A contoured tank for an aircraft and an aircraft

Abstract

The application discloses a special-shaped oil tank for an aircraft and the aircraft, relates to the technical field of aircraft part manufacturing, and comprises an oil tank shell, which comprises a first cavity section and a second cavity section; the shapes of the first cavity section and the second cavity section are both similar to a cylinder; the cross-sectional area of the second cavity section is larger than that of the first cavity section; the second cavity section extends out of the first cavity section along a radial direction; a partition plate is arranged in the second cavity section and is smoothly connected with the end of the first cavity section; the partition plate divides the second cavity section into an oil storage cavity and a bearing cavity; the oil storage cavity is communicated with the first cavity section and is used for storing and providing fuel for the aircraft; and the bearing cavity is used for bearing single-machine equipment of the aircraft. Since the bearing cavity, the oil storage cavity and the first cavity section are arranged in an integrated mode, a connecting structure is not needed to connect the bearing cavity, the oil storage cavity and the first cavity section, the space occupied by the connecting structure is reduced, and thus the oil storage capacity of the oil storage cavity and the first cavity section in the oil tank shell can be improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft part manufacturing, in particular to a special-shaped oil tank for an aircraft and the aircraft. BACKGROUND

[0002] During the flight of an air-breathing hypersonic aircraft, an oil tank for storing fuel is needed to provide a power source for the aircraft. Therefore, when designing the structure of the aircraft, space needs to be reserved for placing the fuel storage tank and the oil tank.

[0003] The oiling capacity of the oil tank directly determines the range of the air-breathing hypersonic aircraft. In the prior art, most oil tanks are regular oil tanks, which are suitable for different types of aircraft.

[0004] However, the installation of regular oil tanks is affected by the shape of the aircraft, which may result in the fact that part of the space is not utilized, and additional cabin section bearing structures need to be installed, which is complex in structure and reduces the utilization rate of space, the oiling capacity, and thus the range of the aircraft. SUMMARY

[0005] In view of the defects in the prior art, the present application provides a special-shaped oil tank for an aircraft and the aircraft, which can solve the problem that the installation of regular oil tanks in the prior art is affected by the shape of the aircraft, which may result in the fact that part of the space is not utilized, and additional cabin section bearing structures need to be installed, which is complex in structure and reduces the utilization rate of space, the oiling capacity, and thus the range of the aircraft.

[0006] To achieve the above-mentioned purposes, the technical scheme adopted by the present application is as follows:

[0007] On the one hand, the present application provides a special-shaped oil tank for an aircraft, which comprises:

[0008] An oil tank shell comprising a first cavity section and a second cavity section, the shapes of the first cavity section and the second cavity section are both cylindrical, the cross-sectional area of the second cavity section is greater than that of the first cavity section, the second cavity section extends radially out of the first cavity section, a partition plate is arranged in the second cavity section, the partition plate is smoothly connected with the end of the first cavity section, the partition plate divides the second cavity section into an oil storage cavity and a bearing cavity, the oil storage cavity is in communication with the first cavity section and is used for storing and providing fuel to the aircraft, and the bearing cavity is used for bearing single-machine equipment of the aircraft.

[0009] On the basis of the above technical scheme,

[0010] In some optional schemes, an additional cavity section is further included, which is arranged below the first cavity section and in communication with the first cavity section, and the shape of the additional cavity section is matched with the shape of the aircraft structure.

[0011] In some alternatives, the first cavity section and the oil storage cavity each comprise an oil cavity skin and an oil cavity grid rib, the oil cavity skin is attached to the oil cavity grid rib, the additional cavity section comprises an additional skin and an additional grid rib, the additional grid rib has a smaller distance between adjacent longitudinal ribs than the oil cavity grid rib, and the distance between adjacent longitudinal ribs decreases as the load distribution increases.

[0012] In some alternatives, the upper side of the first cavity section and the oil storage cavity is provided with a heat protection layer, the heat protection layer is used for heat protection of the oil storage cavity.

[0013] In some alternatives, the oil storage cavity is provided with a filling port, the filling port is used for filling fuel into the oil storage cavity.

[0014] In some alternatives, the oil storage cavity is provided with a vent, the vent is used for communication with the external environment.

[0015] In some alternatives, the oil storage cavity is provided with a pressure sensor, the pressure sensor is used for detecting the oil pressure in the oil storage cavity.

[0016] In some alternatives, the oil tank shell is a carbon fiber reinforced cyanate ester composite material part.

[0017] In some alternatives, the first cavity section is provided with an opening at the end away from the oil storage cavity, and the opening is provided with a sealing cover plate.

[0018] In another aspect, the application also provides a flying vehicle comprising the above-mentioned special-shaped oil tank for a flying vehicle.

[0019] Compared with the prior art, the application has the following advantages:

[0020] In use of the irregular fuel tank for aircraft, the tank shell is divided into a first cavity section and a second cavity section, the shapes of the first cavity section and the second cavity section are both similar to cylinders, and the cross-sectional area of the second cavity section is larger than that of the first cavity section, the second cavity section is divided into an oil storage cavity and a bearing cavity by a partition plate, and the oil storage cavity is in communication with the first cavity section and used for storing and providing fuel for the aircraft, and the bearing cavity is used for bearing the single machine equipment of the aircraft. Since the second cavity section is divided into the oil storage cavity and the bearing cavity by the partition plate, and the oil storage cavity is in communication with the first cavity section, the bearing cavity, the oil storage cavity and the first cavity section are arranged integrally, no additional connecting structure is needed to connect the bearing cavity, the oil storage cavity and the first cavity section, the space occupied by the connecting structure is reduced, and then the oil storage capacity of the oil storage cavity and the first cavity section in the tank shell can be improved, the oil storage capacity of the irregular fuel tank for aircraft is improved, the space utilization rate is improved, and the problems that the regular fuel tank in the prior art is affected by the shape of the aircraft during installation, part of the space is not used, and an additional cabin bearing structure needs to be installed, the structure is complex, the space utilization rate is reduced, the oil storage capacity is reduced, and the flight range of the aircraft is affected are solved. BRIEF DESCRIPTION OF DRAWINGS

[0021] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed to be used in the embodiment description will be briefly introduced. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor.

[0022] Figure 1 It is a cross-sectional structure schematic diagram of an embodiment of the irregular fuel tank for aircraft of the present application.

[0023] Figure 2 It is a front view structure schematic diagram of an embodiment of the irregular fuel tank for aircraft of the present application.

[0024] Figure 3 It is a structure schematic diagram of an embodiment of the irregular fuel tank for aircraft of the present application.

[0025] Figure 4 It is a side view structure schematic diagram of an embodiment of the irregular fuel tank for aircraft of the present application.

[0026] Figure 5 It is a side view structure schematic diagram of an embodiment of the irregular fuel tank for aircraft of the present application.

[0027] Figure 6 It is a side view structure schematic diagram of an embodiment of the irregular fuel tank for aircraft of the present application.

[0028] Figure 7This is a side view of the oil storage cavity in an embodiment of an irregularly shaped fuel tank for an aircraft according to the present invention;

[0029] Figure 8 This is a side view of the first cavity section in an embodiment of an irregularly shaped fuel tank for an aircraft according to the present invention.

[0030] In the diagram: 1. Oil storage cavity; 11. Oil cavity skin; 12. Oil cavity mesh reinforcement; 2. Bearing cavity; 21. Shell skin; 22. Shell mesh reinforcement; 3. Additional cavity section; 4. Heat insulation layer; 5. Filling port; 6. Vent port; 7. Pressure sensor; 8. Sealing cover plate; 9. Divider plate; 10. Oil tank shell; 101. First cavity section; 102. Second cavity section. Detailed Implementation

[0031] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0032] The following describes in further detail an embodiment of the present invention, including a non-standard fuel tank for an aircraft and the aircraft, with reference to the accompanying drawings.

[0033] like Figures 1-8 As shown, in one aspect, this application provides an irregularly shaped fuel tank for an aircraft, comprising:

[0034] The fuel tank outer shell 10 includes a first cavity 101 and a second cavity 102. Both the first cavity 101 and the second cavity 102 are cylindrical in shape, and the cross-sectional area of ​​the second cavity 102 is larger than that of the first cavity 101. The second cavity 102 extends radially out of the first cavity 101. A partition plate 9 is provided in the second cavity 102, and the partition plate 9 is smoothly connected to the end of the first cavity 101. The partition plate 9 divides the second cavity 102 into a fuel storage cavity 1 and a bearing cavity 2. The fuel storage cavity 1 is connected to the first cavity 101 and is used to store and supply fuel to the aircraft. The bearing cavity 2 is used to carry the aircraft's single-unit equipment.

[0035] In use of the irregular fuel tank for aircraft, the tank shell 10 is divided into a first cavity section 101 and a second cavity section 102, the shapes of the first cavity section 101 and the second cavity section 102 are both similar to cylinder, and the cross-sectional area of the second cavity section 102 is larger than that of the first cavity section 101, the second cavity section 102 is divided into an oil storage cavity 1 and a carrying cavity 2 by a partition plate 9, and the oil storage cavity 1 is in communication with the first cavity section 101, used for storing and providing fuel for the aircraft, and the carrying cavity 2 is used for carrying single machine equipment of the aircraft. Since the second cavity section 102 is divided into the oil storage cavity 1 and the carrying cavity 2 by the partition plate 9, and the oil storage cavity 1 is in communication with the first cavity section 101, the carrying cavity 2, the oil storage cavity 1 and the first cavity section 101 are arranged integrally, without using additional connecting structure to connect the carrying cavity 2, the oil storage cavity 1 and the first cavity section 101, the space occupied by the connecting structure is reduced, thereby the oil storage capacity of the oil storage cavity 1 and the first cavity section 101 in the tank shell 10 can be improved, the oil storage capacity of the irregular fuel tank for aircraft is improved, the space utilization rate is improved, and the problems of the prior art that the regular fuel tank is affected by the shape of the aircraft during installation, part of the space is not used, and additional cabin section carrying structure needs to be installed, the structure is complex, the space utilization rate is reduced, the oil storage capacity is reduced, and the flight range of the aircraft is affected are solved.

[0036] In the example, the partition plate 9 is an arc-shaped plate protruding in opposite directions to the second cavity section 102, so that the cross section of the oil storage cavity 1 is in the shape of a crescent. Part of the cavity wall of the carrying cavity 2 includes a shell skin 21 and a shell grid rib 22, the shell skin 21 is attached to the shell grid rib 22, the thickness of the shell skin 21 is 3-5mm, preferably 4mm, and the width of the shell grid rib 22 is 10mm and the height is 7mm.

[0037] As shown in Figure 1 and Figure 2 In some optional embodiments, an additional cavity section 3 is further included, the additional cavity section 3 is arranged below the first cavity section 101 and in communication with the first cavity section 101, and the shape of the additional cavity section 3 matches the shape of the aircraft structure.

[0038] In the example, the irregular fuel tank for aircraft further includes an additional cavity section 3, the additional cavity section 3 is arranged below the first cavity section 101 and in communication with the first cavity section 101, and the shape of the additional cavity section 3 matches the shape of the aircraft structure, further improving the oil storage capacity of the irregular fuel tank for aircraft, improving the oil storage capacity of the irregular fuel tank for aircraft, and improving the space utilization rate.

[0039] As shown in Figure 1 and Figure 2As shown, in some optional embodiments, both the first cavity segment 101 and the oil storage cavity 1 include an oil cavity skin 11 and an oil cavity mesh reinforcement 12. The oil cavity skin 11 is attached to the oil cavity mesh reinforcement 12. The additional cavity segment 3 includes an additional skin and an additional mesh reinforcement. The spacing between adjacent longitudinal reinforcements in the additional mesh reinforcement is smaller than the spacing between adjacent longitudinal reinforcements in the oil cavity mesh reinforcement 12, and the spacing between adjacent longitudinal reinforcements decreases as the load distribution increases.

[0040] In this embodiment, both the first cavity segment 101 and the oil storage cavity 1 include an oil cavity skin 11 and an oil cavity mesh rib 12. The oil cavity skin 11 is attached to the oil cavity mesh rib 12 to form the cavity wall. The additional cavity segment 3 includes an additional skin and an additional mesh rib. The additional skin is attached to the additional mesh rib to form the cavity wall of the additional cavity segment 3. The spacing between adjacent longitudinal ribs in the additional mesh rib is smaller than the spacing between adjacent longitudinal ribs in the oil cavity mesh rib 12, and the spacing between adjacent longitudinal ribs decreases as the load distribution increases, thereby enhancing the load-bearing capacity of the irregularly shaped fuel tank used in the aircraft and making the structure more stable.

[0041] In this example, the thickness of the oil cavity skin 11 is 3-10 mm, preferably 4 mm. The oil cavity mesh ribs 12 are arranged in a "well" shape, with a width of 10-50 mm, preferably 20 mm, and a height of 5-15 mm, preferably 10 mm. The width of the shell mesh ribs 22 is 1 / 3-1 / 2 of the width of the oil cavity mesh ribs 12, and the height of the shell mesh ribs 22 is 1 / 2-2 / 3 of the height of the oil cavity mesh ribs 12.

[0042] like Figure 1 and Figure 2 As shown, in some optional embodiments, a heat-insulating layer 4 is provided on the upper side of the first cavity 101 and the oil storage cavity 1, and the heat-insulating layer 4 is used for thermal protection of the oil storage cavity 1.

[0043] In this embodiment, a heat-insulating layer 4 is provided on the upper side of the first cavity 101 and the oil storage cavity 1. The heat-insulating layer 4 is used for thermal protection of the oil storage cavity 1 to prevent the irregularly shaped fuel tank used for the aircraft from overheating and affecting the safety of the aircraft.

[0044] In this example, heat-insulating layer 4 is a quartz fiber reinforced phenolic resin matrix composite material. The molding process for heat-insulating layer 4 is compression molding and RTM (Regenerative Thermal Mold) process.

[0045] like Figures 1-3 As shown, in some optional embodiments, the oil storage chamber 1 is provided with a filling port 5, which is used to fill fuel into the oil storage chamber 1.

[0046] In this embodiment, a filling port 5 is provided on the oil storage cavity 1. The filling port 5 is used to add fuel into the oil storage cavity 1, which facilitates the addition of fuel to the irregularly shaped fuel tank of the aircraft and makes it convenient for personnel to operate.

[0047] likeFigures 1-3 As shown, in some optional embodiments, the oil storage cavity 1 is provided with a vent 6, which is used to communicate with the external environment.

[0048] In this embodiment, a vent 6 is provided on the oil storage chamber 1. The vent 6 is used to communicate with the external environment, balance the pressure difference between the oil storage chamber 1 and the first chamber section 101 and the external environment, so that fuel can be supplied normally.

[0049] like Figure 1 As shown, in some optional embodiments, a pressure sensor 7 is provided on the oil storage cavity 1, and the pressure sensor 7 is used to detect the oil pressure in the oil storage cavity 1.

[0050] In this embodiment, a pressure sensor 7 is provided on the oil storage cavity 1. The pressure sensor 7 is used to detect the oil pressure in the oil storage cavity 1, which facilitates pressure detection of the oil storage cavity 1 and the first cavity section 101, and can improve the safety of the irregularly shaped fuel tank used in the aircraft.

[0051] In some alternative embodiments, the fuel tank housing 10 is made of carbon fiber reinforced cyanate ester composite material.

[0052] In this embodiment, the fuel tank outer shell 10 is made of carbon fiber reinforced cyanate ester composite material, which reduces the weight of the irregular fuel tank used in the aircraft. The weight of the fuel tank using carbon fiber reinforced cyanate ester composite material is 1 / 3 to 1 / 2 of that of the metal fuel tank.

[0053] like Figure 1 As shown, in some optional embodiments, the first cavity 101 has an opening at the end away from the oil storage cavity 1, and a sealing cover plate 8 is provided on the opening.

[0054] In this embodiment, an opening is provided at the end of the first cavity 101 away from the oil storage cavity 1, and a sealing cover plate 8 is provided on the opening. When the irregular fuel tank for aircraft is used normally, the sealing cover plate 8 is placed on the opening. When it is necessary to use the fuel bladder for refueling, the sealing cover plate 8 can be removed and fuel can be added into the first cavity 101 through the opening.

[0055] In this example, the sealing cover plate 8 is a convex plate. Both the sealing cover plate 8 and the first cavity section 101 are provided with an axial sealing groove to cooperate in sealing the first cavity section 101. The sealing cover plate 8 and the first cavity section 101 are sealed with two axial sealing rings.

[0056] The sealing cover plate 8 is made of structural steel, titanium alloy, aluminum alloy, magnesium alloy and carbon fiber reinforced resin matrix composite material.

[0057] like Figures 1-8 As shown, on the other hand, this application also provides an aircraft that includes the aforementioned irregular fuel tank for an aircraft.

[0058] In use of the irregular fuel tank for aircraft, the tank shell 10 is divided into a first cavity section 101 and a second cavity section 102, the first cavity section 101 and the second cavity section 102 are both in the shape of a cylinder, and the cross-sectional area of the second cavity section 102 is larger than that of the first cavity section 101, the second cavity section 102 is divided into an oil storage cavity 1 and a bearing cavity 2 by a partition plate 9, and the oil storage cavity 1 is in communication with the first cavity section 101, used for storing and providing fuel for the aircraft, and the bearing cavity 2 is used for bearing the single machine equipment of the aircraft. Since the second cavity section 102 is divided into the oil storage cavity 1 and the bearing cavity 2 by the partition plate 9, and the oil storage cavity 1 is in communication with the first cavity section 101, the bearing cavity 2, the oil storage cavity 1 and the first cavity section 101 are arranged integrally, without using additional connecting structure to connect the bearing cavity 2, the oil storage cavity 1 and the first cavity section 101, the space occupied by the connecting structure is reduced, thereby the oil storage capacity of the oil storage cavity 1 and the first cavity section 101 in the tank shell 10 can be improved, thereby the oil storage capacity of the irregular fuel tank for aircraft is improved, the space utilization rate is improved, and the problem that the regular fuel tank in the prior art is affected by the shape of the aircraft during installation, which may cause part of the space not to be utilized, and additional cabin bearing structure needs to be installed, the structure is complex, the space utilization rate is reduced, the oil storage capacity is reduced, and the flight range of the aircraft is affected is solved.

[0059] In the description of the present application, it should be noted that the positions or position relationships indicated by the terms "upper", "lower", etc. are based on the positions or position relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular position, be constructed and operated in a particular position, and therefore cannot be understood as a limitation on the present application. Unless otherwise specified and limited, the terms "mounting", "connection", "connection" should be understood broadly, for example, it can be fixed connection, or detachable connection, or integral connection; it can be mechanical connection, or electrical connection; it can be direct connection, or indirect connection through an intermediate medium, or internal communication of two elements. For those skilled in the art, the specific meanings of the above terms in the present application can be understood according to the specific circumstances.

[0060] It should be noted that, in the present application, the relational terms such as "first" and "second", and the like, are used solely to distinguish one entity or action from another, without necessarily requiring or implying any actual relationship or order between such entities or actions. Moreover, the terms "comprises", "comprising", or any other variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but can also include other elements not expressly listed or inherent to such process, method, article, or apparatus. An element proceeded by "comprises... a" does not, without more constraints, exclude the existence of additional identical elements in the process, method, article, or apparatus that comprises the element.

[0061] The foregoing is considered as illustrative only of the principles of the application. Numerous modifications and changes will readily occur to those skilled in the art, and the generic principles defined herein can be applied to other embodiments without departing from the spirit or scope of the application. Therefore, the application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A contoured tank for an aircraft, characterized in that, The application relates to an aircraft fuel tank, which comprises: a tank shell (10) comprising a first cavity section (101) and a second cavity section (102), the first cavity section (101) and the second cavity section (102) are both in the shape of a cylinder, the cross-sectional area of the second cavity section (102) is larger than that of the first cavity section (101), the axial length of the second cavity section (102) is smaller than that of the first cavity section (101), the second cavity section (102) extends radially from the first cavity section (101), a partition plate (9) is arranged in the second cavity section (102), the partition plate (9) is connected to the end of the first cavity section (101) in a smooth manner, the partition plate (9) divides the second cavity section (102) into an oil storage cavity (1) and a bearing cavity (2), the oil storage cavity (1) is communicated with the first cavity section (101) and is used for storing and providing fuel for an aircraft, and the bearing cavity (2) is used for bearing single-machine equipment of the aircraft; an additional cavity section (3) is further arranged below the first cavity section (101) and is communicated with the first cavity section (101), and the shape of the additional cavity section (3) is matched with the structure shape of the aircraft.

2. A contoured tank for an aircraft as defined in claim 1, wherein, The first cavity section (101) and the oil storage cavity (1) both comprise an oil cavity skin (11) and an oil cavity grid rib (12), the oil cavity skin (11) is attached to the oil cavity grid rib (12), the additional cavity section (3) comprises an additional skin and an additional grid rib, the distance between adjacent longitudinal ribs in the additional grid rib is smaller than that in the oil cavity grid rib (12), and the distance between adjacent longitudinal ribs is reduced with the increase of load distribution.

3. A contoured tank for an aircraft as defined in claim 1, wherein, The upper side of the first cavity section (101) and the oil storage cavity (1) is provided with a heat protection layer (4), and the heat protection layer (4) is used for heat protection of the oil storage cavity (1).

4. A contoured tank for an aircraft as defined in claim 1, wherein, The oil storage cavity (1) is provided with a filling port (5), and the filling port (5) is used for filling fuel into the oil storage cavity (1).

5. A contoured tank for an aircraft as defined in claim 1, wherein, The oil storage cavity (1) is provided with a vent (6), and the vent (6) is used for communication with the external environment.

6. A contoured tank for an aircraft as defined in claim 1, wherein, The oil storage cavity (1) is provided with a pressure sensor (7), and the pressure sensor (7) is used for detecting the oil pressure in the oil storage cavity (1).

7. A contoured tank for an aircraft as defined in claim 1, wherein, The tank shell (10) is made of carbon fiber reinforced cyanate ester composite material.

8. A contoured tank for an aircraft as defined in claim 1, wherein, An opening is arranged at the end of the first cavity section (101) away from the oil storage cavity (1), and a sealing cover plate (8) is arranged on the opening.

9. An aircraft, characterized in that The application further relates to a special-shaped fuel tank for an aircraft, which comprises any one of the aircraft fuel tanks according to claims 1-8.

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