CN212047911U - Oil tank structure for reducing dead oil in integral oil tank of airplane - Google Patents
Oil tank structure for reducing dead oil in integral oil tank of airplane Download PDFInfo
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- CN212047911U CN212047911U CN202020219252.4U CN202020219252U CN212047911U CN 212047911 U CN212047911 U CN 212047911U CN 202020219252 U CN202020219252 U CN 202020219252U CN 212047911 U CN212047911 U CN 212047911U
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- pmi foam
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Abstract
The utility model discloses an oil tank structure for reducing dead oil in an integral oil tank of an airplane, which is suitable for the technical field of integral wing oil tank structures of airplanes and comprises an airplane oil tank; also comprises PMI foam filled in dead oil areas of airplane fuel tanks. The utility model discloses an oil tank structure for reducing dead oil in an integral oil tank of an airplane, which improves the condition that a great number of dead oil areas exist in the existing integral wing oil tank of the airplane by filling PMI foam in the dead oil areas of the integral oil tank of the airplane, avoids the influence of a great number of dead oil on the fuel utilization rate of the integral wing oil tank of the wing oil tank and increases the weight of the airplane; meanwhile, the PMI foam is used for filling the dead oil area of the oil tank, so that the PMI foam can be used as a part of the sealing of the aircraft oil tank, the aircraft oil tank is better sealed in the dead oil area, and oil leakage is reduced.
Description
Technical Field
The utility model relates to an aircraft tank technical field, concretely relates to reduce oil tank structure of interior stagnant oil of whole oil tank of aircraft.
Background
The part of the fuel which is stored in the integral fuel tank of the airplane and cannot be consumed by the airplane engine is called unusable fuel, and the unusable fuel which is still remained in the integral fuel tank structure after the fuel is discharged by the fuel discharging device is called dead fuel.
Under the condition that the requirements of airplane performance and overall layout are met, in order to increase the range, in the design scheme of the integral oil tank, the integral oil tank structure layout with the coexistence of two structural forms of metal and composite materials is used, and the structural layout of the integral oil tank airtight cabin of the independent airplane body and the independent wings is formed through high-precision matching and sealing connection of the involutory parts. Although the oil carrying capacity of the airplane is improved, a large amount of dead oil is generated in the oil tank, the utilization rate of fuel oil in the oil tank is reduced, the airplane can meet the requirement of flight oil only by increasing the oil carrying capacity, and the weight of the airplane is increased; in addition, the whole oil tank structure also causes that the sealant in certain areas of the oil tank is difficult to fill in place, which is very easy to cause oil leakage of the oil tank.
SUMMERY OF THE UTILITY MODEL
The utility model provides a to prior art, a reduce oil tank structure of interior stagnant oil of the whole oil tank of aircraft.
The utility model discloses a following technical scheme realizes: the tank structure for reducing the dead oil in the whole fuel tank of the airplane comprises the airplane fuel tank and PMI foam filled in the dead oil area of the airplane fuel tank.
The method comprises the steps that the dead oil area of the airplane fuel tank is determined after airplane fuel oil is injected and then oil is discharged, and the size and the shape of PMI foam are consistent with the shape of the dead oil area of the airplane fuel tank to be filled.
The PMI foam is filled in the dead oil area of the airplane oil tank, so that the condition that a large number of dead oil areas exist in the existing airplane integral wing oil tank is improved, the influence of a large number of dead oil on the fuel oil utilization rate of the airplane oil tank is avoided, and the weight of the airplane is increased; and because the shape of the dead oil area of the oil tank is complex, the sealant is difficult to fill in place in the sealing process, and the oil leakage event of the oil tank is easily caused, and the PMI foam is adopted to fill the dead oil area of the oil tank, so that the PMI foam can be used as a part of the sealing of the airplane oil tank, the airplane oil tank can be better sealed in the dead oil area, and the oil leakage is reduced.
Further, the aircraft fuel tank comprises a composite material part made of a composite material and a metal material part made of a metal material; the PMI foam and the composite material are bonded by adopting a sealant; the PMI foam is mechanically connected to the metal material part.
The composite material part is prepared from an aviation composite material, and has high toughness. However, when holes are formed in the composite material part, damage such as splitting is easy to occur, and after the holes are formed, the composite material part needs to be subjected to nondestructive testing, so that when the PMI foam needs to be filled in the composite material part, the PMI foam is fixed by using a sealant instead of using mechanical connection methods such as rivets, bolts and screws. The fixing method can avoid partial hole making of the composite material, and does not need nondestructive testing after PMI foam is filled.
And the metal material part does not need nondestructive testing after the hole is formed, and the situation of splitting can not occur, so the metal material part can be connected with the PMI foam in a mechanical connection mode, and the fixing effect of the metal material part is better.
Preferably, the metal material part and the PMI foam are connected in a mechanical connection mode, and meanwhile, the metal material part and the PMI foam can be sealed and bonded by adopting a sealant, so that a better sealing and fixing effect is achieved.
Furthermore, the sealant is a low-density modified polysulfide sealant which is long in service life, light in weight and suitable for filling and sealing after the aircraft fuel tank is assembled.
Further, the PMI foam and the metal material portion are connected by screws, bolts, or rivets.
Furthermore, the fuel tank structure is also provided with a corner piece for connecting the PMI foam and the aircraft fuel tank, so that the connection between the PMI foam and the aircraft fuel tank is more stable.
Further, the angle sheet is mechanically connected with the metal material part; the corner pieces and the composite material part are bonded by adopting a sealant; the corner pieces and the PMI foam are bonded by adopting a sealant. The corner pieces and the metal material part and the composite material part respectively adopt different connection modes, and the principle of the corner pieces and the metal material part and the composite material part is basically the same as that of the PMI foam and the metal material part and the composite material part which adopt different connection modes, so that the corner pieces and the metal material part and the composite material part are not repeated.
Compared with the prior art, the utility model, following advantage and beneficial effect have:
(1) the utility model provides a reduce oil tank structure of interior dead oil of aircraft whole oil tank, through filling the PMI foam in aircraft oil tank dead oil region, improve the condition that has a large amount of dead oil regions in the existing aircraft whole wing oil tank, avoid wing oil tank a large amount of dead oil to influence aircraft oil tank fuel utilization ratio, increase aircraft weight; meanwhile, the PMI foam is used for filling the dead oil area of the oil tank, so that the PMI foam can be used as a part of the sealing of the aircraft oil tank, the aircraft oil tank is better sealed in the dead oil area, and oil leakage is reduced.
(2) The utility model provides a PMI foam adopts different connection, sealed mode to combined material part and metal material part in the oil tank structure of dead oil in the whole oil tank of reduction aircraft, makes its fixed effect better and do not influence the intensity of whole wing oil tank of aircraft itself, does not increase processes such as nondestructive test.
(3) The utility model provides a reduce oil tank structure of interior stagnant oil of whole oil tank of aircraft still is provided with the corner piece, and the corner piece also adopts different connected modes with combined material part and metal material part, reaches the technological effect of reinforcing PMI foam and the whole wing oil tank of aircraft connection effect.
Drawings
FIG. 1 is a schematic structural diagram of a PMI foam filled in an aircraft dead oil area in embodiment 1 of the present invention;
fig. 2 is a schematic structural view of a corner piece and a metal material part connected in embodiment 2 of the present invention;
FIG. 3 is a schematic structural view of the connection between the corner piece and the composite material part in example 2 of the present invention;
fig. 4 is a schematic structural view of a metal material part of the present invention in which corner pieces are mounted on both sides thereof in example 2;
wherein: 1-PMI foam, 2-aircraft tank, 21-composite part, 22-metal part, 3-corner piece.
Detailed Description
The present invention will be described in further detail with reference to examples, but the present invention is not limited thereto.
The utility model is suitable for an aircraft whole wing oil tank, it fills the dead oil region of aircraft whole wing oil tank through PMI foam 1, reaches the sealed technological effect that reduces aircraft whole wing oil tank dead oil, improves the fuel utilization ratio of aircraft, reduces aircraft weight, improves aircraft whole wing oil tank.
Example 1
As shown in figures 1-3, the tank structure for reducing dead oil in the whole fuel tank of the airplane comprises an airplane fuel tank 2 and PMI foam 1 filled in a dead oil area of the airplane fuel tank 2.
The dead oil area of the aircraft fuel tank 2 is determined after the fuel oil is injected into the aircraft fuel tank and then discharged, and the size and the shape of the PMI foam 1 are consistent with the shape of the dead oil area of the aircraft fuel tank 2 to be filled. For example: the shape and the size of the PMI foam 1 can be different shapes such as a triangular cone, a trapezoidal table and a square table, and the actual shape of the PMI foam is determined according to the shape of a dead oil area to be filled in an oil tank of the integral wing of the airplane.
The aircraft fuel tank 2 comprises a composite material part 21 made of composite material and a metal material part 22 made of metal material; the PMI foam 1 and the composite material part 21 are bonded by adopting a sealant; the PMI foam 1 is mechanically connected to the metallic material portion 22. The adjacent PMI foams 1 are bonded together by a sealant. The sealant is a low-density modified polysulfide sealant.
The mechanical connection of the PMI foam 1 to the metallic material portion 22 is achieved by means of screws, bolts or rivets.
The composite portion 21 is made of an aerospace composite material, and has high toughness. However, since the composite material portion 21 is likely to be damaged by cleavage or the like when the composite material portion 21 is drilled, and the composite material portion 21 needs to be subjected to nondestructive inspection after the drilling, when the composite material portion 21 needs to be filled with the PMI foam 1, the PMI foam 1 is fixed by a sealant without using a mechanical connection means such as a rivet, a bolt, a screw, or the like, and the PMI foam 1 is fixed by adhesion. The fixing method can avoid the hole making of the composite material part 21, and the nondestructive testing is not needed after the PMI foam 1 is filled. And the metal material part 22 does not need nondestructive testing after the hole is formed, and the situation of splitting does not occur, so the metal material part can be connected with the PMI foam 1 in a mechanical connection mode, and the fixing effect of the metal material part is better.
The low-density modified polysulfide sealant has long service life and light weight, and is suitable for filling and sealing after the aircraft fuel tank 2 is assembled.
The utility model improves the condition that the existing airplane integral wing oil tank has a large number of dead oil areas by filling PMI foam 1 in the dead oil areas of the airplane oil tank 2, avoids the influence of a large number of dead oil on the fuel utilization rate of the airplane oil tank 2 and increases the airplane weight; and because the shape of the dead oil area of the oil tank is complex, the sealant is difficult to fill in place in the sealing process, and the oil leakage event of the oil tank is very easy to cause, and the PMI foam 1 is adopted to fill the dead oil area of the oil tank, so that the PMI foam 1 can be used as a part for sealing the aircraft oil tank 2, the aircraft oil tank 2 can be better sealed in the dead oil area, and the oil leakage is reduced.
The specific implementation process comprises the following steps: before filling the dead oil area of the airplane, filling the oil tank of the integral wing of the airplane with airplane fuel oil, and then discharging the airplane fuel oil until the fuel oil can not be discharged, wherein the area with the airplane fuel oil in the oil tank of the integral wing of the airplane is the dead oil area; if the airplane is already put into use, after the fuel in the dead fuel area is used up, the fuel in the whole wing fuel tank of the airplane is detected, and the dead fuel area in the whole wing fuel tank of the airplane can be known. And then according to the shape and the size of the dead oil area, cutting out PMI foam 1 with different shapes, then filling the PMI foam 1 with the corresponding shape and size into the dead oil area, and fixing the PMI foam 1 by one of sealing glue and/or rivets, bolts and screws.
Example 2
The embodiment is improved on the basis of embodiment 1, and the improvement is as follows: as shown in fig. 4, the tank structure is further provided with a corner piece 3 for connecting the PMI foam 1 and the aircraft tank 2, so that the connection of the PMI foam 1 and the aircraft tank 2 is more stable.
As shown in fig. 2, the corner piece 3 is mechanically connected with the metal material part 22; as shown in fig. 3, the corner pieces 3 are bonded to the composite material portion 21 by using a sealant; the corner pieces 3 are bonded with the PMI foam 1 through a sealant. The fillet 3 and the metal material part 22 and the composite material part 21 are respectively connected in different manners, and the principle of the fillet is basically the same as that of the PMI foam 1 and the metal material part 22 and the composite material part 21 in different manners, so that the details are not repeated.
Preferably, as shown in fig. 4, when both sides of a wall plate made of a certain metal material in the tank structure need to be filled with PMI foam 1, a bolt penetrating through the wall plate can be used to fix the corner piece 3, so that the PMI foam 1 on both sides of the wall plate can be connected into a whole, and the fixing effect is better.
Other parts in this embodiment are substantially the same as those in embodiment 1, and thus are not described in detail.
The above is only the preferred embodiment of the present invention, not to the limitation of the present invention in any form, all the technical matters of the present invention all fall into the protection scope of the present invention to any simple modification and equivalent change of the above embodiments.
Claims (7)
1. A fuel tank structure for reducing dead fuel in an integral fuel tank of an airplane comprises an airplane fuel tank (2); the method is characterized in that: also comprises PMI foam (1) filled in dead oil areas of the aircraft fuel tank (2).
2. A tank construction for reducing dead oil in an aircraft fuel tank as claimed in claim 1, wherein: the aircraft fuel tank (2) comprises a composite material part (21) made of a composite material and a metal material part (22) made of a metal material; the PMI foam (1) is bonded with the composite material part (21) by adopting a sealant; the PMI foam (1) is mechanically connected to a metal material part (22).
3. A tank construction for reducing dead oil in an aircraft fuel tank as claimed in claim 2, wherein: the PMI foam (1) is connected to the metal material part (22) by means of screws, bolts or rivets.
4. A tank construction for reducing dead oil in an aircraft fuel tank as claimed in claim 1, wherein: the adjacent PMI foams (1) are bonded through a sealing adhesive.
5. A fuel tank structure for reducing dead fuel in an integral fuel tank of an aircraft according to any one of claims 2 to 4, wherein: also provided are corner pieces (3), wherein the corner pieces (3) are used for connecting the PMI foam (1) and the aircraft fuel tank (2).
6. A tank structure for reducing dead oil in an aircraft integral tank as claimed in claim 5, wherein: the angle sheet (3) is mechanically connected with the metal material part (22); the corner pieces (3) and the composite material part (21) are bonded by adopting a sealant; the corner pieces (3) are bonded with the PMI foam (1) by adopting a sealant.
7. The fuel tank structure for reducing dead fuel in an integral fuel tank of an airplane as claimed in any one of claims 2 to 4 and 6, wherein: the sealant is a low-density modified polysulfide sealant.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020219252.4U CN212047911U (en) | 2020-02-27 | 2020-02-27 | Oil tank structure for reducing dead oil in integral oil tank of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020219252.4U CN212047911U (en) | 2020-02-27 | 2020-02-27 | Oil tank structure for reducing dead oil in integral oil tank of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212047911U true CN212047911U (en) | 2020-12-01 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020219252.4U Active CN212047911U (en) | 2020-02-27 | 2020-02-27 | Oil tank structure for reducing dead oil in integral oil tank of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212047911U (en) |
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2020
- 2020-02-27 CN CN202020219252.4U patent/CN212047911U/en active Active
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