CN101028866A - Aircraft with wing sweepback angle change - Google Patents
Aircraft with wing sweepback angle change Download PDFInfo
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- CN101028866A CN101028866A CN 200710071973 CN200710071973A CN101028866A CN 101028866 A CN101028866 A CN 101028866A CN 200710071973 CN200710071973 CN 200710071973 CN 200710071973 A CN200710071973 A CN 200710071973A CN 101028866 A CN101028866 A CN 101028866A
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Abstract
An airplane able to change the backswept of its wing is disclosed. The wing is linked to airplane body via pin axle. Two shape memory alloy bars are symmetrically fixed to airplane body along it axis and behind said pin axles. The both ends of said shape memory alloy bars are respectively linked with one end of relative connection rod, whose another end is pivoted with a slide block able to slide in a slot on wing. The external surface of wing is sealed by shape memory polymer layer.
Description
Technical field
The present invention relates to a kind of aircraft.
Background technology
Wing is the aircraft major part of configuration again awing.There is the change wing profile (as wing setting, the span and aerofoil profile etc.) on order ground can increase the airworthiness of wing effectively awing.Wherein, the effect of the change span and wing area is the most outstanding.Such as, aircraft requires wing to have high aspect ratio, big wing area and less sweepback angle when cruising usually, and wants high-speed flight, just requires low aspect ratio, little wing area and bigger sweepback angle.In the aircraft flight process, when perpendicular to the air-flow velocity of the leading edge of a wing during near velocity of sound, upper surface of the airfoil local air flow speed will shock wave occur above velocity of sound, and flight resistance is sharply increased.Swept-back wing aircraft is compared with the straight wing aircraft because the air-flow velocity component vertical with the leading edge of a wing is lower than flying speed, only just shock wave can occur under higher flying speed, thereby postpone the generation of shock wave.Even the generation shock wave also can weaken shock strength, reduce flight resistance.The big swept back wing that the modern supersonic aircraft extensively adopts, supersonic drag is less, but pneumatic efficiency is low during low speed, and lift efficiency is bad, with the good little sweepback angle wing of low-speed performance supersonic performance is degenerated.Aircraft take off land and during low-speed operations with less sweepback angle, thereby have higher low speed cruise efficient and the bigger landing lift that takes off.With bigger sweepback angle, very favourable when supersonic flight for the resistance that reduces supersonic flight.In addition, when supersonic bomber and attack plane are done extreme low-altitude high-speed flight,, also require wing that big sweepback angle is arranged in order to reduce jolting that smooth air not causes.
And the major defect of existing switch-blade vehicle is that wing rotating mechanism complexity, weight are big.The load of movable outer wing all concentrates on the pivot, and pivot must rotate neatly.Fixed-wing or fuselage interior also will be reserved the movable wing part that enough spaces hold indentation.Slit between fixed-wing or fuselage and the movable wing needs seal closure to reduce resistance.In addition, the strong actuating device of a cover to be arranged also, could change the sweepback angle apace awing.But these bring the increase of structural weight and the reduction of a part of performance again simultaneously, and have improved development cost and technical risk.
Summary of the invention
The purpose of this invention is to provide a kind of aircraft that changes wing setting, it can solve existing switch-blade vehicle and have wing rotating mechanism complexity, weight is big, development cost is high, operation easier is big, airworthiness is low problem.
The present invention is made up of fuselage, wing, shape-memory polymer covering, bearing pin, marmem rod, connecting rod, slide block; Bearing pin is equipped with at described fuselage two side-prominent positions, the head end of wing is connected with fuselage by bearing pin, two symmetrically arranged marmem rods of the axis along fuselage fixedly are housed on the fuselage of bearing pin back, the two ends of marmem rod are connected with an end of corresponding connecting rod respectively, the other end and the slide block of connecting rod are hinged, slide block seals with the shape-memory polymer covering with the chute sliding block joint that is arranged on the wing, the outside face of wing.
The present invention has following beneficial effect: in the present invention, utilize the drive source of marmem rod as the wing sweepback, by the cooperate sweepback angle that change wing of marmem rod with connecting rod and slide block.The marmem rod adopts the method heating of resistor wire heating, apply the rotation of certain angle in advance the marmem rod, after to the heating of marmem rod, heat drives and makes the marmem rod return to original shape, the drivening rod rotation, slide block is slided along the chute on the wing, rotate thereby drive wing.Therefore, the present invention compares with existing switch-blade vehicle, have light weight, the wing rotating mechanism is simple, easy to maintenance, development cost is low, easy operation, airworthiness advantages of higher, thereby can improve the operational performance and the safety of armament systems widely, reduce weapon risk and the maintenance cost in the process under arms.One of most important factor is a kind of special material that is called shape-memory polymer (SMP) in the variable-sweep wing design.SMP has a kind of special memory function, and after the SMP material was changed to the difformity layout, the SMP molecule will be organized structure again recovering its original shape, the initial configuration of SMP material, and just its " memory " shape is that a kind of rigid body is the high-modulus form.When the SMP material is heated, will become a kind of low modulus elastomer behind high frequency light or the electric excitation, thereby can change the shape of SMP material arbitrarily.Here, when wing during to sweepback, the space of the front side of wing and fuselage junction will be strengthened, and the space of wing rear side and fuselage junction will diminish, and this moment, the SMP covering of wing front side will be stretched, and the SMP covering of wing rear side will be compressed; When wing recovers normal position, the space of the front side of wing and fuselage junction will reduce, the space of wing rear side and fuselage junction will increase, this moment can be by heat, high frequency light or electric excitation SMP, it is returned to the original form is the SMP covering shortening of wing front side, the elongation of wing rear side SMP covering, and then the change in location of adaptation wing remain wing and fuselage and are tightly connected.SMP of the present invention has advantages such as good, the high and low density of reliability of big (can reach the 10MPa magnitude), stability of motion, high rigidity, high strength and low cost of dependent variable big (maximum can reach 200%), recovery stress.In the long run, variation on this wing profile can make aircraft reach higher speed, and have high fuel efficiency, high flight quality, high safety performance, and better operability, faster landing speed, adapt to the liftoff site of various conditions, realization is carried out speed change, degree of uprising, is become the flight of flight parameter according to different task, and has the long hang time.The present invention not only can change wing shapes, utilize correlation technique of the present invention can also be used for military firearm construction such as adjustable wing cruise missile, naval vessel Submarine Structure, for safe, intellectuality, the self adaptationization that realizes armament systems provides strong basic guarantee, improve the operational performance and the safety of armament systems (especially unmanned planes) widely, reduced risk and maintenance cost in the weapon military service process.
Description of drawings
Fig. 1 is birds-eye view of the present invention (wing setting is constant), and Fig. 2 is the upward view of Fig. 1, and Fig. 3 is birds-eye view of the present invention (a change wing setting), and Fig. 4 is the upward view of Fig. 3, and Fig. 5 is the left view of slide block 7 and wing 2 sliding block joints.
The specific embodiment
The specific embodiment one: in conjunction with Fig. 1～Fig. 5 present embodiment is described, present embodiment is made up of fuselage 1, wing 2, shape-memory polymer covering 3, bearing pin 4, marmem rod 5, connecting rod 6, slide block 7; Bearing pin 4 is equipped with at 1 liang of side-prominent position of described fuselage, the head end of wing 2 is connected with fuselage 1 by bearing pin 4, two symmetrically arranged marmem rods 5 of the axis along fuselage 1 fixedly are housed on the fuselage 1 of bearing pin 4 back, the two ends of marmem rod 5 are connected with an end of corresponding connecting rod 6 respectively, the other end of connecting rod 6 and slide block 7 are hinged, slide block 7 and chute 8 sliding block joints that are arranged on the wing 2, the outside face of wing 2 seals with shape-memory polymer covering 3.
The specific embodiment two: in conjunction with Fig. 1～Fig. 4 present embodiment is described, the shape-memory polymer of present embodiment is pure shape-memory polymer or shape memory polymer composite material; Described pure shape-memory polymer is that polystyrene shape-memory polymer, epoxy resin shape-memory polymer, cyanate are wherein a kind of of shape-memory polymer, shape memory polyurethane, shape memory polyester, shape memory SB, shape memory using trans-polyisoprene or shape memory polynorbornene; Described shape memory polymer composite material is made up of shape-memory polymer matrix phase material and reinforcing phase material; Described shape-memory polymer matrix phase material is that polystyrene shape-memory polymer, epoxy resin shape-memory polymer, cyanate are wherein a kind of of shape-memory polymer, shape memory polyurethane, shape memory polyester, shape memory SB, shape memory using trans-polyisoprene or shape memory polynorbornene; Described reinforcing phase material is wherein a kind of of carbon fiber, glass fibre, Kevlar fiber, boron fiber, graphite fiber, silicon carbide fibre, carbon black, CNT, graphite, silicon carbide powder, copper powder, silver powder or aluminium powder; The type of heating of described shape-memory polymer is that directly energising is heated or heated by resistor wire.Adopt above-mentioned shape-memory polymer, when room temperature, (be lower than the glass transition temperature of shape-memory polymer, T
g) modulus of elasticity is bigger, when the glass transition temperature that is heated to shape-memory polymer was above, the modulus of elasticity of shape-memory polymer covering reduced, and plasticity strengthens, under extraneous stress, the passive ideal form that is deformed into of shape-memory polymer covering energy; (＜T when under the situation that keeps external force constraint, cooling the temperature to room temperature
g), the shape-memory polymer modulus of elasticity raises, and after the external force unloading, the shape-memory polymer covering can keep the shape after the distortion, and the energy long term storage; When being heated to shape-memory polymer T once more
gWhen above, the shape-memory polymer covering can initiatively return back to the shape of the most original (after the demoulding).So be provided with, the shape-memory polymer covering can show hot mechanical cycles performances such as the elongation-retraction, bending-stretching, extension, compression-elongation of zero damage or less damage.This SMP has dependent variable big (maximum can reach 200%), and recovery stress is advantages such as good, the high and low density of reliability of big (can reach the 10MPa magnitude), stability of motion, high rigidity, high strength and low cost.Other composition and annexation are identical with the specific embodiment one.
The specific embodiment three: in conjunction with Fig. 1～Fig. 4 present embodiment is described, the marmem rod 5 of present embodiment is wherein a kind of of TiNi marmem rod, Cu-Zn marmem rod, Cu-Al-Ni marmem rod, Cu-Sn marmem rod, Mn-Cu marmem rod, Fe-Pt marmem rod or Fe-Mn-Si marmem rod.Marmem rod 5 is (ambient temperature is lower than marmem martensite inversion temperature) under extraneous twisting resistance effect, marmem rod 5 produces certain torsional deflection (torsional strain is lower than 10%), then to 5 heating of marmem rod, austenite takes place to martensitic transformation in marmem rod 5, torsional deflection returns back to original-shape, and the type of heating of described marmem rod is that directly energising is heated or heated by resistor wire.Adopt the marmem rod 5 of above-mentioned material have moment of torsion big, can reply that windup-degree are big, speed of response fast, the repeatable high characteristics of heat-mechanical cycles.In addition, as adopting the energising heating, above marmem rod also has electrical response characteristics, is convenient to the motion of control system.
Claims (10)
1, a kind of aircraft that changes wing setting, it is made up of fuselage (1), wing (2), shape-memory polymer covering (3), bearing pin (4), marmem rod (5), connecting rod (6), slide block (7); It is characterized in that described fuselage (1) two side-prominent position is equipped with bearing pin (4), the head end of wing (2) is connected with fuselage (1) by bearing pin (4), the fuselage (1) of bearing pin (4) back is gone up two symmetrically arranged marmem rods of the axis along fuselage (1) (5) fixedly is housed, the two ends of marmem rod (5) are connected with an end of corresponding connecting rod (6) respectively, the other end of connecting rod (6) and slide block (7) are hinged, slide block (7) seals with shape-memory polymer covering (3) with chute (8) sliding block joint that is arranged on the wing (2), the outside face of wing (2).
2, a kind of aircraft that changes wing setting according to claim 1 is characterized in that described shape-memory polymer is pure shape-memory polymer or the compound material of shape-memory polymer.
3, a kind of aircraft that changes wing setting according to claim 2 is characterized in that described pure shape-memory polymer is that polystyrene shape-memory polymer, epoxy resin shape-memory polymer, cyanate are wherein a kind of of shape-memory polymer, shape memory polyurethane, shape memory polyester, shape memory SB, shape memory using trans-polyisoprene or shape memory polynorbornene.
4, a kind of aircraft that changes wing setting according to claim 2 is characterized in that described shape memory polymer composite material is made up of shape-memory polymer matrix phase material and reinforcing phase material.
5, a kind of aircraft that changes wing setting according to claim 4 is characterized in that described shape-memory polymer matrix phase material is that polystyrene shape-memory polymer, epoxy resin shape-memory polymer, cyanate are wherein a kind of of shape-memory polymer, shape memory polyurethane, shape memory polyester, shape memory SB, shape memory using trans-polyisoprene or shape memory polynorbornene;
6, a kind of aircraft that changes wing setting according to claim 4 is characterized in that described reinforcing phase material is wherein a kind of of carbon fiber, glass fibre, Kevlar fiber, boron fiber, graphite fiber, silicon carbide fibre, carbon black, CNT, graphite, silicon carbide powder, copper powder, silver powder or aluminium powder.
7, a kind of aircraft that changes wing setting according to claim 1 and 2, the type of heating that it is characterized in that described shape-memory polymer are that directly energising is heated or heated by resistor wire.
8, a kind of aircraft that changes wing setting according to claim 1 is characterized in that described marmem rod (5) is wherein a kind of of TiNi marmem rod, Cu-Zn marmem rod, Cu-Al-Ni marmem rod, Cu-Sn marmem rod, Mn-Cu marmem rod, Fe-Pt marmem rod or Fe-Mn-Si marmem rod.
9, a kind of aircraft that changes wing setting according to claim 8, the type of heating that it is characterized in that described marmem rod (5) are that directly energising is heated or heated by resistor wire.
10, a kind of aircraft that changes wing setting according to claim 1 is characterized in that chute (8) on the described wing (2) is along the length direction setting of wing (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007100719734A CN100429119C (en) | 2007-03-30 | 2007-03-30 | Aircraft with wing sweepback angle change |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007100719734A CN100429119C (en) | 2007-03-30 | 2007-03-30 | Aircraft with wing sweepback angle change |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101028866A true CN101028866A (en) | 2007-09-05 |
| CN100429119C CN100429119C (en) | 2008-10-29 |
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| Application Number | Title | Priority Date | Filing Date |
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| CNB2007100719734A Expired - Fee Related CN100429119C (en) | 2007-03-30 | 2007-03-30 | Aircraft with wing sweepback angle change |
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| CN (1) | CN100429119C (en) |
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| WO2009140021A1 (en) * | 2008-05-14 | 2009-11-19 | Raytheon Company | Shape-changing structure member with embedded spring |
| US7728267B2 (en) | 2007-02-02 | 2010-06-01 | Raytheon Company | Methods and apparatus for adjustable surfaces |
| CN101767647A (en) * | 2010-03-02 | 2010-07-07 | 北京航空航天大学 | Self-locking 90-degree full-wing variable sweepback transmission mechanism |
| US7939178B2 (en) | 2008-05-14 | 2011-05-10 | Raytheon Company | Shape-changing structure with superelastic foam material |
| CN102060100A (en) * | 2010-12-14 | 2011-05-18 | 上海智晟航空科技有限公司 | Aircraft fuselage-wing connecting mechanism |
| US8056853B2 (en) | 2008-11-25 | 2011-11-15 | Raytheon Company | Reconfigurable wing and method of use |
| CN101734369B (en) * | 2010-01-28 | 2012-06-06 | 哈尔滨工业大学 | Shape memory polymer-based air filling extensible wing and methods for manufacturing same |
| CN102530238A (en) * | 2012-02-23 | 2012-07-04 | 北京理工大学 | Unmanned aerial vehicle with variable sweepbacks and spans of wings |
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