CN109573077A - A kind of aircraft explosion resistant structure and its design method - Google Patents
A kind of aircraft explosion resistant structure and its design method Download PDFInfo
- Publication number
- CN109573077A CN109573077A CN201910104669.8A CN201910104669A CN109573077A CN 109573077 A CN109573077 A CN 109573077A CN 201910104669 A CN201910104669 A CN 201910104669A CN 109573077 A CN109573077 A CN 109573077A
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- CN
- China
- Prior art keywords
- cabin
- aircraft
- load section
- resistant structure
- span line
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention 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 invention also discloses the design methods of aircraft explosion resistant structure.Structure of the invention form 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
Technical field
The present invention relates to a kind of explosion resistant structures, and in particular to a kind of aircraft explosion resistant structure, the present invention also provides resistance of airplane
The design method of quick-fried 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 the finally invention can be with
Ignition in cabin is prevented, secondary disaster is prevented.
Summary of the invention
The aircraft in flight course is destroyed by explosive in order to prevent, causes fatal crass and other negative consequences, this hair
It is bright that a kind of aircraft explosion resistant structure is provided, to protect aircraft and passenger to be not affected or less affected by injury after explosive charge.
The present invention is implemented as follows:
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 present invention also provides a kind of design methods of aircraft explosion resistant structure, comprising:
According to the maximum equivalent weight requirements of protection, determine that the diameter and thickness of explosion resistant structure main body load section, corresponding design are quick-fried
Hong product span line will fully consider that load section ultra-high molecular weight polyethylene is entwined outer in design agents load section
Layer and polyurethane foamed material impact energy-absorbing internal layer thickness, be in cabin front and back axis by the shell of column axis of column load section
90 degree, then detonation product span line both ends are connect with the cabin venting of dust explosion hole in cabin two side walls, so as to complete flying
The design of machine explosion resistant structure.
When specifically used, explosive is put into the explosive placement space among main body load section internal layer, then by load
Section is connect with detonation product span line, and after explosion, shock wave breaks up the cabin venting of dust explosion hole of two sides, by hole pressure release, effectively
Reduce influence of the explosion to aircraft.Structure of the invention form is simple, light weight, and antiknock fire-resistant effect is good, and explosion time energy is occurring
The safety of effective protection aircraft and passenger.
Detailed description of the invention
Fig. 1 is the schematic cross-sectional view of aircraft explosion resistant structure provided by the invention.
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 invention has been described for explanatory embodiment of the invention, and above-described embodiment is only this hair
Bright preferable embodiment, embodiment of the present invention are not limited by the above embodiments, it should be appreciated that those skilled in the art
Member can be designed that a lot of other modification and implementations, these modifications and implementations will fall in principle disclosed in the present application
Within scope and spirit.
Claims (6)
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.
6. the design method of aircraft explosion resistant structure described in claim 1 to 5 any claim, characterized by comprising:
According to the maximum equivalent weight requirements of protection, determine that the diameter and thickness of explosion resistant structure main body load section, corresponding design detonation produce
Object span line, in design agents load section, to fully consider outer layer that load section ultra-high molecular weight polyethylene is entwined and
The thickness of the impact energy-absorbing internal layer of polyurethane foamed material, is in 90 by the shell of column axis of column load section and cabin front and back axis
Detonation product span line both ends, then connect, so as to complete aircraft by degree with the cabin venting of dust explosion hole in cabin two side walls
The design of explosion resistant structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910104669.8A CN109573077B (en) | 2019-02-01 | 2019-02-01 | Aircraft antiknock structure and design method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910104669.8A CN109573077B (en) | 2019-02-01 | 2019-02-01 | Aircraft antiknock structure and design method thereof |
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| Publication Number | Publication Date |
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| CN109573077A true CN109573077A (en) | 2019-04-05 |
| CN109573077B CN109573077B (en) | 2023-09-01 |
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| CN109573077B (en) | 2023-09-01 |
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