CN205554562U - Anti wind suddenly of self -adaptation wing of buckling - Google Patents

Abstract

The utility model relates to an anti wind suddenly of self -adaptation wing of buckling flap aircraft, including the aircraft body, and run through in the main wing roof beam of aircraft body, its characterized in that: still including locating inner wing on the main wing roof beam and through the elasticity hinge with the outer wing that the inner wing is connected and can buckles and dismantle. One or more than one the one end of elasticity hinge is fixed in the bottom surface of inner wing, the other end is fixed in the bottom surface of outer wing. The aircraft this internal or still be equipped with on the inner wing and be used for makeeing the first actuator that the outer wing initiative is buckled. The utility model discloses the beneficial effect who has is: the outer wing can be buckled down in the effect of wind bending moment power suddenly passively, also can initiatively buckle under with at the masterpiece of crimpleing of first actuator, and it is can narrow space current smoothly to realize that the anti -wind increases surely again.

Description

The anti-prominent windbend flap of self adaptation

Technical field

The utility model relates to vehicle technology field, especially relates to one and has the anti-prominent wind function of self adaptation Aircraft bending the wing.

Background technology

Aircraft especially unmanned plane is recently as the fast development of science and technology and all kinds of specific demand It is continuously increased, starts to be widely used.

But, current existing unmanned plane can realize wing bending in flight course, and realizes stronger Anti-the actually rare of wind energy power that dash forward.Confirm after deliberation, reduce the prominent wind bending moment flight stability to unmanned plane There is greatly help.

In order to solve the problems referred to above and realize target, inventor has invented the adaptive of a kind of compact conformation Prominent wind aircraft should be resisted to bend the wing, utilize elastic hinge structure to achieve unmanned plane outer wing in prominent wind bending moment power During effect, it is possible to bending.

Utility model content

The utility model purpose be to provide a kind of scientific and reasonable for structure, control precisely, smoothness of verting, anti- The anti-prominent windbend flap of the self adaptation being applicable to aircraft that prominent wind energy power is strong.

The utility model is solved the technical problem that and is realized by the following technical solutions:

The anti-prominent windbend flap of self adaptation, including aircraft body, and through described aircraft body Main spar, it is characterised in that: also include the inner wing being located on described main spar and pass through elastic hinge It is connected with described inner wing and the outer wing of bent dismounting.

The bottom surface of described inner wing is fixed in one end of one or more described elastic hinges, and the other end is solid Bottom surface due to described outer wing.

It is additionally provided with in described aircraft body or on described inner wing to promote the actively bending of described outer wing First actuator.

The bottom surface of described outer wing is fixed in one end of a kind of rope, and the other end is fixed on described first actuator Output revolving shaft on, described rope can be crispaturaed by described output revolving shaft, and then pulls described in described outer flapwise Aircraft body bends, it is achieved passing through smoothly of narrow space.

The second actuator of being additionally provided with to drive described main spar to rotate in described aircraft body, with And in order to set up the support of described main spar.

It is further opened with on the bracket placing the draw-in groove of described main spar or perforation and in order to limit Make the limited block that described main spar is subjected to displacement.

The protective casing setting described second actuator in order to cover it is additionally provided with, in institute in described aircraft body State the louvre being further opened with on protective casing dispelling the heat.

Being additionally provided with on described inner wing can the flaperon of assisted control attitude of flight vehicle.

In described aircraft body, be additionally provided with a kind of intelligent controller, described intelligent controller respectively with institute State the first actuator and the second actuator is connected by communication, and control described first actuator and the second actuator Can stop at any corner postiton.

The utility model has the beneficial effect that outer wing passively can bend under the effect of prominent wind bending moment power, Also actively can bend under power of the crispaturaing effect of the first actuator, can realize wind resistance increasing surely again can narrow sky Between pass through smoothly.

Accompanying drawing explanation

In order to be illustrated more clearly that the utility model embodiment or technical scheme of the prior art, below The accompanying drawing used required in embodiment or description of the prior art will be briefly described.

Fig. 1 is overall cross-sectional view of the present utility model；

Fig. 2 is the cross-sectional view of the utility model medium-height trestle 6.

Detailed description of the invention

For the technological means making the utility model realize, creation characteristic, reach purpose and be prone to bright with effect White understanding, below in conjunction with specific embodiment, is expanded on further the utility model.

With reference to Fig. 1, the anti-prominent windbend flap of self adaptation shown in 2, including aircraft body 1, through flying Row device body 1 and its two ends lay respectively at the main spar 2 of these aircraft body 1 both sides, are fixedly mounted on master Inner wing 3 on spar 2 and being connected with inner wing 3 and the outer wing of bent dismounting by elastic hinge 5 4。

Wherein, main spar 2 is directly set up in two sides of aircraft body 1 by bearing, or, The internally installed support 6 having to set up main spar 2 at aircraft body 1.As in figure 2 it is shown, at this It is further opened with on support 6 placing the draw-in groove of main spar 2 or perforation 61 and in order to limit main spar The limited block 62 that 2 are subjected to displacement；

Being also equipped with on inner wing 3 can the flaperon 31 of assisted control attitude of flight vehicle；

The bottom surface of inner wing 3 is fixed in one end of one or more elastic hinges 5, and the other end is fixed on outer wing 4 Bottom surface, the lift of this outer wing 4 calculates and the torque arithmetic of elastic hinge 5 will be according to equation below Obtain:

The lift computing formula of this outer wing 4:

The lift computing formula of outer wing:

$L=\frac{1}{2}\·\mathrm{\ρ}\·V_{\mathrm{\∞}}^2\·C_L\·S$

ρ atmospheric density (can be obtained by the local density meter of inquiry)

——V_∞Speed of incoming flow (can be calculated by vehicle flight speeds, or directly record)

——C_LOuter section of airfoil lift coefficient (can pass through wind tunnel test, CFD Numerical Experiment obtains)

The outer section wing area (can directly record) of S

This elastic hinge 5 torque arithmetic formula:

M elastic hinge moment of torsion

K torsion spring stiffness

——Working torsional angle

E elasticity modulus of materials

D steel wire diameter

D mean diameter of coil

The n number of effective coils

In the inside of aircraft body 1 or on inner wing 3, it is additionally provided with to promote outer wing 4 the most curved First actuator 7 of folding.The bottom surface of outer wing 4 is fixed in one end of a kind of rope 8, and the other end is fixed on On the output revolving shaft of one actuator 7, this rope 8 can be crispaturaed by the output revolving shaft of the first actuator 7, enters And pull outer wing 4 to bend to aircraft body 1 direction, it is achieved passing through smoothly of narrow space.

The second actuator 9 of being additionally provided with in the inside of aircraft body 1 to drive main spar 2 to rotate, with And the protective casing 10 of the second actuator 9 is set in order to cover, protective casing 10 is further opened with dispelling the heat Louvre.

Being additionally provided with a kind of intelligent controller 11 in aircraft body 1, this intelligent controller 11 is respectively with the One actuator 7 and the second actuator 9 are connected by communication, and control the first actuator 7 and the second actuator 9 Can stop at any corner postiton.

Outer wing 4 described in the utility model passively can bend under the effect of prominent wind bending moment power, it is possible to Actively bending under power of the crispaturaing effect of one actuator 7, can realize wind resistance increase steady the most again can narrow space smooth Current.

Of the present utility model general principle and principal character and of the present utility model excellent have more than been shown and described Point.Skilled person will appreciate that of the industry, the utility model is not restricted to the described embodiments, above-mentioned Principle of the present utility model is simply described, without departing from the utility model described in embodiment and specification On the premise of spirit and scope, the utility model also has various changes and modifications, these changes and improvements In the range of both falling within claimed the utility model.The utility model claims scope by appended power Profit claim and equivalent thereof define.

Claims (9)

1. the anti-prominent windbend flap of self adaptation, including aircraft body, and the main spar through described aircraft body, it is characterised in that: also include being located at the inner wing on described main spar and being connected and the outer wing of bent dismounting with described inner wing by elastic hinge.

The anti-prominent windbend flap of self adaptation the most according to claim 1, it is characterised in that: the bottom surface of described inner wing is fixed in one end of one or more described elastic hinges, and the other end is fixed on the bottom surface of described outer wing.

The anti-prominent windbend flap of self adaptation the most according to claim 1, it is characterised in that: it is additionally provided with to promote the first actuator of described outer wing actively bending in described aircraft body or on described inner wing.

The anti-prominent windbend flap of self adaptation the most according to claim 3, it is characterized in that: the bottom surface of described outer wing is fixed in one end of a kind of rope, the other end is fixed on the output revolving shaft of described first actuator, described rope can be crispaturaed by described output revolving shaft, and then pull aircraft body bending described in described outer flapwise, it is achieved passing through smoothly of narrow space.

The anti-prominent windbend flap of self adaptation the most according to claim 1, it is characterised in that: the second actuator of being additionally provided with to drive described main spar to rotate in described aircraft body and in order to set up the support of described main spar.

The anti-prominent windbend flap of self adaptation the most according to claim 5, it is characterised in that: it is further opened with on the bracket placing the draw-in groove of described main spar or perforation and in order to limit the limited block that described main spar is subjected to displacement.

The anti-prominent windbend flap of self adaptation the most according to claim 5, it is characterised in that: in described aircraft body, it is additionally provided with the protective casing setting described second actuator in order to cover, described protective casing is further opened with the louvre dispelled the heat.

The anti-prominent windbend flap of self adaptation the most according to claim 1, it is characterised in that: being additionally provided with on described inner wing can the flaperon of assisted control attitude of flight vehicle.

9. according to the anti-prominent windbend flap of the self adaptation described in claim 3 or 5, it is characterized in that: in described aircraft body, be additionally provided with a kind of intelligent controller, described intelligent controller is connected by communication with described first actuator or the second actuator respectively, and controls described first actuator or the second actuator can be stopped at any corner postiton.