CN114802779A - Aircraft fuel tank with penetration and damage resisting protection effect and design method thereof - Google Patents
Aircraft fuel tank with penetration and damage resisting protection effect and design method thereof Download PDFInfo
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- CN114802779A CN114802779A CN202210714921.9A CN202210714921A CN114802779A CN 114802779 A CN114802779 A CN 114802779A CN 202210714921 A CN202210714921 A CN 202210714921A CN 114802779 A CN114802779 A CN 114802779A
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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
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/02—Tanks
- B64D37/06—Constructional adaptations thereof
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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
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/32—Safety measures not otherwise provided for, e.g. preventing explosive conditions
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
Abstract
The invention discloses an aircraft fuel tank with penetration-resistant damage protection effect and a design method thereof, wherein the aircraft fuel tank comprises a fuel tank wall surface layer, a leakage-proof rubber layer, an energy-absorbing foam layer, a toughened fiber fabric layer and a passivated ceramic layer; the method comprises the following steps: firstly, determining an initial value of the thickness of each layer of structure of an aircraft fuel tank; secondly, determining a primary correction value of the thickness of each layer of structure of the fuel tank of the airplane; determining a secondary correction value of the thickness of each layer of the structure of the fuel tank of the airplane; determining a third correction value of the thickness of each layer of the structure of the fuel tank of the airplane; and fifthly, designing and manufacturing the fuel tank of the airplane. According to the invention, the protective layer is arranged outside the wall surface layer of the fuel tank, and combines the ceramic protection and passivation effect, the toughening and anti-crushing effect of the fiber fabric, the honeycomb plastic energy absorption effect, the rubber buffering and expansion blocking effect and other effects, so that the penetration and damage protection of the fuel tank are realized to the maximum extent, and the viability of the fuel tank structure is ensured.
Description
Technical Field
The invention belongs to the technical field of airplane structure design, and particularly relates to an airplane fuel tank with penetration and damage resistant protection effects and a design method thereof.
Background
For improving the operational efficiency of military aircraft, the critical indexes such as attendance rate and operational damage rate of military aircraft need to be guaranteed, which makes requirements on the damage resistance of a structural platform of the military aircraft in a complex operational environment.
At present, two main means are provided for improving the penetration and damage resistance of a fuel tank, one is to add a protective structure in the tank body to protect the integrity of the whole structure of the tank body in a mode of damaging shock waves or absorbing shock wave energy, and the other is to attach a high-strength protective material on the surface to resist penetration of projectiles and fragments, so that the aim of protecting the tank body is fulfilled. However, the two design methods have certain defects, the first method can avoid large-area damage of the fuel tank or reduce the damage degree caused by bird strike or explosion shock wave action, but cannot avoid oil leakage and explosion of the fuel tank caused by the breakdown of a projectile or a fragment, is only suitable for wing fuel tanks of civil aircrafts, and is difficult to install a protection structure at the inner side; the second method utilizes the characteristic of high modulus and high strength of the ceramic protective material to improve the penetration and damage resistance of the fuel tank, but the ceramic material has poor toughness and poor energy absorption effect, and the penetration and damage resistance cannot reach the best, so that the tearing area of the fuel tank can be increased, and the oil leakage can be increased.
Disclosure of Invention
The invention aims to solve the technical problem that the defects in the prior art are overcome, and provides an aircraft fuel tank with an anti-penetration damage protection effect and a design method thereof, wherein a protective layer is arranged outside a wall surface layer of the fuel tank, so that the wall surface layer of the fuel tank can be effectively protected, and only when the protective layer fails, the wall surface layer of the fuel tank can be damaged and oil can leak; meanwhile, the protective layer is made of four different materials, so that the protective layer well combines the functions of ceramic protection and passivation, fiber fabric toughening and anti-crushing, honeycomb plastic energy absorption, rubber buffering, expansion and blockage and the like, the penetration and damage protection of the fuel tank is realized to the maximum extent, the fuel tank is prevented from being punctured and leaking oil or being exploded by fire, and the viability of the fuel tank structure is guaranteed.
In order to solve the technical problems, the invention adopts the technical scheme that: an aircraft fuel tank with anti-penetration damage protection effect, which is characterized in that: the energy-absorbing and energy-absorbing protective layer comprises a fuel tank wall surface layer serving as an aircraft fuel tank body and a protective layer coated outside the fuel tank wall surface layer, wherein the protective layer comprises a leakage-proof rubber layer, an energy-absorbing foam layer, a toughened fiber fabric layer and a passivated ceramic layer which are sequentially arranged from inside to outside;
the toughened fiber fabric layer is bonded with the passivated ceramic layer, an expansion gap is formed between the outer wall of the oil tank wall surface layer and the inner wall of the anti-leakage rubber layer, the outer wall of the anti-leakage rubber layer is attached to the inner wall of the energy-absorbing foam layer, and the inner wall of the toughened fiber fabric layer is attached to the outer wall of the energy-absorbing foam layer.
Foretell aircraft fuel tank with anti penetration damage safeguard effect, its characterized in that: the anti-leakage rubber layer is of an expansion rubber layer structure made of a rubber material with high oil absorption resin as a modifier, and the thickness of the anti-leakage rubber layer is 1-2 mm.
The aircraft fuel tank with the penetration and damage resisting protection effect is characterized in that: the energy-absorbing foam layer is of an energy-absorbing honeycomb layer structure made of honeycomb materials, and the thickness of the energy-absorbing foam layer is 5-20 mm.
The aircraft fuel tank with the penetration and damage resisting protection effect is characterized in that: the toughening fiber fabric layer is of a toughening fiber fabric layer structure made of carbon fiber fabrics, and the thickness of the toughening fiber fabric layer is 0.2-0.6 mm.
The aircraft fuel tank with the penetration and damage resisting protection effect is characterized in that: the passivation ceramic layer is a high-strength ceramic layer structure made of aluminum oxide, boron carbide or silicon carbide, and the thickness of the passivation ceramic layer is 1-2 mm.
The aircraft fuel tank with the penetration and damage resisting protection effect is characterized in that: the oil tank wall surface layer is made of an aluminum alloy material, and the wall thickness of the oil tank wall surface layer is 0.5 mm-2 mm.
Meanwhile, the invention also discloses a design method of the aircraft fuel tank with the penetration and damage resistant protection effect, which is characterized by comprising the following steps:
step one, determining an initial value of the thickness of each layer of the aircraft fuel tank: respectively selecting materials of a wall surface layer of the fuel tank, a leakage-proof rubber layer, an energy-absorbing foam layer, a toughened fiber fabric layer and a passivated ceramic layer according to the overall weight requirement and the war damage resistance design requirement of the aircraft fuel tank, and preliminarily determining the initial value of the thickness of each layer of the structure of the aircraft fuel tank and the initial value of the expansion gap;
step two, determining a primary correction value of the thickness of each layer of the aircraft fuel tank: processing and manufacturing a first flat plate test piece with the same cross section structure as the aircraft fuel tank by taking the initial value of the thickness of each layer of the aircraft fuel tank determined in the step one as a reference, performing a simulation test on the aircraft fuel tank when the aircraft fuel tank is impacted by a projectile or a fragment at a set speed by adopting the first flat plate test piece, and correcting the initial value of the thickness of each layer of the aircraft fuel tank determined in the step one to obtain the corresponding thickness of each layer of the structure when the first flat plate test piece is punctured or the surface layer of the wall of the fuel tank is cracked, wherein the corresponding thickness of each layer of the structure is used as a primary correction value of the thickness of each layer of the aircraft fuel tank;
step three, determining a secondary correction value of the thickness of each layer of the aircraft fuel tank: processing and manufacturing a rigid box body and a second flat plate test piece with the same cross-sectional structure as the aircraft fuel tank by taking the primary corrected value of the thickness of each layer of the aircraft fuel tank determined in the step two as a reference, arranging an opening at one side of the rigid box body, installing the second flat plate test piece at the outer side of the opening, adopting the rigid box body to install the second flat plate test piece to perform a simulation test when the aircraft fuel tank is impacted by a projectile or a fragment at a set speed, and correcting the primary corrected value of the thickness of each layer of the structure of the aircraft fuel tank determined in the step two again to obtain the corresponding thickness of each layer of the structure of the second flat plate test piece when the second flat plate test piece is punctured or the surface layer of the wall of the fuel tank is cracked to serve as a secondary corrected value of the thickness of each layer of the structure of the aircraft fuel tank;
water is injected into the rigid box body, and a gap between the rigid box body and the second flat plate test piece is sealed;
step four, determining a third correction value of the thickness of each layer of the aircraft fuel tank: processing and manufacturing an aircraft fuel tank test piece by taking the secondary corrected value of each layer of structural thickness of the aircraft fuel tank determined in the third step as a reference, filling fuel oil and inert gas in the aircraft fuel tank test piece, performing a simulation test on the aircraft fuel tank when the aircraft fuel tank is impacted by a projectile or a fragment at a set speed by adopting the aircraft fuel tank test piece, and performing secondary correction on each layer of structural thickness of the aircraft fuel tank determined in the third step to obtain the corresponding layer of structural thickness when the aircraft fuel tank test piece is not punctured or a fuel tank wall surface layer is not cracked or a fuel tank wall surface layer is cracked, and taking the corresponding layer of structural thickness as a tertiary corrected value of each layer of structural thickness of the aircraft fuel tank;
designing and manufacturing an aircraft fuel tank: according to the capacity of the aircraft fuel tank, the initial value of the expansion gap determined in the step one and the third corrected value of the thickness of each layer of the structure of the aircraft fuel tank determined in the step four are taken as the reference, an aircraft fuel tank test piece is manufactured, a simulation test is carried out when the aircraft fuel tank is impacted by a projectile or a fragment at a set speed by adopting the aircraft fuel tank test piece, the impact speed of the projectile or the fragment is gradually increased to carry out an acceleration impact test until the aircraft fuel tank test piece is punctured, the final value of each layer of the structure thickness corresponding to the self-sealing of the tested puncture hole in the set time of the leak-proof rubber layer of the aircraft fuel tank test piece and the corrected value of the expansion gap are obtained, and the aircraft fuel tank is manufactured according to the final value of each structure thickness of each layer of the aircraft fuel tank test piece and the corrected value of the expansion gap.
The above method is characterized in that: step two, step three and step four correct the method to each layer thickness of fuel tank of the plane identically, if the test piece is not punctured or the surface course of fuel tank wall does not break after the simulation test process, the corrected value of each layer thickness of fuel tank of the plane is zero;
and if the test piece is punctured or the surface layer of the fuel tank wall is cracked in the test simulation test, thickening one or more layers of the energy-absorbing foam layer, the toughened fiber fabric layer and the passivated ceramic layer of the test piece and remanufacturing the test piece for impact test until the test piece is not punctured or the surface layer of the fuel tank wall is not cracked after the impact test, and taking the thickness of each layer of structure corresponding to the test piece at the moment as the corrected value of the thickness of each layer of structure of the fuel tank of the airplane.
The above method is characterized in that: step five, if the aircraft fuel tank test piece can be self-sealed within a set time after being punctured or the fuel tank wall surface layer is broken, processing and manufacturing the aircraft fuel tank according to the three corrected values of the thicknesses of the structures of the aircraft fuel tank test piece layer and the initial value of the expansion gap;
if the aircraft fuel tank test piece can not carry out the self sealss in the settlement time after being punctured or the oil tank wall surface course takes place to break, the material on leak protection rubber layer, increase leak protection rubber layer in the adjustment aircraft fuel tank test piece thickness reduce behind the initial value of inflation clearance, make aircraft fuel tank test piece again and carry out the shock test with higher speed, can carry out the self sealss in the settlement time until aircraft fuel tank test piece is punctured or the oil tank wall surface course takes place to break after, according to this moment aircraft fuel tank test piece correspond each layer structure thickness with inflation clearance processing preparation aircraft fuel tank.
Compared with the prior art, the invention has the following advantages:
1. the aircraft fuel tank adopted by the invention can effectively protect the fuel tank wall surface layer by arranging the protective layer outside the fuel tank wall surface layer, and the fuel tank wall surface layer can be damaged and leaked only when the protective layer fails.
2. According to the aircraft fuel tank adopted by the invention, the passivated ceramic layer is used as the outermost layer structure of the protective layer, when a powerful bullet impacts the ceramic surface, the bullet or fragment is passivated due to the fact that the ceramic hardness is higher than the flying speed of the bullet, and kinetic energy is absorbed and the speed is reduced in the processes of crushing, erosion friction and fracture energy absorption of the ceramic surface.
3. According to the aircraft fuel tank adopted by the invention, the toughening fiber fabric layer is adhered to the inner surface of the passivation ceramic layer, so that the defect of poor toughness of the passivation ceramic layer can be overcome by the toughening fiber fabric layer, the ceramic is ensured to be reliably connected together after being broken, and the effect of further preventing a projectile or fragment is achieved.
4. According to the aircraft fuel tank adopted by the invention, the energy-absorbing foam layer is arranged on the inner side of the toughened fiber fabric layer, so that the effect of absorbing the impact kinetic energy of a projectile or a fragment can be achieved, the speed of the projectile or the fragment is reduced by absorbing energy through plastic deformation of the honeycomb material in the energy-absorbing foam layer, and the toughened fiber fabric layer is prevented from being broken under the condition of great deformation.
5. According to the aircraft fuel tank adopted by the invention, the leakproof rubber layer is used as the innermost layer structure of the protective layer, so that the leakproof rubber layer can play a role in relieving the shaking impact of the wall surface layer of the fuel tank, meanwhile, under the action of a high-energy projectile or fragment, the rubber layer can play a further energy-absorbing and buffering role, and when the outer three-layer structure cannot completely prevent the projectile or fragment, the wall surface layer of the fuel tank is penetrated, oil flowing out of the wall surface layer of the fuel tank can go deep into the leakproof rubber layer, so that the leakproof rubber layer is rapidly expanded, the projectile hole is blocked, and the oil is prevented from continuously flowing out; meanwhile, the oil tank has the function of isolating air, and prevents oil in the surface layer of the wall of the oil tank from being ignited and exploded due to high temperature or open fire.
6. The method is adopted, the protection effect of the aircraft fuel tank is verified by sequentially adopting the flat plate test piece, the flat plate test piece is arranged on the rigid box body, the protection effect of the aircraft fuel tank is verified under the condition of liquid filling, the actual aircraft fuel tank test piece is manufactured to verify the protection effect of the aircraft fuel tank, and then gradually correcting the thickness of each layer of the structure of the fuel tank of the airplane to obtain a corrected value of the thickness of each layer of the structure of the fuel tank of the airplane, then an actual aircraft fuel tank test piece is adopted to carry out an accelerated impact test so as to ensure that the aircraft fuel tank test piece can realize self-sealing within a set time after penetration, and then obtain the final value of each layer structure thickness of confirming the aircraft fuel tank, can effectively guarantee the protective effect of the aircraft fuel tank of design, can effectively reduce the waste of material in the aircraft fuel tank test process simultaneously.
In conclusion, the protective layer is arranged outside the oil tank wall surface layer, so that the oil tank wall surface layer can be effectively protected, and the oil tank wall surface layer can be damaged and leaked only when the protective layer fails; meanwhile, the protective layer is made of four different materials, so that the protective layer well combines the functions of ceramic protection and passivation, fiber fabric toughening and anti-crushing, honeycomb plastic energy absorption, rubber buffering, expansion and blockage and the like, the penetration and damage protection of the fuel tank is realized to the maximum extent, the fuel tank is prevented from being punctured and leaking oil or being exploded by fire, and the viability of the fuel tank structure is guaranteed.
The technical solution of the present invention is further described in detail by the accompanying drawings and embodiments.
Drawings
FIG. 1 is a schematic structural diagram of the present invention.
FIG. 2 is a block flow diagram of the method of the present invention.
Fig. 3 is a schematic structural view of the rigid case of the present invention.
FIG. 4 is a schematic view of a connection structure between the rigid box and the second flat plate test piece according to the present invention.
Description of reference numerals:
1-oil tank wall surface layer; 2-a leakage-proof rubber layer; 3-an energy absorbing foam layer;
4-a layer of toughened fibrous fabric; 5-passivating the ceramic layer; 6-rigid box body;
6-1-opening; 7-second plate test piece.
Detailed Description
The aircraft fuel tank with the penetration and damage resisting protection effect as shown in fig. 1 comprises a fuel tank wall surface layer 1 serving as an aircraft fuel tank body and a protection layer coated outside the fuel tank wall surface layer 1, wherein the protection layer comprises a leakage-proof rubber layer 2, an energy-absorbing foam layer 3, a toughened fiber fabric layer 4 and a passivated ceramic layer 5 which are sequentially arranged from inside to outside and outside the fuel tank wall surface layer 1;
toughened fiber fabric layer 4 bonds with passivation ceramic layer 5 and is in the same place, the expansion gap has between the outer wall on oil tank wall surface course 1 and the inner wall on leak protection rubber layer 2, the outer wall on leak protection rubber layer 2 is laminated with the inner wall on energy-absorbing foam layer 3 mutually, toughened fiber fabric layer 4's inner wall is laminated with the outer wall on energy-absorbing foam layer 3 mutually.
During the in-service use, through inciting somebody to action the inoxidizing coating setting is in the outside of oil tank wall surface course 1, can effectively protect oil tank wall surface course 1, only works as when the inoxidizing coating is inefficacy, just can lead to the damaged oil leak of oil tank wall surface course 1.
The fuel tank wall surface layer 1 is coated with four layers of different materials to form a protective layer, and the protective layer well combines the functions of ceramic protection and passivation, fiber fabric toughening and anti-crushing, honeycomb plastic energy absorption, rubber buffering, expansion and blockage and the like, so that penetration and damage protection of the fuel tank is realized to the maximum extent, the fuel tank is prevented from being punctured and leaking oil or exploding due to fire, and the viability of the fuel tank structure is guaranteed.
It should be noted that, by using the passivated ceramic layer 5 as the outermost layer structure of the protective layer, when a powerful bullet impacts the ceramic surface, the ceramic hardness is higher than the flying speed of the bullet, so that the bullet or fragment is passivated, and kinetic energy is absorbed and the speed is reduced in the processes of crushing, erosion friction and fracture energy absorption of the ceramic surface.
Particularly, the toughening fiber fabric layer 4 is adhered to the inner surface of the passivated ceramic layer 5, so that the toughening fiber fabric layer 4 can make up the defect of poor toughness of the passivated ceramic layer 5, ensure that the ceramic is still reliably connected together after being broken, and further play a role in preventing projectiles or fragments.
When the energy-absorbing foam layer 3 is arranged on the inner side of the toughened fiber fabric layer 4, the effect of absorbing impact kinetic energy of a projectile or a fragment can be achieved, the speed of the projectile or the fragment is reduced through plastic deformation energy absorption of honeycomb materials in the energy-absorbing foam layer 3, and the toughened fiber fabric layer 4 is prevented from being broken under the condition of great deformation.
In practical use, the anti-leakage rubber layer 2 is used as the innermost layer structure of the protective layer, so that the anti-leakage rubber layer 2 can play a role in relieving shaking impact of the oil tank wall surface layer 1, meanwhile, under the action of a high-energy projectile or fragment, the rubber layer can play a further energy-absorbing buffering role, and when the outer three-layer structure cannot completely prevent the projectile or fragment, so that the oil tank wall surface layer 1 is penetrated, oil flowing out of the oil tank wall surface layer 1 can go deep into the anti-leakage rubber layer 2, so that the anti-leakage rubber layer 2 is rapidly expanded to block a projectile hole, and the oil is prevented from continuously flowing out; meanwhile, the air isolation effect is achieved, and the oil in the oil tank wall surface layer 1 is prevented from being ignited and exploded due to high temperature or open fire.
It should be noted that, by providing an expansion gap between the outer wall of the tank wall surface layer 1 and the inner wall of the leakage-proof rubber layer 2, it is avoided that the leakage-proof rubber layer 2 expands to generate extra pressure on the tank wall surface layer 1.
In this embodiment, the leakage-proof rubber layer 2 is an expansion rubber layer structure made of a rubber material using a high oil absorption resin as a modifier, and the thickness of the leakage-proof rubber layer 2 is 1mm to 2 mm.
In actual use, the leakage-proof rubber layer 2 has stronger expansion performance.
In this embodiment, the energy-absorbing foam layer 3 is an energy-absorbing honeycomb layer structure made of a honeycomb material, and the thickness of the energy-absorbing foam layer 3 is 5mm to 20 mm.
When the energy-absorbing foam layer is actually used, the energy-absorbing foam layer 3 has strong energy-absorbing performance, and the energy-absorbing foam layer 3 is made of honeycomb aluminum.
In this embodiment, the toughened fiber fabric layer 4 is a toughened fiber fabric layer structure made of a carbon fiber fabric, and the thickness of the toughened fiber fabric layer 4 is 0.2mm to 0.6 mm.
In actual use, the number of layers of the carbon fiber fabric adopted by the toughening fiber fabric layer 4 is determined according to the thickness, strength and penetration resistance design requirements of the ceramic material.
In this embodiment, the passivated ceramic layer 5 is a high-strength ceramic layer structure made of aluminum oxide, boron carbide or silicon carbide, and the thickness of the passivated ceramic layer 5 is 1mm to 2 mm.
In practical use, the compressive strength of the passivated ceramic layer 5 is not less than 1000MPa, and the passivated ceramic layer 5 on the outermost layer can utilize the extremely high elastic modulus and fracture strength of the ceramic material to greatly prevent the penetration capability of a projectile or a fragment.
In this embodiment, the oil tank wall surface layer 1 is made of an aluminum alloy material, and the wall thickness of the oil tank wall surface layer 1 is 0.5mm to 2 mm.
A method for designing an aircraft fuel tank with penetration damage prevention effect as shown in fig. 2 comprises the following steps:
step one, determining an initial value of the thickness of each layer of the aircraft fuel tank: according to the overall weight requirement and the war damage resistance design requirement of the aircraft fuel tank, materials of a fuel tank wall surface layer 1, a leakage-proof rubber layer 2, an energy-absorbing foam layer 3, a toughened fiber fabric layer 4 and a passivated ceramic layer 5 are respectively selected, and the initial value of the thickness of each layer of the aircraft fuel tank and the initial value of the expansion gap are preliminarily determined;
step two, determining a primary correction value of the thickness of each layer of the aircraft fuel tank: processing and manufacturing a first flat plate test piece with the same cross section structure as the aircraft fuel tank by taking the initial value of the thickness of each layer of the aircraft fuel tank determined in the step one as a reference, performing a simulation test on the aircraft fuel tank when the aircraft fuel tank is impacted by a projectile or a fragment at a set speed by adopting the first flat plate test piece, and correcting the initial value of the thickness of each layer of the aircraft fuel tank determined in the step one to obtain the corresponding thickness of each layer of the structure when the first flat plate test piece is punctured or the surface layer of the wall of the fuel tank is cracked, wherein the corresponding thickness of each layer of the structure is used as a primary correction value of the thickness of each layer of the aircraft fuel tank;
in practical use, when the first flat plate test piece is used for a simulation test of an aircraft fuel tank impacted by a projectile or a fragment at a set speed, the first flat plate test piece is installed at a proper position, then the projectile or the fragment is used for impacting the first flat plate test piece at the set speed, and when the projectile or the fragment impacts the first flat plate test piece, the passivated ceramic layer structure of the first flat plate test piece is impacted firstly.
It should be noted that when the first flat test piece is punctured or the tank wall surface layer is cracked, oil leakage occurs from the punctured hole.
Step three, determining a secondary correction value of the thickness of each layer of the aircraft fuel tank: processing and manufacturing a rigid box body 6 and a second flat plate test piece 7 with the same cross section structure as the aircraft fuel tank by taking the primary corrected value of the thickness of each layer structure of the aircraft fuel tank determined in the step two as a reference as shown in figures 3 and 4, an opening 6-1 is arranged on one side of the rigid box body 6, the second flat plate test piece 7 is arranged on the outer side of the opening 6-1, the second flat plate test piece 7 is arranged on the rigid box body 6 to carry out a simulation test when the aircraft fuel tank is impacted by a projectile or a fragment at a set speed, correcting the primary corrected value of the thickness of each layer of the structure of the aircraft fuel tank determined in the step two again to obtain the corresponding thickness of each layer of the structure when the second flat plate test piece 7 is broken down or the surface layer of the fuel tank wall is broken, and using the thickness of each layer of the structure as a secondary corrected value of the thickness of each layer of the structure of the aircraft fuel tank;
wherein, water is injected into the rigid box body 6, and the gap between the rigid box body 6 and the second flat plate test piece 7 is sealed;
in practical use, the opening 6-1 of the rigid box body 6 is a square opening, the second flat plate test piece 7 is installed on the outer side of the opening 6-1 through a bolt, the oil tank wall surface layer of the second flat plate test piece 7 is closely attached to the outer side wall of the rigid box body 6 to be arranged, and water is injected into the rigid box body 6 to replace fuel oil.
When a simulation test is performed by mounting the second flat plate test piece 7 on the rigid box body 6 when the aircraft fuel tank is impacted by a projectile or a fragment at a set speed, the projectile or the fragment impacts the second flat plate test piece 7, and the position where the projectile or the fragment impacts the second flat plate test piece 7 is positioned outside the opening 6-1 of the rigid box body 6.
Step four, determining a third correction value of the thickness of each layer of the aircraft fuel tank: processing and manufacturing an aircraft fuel tank test piece by taking the secondary corrected value of each layer of structure thickness of the aircraft fuel tank determined in the third step as a reference, filling fuel and inert gas in the aircraft fuel tank test piece, performing a simulation test on the aircraft fuel tank when the aircraft fuel tank is impacted by a projectile or a fragment at a set speed by adopting the aircraft fuel tank test piece, and performing secondary correction on each layer of structure thickness of the aircraft fuel tank determined in the third step to obtain each layer of structure thickness corresponding to the condition that the aircraft fuel tank test piece is not punctured or a fuel tank wall surface layer is not cracked or a fuel tank wall surface layer is cracked, wherein the each layer of structure thickness is used as a third corrected value of each layer of structure thickness of the aircraft fuel tank;
during the in-service use, fill inert gas to aircraft fuel tank test piece, the probability that the blasting takes place for aircraft fuel tank test piece can be fine reduced.
Designing and manufacturing an aircraft fuel tank: according to the capacity of aircraft fuel tank, with confirm in step one the cubic corrected value of each layer structure thickness of the aircraft fuel tank of initial value and the step of confirming in four of expansion gap is the benchmark, preparation aircraft fuel tank test piece, adopt aircraft fuel tank test piece to carry out the aircraft fuel tank by projectile or rupture disk simulation test when striking with the settlement speed, and improve the impact velocity of projectile or rupture disk gradually and carry out acceleration impact test until aircraft fuel tank test piece is punctured, the leak protection rubber layer that obtains aircraft fuel tank test piece can carry out the final value of each layer structure thickness that corresponds when self-sealing to the perforation of experiment in the settlement time and the corrected value of expansion gap, according to the final value of each structure thickness of aircraft fuel tank test piece layer and the corrected value processing preparation aircraft fuel tank of expansion gap.
It should be noted that, when the acceleration impact test of the aircraft fuel tank test piece is performed, explosion protection measures need to be taken, so that the aircraft fuel tank test piece is ensured not to be subjected to combustion and explosion under the test working condition, the normal operation of the test is ensured, and the safety of personnel and property is ensured.
When in actual use, the protection effect of the aircraft fuel tank is verified by sequentially adopting the flat plate test piece, the flat plate test piece is arranged on the rigid box body 6, the protection effect of the aircraft fuel tank is verified under the condition of liquid filling, the actual aircraft fuel tank test piece is manufactured to verify the protection effect of the aircraft fuel tank, and then gradually correcting the thickness of each layer of the structure of the fuel tank of the airplane to obtain a corrected value of the thickness of each layer of the structure of the fuel tank of the airplane, then an actual aircraft fuel tank test piece is adopted to carry out an accelerated impact test so as to ensure that the aircraft fuel tank test piece can realize self-sealing within a set time after penetration, and then the final value of each layer structure thickness of the aircraft fuel tank is determined, the protection effect of the designed aircraft fuel tank can be effectively guaranteed, and meanwhile, the waste of materials in the test process of the aircraft fuel tank can be effectively reduced.
In the specific implementation, the thickness correction methods for each layer of the aircraft fuel tank in the second step, the third step and the fourth step are the same, and if the test piece is not punctured or the surface layer of the fuel tank wall is not broken after the simulation test process is finished, the thickness correction value for each layer of the aircraft fuel tank is zero;
and if the test piece is punctured or the surface layer of the fuel tank wall is cracked in the test simulation test, thickening one or more layers of the energy-absorbing foam layer, the toughened fiber fabric layer and the passivated ceramic layer of the test piece and remanufacturing the test piece for impact test until the test piece is not punctured or the surface layer of the fuel tank wall is not cracked after the impact test, and taking the thickness of each layer of structure corresponding to the test piece at the moment as the corrected value of the thickness of each layer of structure of the fuel tank of the airplane.
When the test piece is actually used, when one or more of the energy-absorbing foam layer, the toughened fiber fabric layer and the passivated ceramic layer of the test piece are thickened, the thicknesses of the energy-absorbing foam layer, the toughened fiber fabric layer and the passivated ceramic layer are gradually increased by about 10%.
In the fifth step, if the aircraft fuel tank test piece can be self-sealed within a set time after being punctured or the fuel tank wall surface layer is cracked, the aircraft fuel tank is processed and manufactured according to the three corrected values of the thicknesses of the structures of the aircraft fuel tank test piece layer and the initial value of the expansion gap;
if the aircraft fuel tank test piece can not carry out the self sealss in the settlement time after being punctured or the oil tank wall surface course takes place to break, the material on leak protection rubber layer, increase leak protection rubber layer in the adjustment aircraft fuel tank test piece thickness reduce behind the initial value of inflation clearance, make aircraft fuel tank test piece again and carry out the shock test with higher speed, can carry out the self sealss in the settlement time until aircraft fuel tank test piece is punctured or the oil tank wall surface course takes place to break after, according to this moment aircraft fuel tank test piece correspond each layer structure thickness with inflation clearance processing preparation aircraft fuel tank.
During the in-service use, after aircraft fuel tank test piece was punctured, the fuel in the aircraft fuel tank test piece spills to the leak protection rubber layer on, and then makes the leak protection rubber layer take place the inflation and can carry out the self sealss to the perforation department that aircraft fuel tank test piece punctured, and then avoids the fuel further to take place to leak.
It should be noted that the adjustment of the material of the leak-proof rubber layer in the fuel tank test piece of the aircraft means that the amount of the high oil-absorbent resin component in the leak-proof rubber layer is increased and the initial value of the expansion gap is reduced by not more than 0.5mm each time.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and all simple modifications, changes and equivalent structural changes made to the above embodiment according to the technical spirit of the present invention still fall within the protection scope of the technical solution of the present invention.
Claims (9)
1. An aircraft fuel tank with anti-penetration damage protection effect, which is characterized in that: the anti-leakage protective layer comprises a fuel tank wall surface layer (1) serving as an aircraft fuel tank body and a protective layer coated outside the fuel tank wall surface layer (1), wherein the protective layer comprises a leakage-proof rubber layer (2), an energy-absorbing foam layer (3), a toughened fiber fabric layer (4) and a passivation ceramic layer (5) which are sequentially arranged from inside to outside;
toughened fiber fabric layer (4) bonds with passivation ceramic layer (5) and is in the same place, the expansion gap has between the outer wall of oil tank wall surface course (1) and the inner wall on leak protection rubber layer (2), the outer wall on leak protection rubber layer (2) is laminated with the inner wall on energy-absorbing foam layer (3) mutually, the inner wall on toughened fiber fabric layer (4) is laminated with the outer wall on energy-absorbing foam layer (3) mutually.
2. An aircraft fuel tank having protection against penetration damage according to claim 1, wherein: the anti-leakage rubber layer (2) is of an expansion rubber layer structure made of rubber materials with high oil absorption resin as a modifier, and the thickness of the anti-leakage rubber layer (2) is 1-2 mm.
3. An aircraft fuel tank having protection against penetration damage according to claim 1, wherein: the energy-absorbing foam layer (3) is of an energy-absorbing honeycomb layer structure made of honeycomb materials, and the thickness of the energy-absorbing foam layer (3) is 5-20 mm.
4. An aircraft fuel tank having protection against penetration damage according to claim 1, wherein: the toughening fiber fabric layer (4) is a toughening fiber fabric layer structure made of carbon fiber fabric, and the thickness of the toughening fiber fabric layer (4) is 0.2-0.6 mm.
5. An aircraft fuel tank having protection against penetration damage according to claim 1, wherein: the high-strength ceramic layer structure is characterized in that the passivated ceramic layer (5) is a high-strength ceramic layer structure made of aluminum oxide, boron carbide or silicon carbide, and the thickness of the passivated ceramic layer (5) is 1-2 mm.
6. An aircraft fuel tank having protection against penetration damage according to claim 1, wherein: the oil tank wall surface layer (1) is made of an aluminum alloy material, and the wall thickness of the oil tank wall surface layer (1) is 0.5-2 mm.
7. A method of designing an aircraft fuel tank having protection against penetration damage according to claim 1, comprising the steps of:
step one, determining an initial value of the thickness of each layer of the aircraft fuel tank: respectively selecting materials of a fuel tank wall surface layer (1), a leakage-proof rubber layer (2), an energy-absorbing foam layer (3), a toughening fiber fabric layer (4) and a passivation ceramic layer (5) according to the overall weight requirement and the war damage resistance design requirement of the aircraft fuel tank, and preliminarily determining the initial value of the structure thickness of each layer of the aircraft fuel tank and the initial value of the expansion gap;
step two, determining a primary correction value of the thickness of each layer of the aircraft fuel tank: processing and manufacturing a first flat plate test piece with the same cross section structure as the aircraft fuel tank by taking the initial value of the thickness of each layer of the aircraft fuel tank determined in the step one as a reference, performing a simulation test on the aircraft fuel tank when the aircraft fuel tank is impacted by a projectile or a fragment at a set speed by adopting the first flat plate test piece, and correcting the initial value of the thickness of each layer of the aircraft fuel tank determined in the step one to obtain the corresponding thickness of each layer of the structure when the first flat plate test piece is punctured or the surface layer of the wall of the fuel tank is cracked, wherein the corresponding thickness of each layer of the structure is used as a primary correction value of the thickness of each layer of the aircraft fuel tank;
step three, determining a secondary correction value of the thickness of each layer of the aircraft fuel tank: processing and manufacturing a rigid box body (6) and a second flat plate test piece (7) with the same cross section structure as the aircraft fuel tank by taking the primary corrected value of the thickness of each layer structure of the aircraft fuel tank determined in the step two as a reference, an opening (6-1) is arranged on one side of the rigid box body (6), the second flat plate test piece (7) is arranged on the outer side of the opening (6-1), the second flat plate test piece (7) is arranged on the rigid box body (6) to carry out simulation test when the fuel tank of the airplane is impacted by a projectile or a fragment at a set speed, correcting the primary corrected value of the thickness of each layer of the structure of the aircraft fuel tank determined in the step two again to obtain the corresponding thickness of each layer of the structure when the second flat plate test piece (7) is broken down or the surface layer of the fuel tank wall is broken, and using the thickness of each layer of the structure as a secondary corrected value of the thickness of each layer of the structure of the aircraft fuel tank;
water is injected into the rigid box body (6), and a gap between the rigid box body (6) and the second flat plate test piece (7) is sealed;
step four, determining a third correction value of the thickness of each layer of the aircraft fuel tank: processing and manufacturing an aircraft fuel tank test piece by taking the secondary corrected value of each layer of structural thickness of the aircraft fuel tank determined in the third step as a reference, filling fuel oil and inert gas in the aircraft fuel tank test piece, performing a simulation test on the aircraft fuel tank when the aircraft fuel tank is impacted by a projectile or a fragment at a set speed by adopting the aircraft fuel tank test piece, and performing secondary correction on each layer of structural thickness of the aircraft fuel tank determined in the third step to obtain the corresponding layer of structural thickness when the aircraft fuel tank test piece is not punctured or a fuel tank wall surface layer is not cracked or a fuel tank wall surface layer is cracked, and taking the corresponding layer of structural thickness as a tertiary corrected value of each layer of structural thickness of the aircraft fuel tank;
designing and manufacturing an aircraft fuel tank: according to the capacity of the aircraft fuel tank, the initial value of the expansion gap determined in the step one and the third corrected value of the thickness of each layer of the structure of the aircraft fuel tank determined in the step four are taken as the reference, an aircraft fuel tank test piece is manufactured, a simulation test is carried out when the aircraft fuel tank is impacted by a projectile or a fragment at a set speed by adopting the aircraft fuel tank test piece, the impact speed of the projectile or the fragment is gradually increased to carry out an acceleration impact test until the aircraft fuel tank test piece is punctured, the final value of each layer of the structure thickness corresponding to the self-sealing of the tested puncture hole in the set time of the leak-proof rubber layer of the aircraft fuel tank test piece and the corrected value of the expansion gap are obtained, and the aircraft fuel tank is manufactured according to the final value of each structure thickness of each layer of the aircraft fuel tank test piece and the corrected value of the expansion gap.
8. The method of claim 7, wherein: step two, step three and step four correct the method to each layer thickness of fuel tank of the plane identically, if the test piece is not punctured or the surface course of fuel tank wall does not break after the simulation test process, the corrected value of each layer thickness of fuel tank of the plane is zero;
and if the test piece is punctured or the surface layer of the fuel tank wall is cracked in the test simulation test, thickening one or more layers of the energy-absorbing foam layer, the toughened fiber fabric layer and the passivated ceramic layer of the test piece and remanufacturing the test piece for impact test until the test piece is not punctured or the surface layer of the fuel tank wall is not cracked after the impact test, and taking the thickness of each layer of structure corresponding to the test piece at the moment as the corrected value of the thickness of each layer of structure of the fuel tank of the airplane.
9. The method of claim 7, wherein: step five, if the aircraft fuel tank test piece can be self-sealed within a set time after being punctured or the fuel tank wall surface layer is cracked, processing and manufacturing the aircraft fuel tank according to the three-time correction value of each structure thickness of the aircraft fuel tank test piece layer and the initial value of the expansion gap;
if the aircraft fuel tank test piece can not carry out the self sealss in the settlement time after being punctured or the oil tank wall surface course takes place to break, the material on leak protection rubber layer, increase leak protection rubber layer in the adjustment aircraft fuel tank test piece thickness reduce behind the initial value of inflation clearance, make aircraft fuel tank test piece again and carry out the shock test with higher speed, can carry out the self sealss in the settlement time until aircraft fuel tank test piece is punctured or the oil tank wall surface course takes place to break after, according to this moment aircraft fuel tank test piece correspond each layer structure thickness with inflation clearance processing preparation aircraft fuel tank.
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| CN114953979A (en) * | 2022-08-01 | 2022-08-30 | 上海秦耀航空试验技术有限公司 | Oil tank |
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