CN103171758A - Lift-rising method of flying wing type airplane - Google Patents
Lift-rising method of flying wing type airplane Download PDFInfo
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- CN103171758A CN103171758A CN2011104308484A CN201110430848A CN103171758A CN 103171758 A CN103171758 A CN 103171758A CN 2011104308484 A CN2011104308484 A CN 2011104308484A CN 201110430848 A CN201110430848 A CN 201110430848A CN 103171758 A CN103171758 A CN 103171758A
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Abstract
The invention provides a lift-rising method of a flying wing type airplane, which can solve the problems of low control efficiency and poor rising and landing performances of the flying wing type airplane, the method can effectively satisfy the lift force requirements at a rising and landing phase, and the rising and landing performances of the flying wing type airplane can be enhanced. The lift-rising method is the cooperation of vector force and lift-rising apparatus such as leading and trailing edge flaps. The leading edge flap and the trailing edge flap can provide the lift force and resisting force for satisfying a task segment at the rising and landing phases, but the flying wing type airplane is difficult to trim the pitching moment. The vector force is introduced before center of gravity of the flying wing, the rising and landing performances can be enhanced at two aspects of force and moment, wherein the moment is used for trimming the nose-down pitching moment generated by the lift-rising apparatus, and force can balance partial weight. The lift-rising method can be used for the flying wing type airplane, the technology is simple, and the effect is obvious.
Description
Technical field
The present invention relates to fixed wing aircraft design field in aviation aircraft, be particularly useful for small-sized Flying-wing aircraft short take-off and landing (STOL) technical field.
Background technology
Blended wing-body refers to that wing and fuselage are fused into one, and unlike fuselage and the wing of aircraft have obvious boundary usually.Such fusion makes fuselage produce lift as the part of wing.
Flying-wing adopts wing body to merge and the anury design mostly, has following advantage:
-integrated optimum pneumatic topological design; Pneumatic efficiency is high, and resistance is little, and 1ift-drag ratio is high;
-structural weight is good, good rigidly, and load distributes and reaches best along spanwise distribution;
-for Large Civil Aircraft, Flying-wing can increase propelling power spaces; For military aircraft, has good Stealth Fighter.
Shortcoming is:
-primary control surface is near apart from center of gravity, and rudder effectiveness is low, and the landing poor performance of taking off causes certain stability not enough for reducing the trim loss.
-due to the moment trim effect that there is no the horizontal tail elevating rudder, the Flying-wing aircraft can't adopt the pneumatic high lift devices such as the leading edge, trailing edge of conventional airplane, cause its available maximum lift coefficient very low, the trim slope of lift curve is less, therefore at the landing that needs lift-rising and low-speed operations stage poor-performing.
The pneumatic design of aircraft wing, to consider high-speed flight and maneuverability requirement on the one hand, on the other hand when take-off and landing, reduce as far as possible again flying speed, shorten ground run distance, cruise performance loss with minimum meets the requirements of landing field domain performance, usually means should have than cruising flight high a lot of lift coefficient and drag coefficient for fixed wing aircraft when landing, and requires to have very high lift coefficient and high 1ift-drag ratio when taking off.Therefore need to adopt comings and goings face high lift device to satisfy the demand of high coefficient of lift combined on the wing of configuration that cruises.
Conventional all-wing aircraft does not use high lift device.Reason has two aspects: 1, and lifting rudder face driving efficiency is low, is difficult to the pitching moment variation that trim brings because high lift device uses.2, main high lift device---the position of trailing edge flap on conventional airplane, often the rudder face as lifting trim and manipulation uses in Flying-wing, the larger all-wing aircraft of part sweepback is only arranged by the elevon control (but also being difficult to the moment variations that trim wing flap lift-rising brings) of wing tip trailing edge, therefore, be difficult to again the inboard wing trailing edge is used as flap deflection, otherwise trim and manipulation will partly or entirely be lost efficacy.
In sum, conventional all-wing aircraft is because rudder effectiveness is low, be difficult to trim for avoiding larger moment occurring, consider take-off and landing, configuration can't use high lift device as conventional airplane, can only adopt little lift coefficient thereby determined to take off when landing, namely adopt the wing less than conventional airplane to carry.
Summary of the invention
The present invention is directed to the weakness of all-wing aircraft, a kind of lift-rising method of flying wing aircraft has been proposed, it is the combination of the front vectorial force of center of gravity and conventional high lift device, the method is for all-wing aircraft, can satisfy the landing stage of taking off to the demand of lift, can satisfy moment trim requirement, and can improve fore-and-aft control efficient, improve stability, reduce simultaneously certain aerodynamic lift burden.If reasonable in design, even can realize the short take-off and landing (STOL) ability of Flying-wing.
According to an aspect of the present invention, provide a kind of lift-rising method of all-wing aircraft type aircraft, described all-wing aircraft type aircraft comprises:
The all-wing aircraft fuselage,
Wing,
Sustainer, main engine,
It is characterized in that
Utilize conventional pneumatic high lift device to satisfy the requirement of landing stage to lift coefficient and drag coefficient of taking off, utilize a normal vector force generating apparatus, produce normal vector power, described normal vector power can balance all-wing aircraft type aircraft a part of weight, and the generation pitching moment, the pitching moment that the trim high lift device produces.
Description of drawings
Fig. 1 has shown the action effect of conventional high lift device.
Fig. 2 is the whole diagram of the unmanned all-wing aircraft of introducing vectorial force according to an embodiment of the invention.
Fig. 3 has shown high lift device according to an embodiment of the invention---trailing edge camber flap diagram.
Fig. 4 has shown high lift device according to an embodiment of the invention---the droope snoot diagram.
The specific embodiment
According to one embodiment of present invention, as shown in Figure 2, introduce vectorial force in Flying-wing, this vectorial force can be provided by multiple engine installation, the direction of power can change also and can fix, but needs to guarantee that the front lift direction of center of gravity (3) has this component of force (1).In embodiments of the invention shown in Figure 2, this vectorial force is provided by ducted fan (2).This ducted fan (2) is fixed on all-wing aircraft fuselage (8), and is positioned on vertical plane of symmetry of all-wing aircraft fuselage (8), the front of full machine center of gravity (3).The effect of normal vector power (1) is presented as:
-as lift, it can balance part weight;
-be positioned at center of gravity (3) front, this vectorial force (1) can produce the nose-up pitching moment of relative center of gravity (3), the nose-down pitching moment that this moment can balance be taken off, produced when when landing, the pneumatic high lift device such as droope snoot (5) and trailing edge flap (9) is opened.
In one embodiment of the invention, adopted the droope snoot (5) of simple-type, as shown in Figure 4, this droope snoot (5) is positioned at the leading edge of wing (4); Lower when inclined to one side when leading edge wing flap (5), and realize that by joint segments (11) surface blending is connected between wing (4).Trailing edge flap (9) adopts camber flap, and as shown in Figure 3, wing (4) is realized deflection relatively.
The pneumatic high lift device such as droope snoot (5) and trailing edge flap (9) coordinates applicable, and its lift-rising effect as shown in Figure 1.Trailing edge flap (9) is partially lower, can increase the camber of aerofoil profile.Reduce simultaneously to produce at the aerofoil profile upper surface critical angle of attack of flow separation.Leading edge of a wing wing flap (5) is lower when inclined to one side, and in the angle-of-attack range of lift curve linearity range, its lift is actually and does not increase, but can impel the angle of attack that separates beginning to be deferred to larger scope, thereby has increased the value of the critical angle of attack and maximum lift coefficient.
In summary, we are at the lift-rising method of flying wing aircraft of invention: to the high lift device that all-wing aircraft adopts conventional airplane to use, introduce vectorial force simultaneously before center of gravity, this power is the moment brought of balance high lift device not only, and can be as a part of By Using Active Lift.
According to a specific embodiment of the present invention, the small-sized all-wing aircraft unmanned plane of take-off weight 2.5kg, adopt the sweepback tapered airfoil, the ducted fan (2) that vectorial force (1) is 90mm by a diameter is realized, be fixed on fuselage (8) upper apart from the average pneumatic string of center of gravity (3) 50% place, towards the lift direction.This model fan maximum lift 2kg.Sustainer, main engine (7) is placed in the back.The aileron (10) that the horizontal directional control rudder face of this all-wing aircraft is outer panel, horizontal course stability is provided by a pair of vertical tail (6) that is positioned at wing tip, and the design parameters of all-wing aircraft is as follows:
Beneficial effect of the present invention comprises:
The lift-rising successful.Be applied on all-wing aircraft and easily realize.
Before introducing center of gravity, vectorial force is clear technically, and the lift contribution is considerable.
In sum, solve the trim problem by introducing vectorial force, use the high lift devices such as droope snoot and trailing edge flap in all-wing aircraft, can effectively solve all-wing aircraft to take off the landing stage, the problem such as lift coefficient is little, and wing load is little can increase lift, improves takeoff and landing performance.And this mode realizes simply, technology maturation.
Claims (5)
1. the lift-rising method of an all-wing aircraft type aircraft, described all-wing aircraft type aircraft comprises:
All-wing aircraft fuselage (8),
Wing (4),
Sustainer, main engine (7),
It is characterized in that
Utilize a normal vector force generating apparatus (2), produce normal vector power (1), a part of weight that described normal vector power (1) can balance all-wing aircraft type aircraft, and produce pitching moment.
2. according to claim 1 method, is characterized in that
Described normal vector force generating apparatus (2) is a ducted fan (2) that is fixed on all-wing aircraft fuselage (8).
3. according to claim 2 method, is characterized in that
Described ducted fan (2) is arranged on all-wing aircraft fuselage (8), and is positioned on vertical plane of symmetry of all-wing aircraft fuselage (8), and is positioned at the front of center of gravity (3).
4. according to claim 3 method, is characterized in that
Described vectorial force (1) can produce the nose-up pitching moment around center of gravity (3), the nose-down pitching moment that when this moment can balance be taken off or landed than high coefficient of lift combined under At High Angle of Attack, described all-wing aircraft produces.
5. one of according to claim 1-4 method, is characterized in that further comprising
When inclined to one side under leading edge wing flap (5), realize that by joint segments (11) described droope snoot (5) is connected with surface blending between wing (4), wherein said droope snoot (5) is leading edge simple-type and that be positioned at wing (4)
Employing wing (4) relatively realizes the trailing edge flap (9) of deflection, and described trailing edge flap (9) is camber flap,
Wherein
When inclined to one side under described trailing edge flap (9), can increase the camber of aerofoil profile, reduce simultaneously to produce at the aerofoil profile upper surface critical angle of attack of flow separation,
When inclined to one side under leading edge of a wing wing flap (5), in the angle-of-attack range of lift curve linearity range, airfoil lift is actually and does not increase, but can impel the angle of attack that separates beginning to be deferred to larger scope, thereby has increased the value of the critical angle of attack and maximum lift coefficient.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011104308484A CN103171758A (en) | 2011-12-20 | 2011-12-20 | Lift-rising method of flying wing type airplane |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011104308484A CN103171758A (en) | 2011-12-20 | 2011-12-20 | Lift-rising method of flying wing type airplane |
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| CN103171758A true CN103171758A (en) | 2013-06-26 |
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| CN2011104308484A Pending CN103171758A (en) | 2011-12-20 | 2011-12-20 | Lift-rising method of flying wing type airplane |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107728634A (en) * | 2017-10-30 | 2018-02-23 | 刘先涛 | For controlling the flight control method and system of aircraft landing |
| CN109515685A (en) * | 2017-09-18 | 2019-03-26 | 波音公司 | Trim is taken off using stabilization and elevator |
| CN112849387A (en) * | 2021-01-22 | 2021-05-28 | 西北工业大学 | Flying wing reverse-bending wing section considering power installation platform |
| CN113562162A (en) * | 2021-08-07 | 2021-10-29 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for using wing trailing edge flaperon for improving large attack angle pitching characteristic of airplane |
| CN117436194A (en) * | 2023-12-19 | 2024-01-23 | 中国航空工业集团公司西安飞机设计研究所 | Wing position adjustment quantity determination method and device taking take-off maneuvering performance as constraint |
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| GB375515A (en) * | 1930-06-04 | 1932-06-30 | Jean Frederic Georges Marie Le | Tail-less aeroplane constituted by a three-element wing |
| US4566657A (en) * | 1979-05-21 | 1986-01-28 | Grow Harlow B | Span loaded flying wing control |
| CN1754145A (en) * | 2003-04-23 | 2006-03-29 | 洛德公司 | Aircraft vehicular propulsion system monitoring device and method |
| DE202006011211U1 (en) * | 2006-07-14 | 2006-09-28 | Striebel, Christhard | Aircraft, has covering device uncovering/covering passage opening in opening position/covering position, where covering device includes cover unit, which moves from opening position to covering position by switching |
| US20070246601A1 (en) * | 2004-10-07 | 2007-10-25 | Layton Otis F | Manned/unmanned V.T.O.L. flight vehicle |
| CN102120489A (en) * | 2011-02-28 | 2011-07-13 | 南昌航空大学 | Tilt ducted unmanned aerial vehicle |
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2011
- 2011-12-20 CN CN2011104308484A patent/CN103171758A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB375515A (en) * | 1930-06-04 | 1932-06-30 | Jean Frederic Georges Marie Le | Tail-less aeroplane constituted by a three-element wing |
| US4566657A (en) * | 1979-05-21 | 1986-01-28 | Grow Harlow B | Span loaded flying wing control |
| CN1754145A (en) * | 2003-04-23 | 2006-03-29 | 洛德公司 | Aircraft vehicular propulsion system monitoring device and method |
| US20070246601A1 (en) * | 2004-10-07 | 2007-10-25 | Layton Otis F | Manned/unmanned V.T.O.L. flight vehicle |
| DE202006011211U1 (en) * | 2006-07-14 | 2006-09-28 | Striebel, Christhard | Aircraft, has covering device uncovering/covering passage opening in opening position/covering position, where covering device includes cover unit, which moves from opening position to covering position by switching |
| CN102120489A (en) * | 2011-02-28 | 2011-07-13 | 南昌航空大学 | Tilt ducted unmanned aerial vehicle |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109515685A (en) * | 2017-09-18 | 2019-03-26 | 波音公司 | Trim is taken off using stabilization and elevator |
| CN109515685B (en) * | 2017-09-18 | 2023-07-11 | 波音公司 | Aircraft takeoff trim using stabilizer and elevator |
| CN107728634A (en) * | 2017-10-30 | 2018-02-23 | 刘先涛 | For controlling the flight control method and system of aircraft landing |
| CN112849387A (en) * | 2021-01-22 | 2021-05-28 | 西北工业大学 | Flying wing reverse-bending wing section considering power installation platform |
| CN112849387B (en) * | 2021-01-22 | 2022-11-08 | 西北工业大学 | Flying wing reverse-bending wing section considering power installation platform |
| CN113562162A (en) * | 2021-08-07 | 2021-10-29 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for using wing trailing edge flaperon for improving large attack angle pitching characteristic of airplane |
| CN113562162B (en) * | 2021-08-07 | 2023-12-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for using wing trailing edge flap for improving pitching characteristic of large incidence angle of aircraft |
| CN117436194A (en) * | 2023-12-19 | 2024-01-23 | 中国航空工业集团公司西安飞机设计研究所 | Wing position adjustment quantity determination method and device taking take-off maneuvering performance as constraint |
| CN117436194B (en) * | 2023-12-19 | 2024-03-19 | 中国航空工业集团公司西安飞机设计研究所 | Wing position adjustment quantity determination method and device taking take-off maneuvering performance as constraint |
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Application publication date: 20130626 |