CN206719524U - It is a kind of to reduce wing structure of the winglet to wing root bending moment - Google Patents

Abstract

A kind of reduction winglet described in the utility model belongs to unmanned plane wing structure technical field to the wing structure of wing root bending moment, is designed to solve the problems such as existing unmanned plane winglet is to huge bending moment caused by wing root.The utility model includes wing-body（1）Be arranged on the two panels of wing end in wing-body（1）The winglet of upper arrangement, two panels winglet are separately positioned on the upper and lower part of wing end face, constitute a winglet unit.The utility model is while single winglet huge bending moment to caused by aircraft wing root is reduced, additionally it is possible to reduces induced drag suffered by aircraft, mitigates construction weight, save oil consumption, reduces flight cost.

Description

It is a kind of to reduce wing structure of the winglet to wing root bending moment

Technical field

The utility model belongs to unmanned plane wing structure technical field, and it is curved to wing root to relate generally to a kind of reduction winglet The wing structure of square.

Background technology

Winglet is similar to the small wing of aerofoil surface, approximately perpendicular to aerofoil surface.Come for most of unmanned planes Say, in cruise, induced drag accounts for the 40% of aircraft drag overall, if can reduce induced drag suffered by unmanned plane, to saving oil Consumption and the operating cost for reducing aircraft have very big economic value.It is in the design of unmanned plane aerofoil surface increase winglet A kind of advanced technology, as long as the air-flow of the wing tip flight range of the curvature of winglet aerofoil and installation direction and unmanned plane Match proper, winglet will produce inside side force, can suppress wing tip vortex, reduce induced drag.But the wing Tip winglet can produce the bending moment to airfoil root while induced drag is reduced to the internal-direction-force of inner side suffered by it. In this case, if using a larger camber angle to design to meet to reduce the condition of induced drag, then this moment of flexure It is huge, can undoubtedly increases the main screw lift of unmanned plane to meet intensity requirement.

Utility model content

For the problems of in the prior art, the utility model designs and discloses a kind of winglet that reduces to the wing The wing structure of root moment of flexure.The purpose of this utility model is：Wing structure is made in reduction winglet to unmanned plane airfoil root While into huge bending moment, additionally it is possible to reduce induced drag suffered by unmanned plane, mitigate construction weight.

For achieving the above object, the concrete technical scheme that the utility model is taken is：One kind reduces winglet pair The wing structure of wing root bending moment, it is made up of wing-body and the winglet unit being located at wing-body wing tip；Wherein wingtip Winglet unit includes first winglet and second winglet；First winglet is arranged on the wing tip of wing-body Upper surface on, positioned at 100% length position；Second winglet is located at the lower surface of 100 lengths of the wing-body On；First winglet and second winglet connect with wing-body wing tip and merge transition.

A kind of described reduction winglet to the wing structure of wing root bending moment, wherein：First winglet and second Slanted angle α between the string plane of piece winglet and the vertical plane of ground level₁With slanted angle α₂Scope be 2 °~31 °； A kind of described reduction winglet to the wing structure of wing root bending moment, wherein：First winglet and second wingtip are small It is established angle β between the root chord line and wing-body wing tip chord line of the wing, established angle β scope is -4 °~0 °；Described one Kind reduces wing structure of the winglet to wing root bending moment, wherein：First winglet positioned at wing-body wing tip top The span be equal to wing-body wing tip chord length；Wing root chord length is equal to 0.64 times of wing-body wing tip chord length；Wing tip chord length etc. In 0.24 times of wing-body wing tip chord length；A kind of described reduction winglet is to the wing structure of wing root bending moment, its middle position It is equal to 0.6 times of wing-body wing tip chord length in the span of second winglet of wing-body wing tip chord length bottom, wing root Chord length is equal to 0.52 times of wing-body wing tip chord length, and wing tip chord length is equal to 0.16 times of wing-body wing tip chord length.

A kind of winglet that reduces described in the utility model is to the wing structure of wing root bending moment, wherein winglet unit It can reduce single winglet while induced drag is suppressed to the moment of flexure caused by airfoil root, finish so as to mitigate Structure weight, increase the air mileage of unmanned plane in the case of equal fuel load, reduce flight cost, improve the motor-driven of unmanned plane Property.

Brief description of the drawings

Fig. 1 is structural representation of the present utility model；

Fig. 2 is slanted angle schematic diagram between the string plane of winglet and the vertical plane of ground level in the utility model；

Fig. 3 is winglet established angle schematic diagram in the utility model；

Fig. 4 is the utility model winglet cell configuration schematic diagram.

In figure：1. wing-body；2nd, first winglet；3rd, second winglet；4th, slanted angle α₁；5th, tilt Angle α₂；6th, established angle β；7th, wing tip chord length；8th, first winglet span；9th, first winglet wing root chord length；10、 First winglet wing tip chord length；11st, second winglet span；12nd, second winglet wing root chord length；13rd, Two winglet wing tip chord lengths.

Embodiment

It is as follows that specific embodiment of the present utility model is provided below in conjunction with the accompanying drawings：As shown in Figure 1, Figure 2, Figure 3, Figure 4, originally A kind of reduction winglet described in utility model by wing-body 1 and is located at wing-body 1 to the wing structure of wing root bending moment Winglet unit at wing tip is formed；Wherein winglet unit includes first winglet 2 and second winglet 3；On the upper surface for the wing tip that first winglet 2 is arranged on wing-body 1, positioned at 100% length position；Second wingtip Winglet 3 is arranged on the lower surface of 100% length of wing-body 1；First winglet 2 and second winglet 3 and machine The wing tip of wing body 1 connects and merges transition；Install two panels winglet after, can suppress unmanned plane cruise when induced drag While, reduce single winglet to the moment of flexure caused by airfoil root.First winglet 2 and second wing during installation Slanted angle α between the string plane of tip winglet 3 and the vertical plane of ground level₁4 and slanted angle α₂5 angular range is 2o ~31 o；Its preferred value is 4 o.The root chord line of first winglet 2 and second winglet 3 and the wing of wing-body 1 It is established angle β 6 between sharp chord line, established angle β 6 angular range is the o of -4 o~0；Its preferred value is -2 o；Positioned at machine First winglet span 8 on the wing tip top of wing body 1 is equal to the wing tip chord length 7 of wing-body 1；First winglet wing root Chord length 9 is equal to 0.64 times of the wing tip chord length 7 of wing-body 1, and first winglet wing tip chord length 10 is equal to the wing tip of wing-body 1 0.24 times of chord length 7；Positioned at second winglet span of second winglet 3 of the wing tip bottom of wing-body 1 11 are equal to 0.6 times of the wing tip chord length 7 of wing-body 1, and second winglet wing root chord length 12 is equal to the wing tip chord length of wing-body 1 0.52 times of 7, second winglet wing tip chord length 13 are equal to 0.16 times of the wing tip chord length 7 of wing-body 1.

Claims (5)

1. a kind of reduce wing structure of the winglet to wing root bending moment, including wing-body（1）, it is characterized in that：Wing-body （1）Wing tip at be provided with winglet unit, winglet unit includes first winglet（2）With second winglet （3）；First winglet（2）It is arranged on wing-body（1）On the upper surface of wing tip, positioned at 100% length position；Second Winglet（3）It is arranged on wing-body（1）Lower surface on, position is drawn in 100% length position；First winglet（2）With Second winglet（3）With wing-body（1）Wing tip connect and merge transition.

2. a kind of winglet that reduces according to claim 1 is to the wing structure of wing root bending moment, it is characterized in that：First Winglet（2）With second winglet（3）String plane and ground level vertical plane between slanted angle α₁（4）With incline Bevel angle α₂（5）Angular range be the o of 2o~31；Its preferred value is 4 o.

3. a kind of winglet that reduces according to claim 1 is to the wing structure of wing root bending moment, it is characterized in that：First Winglet（2）With second winglet（3）Root chord line and wing-body（1）Angle between wing tip chord line is peace Fill angle beta（6）, established angle β（6）Angular range be the o of -4 o~0；Its preferred value is -2 o.

4. a kind of winglet that reduces according to claim 1 is to the wing structure of wing root bending moment, it is characterized in that：First The winglet span（8）Equal to wing-body（1）Wing tip chord length（7）, first winglet wing root chord length（9）Equal to wing sheet Body（1）Wing tip chord length（7）0.64 times, first winglet wing tip chord length（10）Equal to wing-body（1）Wing tip chord length（7） 0.24 times.

5. a kind of winglet that reduces according to claim 1 is to the wing structure of wing root bending moment, it is characterized in that：Second The winglet span（11）Equal to wing-body（1）Wing tip chord length（7）0.6 times, second winglet wing root chord length（12） Equal to wing-body（1）Wing tip chord length（7）0.52 times, second winglet wing tip chord length（13）Equal to wing-body（1） Wing tip chord length（7）0.16 times.