CN107226193A - A kind of method for reducing aircraft fuselage flight resistance - Google Patents
A kind of method for reducing aircraft fuselage flight resistance Download PDFInfo
- Publication number
- CN107226193A CN107226193A CN201710434378.6A CN201710434378A CN107226193A CN 107226193 A CN107226193 A CN 107226193A CN 201710434378 A CN201710434378 A CN 201710434378A CN 107226193 A CN107226193 A CN 107226193A
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- fuselage
- aircraft fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/0009—Aerodynamic aspects
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/06—Helicopters with single rotor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0045—Fuselages characterised by special shapes
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The present invention discloses a kind of method for reducing aircraft fuselage flight resistance, belongs to airborne vehicle technical field.Pass through change of flight device fuselage appearance dimension scale, aircraft fuselage appearance and size is set to meet the condition that height and length are far longer than width, the characteristics of using the positive section of its fuselage and elongated cross section, significantly reduce the resistance when flight of aircraft forward direction or VTOL.The depth-width ratio and length-width ratio that aircraft fuselage profile should typically be made >=2, can be realized using the monoblock type airframe structure for the condition that meets or combine to form fuselage with cabin using deflector.The present invention can improve the air dynamic behaviour of airborne vehicle, significantly reduce flight resistance, effectively neutralizing VTOL and at a high speed flat winged contradiction, flight mechanism is set more to coordinate, improve stability, wind loading rating, security, mobility, reliability, ease-to-operate and the applicability of airborne vehicle, airborne vehicle volume can be reduced, simplify structure, reduce cost, civil aviation and unmanned plane field is widely applicable to.
Description
Technical field
It is specifically a kind of to reduce aircraft fuselage flight resistance the present invention relates to a kind of aircraft condition improvement technology
The method of power, belongs to aircraft technical field.
Background technology
At present, airborne vehicle mainly uses column and spherical fuselage, spherical fuselage aircraft（Such as helicopter）Windage is larger,
Vertical lift and horizontal flight both of which are interfered, and " P jumps " occur when serious；And by engine arrangement in machine
Body, center of gravity is higher, and vertical lift and horizontal flight mode transfer process stability are poor；Particularly stiff two kinds of flights of superposition
Principle, flight mechanism inaccurate coordination, mechanism is complicated, and manipulation is difficult, and mobility is poor；Interfere serious, inefficiency.Column machine
Body aircraft（Such as various common fixed wing aircrafts）Technical comparing is ripe, but needs runway run-up high speed landing, using costliness,
Easily limited by landing site and weather condition, carbon emission is high, popularization is difficult.
Existing VTOL airborne vehicle only has column and spherical two kinds of fuselage configurations, causes airborne vehicle in VTOL
Windage it is larger, balance difficulties, influence flight safety, reduce efficiency, add energy consumption and noise；Especially in the presence of vertical liter
The situation that drop and horizontal flight both of which are interfered, two kinds of offline mode conversions are difficult, stability is poor.In addition, existing hang down
The design organization of straight landing airborne vehicle is complicated, center of gravity is higher, causes manipulation difficulty, poor mobility, serious interference, inefficient.
In view of the above-mentioned problems, correlation technique is attempted to solve using complicated Technology Ways, but almost it is required for larger cost and complexity
The cooperation of structure, lacks unpowered forced landing measure, and accident survival rate is low.For low cost simple structure solution, at present
There is not been reported.
The content of the invention
The technical problem to be solved in the present invention is in face of VTOL and winged at a high speed for existing aircraft body structure
Attended to one thing and lose sight of another and the uncoordinated deficiency of flight mechanism during row two states, propose a kind of side for reducing aircraft fuselage flight resistance
Method, airborne vehicle width is shunk by adjusting fuselage, changes aircraft fuselage aerodynamic configuration feature so that vertical direction and level
Direction air-flow is not blocked, is made flight mechanism in order so as to reach, is reduced flight resistance, reduction manipulation difficulty, simplifies working machine
Structure, the purpose for reducing cost, improving flight stability and security etc..
In order to solve the above technical problems, the present invention provides a kind of method for reducing aircraft fuselage flight resistance, change and fly
Row device fuselage appearance dimension scale, makes aircraft fuselage appearance and size meet the condition that height and length are far longer than width, profit
The characteristics of with the positive section of its fuselage and elongated cross section, significantly reduce the resistance when flight of aircraft forward direction or VTOL
Power.Aircraft fuselage appearance and size meets height and length is far longer than width, and the fuselage general performance that can make airborne vehicle is " piece
The feature of shape ", from while can ensureing that airborne vehicle does not block downwash flow in VTOL, does not also hide in high-speed flight
Windstream is kept off, the air drag of airborne vehicle is substantially reduced, VTOL is solved and equals winged contradiction at a high speed.Methods described
In, specific required fuselage appearance length, height, the ratio of width are determined according to actual needs, are met in aircraft and are not hidden
Keep off air flow demand.
It is described aircraft fuselage appearance and size satisfaction height and length is far longer than width, it is to instigate outside aircraft fuselage
>=2, the specific value of depth-width ratio and length-width ratio is actually needed determination to the depth-width ratio and length-width ratio of shape according to airborne vehicle size etc.,
Meet " sheet " feature of fuselage, reduce flight air drag.
Make that aircraft fuselage appearance and size meets height and length is far longer than width preferably, described, referring to can be with
The depth-width ratio and length-width ratio optimum range of aircraft fuselage profile are controlled between 3-10, with specific reference to being actually needed selection.
In this method, when fuselage is vertical, depth-width ratio is more than length-width ratio, and then length-width ratio is more than when fuselage is horizontal
Depth-width ratio.Pass through the particular geometry of the aircraft fuselage, it is ensured that fuselage is for air-flow horizontally and vertically
It is unobstructed, the good VTOL of formation and horizontal flight aerodynamic characteristic.
In order that the aircraft fuselage appearance and size meets height and length is far longer than width, it can use and meet bar
The monoblock type airframe structure of part is realized, also can combine to form fuselage with cabin using deflector, and fuselage is extended by deflector
Length or width, meet fuselage appearance depth-width ratio and length-width ratio requirement.Monolithic construction is used to meet before " sheet " be characterized as
Carry, use combining structure for the purpose of protruding " sheet " feature of fuselage by deflector, increase the application surface of this method.
When the length or width of the use deflector extension fuselage, deflector used is continuous surface structure, that is, is not had
The continuous surface in " cavity ", it is ensured that the continuity of fuselage airflow on surface during work.
The length of fuselage is extended or during width using deflector, deflector can be arranged at the top of cabin, bottom, in
Any position in portion, front portion, rear portion, can form the fuselage shapes such as hold formula, overhead bin formula, middle deck formula, head cabin formula, deck store formula,
Adapt to different environment needs.In concrete operations, sheet fuselage length, height, the adjustment of the ratio of width can be coordinated, according to aviation
Determined the need for the actual conditions such as form, wing, the power configuration of device, meet and ensure smooth flight and reduction resistance.
In this method, can with the cabin of aircraft fuselage described in flexible arrangement, so as to substantially reduce aircraft center of gravity position,
Improve the stability of fuselage.
Cabin width >=0.5m when the sheet fuselage is used for manned, with specific reference to determination is actually needed, meets manned
It is required that.
The windward side section of the aircraft fuselage and deflector should be symmetrical wedge shape, windward side contour line and should be streamline
Type, to reduce air drag.
The present invention uses change of flight device fuselage appearance dimension scale, aircraft fuselage appearance and size is met height and long
Degree is far longer than the method for the condition of width so that either horizontal flight or vertical risen using the airborne vehicle of the inventive method
Drop, the windage of fuselage can reduce to the level of very little, and can meet the conflicting flight operating mode of two kinds of VTOL airborne vehicle
Different needs so that with good adaptability.After the inventive method, deconstruct in the design of conventional lighter-than-air vehicles fuselage
Mutual restriction factor, aircraft centre of gravity can be greatly lowered with free surface jet in short transverse and length direction,
Airborne vehicle roll stability and flight stability can be increased substantially.Because the rotor of sheet fuselage aircraft is on top, fuselage
In bottom, and the airborne vehicle for using this method can land or take off against the wind naturally in fitful wind, no just as wind vane
But not disturbed by fitful wind, on the contrary can using fitful wind clamping improve takeoff and landing stability so that with compared with
Strong wind loading rating.It is our no matter from aerodynamics, or from flight mechanics, or from the angle of vehicle structural mechanics
Method can all improve the reasonability of airframe and the balance of mechanical relationship, so as to mitigate airborne vehicle manual control intensity and difficulty
Degree, brings excellent handling.
The present invention can significantly reduce the flight resistance of airborne vehicle, effectively solve VTOL and equal winged contradiction at a high speed, carry
Stability, wind loading rating, security, mobility, reliability, ease-to-operate and the applicability of high airborne vehicle, can reduce aviation
Body accumulates, simplifies structure, reduces cost, is widely applicable to civil aviation and unmanned plane field.
Brief description of the drawings
Fig. 1 is that the present invention is used for the horizontal fuselage embodiment schematic front view of vertically taking off and landing flyer hold formula.
Fig. 2 is that the present invention is used for the horizontal fuselage embodiment schematic side view of vertically taking off and landing flyer hold formula.
Fig. 3 is that the present invention is used for vertically taking off and landing flyer deck store formula fuselage embodiment schematic diagram.
Fig. 4 is that the present invention is used for vertically taking off and landing flyer front deck formula fuselage embodiment schematic diagram.
Fig. 5 is that the present invention is used for the vertical fuselage embodiment schematic diagram of vertically taking off and landing flyer overhead bin formula.
Fig. 6 is that the present invention is used for the vertical fuselage embodiment schematic diagram of vertically taking off and landing flyer hold formula.
Label in figure：1- fuselages, 1-1- deflectors, 1-2- cabins, 2- vertical rotors, 3- rotors.
Embodiment
Below in conjunction with the accompanying drawings, the embodiment to the present invention is further described in detail.It is unreceipted in embodiment
Technology or product are prior art or can be by buying the conventional products obtained.
Embodiment 1：The method that the present invention reduces aircraft fuselage flight resistance is used for VTOL man-carrying aircraft, specifically
Method is that, by change of flight device fuselage appearance dimension scale, allowing the fuselage appearance of airborne vehicle, to meet depth-width ratio be that 3, length-width ratio is
5 condition, makes aircraft fuselage appearance and size meet the condition that height and length are far longer than width, utilizes the positive section of its fuselage
With cross section it is elongated the characteristics of, pass through the particular geometry of the aircraft fuselage, it is ensured that fuselage is for horizontal direction
Air-flow with vertical direction is unobstructed, the good VTOL of formation and horizontal flight aerodynamic characteristic, significantly reduces aircraft
Resistance when forward direction flight or VTOL.
This method is realized using the monoblock type airframe structure for the condition that meets, and for details, reference can be made to Fig. 1-2.The machine of aircraft fuselage
Cabin width is 0.5m, the windward side section of aircraft fuselage and deflector be symmetrical wedge shape, windward side contour line be it is streamlined,
To reduce air drag.By lowering engine height and arranging other equipment and passenger along cabin bottom, so as to substantially reduce
Aircraft center of gravity position, improves the stability of fuselage.
Embodiment 2：The method that the present invention reduces aircraft fuselage flight resistance is used for VTOL man-carrying aircraft, specifically
Method is that, by change of flight device fuselage appearance dimension scale, allowing the fuselage appearance of airborne vehicle, to meet depth-width ratio be that 5, length-width ratio is
10 condition, makes aircraft fuselage appearance and size meet the condition that height and length are far longer than width, is just being broken using its fuselage
The characteristics of face and elongated cross section, pass through the particular geometry of the aircraft fuselage, it is ensured that fuselage is for level side
Unobstructed to the air-flow with vertical direction, the good VTOL of formation and horizontal flight aerodynamic characteristic significantly reduce flight
The resistance when flight of device forward direction or VTOL.
This method is combined to form aircraft fuselage using deflector with cabin, and deflector is arranged to the front of cabin
Put, form deck store formula fuselage, extend the length or width of fuselage by deflector, meet aircraft body contour depth-width ratio and length
Wide ratio requires that deflector used is continuous surface structure.By the cabin of flexible arrangement aircraft fuselage, so as to substantially reduce winged
Row device position of centre of gravity, improves the stability of fuselage.The cabin width of aircraft fuselage is 0.8m, aircraft fuselage and deflector
Windward side section is that symmetrical wedge-shaped, windward side contour line is streamlined, to reduce air drag.It for details, reference can be made to Fig. 3.
Embodiment 3：The method that the present invention reduces aircraft fuselage flight resistance is used for VTOL man-carrying aircraft, specifically
Method is that, by change of flight device fuselage appearance dimension scale, allowing the fuselage appearance of airborne vehicle, to meet depth-width ratio be that 4, length-width ratio is
8 condition, makes aircraft fuselage appearance and size meet the condition that height and length are far longer than width, utilizes the positive section of its fuselage
With cross section it is elongated the characteristics of, pass through the particular geometry of the aircraft fuselage, it is ensured that fuselage is for horizontal direction
Air-flow with vertical direction is unobstructed, the good VTOL of formation and horizontal flight aerodynamic characteristic, significantly reduces aircraft
Resistance when forward direction flight or VTOL.
This method is combined to form aircraft fuselage using deflector with cabin, and deflector is arranged to the rear portion of cabin
Position, formed front deck formula fuselage, by deflector extend fuselage length or width, meet aircraft body contour depth-width ratio and
Length-width ratio requirement, deflector used is continuous surface structure.By the cabin of flexible arrangement aircraft fuselage, so as to substantially reduce
Aircraft center of gravity position, improves the stability of fuselage.The cabin width of aircraft fuselage is 1m, aircraft fuselage and deflector
Windward side section is that symmetrical wedge-shaped, windward side contour line is streamlined, to reduce air drag.It for details, reference can be made to Fig. 4.
Embodiment 4：The method that the present invention reduces aircraft fuselage flight resistance is used for vertical take-off and landing unmanned airborne vehicle, specifically
Method be by change of flight device fuselage appearance dimension scale, allow airborne vehicle fuselage appearance meet depth-width ratio for 10, length-width ratio
For 3 condition, vertical fuselage is constituted, aircraft fuselage appearance and size is met the condition that height and length are far longer than width,
The characteristics of using the positive section of its fuselage and elongated cross section, pass through the particular geometry of the aircraft fuselage, it is ensured that
Fuselage is unobstructed for air-flow horizontally and vertically, the good VTOL of formation and the pneumatic spy of horizontal flight
Property, significantly reduce the resistance when flight of aircraft forward direction or VTOL.
This method is combined to form aircraft fuselage using deflector with cabin, and deflector is arranged to the lower portion of cabin
Put, form the vertical fuselage of overhead bin formula, deflector is arranged to the upper position of cabin, the vertical fuselage of hold formula is formed, by leading
The length or width of plate extension fuselage are flowed, aircraft body contour depth-width ratio and length-width ratio requirement is met, deflector used is company
Continuous surface texture.The windward side section of aircraft fuselage and deflector be it is symmetrical wedge shape, windward side contour line be it is streamlined, with
Reduce air drag.It for details, reference can be made to Fig. 5-6.
The technology contents of the present invention are described above in conjunction with accompanying drawing, but protection scope of the present invention be not limited to it is described
In content, the knowledge that one skilled in the relevant art possesses, the premise of present inventive concept can also not departed from
Under the technology contents of the present invention are made a variety of changes, within the spirit and principles of the invention, any modification for being made, etc.
With replacement, improvement etc., it should be included in the scope of the protection.
Claims (10)
1. a kind of method for reducing aircraft fuselage flight resistance, it is characterised in that：Change of flight device fuselage appearance dimension scale,
So that the width of aircraft fuselage appearance and size is far smaller than height and length, it is in long narrow shape to form the positive section of fuselage and cross section
The characteristics of, significantly reduce the air drag when flight of aircraft forward direction or VTOL.
2. the method according to claim 1 for reducing aircraft fuselage flight resistance, it is characterised in that：It is described to make aircraft
Fuselage appearance size meets height and length is far longer than width, is to instigate the depth-width ratio and length-width ratio of aircraft fuselage profile equal
≥2。
3. the method according to claim 1 or 2 for reducing aircraft fuselage flight resistance, it is characterised in that：Preferably,
It can control the depth-width ratio of aircraft fuselage between 3-10, length-width ratio is also between 3-10.
4. the method for the reduction aircraft fuselage flight resistance according to claim any one of 1-3, it is characterised in that：As
Vertical fuselage depth-width ratio is more than length-width ratio, and then length-width ratio is more than depth-width ratio as horizontal fuselage；Pass through the aircraft fuselage
Particular geometry, it is ensured that fuselage is unobstructed for air-flow horizontally and vertically, forms good vertical rise
Drop and horizontal flight aerodynamic characteristic.
5. the method according to claim 1 for reducing aircraft fuselage flight resistance, it is characterised in that：It is described to make aircraft
Fuselage appearance size meets height and length is far longer than width, can be realized using the monoblock type airframe structure for the condition that meets,
Also it can combine to form fuselage with cabin using deflector, extend the length or width of fuselage by deflector, meet fuselage appearance
Depth-width ratio and length-width ratio requirement.
6. the method according to claim 5 for reducing aircraft fuselage flight resistance, it is characterised in that：The use water conservancy diversion
When the length or width of plate extension fuselage, deflector used is continuous surface structure.
7. the method for the reduction aircraft fuselage flight resistance according to claim 5 or 6, it is characterised in that：Using water conservancy diversion
When the length or width of plate extension fuselage, deflector can be arranged at any in the top of cabin, bottom, middle part, front portion, rear portion
Position.
8. the method for the reduction aircraft fuselage flight resistance according to claim any one of 1-3, it is characterised in that：According to
The method of reduction aircraft fuselage flight resistance described in claim any one of 1-3, it is characterised in that：Can be with flexible arrangement institute
The cabin of aircraft fuselage is stated, so as to substantially reduce aircraft center of gravity position, the stability of fuselage is improved.
9. the method according to claim 1 or 2 for reducing aircraft fuselage flight resistance, it is characterised in that：The sheet
Cabin width >=0.5m when fuselage is used for manned.
10. airborne vehicle sheet fuselage according to claim 1, it is characterised in that：The aircraft fuselage and deflector
Windward side section should be symmetrical wedge shape, windward side contour line and should be streamlined, to reduce air drag.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710434378.6A CN107226193A (en) | 2017-06-09 | 2017-06-09 | A kind of method for reducing aircraft fuselage flight resistance |
| PCT/CN2018/090417 WO2018224033A1 (en) | 2017-06-09 | 2018-06-08 | Aircraft with imitation beetle elytron wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710434378.6A CN107226193A (en) | 2017-06-09 | 2017-06-09 | A kind of method for reducing aircraft fuselage flight resistance |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107226193A true CN107226193A (en) | 2017-10-03 |
Family
ID=59935894
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710434378.6A Pending CN107226193A (en) | 2017-06-09 | 2017-06-09 | A kind of method for reducing aircraft fuselage flight resistance |
Country Status (1)
| Country | Link |
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| CN (1) | CN107226193A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018224033A1 (en) * | 2017-06-09 | 2018-12-13 | 昆明鞘翼科技有限公司 | Aircraft with imitation beetle elytron wings |
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20171003 |
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