Ford | Improvements in and relating to aeroplane control |
| CN1118591A (en) * | 1993-01-22 | 1996-03-13 | 自由翼飞机公司 | Stol/vtol free wing aircraft with articulated tail boom |
| CN2395985Y (en) * | 1999-11-01 | 2000-09-13 | 卢伯华 | Wing vibration type small aircraft |
| US20060202083A1 (en) * | 2005-03-14 | 2006-09-14 | Milde Karl F Jr | VTOL personal aircraft |
| CN201010044Y (en) * | 2007-03-05 | 2008-01-23 | 苏小明 | Novel wing structure of bionic aircraft |
| CN102040002A (en) * | 2010-12-02 | 2011-05-04 | 北京航空航天大学 | Curve slide-connecting rod mechanism in high lift device of large aircraft |
| CN202593851U (en) * | 2012-03-27 | 2012-12-12 | 南京航空航天大学 | All-moving wing aircraft without control plane |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103466074A (en) * | 2013-09-24 | 2013-12-25 | 中国航天空气动力技术研究院 | Ship-based net collision recovery unmanned aerial vehicle |
| CN103466074B (en) * | 2013-09-24 | 2015-07-29 | 中国航天空气动力技术研究院 | A kind of carrier-borne net that hits reclaims unmanned plane |
| CN104477374A (en) * | 2014-12-15 | 2015-04-01 | 佛山市神风航空科技有限公司 | High-lift-wing aircraft |
| CN105667759A (en) * | 2015-12-28 | 2016-06-15 | 武汉蓝天翔航空科技有限公司 | Movable wing large airplane with flexible take-off or landing function |
| CN106314761A (en) * | 2016-08-31 | 2017-01-11 | 北京航空航天大学 | All-moving wing mechanism applied to small compound helicopter |
| CN106314761B (en) * | 2016-08-31 | 2018-11-23 | 北京航空航天大学 | A kind of all-moving wing mechanism applied to small compound helicopter |
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| Date | Code | Title | Description |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C53 | Correction of patent of invention or patent application | ||
| CB03 | Change of inventor or designer information |
Inventor after: Sun Wen Inventor after: Du Xiaosong Inventor after: Li Fengming Inventor after: Zhang Lifeng Inventor before: Sun Wen Inventor before: Du Xiaosong Inventor before: Li Fengming Inventor before: Zhang Lifeng |
|
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C12 | Rejection of a patent application after its publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20120815 |