CN102616367B - Method for trimming fixed-wing airplane with high lift-drag ratio - Google Patents
Method for trimming fixed-wing airplane with high lift-drag ratio Download PDFInfo
- Publication number
- CN102616367B CN102616367B CN201210113438.1A CN201210113438A CN102616367B CN 102616367 B CN102616367 B CN 102616367B CN 201210113438 A CN201210113438 A CN 201210113438A CN 102616367 B CN102616367 B CN 102616367B
- Authority
- CN
- China
- Prior art keywords
- lift
- wing
- aircraft
- full machine
- moment
- 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.)
- Expired - Fee Related
Links
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
- Toys (AREA)
Abstract
本发明采用高升阻比正弯度翼型，在不利用平尾或鸭翼等带来降低全机升阻比的情况下，来实现机翼零升力矩的配平，充分发挥了正弯度翼型高升阻比特性。为实现机翼零升力矩配平，并且不造成全机升阻比下降，采用重心配置在机翼焦点正下方处的设计布局，以产生大的升阻比和抬头力矩来配平正弯度翼型固有的低头力矩，同时使全机具有纵向静稳定性。既能提高飞机的升阻比，又能使全机具有静稳定性。本发明的一种高升阻比固定翼飞机包括：具有大展弦比正弯度的机翼，用于提供升力，从而提供全机升力；位于机翼的焦点正下方的机身；机翼支撑梁，用于连接所述机身与机翼；设置在机身上的发动机，用于提供推力。本发明还提供了一种固定翼飞机的高升阻比的实现方法。
The present invention adopts positive camber airfoil with high lift-to-drag ratio, and realizes zero-lift moment trimming of the wing without using flat tail or canard to reduce the lift-to-drag ratio of the whole machine, and fully utilizes the high lift-drag of positive camber airfoil than idiosyncratic. In order to achieve zero-lift moment trimming of the wing without causing a decrease in the lift-to-drag ratio of the whole aircraft, the design layout with the center of gravity placed directly below the focus of the wing is adopted to generate a large lift-to-drag ratio and nose-up moment to balance the inherent positive camber airfoil. At the same time, the whole machine has longitudinal static stability. It can not only improve the lift-to-drag ratio of the aircraft, but also make the whole aircraft have static stability. A high-lift-to-drag ratio fixed-wing aircraft of the present invention comprises: a wing with a large aspect ratio positive camber, used to provide lift, thereby providing lift of the whole machine; a fuselage positioned directly below the focal point of the wing; and a wing support beam , used to connect the fuselage and the wings; the engine arranged on the fuselage is used to provide thrust. The invention also provides a method for realizing the high lift-to-drag ratio of the fixed-wing aircraft.
Description
Technical field
The present invention relates to a kind of Calculate Ways of high lift-drag ratio fixed wing aircraft, belong to fixed wing aircraft design field in aviation aircraft.
Technical background
Under same design speed, improve aircraft 1ift-drag ratio, in same design weight situation, aircraft drag is less, and thrust required is less.Aircraft 1ift-drag ratio is larger, and the aerodynamic performance of aircraft is better, and economy is higher.
In order to improve the 1ift-drag ratio of aircraft, select from airplane design aerofoil profile, should select the positive camber aerofoil profile that 1ift-drag ratio is large.But in current airplane design, the airplane design of selecting positive camber aerofoil profile, the trim of wing zero lift moment is all to realize by the mode such as horizontal tail or canard, this has just brought lift and drag losses, reduce full machine 1ift-drag ratio, can not give full play to positive camber aerofoil profile high lift-drag ratio characteristic.
And the aircraft of anury formula layout adopts the way of twisted wings to realize trim conventionally, adopt S aerofoil profile, ensure that the zero lift moment coefficient of aircraft is for just.And S aerofoil profile 1ift-drag ratio is far smaller than positive camber aerofoil profile.The method is that the cost of sacrificing 1ift-drag ratio exchanges stability for.
Summary of the invention
The invention of this aircraft topological design, adopts high lift-drag ratio positive camber aerofoil profile, and does not utilize horizontal tail or canard etc. to bring the means that reduce full machine 1ift-drag ratio, realizes the trim of wing zero lift moment, gives full play to positive camber aerofoil profile high lift-drag ratio characteristic.In order to realize the trim of wing zero lift moment, and do not cause full machine 1ift-drag ratio to decline.The layout that adopts gravity allocation to locate under wing focus to produce large 1ift-drag ratio and nose-up pitching moment, makes full facility have Longitudinal static stability simultaneously.Can improve the 1ift-drag ratio of aircraft, can make again full facility have static stability.
According to an aspect of the present invention, provide a kind of high lift-drag ratio fixed wing aircraft, it is characterized in that comprising:
There is the wing of high aspect ratio positive camber, for lift is provided, thereby provide full machine lift,
Be positioned at the fuselage under the focus of wing,
Wing support beam, for connecting described fuselage and wing,
Be arranged on the driving engine on fuselage, for thrust is provided.
According to another aspect of the present invention, provide a kind of implementation method of high lift-drag ratio of fixed wing aircraft, it is characterized in that comprising:
Provide lift with the wing with high aspect ratio positive camber, thereby full machine lift be provided,
Fuselage is arranged under the focus of wing,
Connect described fuselage and wing with wing support beam,
Provide thrust with the driving engine being arranged on fuselage.
Brief description of the drawings
Fig. 1 (a) is the schematic diagram of the scheme of employing tailplane Calculate Ways.
Fig. 1 (b) is the schematic diagram of the scheme of employing canard Calculate Ways.
Fig. 2 (a) is for adopting the scheme schematic diagram of this new invention layout method trim under noiseless incoming flow effect.
Fig. 2 (b) for adopt this new invention layout method below disturb the scheme schematic diagram of trim under incoming flow effect.
Fig. 2 (c) is for adopting this new invention layout method to disturb up the scheme schematic diagram of trim under incoming flow effect.
Fig. 3 is the schematic diagram that adopts this new invention layout method specific embodiment scheme.
Detailed description of the invention
Adopt the airplane design of independent positive camber aerofoil profile, as being in airfoil lift, act on zero lift moment on wing non-vanishing at 1 o'clock, this moment will make full machine produce nose-down pitching moment.Need the take measures zero lift moment of trim wing.Usual way comprises horizontal tail, canard etc., specifically sees force analysis Fig. 1.
Fig. 1 (a) is for adopting tailplane Calculate Ways, and O point is full machine center of gravity.Positive camber wing (1) zero lift moment is bowed full machine.The lift (Lw) of horizontal tail is downwards, and makes full machine zero lift moment coefficient for just, is nose-up pitching moment, realizes full machine trim.But the method causes full machine loss of lift.
Fig. 1 (b) is for adopting canard Calculate Ways, and O point is full machine center of gravity.Positive camber wing (1) zero lift moment is bowed full machine.The lift (Ly) of canard is for upwards, and makes full machine zero lift moment coefficient for just, is nose-up pitching moment, realizes full machine trim.But the method causes full machine resistance to increase.
And the present invention adopts the trim measure of not losing full machine 1ift-drag ratio.According to one embodiment of present invention, under being disposed to wing focus, full mechanical coke point locates, as shown in Figure 2.
In Fig. 2 (a), in the distance under incoming flow (V0) effect, the stressed and trim situation of full machine is: full machine lift (L) and gravity (G) balance, thrust (T) and air resistance (D) balance; The moment of resistance (D) and center of gravity (O) is nose-up pitching moment, the zero lift moment (M0) that this moment can trim positive camber wing (1), thus realize the moment trim of full machine.And do not lose the 1ift-drag ratio of full machine.The true angle of incidence (a) is the corresponding angle of attack of wing maximum lift-drag ratio for this reason time.
In Fig. 2 (b), aircraft horizontal flight, run into become d a beam to disturb incoming flow (V1) during with horizontal surface, stressed and the trim situation of full machine is: aircraft is d a with respect to the angle of attack that disturbs incoming flow (V1), lift (d L) direction and interference incoming flow (V1) direction are vertically upward, resistance (d D) direction is identical with interference incoming flow (V1) direction, and other power do not change; Resistance (d D) horizontal component and lift (d L) horizontal component and thrust-balancing.Compared with Fig. 2 (a) resistance (D) lift (L), resistance (d D) counterweight mental and physical efforts arm reduces, lift (dL) counterweight mental and physical efforts arm increases, two power are negative with the moment that full machine center of gravity (O) forms, be nose-down pitching moment, (d a) changes, when making full facility have static stability to reduce the increase of the full machine angle of attack.
In Fig. 2 (c), aircraft horizontal flight, run into become d a ' beam to disturb incoming flow (V2) during with horizontal surface, stressed and the trim situation of full machine is: aircraft is d a ' with respect to the angle of attack that disturbs incoming flow (V2), the lift arm of force (dL ') direction with disturb incoming flow (V2) direction vertically upward,, resistance (d D ') direction is identical with interference incoming flow (V1) direction, and other power do not change; Resistance (d D ') horizontal component and lift (d L ') horizontal component and thrust-balancing.。Compared with Fig. 2 (a) resistance (D) lift (L), resistance (d D ') counterweight mental and physical efforts arm reduces, the lift arm of force (d L ') increases center of gravity, the moment that two power and full machine center of gravity (O) form is for just, be nose-up pitching moment, reduce (the d a ') that reduce the full machine angle of attack changes, and makes full facility have static stability.
In sum, the present invention can give full play to positive camber aerofoil profile high lift-drag ratio advantage, improves the 1ift-drag ratio of full machine.
Fig. 3 has shown high lift-drag ratio fixed wing aircraft according to an embodiment of the invention, and it adopts high aspect ratio positive camber wing (1), and fuselage (4) is positioned under wing focus, is connected with wing (1) by wing support beam (2).Realize the sliding landing of running by tricycle landing gear (8,9,10), the interior visual field of driving compartment (6) is good.
As shown in Figure 3, full machine center of gravity is positioned at O point, and wing focus is positioned at O ' point.When aircraft is in the time that airless interference level flies, its full machine lift (L) and gravity (G) balance, driving engine (5) thrust (T) and full machine resistance (D) balance, thus reach full machine power balance; Full machine lift (L), gravity (G) thrust (T) is passed through center of gravity, therefore be zero with respect to center of gravity O pitching moment, and full machine resistance (D) is not by center of gravity O, it is H with respect to the center of gravity O arm of force, with respect to the moment of center of gravity O just in time with wing zero lift moment (M0) trim, thereby realize force balance and the moment balance of full machine.In figure, wing support beam (2) specific design height has determined arm of force H, is determined by the zero lift moment of selected positive camber wing (1).The zero lift moment of resistance under cruising condition (D) and arm of force H-vector moment balance positive camber wing (1).In the time that wing zero lift moment is large, the selected corresponding increase of H value.
The flight control of aircraft realizes by a pair of aileron (2,3) on wing, and aileron (2,3) is in order to the control of Aircraft Lateral side direction.And longitudinal pitch control subsystem of aircraft, by the change of control engine (5) thrust size, realizes the lifting of aircraft.Engine thrust increases, and realizes aircraft altitude and climbs; Engine thrust reduces, and the height of realizing aircraft reduces.
Advantage of the present invention comprises:
Compared with prior art, there is obvious technical advantage in the present invention:
Positive camber aerofoil profile 1ift-drag ratio is large, but in existing airplane design, can not give full play to positive camber aerofoil profile high lift-drag ratio advantage.Reason is mainly: the technical measures of zero liter of pitching moment of trim have reduced the 1ift-drag ratio of full machine.
The present invention is directed to above weakness, proposed a kind of brand-new aircraft layout.By force analysis, can meet power and moment trim requirement, prove that it is effective, and can give full play to the high lift-drag ratio characteristic of positive camber aerofoil profile wing, thereby reach the object that improves aircraft 1ift-drag ratio.
Claims (8)
1. high lift-drag ratio fixed wing aircraft, is characterized in that comprising:
There is the wing (1) of high aspect ratio positive camber, for lift is provided, thereby provide full machine lift (L),
Be positioned at the fuselage (4) under the focus (O ') of wing (1),
Wing support beam (2), for connecting described fuselage (4) and wing (1),
Be arranged on the driving engine (5) on fuselage (4), for thrust (T) is provided,
Wherein
When aircraft is in the time that airless interference level flies, its full machine lift (L) and gravity (G) balance, driving engine (5) thrust (T) and full machine resistance (D) balance, thus reach full machine power balance; Full machine lift (L) and thrust (T) are passed through center of gravity (O), thereby are zero with respect to center of gravity (O) pitching moment,
The length of wing support beam (2) has determined the arm of force (H) of full machine resistance (D) with respect to the center of gravity (O) of described high lift-drag ratio fixed wing aircraft, be that full machine resistance (D) is not by center of gravity (O), and full machine resistance (D) is with respect to the moment of described center of gravity (O) and zero lift moment (M0) trim of described wing, thereby realize force balance and the moment balance of full machine.
2. according to the high lift-drag ratio fixed wing aircraft of claim 1, it is characterized in that further comprising:
A pair of aileron on wing (1) or spoiler (2,3), for realizing the control of Aircraft Lateral side direction,
Wherein longitudinal pitch control subsystem of aircraft, is to realize by the thrust size of control engine (5), thereby realizes the lifting of aircraft, that is: engine thrust increase realizes and mushing, and engine thrust reduces to realize the height reduction of aircraft.
3. according to the high lift-drag ratio fixed wing aircraft of claim 1, it is characterized in that the stagger angle (a) of described wing (1) is:
In the distance under incoming flow (V0) effect, full machine lift (L) and gravity (G) balance, thrust (T) and air resistance (D) balance, zero lift moment (M0) as resistance (D) with the nose-up pitching moment trim positive camber wing (1) of the moment of center of gravity (O), thereby realize the moment trim of full machine, and do not lose the 1ift-drag ratio of full machine, the true angle of incidence (a) is the angle of attack corresponding to wing maximum lift-drag ratio for this reason time.
4. according to the high lift-drag ratio fixed wing aircraft of claim 1, it is characterized in that
When running in aircraft horizontal flight with horizontal surface at an angle (when interference incoming flow (V1) a) of d, stressed and the trim situation of full machine is: aircraft is that (d a) for described angle with respect to the angle of attack that disturbs incoming flow (V1), lift (d L) direction and interference incoming flow (V1) direction are vertically upward, resistance (d D) direction is identical with interference incoming flow (V1) direction, and other power do not change; Resistance (d D) horizontal component and lift (d L) horizontal component and thrust-balancing, compared with while flight with airless interference level, resistance (d D) counterweight mental and physical efforts arm reduces, lift (d L) counterweight mental and physical efforts arm increases, the moment that resistance and lift and full machine center of gravity (O) form is for negative, be nose-down pitching moment, thereby the increase that reduces the full machine angle of attack (d a), and make full facility have Longitudinal static stability.
5. the implementation method of the high lift-drag ratio of fixed wing aircraft, is characterized in that comprising:
Provide lift with the wing (1) with high aspect ratio positive camber, thereby full machine lift (L) be provided,
Fuselage (4) is arranged under the focus (O ') of wing (1),
Connect described fuselage (4) and wing (1) with wing support beam (2),
Provide thrust (T) with the driving engine (5) being arranged on fuselage (4),
Wherein
When aircraft is in the time that airless interference level flies, its full machine lift (L) and gravity (G) balance, driving engine (5) thrust (T) and full machine resistance (D) balance, thus reach full machine power balance;
The length of wing support beam (2) has determined the arm of force (H) of full machine resistance (D) with respect to the center of gravity (O) of described high lift-drag ratio fixed wing aircraft, and full machine resistance (D) does not pass through center of gravity (O),
And the implementation method of promotion resistance further comprises:
Making full machine lift (L) and thrust (T) by center of gravity (O), is zero thereby make with respect to the pitching moment of center of gravity (O),
Make full machine resistance (D) with respect to the moment of described center of gravity (O) and zero lift moment (M0) trim of described wing, thereby realize force balance and the moment balance of full machine.
6. according to the implementation method of the high lift-drag ratio of claim 5, it is characterized in that further comprising:
Realize the control of Aircraft Lateral side direction with a pair of aileron (2,3) on wing (1),
Realize longitudinal pitch control subsystem of aircraft by the thrust size of control engine (5), thereby realize the lifting of aircraft, that is: make to mush by increasing engine thrust, reduce the height of aircraft by reducing engine thrust.
7. according to the implementation method of the high lift-drag ratio of claim 5, it is characterized in that
By determining the stagger angle (a) of described wing (1), make under incoming flow (V0) effect in the distance, full machine lift (L) and gravity (G) balance, thrust (T) and air resistance (D) balance, and make the zero lift moment (M0) as the nose-up pitching moment trim positive camber wing (1) of the moment of resistance (D) and center of gravity (O), thereby realize the moment trim of full machine, and do not lose the 1ift-drag ratio of full machine, the true angle of incidence (a) is the angle of attack corresponding to wing maximum lift-drag ratio for this reason time.
8. according to the implementation method of the high lift-drag ratio of claim 5, it is characterized in that
When running in aircraft horizontal flight with horizontal surface at an angle (when interference incoming flow (V1) a) of d, stressed and the trim situation of full machine is: aircraft is that (d a) for described angle with respect to the angle of attack that disturbs incoming flow (V1), lift (d L) direction and interference incoming flow (V1) direction are vertically upward, resistance (d D) direction is identical with interference incoming flow (V1) direction, and other power do not change; The horizontal component of resistance (d D) and lift (d L) horizontal component and thrust-balancing, compared with while flight with airless interference level, resistance (d D) counterweight mental and physical efforts arm reduces, lift (d L) counterweight mental and physical efforts arm increases, the moment that resistance and lift and full machine center of gravity (O) form is for negative, be nose-down pitching moment, thereby the increase that reduces the full machine angle of attack (d a), and make full facility have Longitudinal static stability.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210113438.1A CN102616367B (en) | 2012-04-17 | 2012-04-17 | Method for trimming fixed-wing airplane with high lift-drag ratio |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210113438.1A CN102616367B (en) | 2012-04-17 | 2012-04-17 | Method for trimming fixed-wing airplane with high lift-drag ratio |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102616367A CN102616367A (en) | 2012-08-01 |
| CN102616367B true CN102616367B (en) | 2014-08-06 |
Family
ID=46556676
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210113438.1A Expired - Fee Related CN102616367B (en) | 2012-04-17 | 2012-04-17 | Method for trimming fixed-wing airplane with high lift-drag ratio |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102616367B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103523205B (en) * | 2013-04-07 | 2016-06-08 | 夏春光 | A kind of wing |
| CN106021786A (en) * | 2016-05-31 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft six-freedom-degree nonlinear equation set balancing method |
| CN112880917A (en) * | 2021-01-13 | 2021-06-01 | 万丰飞机工业有限公司 | Static balancing tool and measuring method for airplane control surface |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4206892A (en) * | 1978-07-24 | 1980-06-10 | Paul B. MacCready, Jr. | Lightweight aircraft |
| US4781341A (en) * | 1981-10-02 | 1988-11-01 | Kasper Witold A | Flying wing aircraft |
| US5054721A (en) * | 1989-03-22 | 1991-10-08 | Translab, Inc. | Vertical takeoff aircraft |
| CN1718506A (en) * | 2005-08-02 | 2006-01-11 | 西北工业大学 | A pitch control method and control mechanism for a miniature aircraft |
-
2012
- 2012-04-17 CN CN201210113438.1A patent/CN102616367B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4206892A (en) * | 1978-07-24 | 1980-06-10 | Paul B. MacCready, Jr. | Lightweight aircraft |
| US4781341A (en) * | 1981-10-02 | 1988-11-01 | Kasper Witold A | Flying wing aircraft |
| US5054721A (en) * | 1989-03-22 | 1991-10-08 | Translab, Inc. | Vertical takeoff aircraft |
| CN1718506A (en) * | 2005-08-02 | 2006-01-11 | 西北工业大学 | A pitch control method and control mechanism for a miniature aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102616367A (en) | 2012-08-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103552682B (en) | A kind of all-wing aircraft and buzzard-type wing connection wing airplane | |
| CN109808913B (en) | A UAV design method with deflectable winglets | |
| CN203666966U (en) | Canard wing configuration aircraft provided with movable strakes | |
| CN102730183B (en) | Novel solar airplane | |
| CN202320772U (en) | High lift device of double-aisle large-type passenger plane | |
| CN103482054B (en) | Low-Reynolds-number wing section matched with full-wing solar unmanned aerial vehicle | |
| CN105905277B (en) | A kind of aerodynamic configuration of aircraft using the rear edge support wing | |
| CN201023653Y (en) | Aerodynamic layout of large aspect ratio forward-swept wing aircraft | |
| CN106005366A (en) | Pneumatic layout of dual flying wings of UAV (Unmanned Aerial Vehicle) | |
| CN107757871B (en) | Airfoil profile for light and small fixed wing unmanned aerial vehicle | |
| CN103231795A (en) | Corporate aircraft engine upper placement and front swept wing duck type layout | |
| CN107187599A (en) | A kind of HAE aerodynamic configuration of aircraft of use two-shipper height rear wing Three-wing-surface | |
| CN203666968U (en) | Negative dihedral aerofoil winglet structure | |
| CN106828872B (en) | Using the high rear wing high altitude long time tandem rotor aircraft aerodynamic arrangement of support empennage | |
| CN103693187A (en) | Wing structure | |
| CN102826216A (en) | Aerodynamic configuration of aircraft | |
| CN102616367B (en) | Method for trimming fixed-wing airplane with high lift-drag ratio | |
| CN106828933A (en) | A kind of HAE tandem rotor aircraft aerodynamic arrangement using upper inverted diherdral difference | |
| CN110182361B (en) | Vertically taking off and landing fixed wing unmanned aerial vehicle capable of tilting | |
| CN202953169U (en) | Novel spoon-shaped blended winglet for civil airplane | |
| CN104401504B (en) | A kind of fixed-wing aerial survey type unmanned aerial vehicle design method | |
| CN103407574B (en) | Novel efficient notch airfoil shape of parafoil unmanned plane and optimum design method thereof | |
| CN103171758A (en) | Lift-rising method of flying wing type airplane | |
| CN211107983U (en) | A tiltable vertical take-off and landing fixed-wing UAV | |
| CN109263855B (en) | Aerodynamic layout of a super-aspect-ratio aircraft using trailing edge support wings |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140806 Termination date: 20150417 |
|
| EXPY | Termination of patent right or utility model |