Aircraft tank arrangement for increasing flight distance and wing area of aircraft, and aircraft

Abstract

The invention provides an aircraft tank device for increasing the flight distance and wing area of an aircraft and the aircraft. The aircraft canister arrangement (200) comprises a fairing (201) formed and configured to: at least partially cover an aircraft wing-aircraft fuselage interface (202); storing fuel; and a lift function is provided. An aircraft (100) comprises such an aircraft tank arrangement (200).

Description

Technical Field

[0001] The present invention relates to an aircraft tank device for increasing the flight distance and wing area of ​​an aircraft. The present invention also relates to an aircraft comprising such an aircraft tank device. Background Art

[0002] In addition to the fuel that is normally required and housed in the aircraft, it is often necessary, especially on long-distance flights, to carry an additional supply of fuel. This additional fuel is usually contained in additional tanks on the outside of the aircraft or, more particularly, such additional tanks may be attached to the lower surface of a wing section for convenience and aerodynamic reasons. These tanks may be released or lowered to reduce the load and drag coefficient on the aircraft or may be released or lowered for safety reasons.

[0003] The fuel of an aircraft is usually placed in the fuselage, main wing, etc., in which a fuel tank is placed, but the capacity of the fuel tank is limited. In the case where more fuel is needed, an additional tank can be placed on the outside of the aircraft. In the conventional method, the additional tank is fixed in the outer shape and attached to the aircraft at the main wing tip, under the main wing or under the fuselage. Conventionally, even if there is no fuel in the additional tank, an additional tank with the same outer shape as the outer shape in the case of full fuel in the additional tank is attached, and the surface area of ​​the tank is large, thereby increasing the drag of the aircraft.

[0004] Those known additional tanks that are placed outside the aircraft have the problem of possibly degrading the flight performance of the aircraft. Summary of the invention

[0005] According to the invention, this problem is solved in each case by the aircraft tank arrangement and the aircraft provided by the present application.

[0006] According to a first aspect of the present invention, there is provided an aircraft tank device for increasing the flight distance and wing area of ​​an aircraft. The aircraft tank device comprises a fairing, the fairing being formed and configured as:

[0007] at least partially covering an aircraft wing-aircraft fuselage interface;

[0008] Storing fuel; and

[0009] Provides lift function.

[0010] In particular, an aircraft tank apparatus is provided for increasing the flight range and wing area of ​​a passenger aircraft or a cargo aircraft.

[0011] According to a second aspect of the present invention, there is provided an aircraft, in particular a passenger aircraft or a cargo aircraft, comprising an aircraft tank arrangement according to the first aspect of the present invention.

[0012] The basic idea of ​​the invention is to provide an additional fuel tank device for a fuel tank device in an aircraft wing, wherein the additional fuel tank device can be equipped as an additional device on existing aircraft and can also be equipped on future aircraft. The main function of the fairing is to provide a smooth profile and reduce drag. The fairing can be used as a cover for gaps and spaces between aircraft parts to reduce form drag and interference drag and improve the appearance. In addition, the aircraft tank device can store about 20m 3 Up to 60m 3 , preferably about 40m 3 In particular, the fairing is formed to increase the wing area to provide a lift function.

[0013] A particular advantage of the solution according to aspects of the invention is that the aircraft tank arrangement provides a greater fuel storage capacity without the need to redesign the wings and without using cargo capacity, for example, a so-called additional center tank can be provided. As a result, less fuel can be stored in the fuselage. Furthermore, fuels with higher volume requirements, such as hydrogen, can be stored in the aircraft, wherein the increased tank volume is arranged outside the standard fuselage.

[0014] Another advantage is that in the case of a water landing, the impact and swimming behavior of the aircraft can be optimized by the aircraft tank device according to the invention. In addition, the flight distance can be extended and the lift of the aircraft can be increased. By increasing the wing area, the additional weight of the aircraft tank device can be compensated. Therefore, the aircraft tank device includes a lifting body design, which also provides a water landing function.

[0015] Furthermore, the aircraft tank device is advantageously positioned substantially at the center of mass of the aircraft.In particular, the invention does not interfere with the function of the landing gear.

[0016] Advantageous embodiments and further developments emerge from the description with reference to the drawings.

[0017] According to some aspects of the invention, the fairing can be connected to an aircraft fuselage and / or an aircraft wing. The aircraft tank device can be equipped as an additional device on an existing aircraft, in particular an existing aircraft fuselage and / or an existing aircraft wing, and can also be equipped on future aircraft. The aircraft tank device can be configured as a module inserted into a standard aircraft fuselage. The fairing can store liquid and / or gaseous fuel, such as kerosene. Therefore, flexibility between long-distance flights and short-distance flights can be provided.

[0018] According to some further aspects of the invention, the fairing is configured as a belly fairing. The belly fairing, also called the ventral fairing, is located on the underside of the aircraft fuselage and between the main aircraft wings. The belly fairing may also cover a cargo storage compartment.

[0019] According to some further aspects of the invention, the fairing is configured to be replaceable so that the size and / or form of the fairing can be selected according to the flight distance. Thus, a smaller aircraft tank device can be installed on the aircraft for short-distance flights. A larger aircraft tank device can be installed on the aircraft for long-distance flights. The replaceable fairing provides a flexible module that can be selected according to the specific needs of each flight.

[0020] According to some further aspects of the invention, the aircraft tank arrangement further comprises a pressure vessel at least partially surrounded by the fairing, wherein the pressure vessel is configured to contain a cryogenic medium. For example, the pressure vessel may be configured as a cryogenic tank. The pressure vessel may contain liquid hydrogen.

[0021] According to some other aspects of the present invention, the aircraft tank device also includes a pilot valve, an exhaust pressure valve and an exhaust box positioned inside the fairing. The pilot valve is a small valve that controls a flow-limited control feed to a separate pilot valve. Typically, the separate valve controls a high pressure or high flow feed. The pilot valve is useful because they allow a small amount of easily operated feed to control a higher pressure or higher flow feed that would otherwise require greater force to operate. The exhaust pressure valve allows the discharge of overpressure or vacuum generated in the atmospheric tank during filling and emptying, or allows pressure changes due to changes in temperature, atmospheric pressure, or due to temperature changes of the fluid or tank, such as heating, heat tracing, or heat exchanger failure.

[0022] According to some further aspects of the invention, the aircraft tank device further comprises a plurality of hinges for attaching the fairing to the aircraft fuselage and / or the aircraft wing. The positions of the hinges may correspond to the positions of similar hinges of a conventional fairing, so that the aircraft tank device may be used and interchanged with other modules of the aircraft.

[0023] According to some further aspects of the invention, the stored fuel is distributed within the fairing so that the center of mass of the aircraft tank arrangement substantially corresponds to the center of mass of the aircraft.

[0024] According to some further aspects of the invention, the aircraft tank device further comprises fuel and air quick disconnect elements. Therefore, the aircraft tank device can be installed and removed more quickly and easily. In addition, during installation / removal and handling, unused fuel remaining in the aircraft tank device can be safely retained in the aircraft tank device.

[0025] According to some further aspects of the invention, the aircraft further comprises an aircraft fuselage and an aircraft wing, wherein the aircraft tank arrangement is configured as a conformal fuel tank mounted to an outer skin of the aircraft fuselage and an outer skin of the aircraft wing.

[0026] According to some further aspects of the invention, an aircraft tank arrangement is fluidly connected to a standard fuel supply and delivery line. For example, the aircraft is a multi-engine passenger aircraft or a multi-engine cargo aircraft. The fuel system of such an aircraft may include a plurality of fuel tanks, which may be located in the wings, the fuselage, or both. Each fuel tank may be equipped with an internal fuel pump and have associated valves and piping to feed the engine, allow fuel supply and fuel discharge, isolate the various tanks, and in some applications allow fuel dumping or optimize the center of gravity of the aircraft. The standard fuel supply and delivery line fluidly connects the plurality of tanks, the aircraft tank arrangement, and the engines of the aircraft.

[0027] According to some further aspects of the invention, the fairing covers at least the upper side of the aircraft wing-aircraft fuselage interface. Furthermore, the fairing may partially cover the lower side of the aircraft wing-aircraft fuselage interface, in particular partially covering the lower side of the aircraft wing-aircraft fuselage interface at a front section and / or a rear section of the aircraft wing-aircraft fuselage interface.

[0028] Optionally, the outer skin of the aircraft tank device may have an area for attaching advertising. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] The invention is explained in more detail below based on an exemplary embodiment shown in a schematic diagram, in which:

[0030] Figure 1 A schematic diagram showing an aircraft tank device for increasing the flight distance and wing area of ​​an aircraft according to an embodiment of the present invention is shown;

[0031] Figure 2 A top view of a conventional aircraft known in the prior art is shown;

[0032] Figure 3 Shown according to Figure 2 A front view of a conventional aircraft;

[0033] Figure 4 shows a schematic top view of an aircraft according to an embodiment of the invention, the aircraft comprising an aircraft tank device according to another embodiment of the invention;

[0034] Figure 5 Shown according to Figure 4 A front view of an aircraft;

[0035] Figure 6 shows a schematic cross-sectional view of an aircraft according to another embodiment of the invention, the aircraft comprising an aircraft tank device according to another embodiment of the invention;

[0036] Figure 7 shows a schematic cross-sectional view of an aircraft according to another embodiment of the invention, the aircraft comprising an aircraft tank arrangement with a pressure vessel according to another embodiment of the invention; and

[0037] Figure 8 A schematic perspective view of an aircraft with a lowered landing gear according to another embodiment of the invention is shown, the aircraft comprising an aircraft tank device according to another embodiment of the invention. DETAILED DESCRIPTION

[0038] The accompanying drawings are intended to convey a further understanding of embodiments of the present invention. They illustrate embodiments and are used in conjunction with the description to explain the principles and concepts of the present invention. Other embodiments and many of the advantages described are apparent in the accompanying drawings. The elements in the accompanying drawings are not necessarily drawn to scale relative to each other. For example, terms indicating directions, such as "at the top," "at the bottom," "at the left," "at the right," "above," "below," "horizontally," "vertically," "in front of," "behind," and similar statements are only used for explanation purposes and are not intended to limit generality to the specific configurations shown in the figures.

[0039] In the drawings, identical elements, features and components having the same function and having the same effect are provided with the same reference signs, unless explained otherwise.

[0040] Figure 1 A schematic diagram of an aircraft tank device 200 for increasing the flight distance and wing area of ​​an aircraft according to an embodiment of the present invention is shown.

[0041] The aircraft tank device 200 includes a fairing 201 formed and configured to at least partially cover an aircraft wing-aircraft fuselage interface 202 and store fuel. The fairing 201 can store about 30m 3 About 50m 3 , especially about 40m 3 of fuel.

[0042] In addition, the fairing 201 is formed and configured to provide a lift function. The lift function can be provided by an increased wing area. The fairing 201 can be connected to the aircraft fuselage 101 and the aircraft wing 102. Therefore, the fairing 201 can include an optimized aerodynamic form. The aircraft tank device 200 also includes at least two hinges 207, and the at least two hinges 207 are used to attach the fairing 201 to the aircraft wing 102. The aircraft tank device 200 can also include a plurality of hinges 207, and the plurality of hinges 207 are used to attach the fairing 201 to the aircraft fuselage 101. The position of the hinge 207 can correspond to the position of a similar hinge of a conventional fairing, so that the aircraft tank device 200 can be used and interchanged with other modules of the aircraft.

[0043] Figure 2 and Figure 3 Shown in top view ( Figure 2 ) and the front view ( Figure 3 ) shows a conventional aircraft 10 known in the prior art. The aircraft 10 is configured as a passenger aircraft or a cargo aircraft.

[0044] The conventional aircraft 10 includes an aircraft fuselage 101, two aircraft wings 102, and a rudder / elevator at the rear end of the aircraft fuselage 101. The section where the two aircraft wings 102 are connected to the aircraft fuselage 101 is called an aircraft wing-aircraft fuselage interface 202. The aircraft wing-aircraft fuselage interface 202 can be embodied as an upper side portion 202a, a front section 202b, and a rear section 202c.

[0045] The fairing for the aircraft wing-aircraft fuselage interface 202 of the conventional aircraft 10 substantially covers the mechanical connection between the aircraft fuselage 101 and the aircraft wing 102. Therefore, the fairing is relatively small and kept to a minimum size.

[0046] Figure 4 and Figure 5 1 shows a schematic diagram of an aircraft 100 according to an embodiment of the present invention, the aircraft 100 includes an aircraft tank device 200 according to another embodiment of the present invention. Specifically, Figure 4 A top view of the aircraft 100 is shown. Figure 5 A front view of the aircraft 100 is shown.

[0047] Figure 4 and Figure 5 The aircraft 100 and Figure 2 and Figure 3 A significant difference from the conventional aircraft 10 in FIG. 1 is that the aircraft 100 includes an aircraft tank arrangement 200 .

[0048] In particular, the aircraft 100 includes an aircraft fuselage 101 and two aircraft wings 102, wherein the aircraft tank device 200 is configured as a conformal fuel tank, which is mounted to the outer skin of the aircraft fuselage 101 and the outer skin of the aircraft wing 102. The conformal fuel tank 200 includes a fairing 201, which is formed and configured to partially cover the aircraft wing-aircraft fuselage interface 202 and store fuel. In addition, the fairing 201 is formed and configured to provide a lift function. The lift function can be provided by increasing the wing area, such as Figure 4 Here, the fairing 201 is configured as a belly fairing. The belly fairing 201, also called ventral fairing, is located on the bottom side of the aircraft fuselage 101 and between the two aircraft wings 102. For example, the fairing 201 has a trapezoidal shape.

[0049] In addition, the fairing 201 is configured to be replaceable so that the size and / or form of the fairing 201 can be selected according to the flight distance. Therefore, the replaceable fairing 201 can be replaced with a small fairing for short-distance flight or a larger fairing for long-distance flight. For example, in addition to the fuel mainly stored in the second fuel tank integrated in the two aircraft wings 102, the conformal fuel tank 200 can also accommodate up to about 40m 3 , especially up to about 55m 3 The stored fuel is distributed inside the fairing 201 so that the mass center of the conformal fuel tank 200 roughly corresponds to the mass center of the aircraft 100.

[0050] exist Figure 5 , it is illustrated that the fairing 201 covers the upper side 202a and partially covers the lower side of the aircraft wing-aircraft fuselage interface 202. In addition, the fairing 201 covers the front section 202b and the rear section 202c of the aircraft wing-aircraft fuselage interface 202.

[0051] Figure 6 A schematic cross-sectional view of an aircraft 100 according to another embodiment of the invention is shown, the aircraft comprising an aircraft tank arrangement 200 according to another embodiment of the invention.

[0052] The exemplary aircraft tank assembly 200 includes a pilot valve 204 , an exhaust pressure valve 205 , an exhaust box 206 , a plurality of hinges 207 , and fuel and air quick disconnect elements 208 .

[0053] For example, the pilot valve 204, the exhaust pressure valve 205, and the exhaust box 206 are located inside the fairing 201. The pilot valve 204, the exhaust pressure valve 205, the exhaust box 206, and the fuel and air quick disconnect element 208 are connected through the standard fuel supply and delivery line 103 of the aircraft 100. The standard fuel supply and delivery line 103 is also connected to the fuel supply and delivery shut-off valve 104 of the aircraft 100. In addition, the fuel and air quick disconnect element 208 can have an integrated fuel supply and delivery shut-off valve. Accordingly, the aircraft tank device 200 can be installed and removed faster and easier through the fuel and air quick disconnect element 208 and the fuel supply and delivery shut-off valve. In addition, during the installation / removal and transportation process, the unused fuel remaining in the aircraft tank device 200 can be safely retained in the aircraft tank device.

[0054] The standard fuel supply and delivery line 103 specifically connects the fuel supply and delivery shutoff valve 104 to the fuel and air quick disconnect element 208, and further connects the fuel and air quick disconnect element 208 to the pilot valve 204, specifically the respective fuel high pilot valve 204 and fuel low pilot valve 204. The exhaust pressure valve 205 is fluidly connected to the fuel low pilot valve 204, and the exhaust tank 206 is fluidly connected to the fuel high pilot valve 204.

[0055] The exhaust pressure valve 205 allows exhaust of overpressure or vacuum created in the atmospheric tank during filling and emptying, or allows pressure changes due to temperature, atmospheric pressure changes or due to temperature changes of the fluid or tank, such as heating, heat tracing or heat exchanger failure.

[0056] The plurality of hinges 207 are configured to attach the fairing 201 to the aircraft fuselage 101 and the two aircraft wings 102. For example, two hinges of the plurality of hinges 207 attach the fairing 201 to the underside of the aircraft wing 102, and another two hinges of the plurality of hinges 207 attach the fairing 201 to the upper side of the aircraft wing 102. For example, another two hinges 207 attach the fairing 201 to the aircraft fuselage 101 above the aircraft wing 102, wherein another hinge 207 attaches the fairing 201 to the aircraft fuselage 101 below the aircraft wing 102. The positions of the hinges 207 may correspond to the positions of similar hinges of a conventional fairing, so that the aircraft canister device 200 may be used and interchanged with other modules of the aircraft 100.

[0057] Figure 7A schematic cross-sectional view of an aircraft 100 according to another embodiment of the invention is shown, comprising an aircraft tank arrangement 200 with a pressure vessel 203 according to another embodiment of the invention. In particular, the cross-sectional view is shown at the front section 202b, which means in front of the aircraft wing 102.

[0058] The aircraft tank device 100 generally includes Figure 1 , Figure 4 , Figure 5 or Figure 6 The same features of the aircraft tank device, wherein Figure 7 The aircraft tank device 100 further comprises a pressure vessel 203 partially or completely surrounded by the fairing 201. The pressure vessel 203 is configured to contain a cryogenic medium, in particular liquid hydrogen. For example, the pressure vessel 203 can be configured as a cryogenic tank.

[0059] At the front section 202 b , the fairing 201 can be hinged to the aircraft fuselage 101 by two hinges 207 , for example.

[0060] Figure 8 A schematic perspective view of an aircraft 100 with a lowered landing gear 105 according to another embodiment of the present invention is shown, the aircraft 100 comprising an aircraft tank device 200 according to another embodiment of the present invention. In particular, Figure 8 A bottom perspective view of aircraft 100 is illustrated.

[0061] The aircraft tank device 200 may be configured as Figure 1 , Figure 4 , Figure 5 , Figure 6 and Figure 7 The aircraft tank device 200 is one of the aircraft tank devices described in . The fairing 201 of the aircraft tank device 200 is arranged at the front section and the rear section of the aircraft wing-aircraft fuselage interface 202. Therefore, the aircraft tank device 200 enlarges the wing area of ​​the aircraft wing 102. Figure 8 It is clearly shown that the landing gear 105 can function in a manner known in the art and is not interfered with by the aircraft tank arrangement 200 .

[0062] As above Figure 1 , Figure 4 , Figure 5 , Figure 6 , Figure 7 and Figure 8 The aircraft tank device 200 described in the drawings can be modified and used for any type of aircraft, such as military aircraft, passenger aircraft or cargo aircraft. The fairing 201 can be configured as any wing-to-fuselage fairing. Alternatively or additionally, the aircraft tank device 200 can include a trailing edge fairing for storing fuel.

[0063] In the above detailed description, various features have been combined in one or more examples to improve the rigor of the description. However, it should be clear in this case that the above description is merely illustrative and is by no means restrictive. It is intended to cover all alternatives, modifications and equivalents of the various features and exemplary embodiments. In view of the above description, many other examples will be immediately and directly clear to those skilled in the art based on their knowledge in the art.

[0064] The exemplary embodiments have been selected and described so that the basic principles of the invention and their application possibilities in practice can be presented in the best possible way. Therefore, the person skilled in the art can modify and utilize the invention and its various exemplary embodiments in the best way according to the intended purpose of use. In the claims and the description, the terms "comprise" and "have" are used as neutral language concepts corresponding to the term "comprises". In addition, the use of the terms "a", "an" and "an" should not in principle exclude multiple features and components described in this way.

[0065] Although at least one exemplary embodiment of the present invention is disclosed herein, it should be understood that modifications, substitutions and alternatives may be obvious to those of ordinary skill in the art, and these modifications, substitutions and alternatives may be carried out without departing from the scope of the present disclosure. The present disclosure is intended to cover any changes or variations of the exemplary embodiments. In addition, in the present disclosure, the terms "include" or "comprise" do not exclude other elements or steps, the terms "one" or "a kind of" do not exclude plural numbers, and the term "or" means either or both. In addition, unless otherwise suggested by the present disclosure or the context, the features or steps already described may also be used in combination with other features or steps and in any order. The present disclosure is hereby incorporated by reference into the complete disclosure of any patent or application to which it claims interest or priority.

[0066] Reference numerals list

[0067] 100 aircraft

[0068] 101 aircraft fuselage

[0069] 102 aircraft wing

[0070] 103 Fuel supply and delivery pipelines

[0071] 104 Fuel supply and delivery stop valve

[0072] 105 landing gear

[0073] 200 aircraft tank device

[0074] 201 fairing

[0075] 202 Aircraft wing-aircraft fuselage junction

[0076] 202a Upper side

[0077] 202b front section

[0078] 202c rear section

[0079] 203 Pressure Vessel

[0080] 204 pilot valve

[0081] 205 Exhaust Pressure Valve

[0082] 206 exhaust box

[0083] 207+ hinges

[0084] 208 Fuel and Air Quick Disconnect Elements

Claims

1. An aircraft tank device (200) for increasing the flight distance and wing area of ​​an aircraft (100), the aircraft tank device (200) being particularly used for increasing the flight distance and wing area of ​​a passenger aircraft or a cargo aircraft, the aircraft tank device (200) comprising a fairing (201), the fairing being formed and configured as: At least partially covering an aircraft wing-aircraft fuselage interface (202); Storing fuel; and Provides lift function.

2. The aircraft tank device (200) according to claim 1, wherein: The fairing (201) can be connected to an aircraft fuselage (101) and / or an aircraft wing (102).

3. The aircraft tank device (200) according to claim 1 or 2, wherein: The fairing (201) is configured as a belly fairing.

4. The aircraft tank device (200) according to one of the preceding claims, wherein: The fairing (201) is configured to be replaceable, so that the size and / or form of the fairing (201) can be selected according to the flight distance.

5. The aircraft tank device (200) according to one of the preceding claims, further comprising a pressure vessel (203) at least partially surrounded by the fairing (201), wherein: The pressure vessel (203) is configured to contain a cryogenic medium.

6. The aircraft canister device (200) according to one of the preceding claims, further comprising a pilot valve (204), an exhaust pressure valve (205) and an exhaust box (206) positioned inside the fairing (201).

7. The aircraft tank device (200) according to one of the preceding claims, further comprising a plurality of hinges (207) for attaching the fairing (201) to an aircraft fuselage (101) and / or an aircraft wing (102).

8. Aircraft tank device (200) according to one of the preceding claims, wherein: The stored fuel is distributed inside the fairing (201) so that the center of mass of the aircraft tank device (200) substantially corresponds to the center of mass of the aircraft (100).

9. Aircraft tank arrangement (200) according to one of the preceding claims, further comprising fuel and air quick disconnect elements (208).

10. An aircraft (100), in particular a passenger aircraft or a cargo aircraft, comprising an aircraft tank device (200) according to one of the preceding claims.

11. The aircraft (100) according to claim 10, further comprising an aircraft fuselage (101) and an aircraft wing (102), wherein: The aircraft tank device (200) is configured as a conformal fuel tank, which is mounted to the outer skin of the aircraft fuselage (101) and the outer skin of the aircraft wing (102).

12. The aircraft (100) according to claim 10 or 11, wherein: The aircraft tank arrangement (200) is fluidly connected to a standard fuel supply and delivery line (103).

13. The aircraft (100) according to one of claims 10 to 12, wherein: The fairing (201) at least covers an upper side portion (202a) of the aircraft wing-aircraft fuselage interface (202).

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