CN103523223B - Transverse course control system and transverse course control method for flying wing configuration - Google Patents
Transverse course control system and transverse course control method for flying wing configuration Download PDFInfo
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- CN103523223B CN103523223B CN201310515066.XA CN201310515066A CN103523223B CN 103523223 B CN103523223 B CN 103523223B CN 201310515066 A CN201310515066 A CN 201310515066A CN 103523223 B CN103523223 B CN 103523223B
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Abstract
The invention relates to a transverse course control system and a transverse course control method for flying wing configuration. For flying wing configuration planes, due to the removal of vertical tails and horizontal tails, the flight efficiency is significantly improved, and the detection performance is low, however the transverse course control ability is poor. Existing transverse course control methods employing differential flaperons, full motion wingtips, spoilers inside and outside wings and other flying wing configuration are low in control efficiency and complex to control, and the poor mobility restricts the development and use of flying wing configuration planes. The transverse course control system consists of: a flying wing configuration plane (1) and a movable handpiece control plane (2). The movable handpiece control plane is a flat handpiece, and is connected to the body of the flying wing configuration plane through an internal driving mechanism. The system and the method provided by the invention can be used for transverse course control of flying wing configuration planes.
Description
Technical field:
The present invention relates to a kind of horizontal course control system of Flying-wing and horizontal course heading control method.
Background technology:
From the development of aircraft with develop from the point of view of, for improving the fuel efficiency of aircraft, obtain high lift-drag ratio, Flying-wing is
Best aircraft configuration selects.Fuselage and wing are combined by Flying-wing's aircraft, and eliminate vertical fin and
Horizontal tail is so as to have the unique advantage that profile is gently smooth, pneumatic efficiency is high and detectivity is very low.Disclosed money abroad
Material shows that the maximum lift-drag ratio of Flying-wing can reach 25～30, and its liter of the high aspect ratio civil aircraft of conventional in layout hinders
Than general 17～20 about；Simultaneously because eliminating the construction weight more than 5% that empennage part can reduce aircraft, few
Vertical tail peace tail piece again can drag reduction 10% about (reducing frictional resistance and part interference drag).Thus aircraft can be made
Time related cost (doc) reduce by more than 30%, the cruising time of aircraft, voyage can be greatly improved simultaneously and effective carry
Lotus, is greatly improved the pneumatic efficiency of aircraft.
Flying-wing's aircraft has many advantages, such as above-mentioned, but its shortcoming is also clearly, due to not having the horizontal tail of routine and hanging down
Tail, it is even unstable that horizontal course is in neutral static-stability, shows particularly evident in supersonic flight.Aircraft keeps steady in the air
Fixed flight needs to keep the power of six degree of freedom and the balance of moment, when needing to change aspect, is such as turned or bows
Then certain angle is deflected by primary control surface when facing upward and produce aerodynamic force, this aerodynamic force produces moment around the center of gravity of airplane and changed
Become attitude, again reach balance when reaching a certain attitude around the power of the center of gravity of airplane and moment.The conventional airplane of normal configuration
It is to produce rolling moment around aircraft longitudinal axis using the deflection of wing aileron when turning, the deflection of utilization orientation rudder simultaneously comes
The unfavorable moment in course that balance is brought due to sideslip, thus realize quick direction controlling.And Flying-wing is not due to having vertical tail
And horizontal tail, thus its horizontal shipping-direction stability and handling characteristic are poor, in the case of meeting high speed crosswind, have and lead to aircraft roll
With the danger entering tailspin.
At present the main horizontal course heading control method of Flying-wing has using the pitching wing flap on wing, elevon, inside and outside
Side spoiler, ' clamshell style ' device, interior Outboard Leading Edge Flap, entirely move wing tip, differential droope snoot, split spoiler, folding
Stream plate, folding and unfolding rudder and lower surface spoiler etc. can intercouple the side force of generation and moment carrying out the control of horizontal course
System, or the asymmetric edge strip using head, edge strip crack etc. generation faint asymmetric side force carrying out Flying-wing's aircraft
Horizontal Heading control, because wing itself is close to position of centre of gravity, lead to and inefficiency complicated to the control method of aircraft.
Due to eliminating vertical fin, Flying-wing's aircraft has higher Stealth Fighter and high lift-drag ratio (flies for Flying-wing
Line efficiency is high), but its cost paid is serious shipping-direction stability and horizontal Heading control problem.Conventional airplane is when turning
It is deflection one side force of generation and the yawing of utilization orientation rudder first, utilize aileron to produce a favourable rolling power simultaneously
Realizing quick direction controlling, due to not having vertical tail and horizontal tail, flaperon is apart from center of gravity position simultaneously for Flying-wing for the coupling of square
Put relatively near, thus its horizontal directional control characteristic is poor.
Or the horizontal course heading control method rudder face coupling of above-mentioned Flying-wing aircraft is complicated, Flight Control Law difficult design,
Control efficiency is relatively low, leads to the mobility of aircraft poor, thus existing Flying-wing is mainly used in air-to-ground attack and bangs
On aircraft bombing class aircraft.
For the aircraft of Flying-wing, when due to but having fallen vertical tail and horizontal tail, flight efficiency significantly improves, to have low simultaneously
Detectable performance, but the control ability in its horizontal course is poor, existing using differential flaperon, entirely move wingtip, outside in wing
The crosswise joint method control efficiency of the Flying-wings such as spoiler is low, it is complicated to manipulate, thus mobility is poor, constrains all-wing aircraft
The development of airplane and use.
Content of the invention:
It is an object of the invention to provide a kind of horizontal course control system of Flying-wing and horizontal course heading control method.
Above-mentioned purpose is realized by following technical scheme:
A kind of horizontal course control system of Flying-wing, its composition includes: Flying-wing's aircraft, mobilizable head rudder
Face, described movable head rudder face is pancake head, described movable head rudder face and described Flying-wing's aircraft
Body connected by internal driving mechanism.
A kind of horizontal course heading control method of the horizontal course control system of Flying-wing, movable head rudder face is driven using internal
Motivation structure around fuselage datum left and right sides, lower left side, upper left side, lower right side, upper right side deflection or rotates, in aeroplane nose during deflection
Both sides produce asymmetry quantum dot thus producing side force, simultaneously this side force with respect to aircraft center of gravity farther out, using described
The horizontal Heading control moment that the side force that aeroplane nose produces is formed around the center of gravity of airplane, realizes efficient to Flying-wing's aircraft
Horizontal Heading control.
Beneficial effect:
1. the present invention improves the horizontal Heading control ability of Flying-wing's aircraft, strengthens the mobility of Flying-wing's aircraft, profit
Produce the horizontal Heading control that asymmetry quantum dot realizes Flying-wing with micro- deflection of head in the head of Flying-wing on one's own initiative
Aerodynamic force new method, by the flat head of Flying-wing be designed to can left and right, lower left side or lower right side deflection movable rudder face,
Asymmetry quantum dot is produced thus producing side force in aeroplane nose both sides, the direct force of achievable Flying-wing aircraft during its deflection
Control and produce horizontal Heading control moment.
Because the electromotor of existing aircraft is more and more heavier, more and more rearward, the head of aircraft is away from center of gravity relatively for the center of gravity of aircraft
Far, the arm of force is longer, and the present invention has higher horizontal Heading control efficiency.The use of the present invention is not limited only to flying shown in Fig. 1
Wing formula airplane, is also applied for the horizontal Heading control of the body of center of gravity high-speed flight more rearward.Rudder face shape is not limited to Fig. 1
Shown in, can be designed using this aerodynamic tool and adjust according to actual needs.
Brief description:
Accompanying drawing 1 be the present invention Flying-wing's aircraft using head deflection as horizontal Heading control rudder face deflection schematic diagram.
Accompanying drawing 2 is a form of structural representation of the movable head rudder face of the present invention.
Specific embodiment:
Embodiment 1:
A kind of horizontal course control system of Flying-wing, its composition includes: Flying-wing's aircraft 1, mobilizable head rudder
Face 2, described movable head rudder face is pancake head, described movable head rudder face and described Flying-wing's aircraft
Body connected by internal driving mechanism.
Embodiment 2:
The horizontal course heading control method of the horizontal course control system according to the above-mentioned Flying-wing of embodiment 1, movable head
Rudder face utilizes internal driving mechanism around fuselage datum left and right sides, lower left side, upper left side, lower right side, upper right side deflection or to rotate, partially
When turning aeroplane nose both sides produce asymmetry quantum dot thus producing side force, simultaneously this side force with respect to aircraft center of gravity relatively
Far, the horizontal Heading control moment being formed around the center of gravity of airplane using the side force that described aeroplane nose produces, is realized to all-wing aircraft
Airplane efficiently horizontal Heading control.
Embodiment 3:
The horizontal course control system of described Flying-wing, in Fig. 1, a-a is that head rudder face merges section with body transition,
A-a leading portion is movable head rudder face, and head rudder face can realize left and right sides, a left side around fuselage datum ox using internal driving mechanism
Downside, upper left side, lower right side, upper right side deflection or rotation, head type specifically determines according to aircraft layout, is mainly subject to head
Stealthy constraint of the fairing fusion of rudder face and whole body and aircraft etc..When head rudder face around fuselage datum ox deflection or rotates,
Realize the horizontal Heading control to aircraft.Length l of head rudder face and deflection angle according to the size of aircraft and motor-driven required partially
Torque is designing.Using head asymmetry quantum dot produce side force and head away from center of gravity feature farther out, even if less
Side force it is also possible to produce enough horizontal Heading control moment, thus realizing to the efficiently horizontal course control of Flying-wing's aircraft
System.
Claims (1)
1. the horizontal course control system of a kind of Flying-wing, its composition includes: Flying-wing's aircraft, mobilizable head rudder face,
It is characterized in that: described movable head rudder face is pancake head, described movable head rudder face and described all-wing aircraft cloth
The body of office's aircraft is connected by internal driving mechanism；The horizontal Heading control side of the horizontal course control system of described Flying-wing
Method, movable head rudder face utilizes internal driving mechanism around fuselage datum left and right sides, lower left side, upper left side, lower right side, upper right side
Deflection, produces asymmetry quantum dot thus producing side force in aeroplane nose both sides during deflection, this side force is with respect to aircraft simultaneously
Center of gravity farther out, the horizontal Heading control moment that formed around the center of gravity of airplane using the side force that described aeroplane nose produces, real
The now horizontal Heading control to Flying-wing's aircraft；When head rudder face deflects around fuselage datum ox, realize the horizontal course control to aircraft
System；Length l of head rudder face and deflection angle design according to the size of aircraft and motor-driven required deflection torque；Using head
Asymmetry quantum dot produce side force and head away from center of gravity feature farther out, even if less side force it is also possible to produce foot
Enough horizontal Heading control moment, thus realize the horizontal Heading control to Flying-wing's aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201310515066.XA CN103523223B (en) | 2013-10-28 | 2013-10-28 | Transverse course control system and transverse course control method for flying wing configuration |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310515066.XA CN103523223B (en) | 2013-10-28 | 2013-10-28 | Transverse course control system and transverse course control method for flying wing configuration |
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| CN103523223A CN103523223A (en) | 2014-01-22 |
| CN103523223B true CN103523223B (en) | 2017-01-25 |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104554705A (en) * | 2014-11-19 | 2015-04-29 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for reducing steering surface hinge moment of general-purpose airplane |
| CN108628335B (en) * | 2016-03-02 | 2021-07-02 | 成都飞机工业（集团）有限责任公司 | Course control method of flying-wing unmanned aerial vehicle |
| CN108116662A (en) * | 2016-11-28 | 2018-06-05 | 成都飞机工业（集团）有限责任公司 | A kind of no empennage airplane yawing control method |
| CN113772087A (en) * | 2021-10-15 | 2021-12-10 | 南京理工大学 | Variant aircraft with variable sweepback wings and head deflection |
| CN116985994B (en) * | 2023-09-21 | 2023-11-28 | 中国空气动力研究与发展中心计算空气动力研究所 | Invisible aircraft |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5538202A (en) * | 1993-11-02 | 1996-07-23 | Northrop Grumman Corporation | Hydraulic actuation system for aircraft control surfaces |
| US8191820B1 (en) * | 2007-12-11 | 2012-06-05 | Northrop Gurmman Corporation | Flying wing aircraft |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2741869Y (en) * | 2004-08-25 | 2005-11-23 | 栾松瑞 | Improved plane turning and lifting device |
| EP2212199B1 (en) * | 2007-11-21 | 2016-06-01 | QinetiQ Limited | Aircraft |
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2013
- 2013-10-28 CN CN201310515066.XA patent/CN103523223B/en not_active Expired - Fee Related
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5538202A (en) * | 1993-11-02 | 1996-07-23 | Northrop Grumman Corporation | Hydraulic actuation system for aircraft control surfaces |
| US8191820B1 (en) * | 2007-12-11 | 2012-06-05 | Northrop Gurmman Corporation | Flying wing aircraft |
Non-Patent Citations (1)
| Title |
|---|
| 一种飞翼布局横航向特性的控制研究;赵霞，秦燕华;《空气动力学学报》;20080630;第26卷(第2期);第235页 * |
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