CN207045691U - It is a kind of can the aircraft leading edge structure hit of anti-bird - Google Patents

Abstract

The utility model is related to it is a kind of can the aircraft leading edge structure hit of anti-bird, belong to field of airplane structure, it includes the first skins front edges, the second skins front edges and front-axle beam, first skins front edges are fixed on the second skins front edges, second skins front edges are fixed on front-axle beam, wherein, the first skins front edges are made with the second skins front edges of two kinds of different materials.It is of the present utility model can the aircraft leading edge structure hit of anti-bird by the way that aircraft wing/empennage leading edge is divided into front and rear two parts, the composite that front portion forms for metal with glass fibre, offer sufficient intensity is hit for the anti-bird of vertical fin leading edge, prevent bird body from penetrating covering, vertical fin leading edge structure is met anti-bird impact design requirement；Rear portion is traditional vertical fin leading edge structure with honeycomb interlayer, can mitigate the leading edge of a wing, empennage leading edge weight.

Description

It is a kind of can the aircraft leading edge structure hit of anti-bird

Technical field

The utility model belongs to the anti-bird of aircraft and hits design field, more particularly to it is a kind of can the aircraft leading edge knot that hits of anti-bird Structure.

Background technology

With the development of airplane design technology so that the flying speed of aircraft in itself is being continuously increased, and flight noise is not Disconnected to reduce, along with people in recent years increasingly focus on the protection to natural environment, factors cause bird to hit number and present year by year Increased trend.Aircraft Bird-Impact accident has been classified as " A " class aviation disaster by Federation Aeronautic International, and aircaft configuration once meets with Meet bird to hit, it will cause serious threat to flight safety, and cause serious consequence.This just hits to the anti-bird of aircaft configuration and set Meter proposes higher requirement, and one of Main Means as anti-bird impact design, optimization design should obtain enough attention And development.

According to the rules：The structures such as plane nose, the leading edge of a wing need to be caused structural damage by the bird collisions of constant weight In the case of, aircraft allows for completing this flight；In addition, the design of tail structure must assure that aircraft with constant weight After bird is bumped against, remain to continue safe flight and landing.

Utility model content

The purpose of this utility model be to provide it is a kind of can the aircraft leading edge structure hit of anti-bird, it is of the prior art for solving The anti-bird of aircraft leading edge structure hits degraded performance, or improves the problem of adding weight while anti-bird hits performance.

To reach above-mentioned purpose, the technical solution adopted in the utility model is：It is a kind of can the aircraft leading edge structure hit of anti-bird, It includes the first skins front edges, the second skins front edges and front-axle beam, and the first skins front edges are fixed on the second skins front edges, the second leading edge Covering is fixed on front-axle beam, wherein, the first skins front edges are made with the second skins front edges of two kinds of different materials.

In the utility model preferred embodiment, the first skins front edges use the composite that metal is formed with glass fibre, The intensity hit for providing anti-bird.

In the utility model preferred embodiment, the second skins front edges use honeycomb sandwich structure, and first is fixed for providing The support force of skins front edges.

In the utility model preferred embodiment, the first skins front edges and the second skins front edges are fixed using riveting method and connected Connect.

In the utility model preferred embodiment, it is described can in the aircraft leading edge structure hit of anti-bird, the first skins front edges with Distance a and b of second skins front edges along leading edge chordwise direction ratio are between 1：5 and 1：Between 1.

In the utility model preferred embodiment, the ratio 1：3.

The utility model can the aircraft leading edge structure hit of anti-bird by the way that aircraft wing/empennage leading edge is divided into front and rear two Point, front portion is the composite of metal and glass fibre composition, hits offer sufficient intensity for the anti-bird of vertical fin leading edge, prevents bird body from wearing Saturating covering, vertical fin leading edge structure is set to meet anti-bird impact design requirement；Rear portion is traditional vertical fin leading edge structure with honeycomb interlayer, The leading edge of a wing, empennage leading edge weight can be mitigated.

Brief description of the drawings

Accompanying drawing herein is merged in specification and forms the part of this specification, show meet it is of the present utility model Embodiment, and for explaining principle of the present utility model together with specification.

Fig. 1 is a kind of aircraft leading edge schematic diagram of the prior art；

Fig. 2 is another aircraft leading edge schematic diagram of the prior art

Fig. 3 is aircraft wing leading edge of the present utility model, empennage leading edge structure schematic diagram.

Reference：

The skins front edges of 1- first, 2- front-axle beams, the skins front edges of 3- second.

Embodiment

To make the purpose, technical scheme and advantage that the utility model is implemented clearer, below in conjunction with the utility model Accompanying drawing in embodiment, the technical scheme in the embodiment of the utility model is further described in more detail.

As Fig. 1 and Fig. 2 be respectively shown in be in the prior art aircraft leading edge using the preceding aircraft leading edge of two kinds of unlike materials Structural representation, the first skins front edges 1 of the individual layer composite formed for metal and glass fibre wherein shown in Fig. 1 are multiple The first skins front edges 1 for closing material are fixed on front-axle beam 2, though the aircraft leading edge of such a structure can bear the bird of certain mass Hit, but the first skins front edges 1 can bring considerable influence due to material reason to aero-structure weight so that aircraft is overall Structure aggravates.And as shown in Figure 2 is the second skins front edges 3 with honeycomb sandwich structure, honeycomb sandwich structure second before Edge covering 3 is also affixed on front-axle beam 2, although the aircraft leading edge structure of such a structure can reduce its weight in weight, But hit in anti-bird and be but short of in performance, it is impossible to withstand bird completely and hit.

In order to solve the above problems, in the utility model by aircraft leading edge (leading edge species include the leading edge of a wing and Empennage leading edge) it is divided into front and rear two parts, the first skins front edges 1 and the second skins front edges 3 use two kinds of different materials to make, with Realize different functions.Wherein, the first skins front edges 1 are primarily subjected to the shock of bird body, therefore it needs stronger shock resistance energy Power, to hit offer sufficient intensity for wing/anti-bird of vertical fin leading edge, prevent bird body from penetrating the first skins front edges, before making wing/vertical fin Edge structure meets anti-bird impact design requirement；Second skins front edges 3 are main to play support between the first skins front edges 1 and front-axle beam 2 Connection function, wing/vertical fin leading edge weight can be mitigated from the material of light weight, moderate strength.

Specifically, it is as shown in Figure 3 it is of the present utility model can the aircraft leading edge structure hit of anti-bird, it includes the first leading edge and covered Skin 1, the second skins front edges 3 and front-axle beam 2, the first skins front edges 1 are fixed on front-axle beam 2 by the second skins front edges 3, the first leading edge The skins front edges 3 of covering 1 and second are made up of two kinds of different materials.

On the basis of above-mentioned technical proposal of the present utility model, the first skins front edges 1 are metal and glass fibre composition Composite is made, and can provide preferable intensity, ensures that bird body does not pass through skins front edges and the front-axle beam 2 of its inside is caused to damage It is bad, and the second skins front edges 2 are the leading edge structure with honeycomb interlayer, it can provide certain intensity and with preferably light Quantify advantage.

In another embodiment of the present utility model, in order that the first skins front edges 1 and the second skins front edges 3 are ensureing On the basis of bonding strength, preferably mitigate weight, the first skins front edges 1 and the second skins front edges 3 and entered by the way of riveting Row connection.

In above-mentioned technical proposal of the present utility model, leading edge has been divided into two parts, the anterior weight of the first skins front edges 1 Measure that heavier but intensity is preferable, the lighter in weight of the second skins front edges 3 but intensity at rear portion are relatively low, if being covered on a large scale using the first leading edge Skin 1, then with all essentially identical using weight caused by composite in the prior art, if the first skins front edges 1 Use range is smaller, again it cannot be guaranteed that aircraft leading edge plays due effect during anti-bird is hit, therefore, in such as Fig. 3 institutes In the schematic diagram shown, length a, b of the first skins front edges 1 and the second skins front edges 3 along aircraft wing/empennage leading edge chordwise direction Ratio should be as 1：5 to 1：Between 1, preferable a:B=1:3.

After aircraft wing/empennage leading edge is by bird collisions, it can not be absorbed using legacy cellular sandwich skins front edges structure The energy that bird body hits, bird body typically can all penetrate skins front edges, penetrate front beam structure after hitting antenna, front beam structure is caused Compared with macrolesion, this will necessarily threaten the flight safety of aircraft, be unsatisfactory for anti-bird impact design requirement.And all using metal and glass The advanced composite material (ACM) of glass fiber composition, although can meet anti-bird impact design requirement, can cause construction weight mistake simultaneously Greatly.In the utility model, by the way that aircraft wing/empennage leading edge is divided into front and rear two parts, front portion is metal and glass fibre The composite of composition, offer sufficient intensity is hit for the anti-bird of vertical fin leading edge, prevents bird body from penetrating covering, expires vertical fin leading edge structure Sufficient anti-bird impact design requirement；Rear portion is traditional vertical fin leading edge structure with honeycomb interlayer, before can mitigating the leading edge of a wing, empennage Edge weight.

It is of the present utility model can the aircraft leading edge structure hit of anti-bird using current material, a little change just is only made in structure The purpose that anti-bird is hit is can reach, has saved material cost, technique making is again uncomplicated, also a saving manually, has preferably in fact The property used.

It is described above, optimal embodiment only of the present utility model, but the scope of protection of the utility model is not This is confined to, any one skilled in the art can readily occur in the technical scope that the utility model discloses Change or replacement, should all cover within the scope of protection of the utility model.Therefore, the scope of protection of the utility model should be with The scope of the claims is defined.

Claims (6)

1. a kind of can the aircraft leading edge structure hit of anti-bird, it is characterised in that it is described can the aircraft leading edge structure hit of anti-bird include the One skins front edges (1), the second skins front edges (3) and front-axle beam (2), the first skins front edges (1) are fixed on the second skins front edges (3), Second skins front edges (3) are fixed on front-axle beam (2), wherein, the first skins front edges (1) use two kinds not with the second skins front edges (3) It is made with material.

2. according to described in claim 1 can the aircraft leading edge structure hit of anti-bird, it is characterised in that the first skins front edges (1) are adopted The composite formed with metal and glass fibre, the intensity hit for providing anti-bird.

3. according to described in claim 1 can the aircraft leading edge structure hit of anti-bird, it is characterised in that the second skins front edges (3) are adopted With honeycomb sandwich structure, the support force of the first skins front edges is fixed for providing.

4. according to described in claim 1 can the aircraft leading edge structure hit of anti-bird, it is characterised in that the first skins front edges (1) with Second skins front edges (3) are fixedly connected using riveting method.

5. according to described in claim 1 can the aircraft leading edge structure hit of anti-bird, it is characterised in that it is described can flying of hitting of anti-bird In machine leading edge structure, the ratio of the first skins front edges (1) and distance a and b of the second skins front edges (3) along leading edge chordwise direction is situated between In 1：5 and 1：Between 1.

6. according to described in claim 5 can the aircraft leading edge structure hit of anti-bird, it is characterised in that the ratio 1：3.