CN104015924A - Track pump pneumatic lifting-body aircraft - Google Patents
Track pump pneumatic lifting-body aircraft Download PDFInfo
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- CN104015924A CN104015924A CN201410250299.6A CN201410250299A CN104015924A CN 104015924 A CN104015924 A CN 104015924A CN 201410250299 A CN201410250299 A CN 201410250299A CN 104015924 A CN104015924 A CN 104015924A
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Abstract
The invention relates to a track pump pneumatic lifting-body aircraft. The track pump pneumatic lifting-body aircraft comprises a machine body, a power propeller, a vertical tail fin, a rudder, a power machine and wings, wherein the machine body and the wings form a conjoined arc shell, a through cavity is arranged in the middle part of the machine body up and down, an inner cavity structured support which is connected with the machine body is installed in the through cavity, the power machine and a driving wheel are installed on the front end of the inner cavity structured support, an output shaft of the power machine is connected with the driving wheel, a driven wheel is installed on the rear end of the inner cavity structured support, a track sleeves the driving wheel and the driven wheel, the driving wheel drives the track to rotate, the middle part of the inner cavity structured support is provided with a supporting guide wheel, the supporting guide wheel is used for supporting the track between the driving wheel and the driven wheel, and the power propeller is arranged in the center of the tail part of the machine body. According to the track pump pneumatic lifting-body aircraft, three parts can produce a lifting force, so that the efficiency for producing the lifting force of the whole aircraft is greater than that of an ordinary airplane, the take-off distance and the landing distance of the aircraft can be greatly shortened, and the take-off and landing property of the aircraft is better.
Description
Technical field
The invention belongs to aircraft, especially a kind of Crawler pump gas formula lifting body aircraft.
Technical background
Middle-size and small-size manned craft (or unmanned plane) is light little flexible because of it, only needs airpark to park and landing, obtains widespread use and develop rapidly in recent years at civil area, and small-sized aircraft is representing an important development direction of future transportation instrument.Existing light, flivver (or unmanned plane) use and flight aspect also exist manyly not as people's will parts, as large in noise, landing distance, voyage are short etc.
Summary of the invention
Object of the present invention is just to provide that a kind of safety performance is good, lift efficiency is high, the landing stable performance of taking off, Crawler pump gas formula lifting body aircraft that can short take-off and landing (STOL).
Crawler pump gas formula lifting body aircraft of the present invention, comprise fuselage, power spin oar, the vertical fin wing, yaw rudder, engine, wing, be characterized in, fuselage and wing are disjunctor arc surfaced shell, waist is cavity up and down, the inner-cavity structure support being connected with fuselage is installed in cavity, the front end of inner-cavity structure support is equipped with engine and driving wheel, the output shaft of engine is connected with driving wheel, flower wheel is equipped with in the rear end of inner-cavity structure support, crawler belt is nested with on driving wheel and flower wheel, driving wheel drives crawler belt to rotate, the middle part of inner-cavity structure support is provided with support guide wheel, support guide wheel for supporting the crawler belt between driving wheel and flower wheel, power spin oar is located at the afterbody central authorities of fuselage.
Crawler pump gas formula lifting body aircraft of the present invention, there is the fuselage of a large aerofoil profile shape, fuselage is large arc surfaced shell, the upper zone face of crawler belt exposes at fuselage upper surface, be the component part of facial contour on this aerofoil profile fuselage, the lower belt surface of crawler belt exposes at fuselage lower surface, is the component part of facial contour under this aerofoil profile fuselage, respectively there is a wing flap fuselage afterbody left and right, for controlling the landing of aircraft; The wing of generating portion lift when fuselage both sides have for cruising flight, respectively there is an aileron in wing outside in left and right, for controlling the rolling of aircraft or turning round; Afterbody is equipped with vertical tail, has yaw rudder on it, for the auxiliary course of controlling aircraft.In forebody fairing, be crew module or flight control unit cabin.The sense of motion of crawler belt is that upper surface moves backward, and lower surface travels forward, and its engine can be motor or combustion engine.Caterpillar drive drives the air-flow of fuselage upper surface to accelerate to flow to fuselage rear, produces the air-flow velocity more faster than aircraft speed of advance in this region; Meanwhile, it also drives the air-flow of fuselage lower surface to move forward, produce in this region than aircraft speed of advance slow many air-flow velocitys.Due to caterpillar drive, make air-flow velocity and its speed of advance on the upper and lower surface of fuselage have very large velocity contrast, between upper and lower surface, there is larger velocity contrast, produce very large cw circulation along fuselage longitudinal cross-section, form thus the larger difference of pressure in the upper and lower surface of fuselage, thereby make fuselage produce very large lift.The support guide wheel of fuselage upper surface crawler belt is used for supporting fuselage appearance, maintains the shape of its aerofoil profile.The thrust power screw propeller of the fairing top of fuselage trailing edge, its effect is mainly to promote aircraft to advance, maintaining aircraft has certain speed forward.
Crawler pump gas formula lifting body aircraft of the present invention, producing lift has three parts: the lift that 1, aircraft fuselage arc surfaced shell top produces due to air-flow rapid flow; 2, the normal lift that aircraft produces after cruising on wing; Thereby the difference of pressure 3, forming due to the very large velocity contrast on upper and lower surface in crawler belt region produces very large lift.So it is more much larger than conventional airplane that entirety produces the efficiency of lift, to take off, landing distance all shortens greatly, the landing performance of taking off is better.
Brief description of the drawings
Fig. 1 is structural representation of the present invention;
Fig. 2 is Fig. 1 schematic top plan view.
Detailed description of the invention
A kind of Crawler pump gas formula lifting body aircraft, comprise fuselage 1, power spin oar 7, the vertical fin wing 8, yaw rudder 9, engine 3, wing 11, be characterized in, fuselage 1 is disjunctor arc surfaced shell with wing 11, fuselage 1 middle part is cavity up and down, the inner-cavity structure support 10 being connected with fuselage 1 is installed in cavity, the front end of inner-cavity structure support 10 is equipped with engine 3 and driving wheel 4, the output shaft of engine 3 is connected with driving wheel 4, flower wheel 6 is equipped with in the rear end of inner-cavity structure support 10, crawler belt 2 is nested with on driving wheel 4 and flower wheel 6, driving wheel 4 drives crawler belt 2 to rotate, the middle part of inner-cavity structure support 10 is provided with supports guide wheel 5, support guide wheel 5 for supporting the crawler belt between driving wheel 4 and flower wheel 6, power spin oar 7 is located at the afterbody central authorities of fuselage 1.
Claims (2)
1. a Crawler pump gas formula lifting body aircraft, comprise fuselage (1), power spin oar (7), the vertical fin wing (8), yaw rudder (9), engine (3), wing (11), it is characterized in that: fuselage (1) is disjunctor arc surfaced shell with wing (11), fuselage (1) middle part is cavity up and down, the inner-cavity structure support (10) being connected with fuselage (1) is installed in cavity, the front end of inner-cavity structure support (10) is equipped with engine (3) and driving wheel (4), the output shaft of engine (3) is connected with driving wheel (4), flower wheel (6) is equipped with in the rear end of inner-cavity structure support (10), crawler belt (2) is nested with on driving wheel (4) and flower wheel (6), power spin oar (7) is located at the afterbody central authorities of fuselage (1).
2. Crawler pump gas formula lifting body aircraft according to claim 1, is characterized in that: the middle part of inner-cavity structure support (10) is provided with supports guide wheel (5), supports guide wheel (5) for supporting the crawler belt between driving wheel (4) and flower wheel (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410250299.6A CN104015924A (en) | 2014-06-09 | 2014-06-09 | Track pump pneumatic lifting-body aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410250299.6A CN104015924A (en) | 2014-06-09 | 2014-06-09 | Track pump pneumatic lifting-body aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104015924A true CN104015924A (en) | 2014-09-03 |
Family
ID=51433005
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410250299.6A Pending CN104015924A (en) | 2014-06-09 | 2014-06-09 | Track pump pneumatic lifting-body aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104015924A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3115293A1 (en) * | 2015-07-08 | 2017-01-11 | Airbus Group SAS | Supercritical fuselage and aircraft comprising such a fuselage |
| CN107878733A (en) * | 2016-09-30 | 2018-04-06 | 通用电气公司 | Translation fan blade for the fan component of aircraft afterbody installation |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110248118A1 (en) * | 2010-04-08 | 2011-10-13 | Meekins John A | Amphibious Aircraft |
| CN102267559A (en) * | 2011-04-24 | 2011-12-07 | 王志成 | Moving-surface aerofoil |
| CN103171766A (en) * | 2011-12-20 | 2013-06-26 | 北京航空航天大学 | Short distance rising and landing unmanned all-wing aircraft |
-
2014
- 2014-06-09 CN CN201410250299.6A patent/CN104015924A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110248118A1 (en) * | 2010-04-08 | 2011-10-13 | Meekins John A | Amphibious Aircraft |
| CN102267559A (en) * | 2011-04-24 | 2011-12-07 | 王志成 | Moving-surface aerofoil |
| CN103171766A (en) * | 2011-12-20 | 2013-06-26 | 北京航空航天大学 | Short distance rising and landing unmanned all-wing aircraft |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3115293A1 (en) * | 2015-07-08 | 2017-01-11 | Airbus Group SAS | Supercritical fuselage and aircraft comprising such a fuselage |
| CN107878733A (en) * | 2016-09-30 | 2018-04-06 | 通用电气公司 | Translation fan blade for the fan component of aircraft afterbody installation |
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| C06 | Publication | ||
| PB01 | Publication | ||
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| C12 | Rejection of a patent application after its publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20140903 |