CN111688910A - Aerodynamic wing aircraft - Google Patents
Aerodynamic wing aircraft Download PDFInfo
- Publication number
- CN111688910A CN111688910A CN201910219531.2A CN201910219531A CN111688910A CN 111688910 A CN111688910 A CN 111688910A CN 201910219531 A CN201910219531 A CN 201910219531A CN 111688910 A CN111688910 A CN 111688910A
- Authority
- CN
- China
- Prior art keywords
- wing
- longitudinal
- jet engine
- fuselage
- tail
- 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.)
- Pending
Links
- 229910000838 Al alloy Inorganic materials 0.000 claims abstract description 7
- 239000000463 material Substances 0.000 claims abstract description 3
- 239000011490 mineral wool Substances 0.000 claims abstract description 3
- 239000007921 spray Substances 0.000 claims abstract 2
- 239000011248 coating agent Substances 0.000 claims description 2
- 238000000576 coating method Methods 0.000 claims description 2
- 238000009413 insulation Methods 0.000 claims description 2
- 238000005507 spraying Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 239000003638 chemical reducing agent Substances 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/06—Adjustable control surfaces or members, e.g. rudders with two or more independent movements
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/16—Aircraft characterised by the type or position of power plants of jet type
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The aerodynamic wing aircraft belongs to the technical field of aviation. The aircraft consists of a fuselage, aerodynamic wings and a jet engine 1. The upper side of the front edge of the longitudinal wing 3 is provided with a jet engine 1 and a flat nozzle 2, and the lower side is hinged with a flap 14. Two sides of the longitudinal wing 3 are provided with wing edges 4, and the tail part is provided with a vertical tail wing 5, a steering rudder 6 and an elevator 7. The framework 12 of the longitudinal wing 3 is an aluminum alloy lattice truss which is connected with the framework of the fuselage, the upper surface of the framework is provided with a heat-resistant layer 10 made of jet engine tail nozzle material, and the space of the framework 12 is filled with a mineral wool heat-insulating layer 11. The jet engine 1 is composed of an engine body and a flat nozzle 2. The front edges of longitudinal wings 3 are uniformly distributed on a group of engines, and spray pipes are gathered in the flat nozzle 2. The tail part of the airplane body structure is only provided with a horizontal tail wing 8 and a speed reducing plate 9 like the existing airplane. The jet generates both thrust and lift. The wing has less windward side, small flight resistance, reduced oil consumption, good invisibility and good maneuverability. For designing new jet aircraft.
Description
Technical Field
The aerodynamic wing aircraft belongs to the technical field of aviation.
Background
The traditional aircraft wing utilizes the air flow generated by the convex upper board surface and the convex lower board surface of the wing to generate lift force. The wing area span is increased along with the takeoff weight, so that the wing structure needs to be enhanced, the airplane weight is increased, the ground maneuverability is reduced, and the technical and economic performance of the airplane is influenced.
Disclosure of Invention
The technical problem to be solved by the aerodynamic wing aircraft is as follows: a new wing structure is designed to generate lift.
The technical scheme is as follows: the wing is arranged along the whole length of the fuselage, and the front edge of the wing surface is provided with a flat jet nozzle.
The aerodynamic wing aircraft (attached figure) consists of three parts, namely a fuselage, an aerodynamic wing and a jet engine 1. The aerodynamic wing consists of a longitudinal wing 3, a wing edge 4, a vertical tail wing 5, a steering rudder 6, an elevator 7, an aileron 13 and a flap 14. The longitudinal wings 3 are fixed to the top surface of the fuselage and arranged along the entire length of the fuselage. The upper side of the wing leading edge is provided with a jet engine 1 and a flat nozzle 2, and high-speed fuel gas sprayed by the jet engine 1 flows along the upper surface of the longitudinal wing 3. Two sides of the longitudinal wing 3 are provided with wing edges 4 vertical to the wing surface, so that the left and right diffusion of the gas flow in the fuselage section can be reduced. Two vertical tail wings 5 are arranged at the tail parts of the longitudinal wings 3, so that the stable flying of the airplane in the left and right directions is ensured. The rear part of the vertical tail wing 5 is hinged with a steering rudder 6 for controlling the left and right steering of the airplane. The rear edge of the longitudinal wing 3 is provided with an elevator 7 for controlling the airplane to ascend and descend. The left and the right of the front edge of the longitudinal wing 3 are respectively hinged with a flap 14, so that the lift force is increased during take-off; when falling, it acts as a speed reducer. Two ends of the front edge of the longitudinal wing 3 are respectively hinged with an overhanging aileron 13, so that the airplane can be inclined transversely to assist in turning when the airplane turns.
The jet engine 1 is composed of an engine body and a flat nozzle 2. The engine body is arranged at the front edge of the longitudinal wing 3 and can be uniformly distributed in one or a group. The nozzles of a group of engines are all collected in a flat nozzle 2.
The tail part of the fuselage is provided with two horizontal tail wings 8 which play a role of horizontal stability. The lower surface of the horizontal tail wing 8 is hinged with a speed reducing plate 9 for reducing speed when falling. The other structures inside and outside the airplane body comprise a cockpit, an instrument control system, a passenger and cargo hold, a front wheel, an undercarriage, a landing wheel and the like of the existing airplane.
The jet speed V of the jet engine 1 during flightSpraying nozzleAnd the airplane is pushed to fly. The aircraft meets the air resistance to ensure the flying speed V of the aircraftFly away＜VSpraying nozzle. Air velocity V of the air under the longitudinal wing 3 with respect to the aircraft rear flowQi (Qi)Is equal to the flying speed VFly awayTherefore, is atQi (Qi)＜VSpraying nozzleThe longitudinal wings 3 generate lift force and float in the air.
The aerodynamic wing aircraft has the beneficial effects that: the air injection generates both thrust and lift; the windward side of the wing is less, the flight resistance is small, the oil consumption is reduced, and the reflection of the received radar waves is less, so that the wing is beneficial to hiding; the wingspan is small, and the ground take-off and landing maneuverability is good.
Drawings
The attached drawing is a schematic view of the structure of an aerodynamic wing aircraft.
In the figure: 1-a jet engine; 2-flat nozzle; 3-longitudinal wing; 4-winged edge; 5-vertical tail; 6-steering rudder; 7-elevator; 8-horizontal tail; 9-a speed reduction plate; 10-a heat-resistant layer; 11-a thermally insulating layer; 12-a backbone; 13-ailerons; 14-a flap; 15-upright post.
Detailed Description
The framework 12 of the longitudinal wing 3 is an aluminum alloy lattice truss, is connected with the framework of the fuselage and bears the load of the fuselage. The upper surface of the longitudinal wing 3 is provided with a heat-resistant layer 10 which is made of a material of a tail jet pipe of the jet engine and can endure jet temperature for a long time. The space of the framework 12 is filled with a mineral wool heat insulation layer 11, so that the air injection temperature can be insulated for a long time. The joint of the front edge of the military aircraft longitudinal wing 3 and the flat nozzle 2 is wedge-shaped, and the military aircraft longitudinal wing is provided with a radar wave scattering layer and a radar wave absorbing coating.
The jet engine 1 is connected with a fuselage skeleton by a vertically arranged aluminum alloy lattice truss, an aluminum alloy skin is coated outside to form an upright post 15, the cross section of the upright post is in a wedge streamline shape, the wedge head scatters radar waves, and the streamline shape reduces air resistance.
Claims (3)
1. Aerodynamic wing aircraft, including fuselage, jet engine (1), characterized by: further comprising an aerodynamic wing; the aerodynamic wing consists of a longitudinal wing (3), a wing edge (4), a vertical tail wing (5), a steering rudder (6), an elevator (7), an aileron (13) and a flap (14); the longitudinal wing (3) is fixed on the top surface of the fuselage and is arranged along the whole length of the fuselage; the upper side of the front edge of the wing is provided with a jet engine (1) and a flat nozzle (2), the two side edges are provided with wing edges (4) of a vertical wing surface, and the tail part is provided with two vertical tail wings (5) hinged with a steering rudder (6); the rear edge of the longitudinal wing (3) is provided with an elevator (7), both sides of the front edge are respectively hinged with a flap (14), and both ends of the front edge are respectively hinged with an overhanging aileron (13);
the jet engine (1) consists of an engine body and a flat nozzle (2); the engine body is arranged at the front edge of the longitudinal wing (3) and can be uniformly distributed in one or a group; the spray pipes of a group of engines are all gathered in a flat nozzle (2);
the tail part of the fuselage is provided with two horizontal tail wings (8), and the lower surfaces of the two horizontal tail wings are hinged with speed reducing plates (9).
2. An aero-wing aircraft according to claim 1 wherein: the framework (12) of the longitudinal wing (3) is an aluminum alloy lattice truss and is connected with the framework of the fuselage; the upper surface of the longitudinal wing (3) is provided with a heat-resistant layer (10) which is made of a jet engine tail nozzle material; the framework (12) is filled with a mineral wool heat insulation layer (11); the joint of the front edge of the longitudinal wing (3) and the flat nozzle (2) is wedge-shaped, and a coating for absorbing radar waves is also arranged.
3. An aero-wing aircraft according to claim 1 wherein: the jet engine (1) is connected with the frame of the airplane body by a vertically arranged aluminum alloy lattice truss; the aluminum alloy skin is wrapped outside to form a column (15), and the cross section of the column is in a wedge streamline shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910219531.2A CN111688910A (en) | 2019-03-16 | 2019-03-16 | Aerodynamic wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910219531.2A CN111688910A (en) | 2019-03-16 | 2019-03-16 | Aerodynamic wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111688910A true CN111688910A (en) | 2020-09-22 |
Family
ID=72475981
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910219531.2A Pending CN111688910A (en) | 2019-03-16 | 2019-03-16 | Aerodynamic wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111688910A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114572381A (en) * | 2022-04-19 | 2022-06-03 | 中国商用飞机有限责任公司 | Tail cone with speed reducing assembly and airplane provided with tail cone |
-
2019
- 2019-03-16 CN CN201910219531.2A patent/CN111688910A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114572381A (en) * | 2022-04-19 | 2022-06-03 | 中国商用飞机有限责任公司 | Tail cone with speed reducing assembly and airplane provided with tail cone |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |