CN103640687B - A kind of full dynamic formula Full-motion wingtip gust alleviation device being applicable to high-aspect-ratio aircraft - Google Patents
A kind of full dynamic formula Full-motion wingtip gust alleviation device being applicable to high-aspect-ratio aircraft Download PDFInfo
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- CN103640687B CN103640687B CN201310643782.6A CN201310643782A CN103640687B CN 103640687 B CN103640687 B CN 103640687B CN 201310643782 A CN201310643782 A CN 201310643782A CN 103640687 B CN103640687 B CN 103640687B
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Abstract
The invention discloses a kind of full dynamic formula Full-motion wingtip gust alleviation device being applicable to high-aspect-ratio aircraft, belong to high-aspect-ratio aircraft wing structure design field.Described device is made up of host wing, full dynamic formula wing tip, elasticity of torsion adapter shaft, locking mechanism, fitful wind detecting sensor and control apparatus.Full dynamic formula wing tip accounts for 10% ~ 20% of wing length, is connected with locking mechanism by elasticity of torsion adapter shaft with host wing.Wing tip there is fitful wind detecting sensor for detecting vertical gust, the control apparatus be made up of leading screw, feed screw nut, motor and slide rail can regulate the position of elasticity of torsion adapter shaft, makes full dynamic formula Full-motion wingtip gust alleviation device of the present invention under different fitful wind intensity, have best gust alleviation effect.The present invention, while meeting high-aspect-ratio aircraft wing structure Essential Performance Requirements, by the detection of active fitful wind, passive gust alleviation technology, makes wing have good gust alleviation effect, and lightweight, and structure is simple.
Description
Technical field
The invention belongs to high-aspect-ratio aircraft wing structure design field, be specifically related to a kind of design being applicable to the full dynamic formula Full-motion wingtip gust alleviation device of high-aspect-ratio aircraft.
Background technology
High-aspect-ratio aircraft is usually subject to the impact of strong fitful wind when flying and produces extra flight force and moment, produce the undesirable additional overload of aircraft, wherein the impact of vertical array wind-induced overload is larger, destroy required flight quality, aircraft is made to bear very large dynamic structural loads, not only make aircraft be difficult to handle, and body volume fatiguability damage, and have impact on the comfort level of chaufeur and passenger simultaneously.Therefore, gust alleviation is the importance of airplane design.The dynamic response of reduction wing and increment load are two main objectives of gust alleviation.
At present, high-aspect-ratio aircraft generally adopts the gust alleviation device depending on active control technology.ACTIVE CONTROL gust alleviation technology realizes gust alleviation by some control surface such as wing flap, aileron, the spoiler etc. controlled on aircraft wing.Normally to produce a pitching moment, aircraft is rotated by elevator deflection, control longitudinal motion by the change of pitch attitude.This method can be delayed, and the overload that can not effectively suppress fitful wind to produce.Therefore there is again the control adopting the By Using Active Lift of closed loop control system, namely relied on the additional control surface of acceleration transducer signals deflection, operate the overload suppressing fitful wind to produce with By Using Active Lift, slow down the impact of aerodynamic loading on aircraft.
Because high aspect ratio wing can produce very large upwarping and torsional deflection under the effect of aerodynamic loading, Aeroelastic Problems is more outstanding, this just requires that high aspect ratio wing has enough large strength and stiffness, makes high aspect ratio wing inherently have larger weight.For high-aspect-ratio aircraft, active control system relative complex, needs to adopt airborne lidar system, can increase the weight of aircraft to a certain extent, affect airworthiness.Therefore in order to improve airworthiness, need to reduce take-off weight, the gust alleviation apparatus design of high-aspect-ratio aircraft becomes more important.
Summary of the invention
The present invention is directed to high-aspect-ratio aircraft adopts traditional ACTIVE CONTROL gust alleviation technology to there is this problem of many weak points, propose a kind of full dynamic formula Full-motion wingtip gust alleviation device being applicable to high-aspect-ratio aircraft, while meeting high-aspect-ratio aircraft wing structure Essential Performance Requirements, by the detection of active fitful wind, passive gust alleviation technology, wing is made to have good gust alleviation effect, and lightweight, structure is simple.
The full dynamic formula Full-motion wingtip gust alleviation device being applicable to high-aspect-ratio aircraft that the present invention proposes is made up of host wing, full dynamic formula wing tip, elasticity of torsion adapter shaft, locking mechanism, fitful wind detecting sensor and control apparatus.Full dynamic formula wing tip accounts for 10% ~ 20% of wing length, is connected with locking mechanism by elasticity of torsion adapter shaft with host wing.Wing tip has fitful wind detecting sensor for detecting vertical gust, fitful wind detecting sensor is connected with locking mechanism by cable.Under regular flight condition, locking mechanism closes, and wing tip and host wing are in locking state, forms a complete wing; When fitful wind detecting sensor detects vertical gust, locking mechanism is opened, and wing tip is in complete dynamic state, turns slow down gust load by producing negative bias of bowing under fitful wind effect.The control apparatus be made up of leading screw, feed screw nut, motor and slide rail can regulate the position of elasticity of torsion adapter shaft, makes full dynamic formula Full-motion wingtip gust alleviation device of the present invention under different fitful wind intensity, have best gust alleviation effect.
The invention has the advantages that:
(1) full dynamic formula Full-motion wingtip gust alleviation device provided by the invention realizes gust alleviation by the structural property parameter changing wing, does not need to consider active response system, and light compared to ACTIVE CONTROL gust alleviation installation weight, structure is simple.
(2) full dynamic formula Full-motion wingtip gust alleviation device meets the requirements such as the intensity of aircraft wing structure design, rigidity, pneumatic, weight and fatigue life, does not have a negative impact to the use of aircraft, maintainability simultaneously.
Accompanying drawing explanation
Fig. 1 is full dynamic formula Full-motion wingtip gust alleviation device schematic diagram;
Fig. 2 is full dynamic formula Full-motion wingtip gust alleviation device partial enlarged drawing;
Fig. 3 is wing structure figure;
Fig. 4 is full dynamic formula Full-motion wingtip gust alleviation device isometric views;
Fig. 5 is control apparatus partial enlarged drawing;
Fig. 6 is elasticity of torsion adapter shaft front elevation;
Fig. 7 is rib and chute front elevation;
Fig. 8 is with or without the wing tip sink-float displacement under full dynamic formula Full-motion wingtip gust alleviation device;
In figure:
1. host wing; 2. full dynamic formula wing tip; 3. elasticity of torsion adapter shaft; 4. locking mechanism;
5. fitful wind detecting sensor; 6. control apparatus; 7. cable; 8. leading screw;
9. feed screw nut; 10. motor; 11. set pins; 12. reinforced ribs;
13. chutes; 14. ribs; 15. long purlins; 16. jacks;
17. slide rails.
Detailed description of the invention
Below in conjunction with accompanying drawing, the full dynamic formula Full-motion wingtip gust alleviation device being applicable to high-aspect-ratio aircraft that the present invention proposes is described in detail.
In the design of aircraft gust alleviation, slowing down completely of fitful wind effect be accomplished, must on fitful wind plane of action same position, same time produce a kind of large pneumatic counter-force same with fitful wind application force, and this point can not realize in systems in practice.At present, civil aircraft mainly utilizes active control technology, by some additional control surface of aircraft wing, such as wing flap, external aileron, spoiler etc. realize gust load alleviation, thus improve traveling comfort that passenger takes, alleviate wing moment of deflection and strengthen Anti-Fatigue performance.For high-aspect-ratio aircraft, active control system relative complex, needs to adopt airborne lidar system and active response system, can increase the weight of aircraft to a certain extent, affect airworthiness.Therefore high-aspect-ratio aircraft adopts traditional ACTIVE CONTROL gust alleviation technology to there is many weak points.The full dynamic formula Full-motion wingtip gust alleviation device that the present invention proposes is actually the detection of a kind of initiatively fitful wind, passive gust alleviation technology, and realize gust alleviation by the part-structure parameter changing wing, structure is simple, lightweight, is applicable to high-aspect-ratio aircraft.
Fig. 1 is the schematic diagram of the full dynamic formula Full-motion wingtip gust alleviation device of high-aspect-ratio aircraft provided by the invention, and described gust alleviation device is made up of host wing 1, full dynamic formula wing tip 2, elasticity of torsion adapter shaft 3, locking mechanism 4, fitful wind detecting sensor 5 and control apparatus 6.Host wing 1 is the base portion of high aspect ratio wing, as Fig. 4, is made up of rib 14, long purlin 15 and covering, mainly produces the lift needed for aircraft.Full dynamic formula wing tip 2 is tip stations of high aspect ratio wing, as Fig. 3, accounts for the 10%-20% of wing length.Full dynamic formula wing tip 2 is connected with host wing 1 by elasticity of torsion adapter shaft 3 and locking mechanism 4.Elasticity of torsion adapter shaft 3 is elastic axiss with certain torsional stiffness, can adopt circle or other section forms, elasticity of torsion adapter shaft 3 has had the set pin 11 of fixation.
Locking mechanism 4 is the mechanisms connecting host wing 1 and full dynamic formula wing tip 2, can open or close after the control signal receiving fitful wind detecting sensor 5.Fitful wind detecting sensor 5 is arranged on full dynamic formula wing tip 2, and is connected with locking mechanism 4 by cable 7; Be connected with motor 10 by cable simultaneously.Fitful wind detecting sensor 5, for detecting vertical gust, can send control signal to control opening or closing of locking mechanism 4.When aircraft normal flight, fitful wind detecting sensor 5 does not detect vertical gust, locking mechanism 4 closes, full dynamic formula wing tip 2 is in locking state with host wing 1, now full dynamic formula wing tip 2 is connected with host wing 1 with locking mechanism 4 by elasticity of torsion adapter shaft 3, thus becomes a complete wing to produce lift.When fitful wind detecting sensor 5 detects vertical gust, export a control signal to locking mechanism 4 by cable 7, locking mechanism 4 is opened, and full dynamic formula wing tip 2 is in complete dynamic state, and full dynamic formula wing tip 2 is connected with host wing 1 by means of only elasticity of torsion adapter shaft 3.Aerodynamic center due to wing is positioned at the chord length place apart from the leading edge of a wing about 25%, and the chord length that the distance of the position distance leading edge of a wing of elasticity of torsion adapter shaft is less than 25%, therefore the position of elasticity of torsion adapter shaft 3 is before wing aerodynamic center, when aircraft runs into affecting of vertical gust, the effective angle of attack of host wing 1 increases the extra flight force and moment of generation, the extra aerodynamic force that full dynamic formula wing tip 2 produces makes full dynamic formula wing tip 2 produce to bow motion and negative bias to turn, the effective angle of attack of full dynamic formula wing tip 2 reduces, aerodynamic force reduces, thus reduce dynamic response and the load of wing, thus realize gust alleviation.
Figure 5 shows that the structural representation of control apparatus 6, control apparatus 6 is made up of leading screw 8, feed screw nut 9, motor 10 and slide rail 17.Leading screw 8 is elongated metal bars, and there is outside thread on surface, is fixed on the output shaft of motor 10, can rotate under the drive of motor 10.Feed screw nut 9 is metal partss, and there is screw thread inner side, is connected with the outside thread of leading screw 8, and feed screw nut 9 can move forward and backward along with the rotation of leading screw 8, and feed screw nut 9 and elasticity of torsion adapter shaft 3 are connected simultaneously.Motor 10 is motor devices, and motor 10 is arranged on slide rail 17, and slide rail 17 is fixed on the web of host wing 1.Slide rail 17 is parallel with elasticity of torsion adapter shaft 3.Motor 10 can start after receiving the control signal that fitful wind detecting sensor 5 sends, and slide rail 17 slides and passes through leading screw 8, feed screw nut 9, drives elasticity of torsion adapter shaft 3 to move.
As can see from Figure 6 elasticity of torsion adapter shaft 3 is provided with set pin 11.Elasticity of torsion axle 3 two ends are connected with the rib 14 on full dynamic formula wing tip 2 with host wing 1 respectively.Reinforced rib 12 is all had, to ensure that there are enough strength and stiffness junction around the junction of elasticity of torsion adapter shaft 3 and rib 14.As can see from Figure 7 rib 14 has chute 13, the dual-side of chute 13 has many group jacks 16, often organizing jack 16 is all given apart from the distance of the leading edge of a wing, and all before wing aerodynamic center.Described set pin 11 with often organize jack 16 and coordinate the location realizing elasticity of torsion adapter shaft 3.Set pin 11 under normal circumstances on elasticity of torsion adapter shaft 3 inserts in the jack 16 of midway location on chute 13, and elasticity of torsion adapter shaft 3 and rib 14 are connected.Preferably, described elasticity of torsion adapter shaft 3 is connected with two or more rib 14 adjacent on host wing 1 and full dynamic formula wing tip 2.
When needing the position adjusting elasticity of torsion adapter shaft 3, fitful wind detecting sensor 5 sends control signal starter motor 10, first motor 10 drives leading screw 8, feed screw nut 9 and elasticity of torsion adapter shaft 3 entirety to slide along slide rail 17 towards the direction of host wing 1 certain displacement, and the set pin 11 on elasticity of torsion adapter shaft 3 is skidded off from the jack 16 chute 13; Then motor 10 drives leading screw 8 to rotate certain number of turns, and feed screw nut 9 drives elasticity of torsion adapter shaft 3 to move on the position of one group of suitable jack 16 on chute 13; Last motor 10 drives leading screw 8, feed screw nut 9 and the direction of elasticity of torsion adapter shaft 3 along slide rail 17 towards wing tip 2 to move, motor 10 is made to get back to initial position on slide rail 17, the set pin 11 on elasticity of torsion adapter shaft 3 is made just in time to insert jack 16 on chute 13, ensure that elasticity of torsion adapter shaft 3 and rib 14 are connected, thus complete the adjustment of elasticity of torsion adapter shaft 3 position.According to the fitful wind intensity that fitful wind detecting sensor 5 detects, fitful wind is divided into different strength grades, specific one group of jack 16 on the corresponding chute 13 of each strength grade.Regulated by the position of control apparatus 6 pairs of elasticity of torsion adapter shafts 3, make full dynamic formula Full-motion wingtip gust alleviation device under different fitful wind intensity, all have best gust alleviation effect, realize actv. gust alleviation.
When fitful wind detecting sensor 5 detects that fitful wind disappears, when aircraft recovers regular flight condition again, first fitful wind detecting sensor 5 sends control signal to motor 10, control apparatus 6 starts the position regulating elasticity of torsion adapter shaft 3, make the aerodynamic center of position near wing of elasticity of torsion adapter shaft 3, now, full dynamic formula wing tip 2 is almost identical with the angle of inclination of host wing 1 under the effect of aerodynamic force, and full dynamic formula wing tip 2 does not almost deflect relative to host wing 1.Fitful wind detecting sensor 5 sends control signal again to locking mechanism 4, and locking mechanism 4 is closed after receiving control signal, and locking mechanism 4 can ensure locked full dynamic formula wing tip 2 and host wing 1 within the scope of certain error in design.So full dynamic formula wing tip 2 and host wing 1 just define a complete wing to produce lift.
Embodiment
The dimensional parameters of a kind of high-aspect-ratio aircraft wing and full dynamic formula Full-motion wingtip gust alleviation device is provided in this example.Wing semispan is 12.84m, wing chord length is 2.14m, the sweepback angle of wing is 30 °, the aspect ratio of wing is 12, the long purlin of wing is positioned at chord length apart from leading edge 30% place, the tip station of single wing accounts for 16% of wing half length, and tip station length is 1.7m, and the position of the elasticity of torsion adapter shaft between wing tip and wing is positioned at chord length apart from leading edge 20% place.Elasticity of torsion adapter shaft adopts circular section form, and its torsional stiffness is 20kN*m
2.Maximum perpendicular gust velocity is 17m/s, and aircraft flight speed is 90m/s.The gust response not adding full dynamic formula wing tip passive gust alleviation device He have the passive gust alleviation device of full dynamic formula wing tip two kinds of situation lower wings is compared in this example.
As can be seen from Figure 8, after high aspect ratio wing installs full dynamic formula Full-motion wingtip gust alleviation device additional, for a specific connection location and torsional stiffness, the displacement that wing tip produces because of fitful wind significantly declines, the maximum displacement of wing tip has reduced to 1.6m from 2.7m, and this fully shows that the passive gust alleviation device of full dynamic formula wing tip can effectively reduce gust response.This is that the position that is connected with wing due to full dynamic formula wing tip is before wing aerodynamic center, when running into vertical gust, full dynamic formula wing tip bow motion namely produce negative bias turn, effective angle of attack is reduced, reduce the wind-induced lift of vertical array, thus realize actv. gust alleviation.
In this example, the full dynamic formula wing tip passive gust alleviation device that the present invention proposes can effectively reduce the wind-induced dynamic response of battle array and load, realize the effect of gust alleviation, simultaneously because full dynamic formula Full-motion wingtip gust alleviation device provided by the invention realizes gust alleviation by the structural property parameter of change wing, do not need to consider active response system, light compared to ACTIVE CONTROL gust alleviation installation weight, structure is simple, is applicable to the gust alleviation of high-aspect-ratio aircraft.
Claims (6)
1. one kind is applicable to the full dynamic formula Full-motion wingtip gust alleviation device of high-aspect-ratio aircraft, comprise host wing, fitful wind detecting sensor and control apparatus, it is characterized in that: described gust alleviation device also comprises full dynamic formula wing tip, elasticity of torsion adapter shaft and locking mechanism, full dynamic formula wing tip accounts for 10% ~ 20% of wing length, is connected with locking mechanism by elasticity of torsion adapter shaft with host wing; Full dynamic formula wing tip has fitful wind detecting sensor for detecting vertical gust, and fitful wind detecting sensor is connected with locking mechanism by cable, is also connected with the motor in control apparatus simultaneously; Under regular flight condition, locking mechanism closes, and wing tip and host wing are in locking state, forms a complete wing; When fitful wind detecting sensor detects vertical gust, locking mechanism is opened, and wing tip is in complete dynamic state, turns slow down gust load by producing negative bias of bowing under fitful wind effect.
2. a kind of full dynamic formula Full-motion wingtip gust alleviation device being applicable to high-aspect-ratio aircraft according to claim 1, is characterized in that: the chord length that the position of described elasticity of torsion adapter shaft is less than 25% apart from the distance of the leading edge of a wing, before wing aerodynamic center.
3. a kind of full dynamic formula Full-motion wingtip gust alleviation device being applicable to high-aspect-ratio aircraft according to claim 1, it is characterized in that: described elasticity of torsion adapter shaft is provided with set pin, elasticity of torsion adapter shaft two ends are connected with the rib on full dynamic formula wing tip with host wing respectively; Rib has chute, the dual-side of chute organizes jack more, described set pin with often organize jack and coordinate the location realizing elasticity of torsion adapter shaft.
4. a kind of full dynamic formula Full-motion wingtip gust alleviation device being applicable to high-aspect-ratio aircraft according to claim 3, is characterized in that: described elasticity of torsion adapter shaft is connected with two or more rib adjacent on host wing and full dynamic formula wing tip.
5. a kind of full dynamic formula Full-motion wingtip gust alleviation device being applicable to high-aspect-ratio aircraft according to claim 3, is characterized in that: all have reinforced rib around described elasticity of torsion adapter shaft and the junction of rib.
6. a kind of full dynamic formula Full-motion wingtip gust alleviation device being applicable to high-aspect-ratio aircraft according to claim 1, is characterized in that: described control apparatus is made up of leading screw, feed screw nut, motor and slide rail; Leading screw is an elongated metal bar, and there is outside thread on surface, is fixed on the output shaft of motor, can rotate under the drive of motor; Have screw thread inside feed screw nut, be connected with the outside thread of leading screw, feed screw nut can move forward and backward along with the rotation of leading screw, and feed screw nut and elasticity of torsion adapter shaft are connected simultaneously; Motor is arranged on slide rail, and slide rail is parallel with elasticity of torsion adapter shaft; Motor starts after receiving the control signal that fitful wind detecting sensor sends, and slide rail slides and also drives elasticity of torsion adapter shaft to move by leading screw and feed screw nut.
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| CN105035311B (en) * | 2015-08-12 | 2017-06-09 | 中国航天空气动力技术研究院 | A kind of aircraft gust alleviation adaptive feedforward control system |
| GB2546246A (en) | 2016-01-05 | 2017-07-19 | Airbus Operations Ltd | An aircraft wing with a movable wing tip device for load alleviation |
| CN107765698B (en) * | 2017-09-04 | 2020-12-29 | 中国航空工业集团公司西安飞行自动控制研究所 | Large aircraft vertical gust load alleviation control method |
| CN113212733B (en) * | 2021-04-30 | 2022-05-10 | 成都飞机工业（集团）有限责任公司 | Large-aspect-ratio conventional-layout unmanned aerial vehicle gust load alleviation method |
| CN115981161B (en) * | 2023-02-07 | 2023-07-11 | 大连理工大学 | Fixed wing aircraft downslide control gain index optimization method based on direct lifting force |
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| US3819135A (en) * | 1972-12-15 | 1974-06-25 | Bendix Corp | System for augmenting aircraft attitude stability using vertical vane type sensors |
| CN2284731Y (en) * | 1996-05-08 | 1998-06-24 | 马金山 | Wingtip structure of plane wing |
| US6821090B1 (en) * | 1997-06-05 | 2004-11-23 | Mcdonnell Douglas Helicopter Company | Gust alleviation/flutter suppression device |
| CN103010451A (en) * | 2012-11-20 | 2013-04-03 | 无锡市万凌钢铁有限公司 | Movable tail wing structure for transport helicopters |
| CN103291561A (en) * | 2013-05-06 | 2013-09-11 | 南京航空航天大学 | Wind turbine blade with split winglet at apex |
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