CN103523223A - 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
- Publication number
- CN103523223A CN103523223A CN201310515066.XA CN201310515066A CN103523223A CN 103523223 A CN103523223 A CN 103523223A CN 201310515066 A CN201310515066 A CN 201310515066A CN 103523223 A CN103523223 A CN 103523223A
- Authority
- CN
- China
- Prior art keywords
- flying
- wing
- aircraft
- course control
- flying wing
- 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.)
- Granted
Links
Images
Landscapes
- Toys (AREA)
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 and horizontal course heading control method of Flying-wing.
background technology:
development and differentiation from aircraft, for improving the fuel efficiency of aircraft, obtain high 1ift-drag ratio, and Flying-wing is that best aircraft configuration is selected.Flying-wing's aircraft combines fuselage and wing, and has cancelled vertical fin and horizontal tail, make its have profile gently smooth, pneumatic efficiency is high and unique advantage that detectability is very low.External disclosed data shows that the maximum lift-drag ratio of Flying-wing can reach 25～30, and its 1ift-drag ratio of high aspect ratio civil aircraft of conventional in layout is generally in 17～20 left and right; Simultaneously, owing to having removed structural weight that empennage parts can reduce aircraft more than 5%, lacked vertical tail peace tail piece again can drag reduction 10% left and right (having reduced friction drag and parts interference drag).Thereby can make the time related cost (DOC) of aircraft reduce more than 30%, can significantly improve cruise duration, voyage and the capacity weight of aircraft simultaneously, can greatly improve the pneumatic efficiency of aircraft.
flying-wing's aircraft has above-mentioned plurality of advantages, but its shortcoming is also very obvious, and owing to there is no conventional horizontal tail and vertical fin, horizontal course is even unstable in neutral static-stability, shows particularly evident when supersonic flight.Aircraft keeps stabilized flight need to keep the balance of the force and moment of six degree of freedom aloft, when needs change aspect, such as turning or producing aerodynamic force by primary control surface deflection certain angle during pitching, this aerodynamic force produces moment around the center of gravity of airplane and changes attitude, and the force and moment around the center of gravity of airplane when reaching a certain attitude reaches balance again.The conventional airplane of normal configuration is to utilize the deflection of wing aileron to produce the rolling moment around aircraft longitudinal axis when turning, and the unfavorable moment in course of simultaneously utilizing the deflection of yaw rudder to come balance to bring due to sideslip, controls thereby realize fast speed direction.And Flying-wing is owing to there is no vertical tail and horizontal tail, thus its horizontal course stability and maneuvering characteristics poor, in the situation that meeting high speed crosswind, have the danger that causes aircraft roll and enter tailspin.
the main horizontal course heading control method of Flying-wing has the pitching wing flap utilizing on wing at present, elevon, interior outside spoiler, ' clamshell style ' device, interior Outboard Leading Edge Flap, complete moving wing tip, differential droope snoot, split spoiler, plate baffle, can folding and unfolding yaw rudder and the side direction force and moment producing that intercouples such as lower surface spoiler carry out the control of horizontal course, or utilize the asymmetric edge strip of head, the faint asymmetric side force of the generations such as edge strip cracks is carried out the horizontal course of Flying-wing's aircraft and is controlled, because wing itself is close to center-of-gravity position, cause control method complexity and inefficiency to aircraft.
flying-wing is owing to having removed vertical fin, and Flying-wing's aircraft has higher Stealth Fighter and high 1ift-drag ratio (flight efficiency is high), yet its cost of paying is serious course stability and horizontal course control problem.First conventional airplane is to utilize the deflection of yaw rudder to produce a side force and yawing moment when turning, the coupling that simultaneously utilizes aileron to produce a favourable rolling moment realizes fast speed direction and controls, Flying-wing is owing to there is no vertical tail and horizontal tail, flaperon is nearer apart from center-of-gravity position simultaneously, thereby its horizontal directional control characteristic is poor.
the coupling of the horizontal course heading control method of above-mentioned Flying-wing aircraft or rudder face is complicated, Flight Control Law difficult design, or control efficiency is lower, causes the manoevreability of aircraft poor, thus existing Flying-wing be mainly used in attacking over the ground with bomber class aircraft on.
aircraft for Flying-wing, when owing to but having fallen vertical tail and horizontal tail, flight efficiency significantly improves, has simultaneously low detectable performance, but the control ability in its horizontal course is poor, the differential flaperon of existing employing, entirely in moving wingtip, wing the horizontal control method control efficiency of the Flying-wings such as outside spoiler low, handle complicated, thereby manoevreability is poor, development and the use of Flying-wing's aircraft have been restricted.
summary of the invention:
the horizontal course control system and the horizontal course heading control method that the object of this invention is to provide a kind of Flying-wing.
above-mentioned object realizes by following technical scheme:
a kind of horizontal course control system of Flying-wing, its composition comprises: Flying-wing's aircraft, mobilizable head rudder face, described movable head rudder face is pancake head, described movable head rudder face is connected by internal driving mechanism with the body of described Flying-wing's aircraft.
a kind of horizontal course heading control method of horizontal course control system of Flying-wing, movable head rudder face utilizes internal driving mechanism around fuselage datum left and right sides, Ce, upper left side, lower-left, lower right side, upper right side deflection or rotation, thereby during deflection, in aeroplane nose both sides, produce asymmetric flowing and produce side force, this side force is far away with respect to the center of gravity of aircraft simultaneously, utilize the side force of described aeroplane nose generation around the formed horizontal course of center of gravity of airplane control torque, realize the efficient horizontal course of Flying-wing's aircraft is controlled.
beneficial effect:
1. the present invention improves the horizontal course control ability of Flying-wing's aircraft, strengthen the manoevreability of Flying-wing's aircraft, the micro-deflection that utilizes head produces at the head of Flying-wing the aerodynamic force new mode that asymmetric horizontal course of flowing to realize Flying-wing is controlled on one's own initiative, by the flat head of Flying-wing be designed to can left and right, lower-left Ce Huo lower right side deflection movable rudder face, thereby during its deflection, in aeroplane nose both sides, produce asymmetric flowing and produce side force, can realize the direct force of Flying-wing's aircraft and control and produce horizontal course control torque.
because the driving engine of existing aircraft is more and more heavier, after the center of gravity of aircraft is more and more leaned on, the head of aircraft is far away apart from center of gravity, and the arm of force is longer, and the present invention has higher horizontal course control efficiency.Use of the present invention is not limited only to the flying wing type layout aircraft shown in Fig. 1, and the horizontal course that is also applicable to the body of the high-speed flight after center of gravity is leaned on is controlled.Rudder face shape is not limited to shown in Fig. 1, can according to actual needs, utilize this aerodynamic tool to design and adjust.
accompanying drawing explanation:
accompanying drawing 1 is that Flying-wing of the present invention aircraft is controlled the deflection schematic diagram of rudder face using head deflection as horizontal course.
accompanying drawing 2 is structural representations of a kind of form of movable head rudder face of the present invention.
the specific embodiment:
embodiment 1:
a kind of horizontal course control system of Flying-wing, its composition comprises: Flying-wing's aircraft 1, mobilizable head rudder face 2, described movable head rudder face is pancake head, described movable head rudder face is connected by internal driving mechanism with the body of described Flying-wing's aircraft.
embodiment 2:
according to the horizontal course heading control method of the horizontal course control system of the above-mentioned Flying-wing of embodiment 1, movable head rudder face utilizes internal driving mechanism around fuselage datum left and right sides, Ce, upper left side, lower-left, lower right side, upper right side deflection or rotation, thereby during deflection, in aeroplane nose both sides, produce asymmetric flowing and produce side force, this side force is far away with respect to the center of gravity of aircraft simultaneously, utilize the side force of described aeroplane nose generation around the formed horizontal course of center of gravity of airplane control torque, realize the efficient horizontal course of Flying-wing's aircraft is controlled.
embodiment 3:
the horizontal course control system of described Flying-wing, in Fig. 1, A-A is that section is merged in head rudder face and body transition, A-A leading portion is movable head rudder face, head rudder face utilizes internal driving mechanism to realize left and right sides, Ce, upper left side, lower-left, lower right side, upper right side deflection or rotation around fuselage datum OX, head type is specifically determined according to aircraft layout, is to be mainly subject to the fairing fusion of head rudder face B and whole body and the stealthy constraint of aircraft etc.When head rudder face B is around fuselage datum OX deflection or rotation, realize the horizontal course of aircraft is controlled.The length L of head rudder face and deflection angle design according to size and the motor-driven required deflecting torque of aircraft.Utilize the raw side force of the asymmetric drift movable property of head and head apart from center of gravity feature far away, even if less side force also can produce enough horizontal course control torques, thereby realize, the efficient horizontal course of Flying-wing's aircraft is controlled.
Claims (2)
- The horizontal course control system of 1.Yi Zhong Flying-wing, its composition comprises: 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 is connected by internal driving mechanism with the body of described Flying-wing's aircraft.
- 2. the horizontal course heading control method of the horizontal course control system of a Flying-wing claimed in claim 1, it is characterized in that: movable head rudder face utilizes internal driving mechanism around fuselage datum left and right sides, Ce, upper left side, lower-left, lower right side, upper right side deflection or rotation, thereby during deflection, in aeroplane nose both sides, produce asymmetric flowing and produce side force, this side force is far away with respect to the center of gravity of aircraft simultaneously, utilize the side force of described aeroplane nose generation around the formed horizontal course of center of gravity of airplane control torque, realize the efficient horizontal course of Flying-wing's aircraft is controlled.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310515066.XA CN103523223B (en) | 2013-10-28 | 2013-10-28 | Transverse course control system and transverse course control method for flying wing configuration |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310515066.XA CN103523223B (en) | 2013-10-28 | 2013-10-28 | Transverse course control system and transverse course control method for flying wing configuration |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103523223A true CN103523223A (en) | 2014-01-22 |
| CN103523223B CN103523223B (en) | 2017-01-25 |
Family
ID=49925673
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310515066.XA Expired - Fee Related CN103523223B (en) | 2013-10-28 | 2013-10-28 | Transverse course control system and transverse course control method for flying wing configuration |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103523223B (en) |
Cited By (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 |
| 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 |
| CN108628335A (en) * | 2016-03-02 | 2018-10-09 | 成都飞机工业（集团）有限责任公司 | A kind of course heading control method of all-wing aircraft unmanned plane |
| CN113772087A (en) * | 2021-10-15 | 2021-12-10 | 南京理工大学 | Variant aircraft with variable sweepback wings and head deflection |
| CN116985994A (en) * | 2023-09-21 | 2023-11-03 | 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 (4)
| 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 |
| CN2741869Y (en) * | 2004-08-25 | 2005-11-23 | 栾松瑞 | Improved plane turning and lifting device |
| US20100252690A1 (en) * | 2007-11-21 | 2010-10-07 | Qinetiq Limited | Aircraft |
| US8191820B1 (en) * | 2007-12-11 | 2012-06-05 | Northrop Gurmman Corporation | Flying wing aircraft |
-
2013
- 2013-10-28 CN CN201310515066.XA patent/CN103523223B/en not_active Expired - Fee Related
Patent Citations (4)
| 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 |
| CN2741869Y (en) * | 2004-08-25 | 2005-11-23 | 栾松瑞 | Improved plane turning and lifting device |
| US20100252690A1 (en) * | 2007-11-21 | 2010-10-07 | Qinetiq Limited | Aircraft |
| US8191820B1 (en) * | 2007-12-11 | 2012-06-05 | Northrop Gurmman Corporation | Flying wing aircraft |
Non-Patent Citations (1)
| Title |
|---|
| 赵霞，秦燕华: "一种飞翼布局横航向特性的控制研究", 《空气动力学学报》 * |
Cited By (7)
| 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 |
| CN108628335A (en) * | 2016-03-02 | 2018-10-09 | 成都飞机工业（集团）有限责任公司 | A kind of course heading control method of all-wing aircraft unmanned plane |
| 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 |
| CN116985994A (en) * | 2023-09-21 | 2023-11-03 | 中国空气动力研究与发展中心计算空气动力研究所 | Invisible aircraft |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103523223B (en) | 2017-01-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8876044B2 (en) | Aircraft with yaw control by differential drag | |
| CN108639339B (en) | Pneumatic layout of unmanned aerial vehicle | |
| US20150048215A1 (en) | Efficient control and stall prevention in advanced configuration aircraft | |
| EP2961652B1 (en) | Canard-locked oblique wing aircraft | |
| CN104554707A (en) | Novel flying wing unmanned aerial vehicle and heading control method thereof | |
| CN105173061A (en) | Plane in supersonic speed plane layout | |
| CN103523223B (en) | Transverse course control system and transverse course control method for flying wing configuration | |
| CN103158856B (en) | Light airscrew flying wing aircraft capable of taking off and landing in short distance | |
| CN202320772U (en) | High lift device of double-aisle large-type passenger plane | |
| CN103587683A (en) | Small-sized aircraft with tiltable rotor wings | |
| CN103171766A (en) | Short distance rising and landing unmanned all-wing aircraft | |
| CN102826216A (en) | Aerodynamic configuration of aircraft | |
| US8262017B2 (en) | Aircraft with forward lifting elevator and rudder, with the main lifting surface aft, containing ailerons and flaps, and airbrake | |
| EP1631493B1 (en) | Aircraft with topside only spoilers | |
| CN108082471B (en) | Variant supersonic aircraft | |
| CN105235889A (en) | Self-adaptive rhombic wing layout of air vehicles | |
| CN115571323A (en) | Flat fusion body overall arrangement aircraft of subsonic speed | |
| CN110775296A (en) | Design method for pressure center backward movement of reusable aerospace vehicle | |
| CN103171758A (en) | Lift-rising method of flying wing type airplane | |
| CN203714171U (en) | High-efficient and stable oblique inverter wing | |
| CN207089635U (en) | The flight control system of the stealthy unmanned plane of Flying-wing | |
| CN109808871A (en) | A kind of all-wing aircraft combination rudder face with high maneuvering characteristics | |
| CN104554739A (en) | Air inlet lip for improving and adjusting course stability of double-engine wing-body blending tailless configuration | |
| CN109703758B (en) | Aerodynamic shape and design method of bidirectional flying wing aircraft | |
| CN208715466U (en) | Unmanned aerial vehicle (UAV) control device and unmanned plane based on flow field control |
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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170125 Termination date: 20171028 |