CN209480004U - A kind of aircraft explosion resistant structure - Google Patents

Abstract

The utility model discloses a kind of aircraft explosion resistant structures, including a columnar load section, load intersegmental part is provided with explosive placement space, the shell of column axis and cabin front and back axis of column load section are in 90 degree, column load section two sides are connected with columnar detonation product span line, and detonation product span line is fixedly connected with cabin or so two wall surfaces respectively.The utility model structure type is simple, light weight, and antiknock fire-resistant effect is good, in the safety that explosion time energy effective protection aircraft and passenger occurs.

Description

A kind of aircraft explosion resistant structure

Technical field

The utility model relates to a kind of explosion resistant structures, and in particular to a kind of aircraft explosion resistant structure.

Background technique

Aircraft can sometimes encounter the bomb threat of terrorist in flight course, if bomb explodes in the sky very It is likely to cause fatal crass.The antiknock safety problem of aircraft is not paid close attention to too much before, the reason is that bomb is by band The probability boarded a plane is small, if in order to prevent explosive charge and equipment safety safeguard can make flight cost substantially aboard It increases, therefore, before new seaworthiness regulation is put into effect, all types do not account for Explosion-Proof.It has put into effect in recent years newly Seaworthiness regulation, it is desirable that the big aircraft of new listing must have certain antiknock ability, i.e. aircraft is carried in the explosion for bearing certain equivalent Under lotus, remain to maintain safe flight and landing.

If protected using traditional anti-knock container method, explosion energy is absorbed by anti-knock container completely, antiknock Container must be made very heavy, and the weight of anti-knock container is the big obstacle for controlling aircraft flight cost.Few document shows, state Using asymmetric energy-absorbing principle in terms of external antiknock, i.e., explosive is placed on the machinery space bulkhead of aircraft privileged site, which is made very Weakness, cabin inside energy-absorbing by way of then passing through and stacking luggage protect passenger and cabin.Most of energy of explosion time explosive Amount is discharged into air by the cabin wall surface blown.But there are two serious drawbacks for the method for this asymmetric energy-absorbing, it is first Adherent explosion before this is difficult to control the hole size and shape that cabin wall surface is blown, this will destroy the shape of aircraft, make aircraft The air drag being subject to when flight is asymmetric, brings difficulty for the flight in later period；Secondly, explosive charge will cause cabin and luggage Destruction and burning, cause secondary disaster.If finding explosive in flight course, explosive is quickly put into aircraft antiknock Structure can not only reduce the weight of antiknock equipment then by the application of this patent, but can control shape that aircraft cabin punches and Size, and make to punch and be symmetrically distributed in centre-line of aircraft will not be influenced too much to flight is continued, and finally the utility model is also Ignition in cabin can be prevented, secondary disaster is prevented.

Utility model content

The aircraft in flight course is destroyed by explosive in order to prevent, causes fatal crass and other negative consequences, this reality A kind of aircraft explosion resistant structure is provided with novel, to protect aircraft and passenger to be not affected or less affected by injury after explosive charge.

The utility model is realized in this way:

A kind of aircraft explosion resistant structure, including a columnar load section, load intersegmental part are provided with explosive placement space, column The shell of column axis and cabin front and back axis of shape load section are in 90 degree, and column load section two sides are connected with columnar detonation product transmission Section, detonation product span line are fixedly connected with cabin or so two wall surfaces respectively.

Load section can directly be connect by the frictional force of the contact surface of the two with detonation product span line, it is only necessary to the two Size is close, because not stressing laterally, it is possible to guarantee effectively connection.

Further scheme is:

The load section includes two layers, and outer layer is entwined by ultra-high molecular weight polyethylene, and internal layer is polyurethane foam The impact absorbing energy layer of foam material.

Ultra-high molecular weight polyethylene (abbreviation UHMWPE) is the unbranched linear polyethylene of 1,500,000 or more molecular weight.It is logical The mode for crossing winding forms column structure similar to polyethylene pipe.

Polyurethane foam uses half hard bubble Semi-rigid U of energy-absorbing polyurethane foam PU.

Further scheme is:

The detonation product span line is as made of carbon fiber winding, and detonation product span line surfaces externally and internally is coated with Zirconium oxide heat resistanceheat resistant ceramic coating.

Carbon fiber can be using the beautiful T1000 carbon fiber in east, and the thickness of zirconium oxide heat resistanceheat resistant ceramic coating is generally in 3mm or so.

Further scheme is:

Cabin venting of dust explosion hole is provided on two wall surfaces of cabin or so, detonation product span line passes through bolt and cabin venting of dust explosion Hole connection.

The diameter of cabin venting of dust explosion hole, slightly larger than the diameter of detonation product span line.

Further scheme is:

The cabin venting of dust explosion hole is closed with plane aluminium alloy covering, but is separated with cabin main body covering.

Bulkhead and cabin at cabin venting of dust explosion hole are not an entirety elsewhere, itself have bulkhead, hole is not Exposed, it will not influence the flight of aircraft after closing, and cabin venting of dust explosion hole is blown after explosion, and it is corresponding to form cabin two sides Hole, but the flight of aircraft will not be influenced.

The utility model is put into the explosive placement space among main body load section internal layer when specifically used, by explosive, Then load section is connect with detonation product span line, after explosion, shock wave breaks up the cabin venting of dust explosion hole of two sides, passes through hole The influence exploded to aircraft is effectively reduced in pressure release.The utility model structure type is simple, light weight, and antiknock fire-resistant effect is good, Explosion time energy effective protection aircraft and the safety of passenger occurs.

Detailed description of the invention

Fig. 1 is the schematic cross-sectional view of aircraft explosion resistant structure provided by the utility model.

Wherein: 1, cabin 2, antiknock load section 3, impact absorbing energy layer 4, product span line 5, cabin venting of dust explosion hole 6, explosive

Specific embodiment

Following specific embodiments are accounted for using 1000gTNT equivalent explosive as standard, the case where other equivalents are occurring When, it can according to need the thickness design for adjusting relevant load section, this adjustment is that those skilled in the art work as according to explosion The size combination related experiment of amount is available, and details are not described herein again.

The impact absorbing energy layer 3 of 100mm thickness is bonded in the inside of the antiknock bearing layer 2 of 40mm thickness with glue first；Antiknock The outer diameter of bearing layer is 500mm, and antiknock bearing layer 2 is fixed by bolts in cabin；Product span line 4 is by the two sections of carbon in left and right The pipeline composition that fiber is entwined, outside are bolted at cabin venting of dust explosion hole 5, and inside is protruded into antiknock load section Portion about 10mm；The product span line of left and right is made of the different carbon fiber column casing of two sections of internal diameters respectively, can be stretched respectively to two sides Contracting, explosive 6 are put into the impact absorbing energy layer 3 inside antiknock bearing layer 2 by the contraction of product span line 4.The thickness of product span line Degree is 8mm, and outer diameter is 436mm and 420mm；The surfaces externally and internally of last explosion resistant structure all applies zirconia ceramics coating, for resisting Explode the high temperature generated.

It separates, is then put into explosive anti-with antiknock load section in use, first pulling open telescopic product span line 4 On the impact absorbing energy layer 3 of quick-fried bearing layer 2, product span line 4 is stretched and is combined with antiknock bearing layer 2.Explosion time air-shock wave Atmosphere is discharged by cabin venting of dust explosion hole with detonation product, energy is largely released, and a part is by antiknock bearing layer 2 and punching Hit the absorption of absorbing energy layer 3, it is ensured that the safety of aircraft and passenger.

Although reference be made herein to the utility model is described in the explanatory embodiment of the utility model, above-described embodiment The only preferable embodiment of the utility model, the embodiments of the present invention are simultaneously not restricted to the described embodiments, it should Understand, those skilled in the art can be designed that a lot of other modification and implementations, these modifications and implementations will be fallen Within scope and spirit disclosed in the present application.

Claims (5)

1. a kind of aircraft explosion resistant structure, it is characterised in that: including a columnar load section, load intersegmental part is provided with explosive and puts Between emptying, the shell of column axis and cabin front and back axis of column load section are in 90 degree, and column load section two sides are connected with columnar quick-fried Hong product span line, detonation product span line are fixedly connected with cabin or so two wall surfaces respectively.

2. aircraft explosion resistant structure according to claim 1, it is characterised in that:

The load section includes two layers, and outer layer is entwined by ultra-high molecular weight polyethylene, and internal layer is polyurethane foam material The impact absorbing energy layer of material.

3. aircraft explosion resistant structure according to claim 1, it is characterised in that:

The detonation product span line is as made of carbon fiber winding, and detonation product span line surfaces externally and internally is coated with oxidation Zirconium heat resistanceheat resistant ceramic coating.

4. aircraft explosion resistant structure according to claim 1, it is characterised in that:

Cabin venting of dust explosion hole is provided on two wall surfaces of cabin or so, detonation product span line passes through bolt and cabin venting of dust explosion hole Connection.

5. aircraft explosion resistant structure according to claim 4, it is characterised in that:

The cabin venting of dust explosion hole is closed with plane aluminium alloy covering, but is separated with cabin main body covering.