Hydrogen storage tank arrangement structure of hydrogen energy aircraft and hydrogen energy aircraft

Abstract

The utility model belongs to the field of hydrogen energy aircrafts, and particularly relates to a hydrogen energy aircraft hydrogen storage tank arrangement structure and a hydrogen energy aircraft, the hydrogen energy aircraft hydrogen storage tank arrangement structure comprises slide rail frames and a plurality of vertical frames, the slide rail frames are symmetrically distributed at two ends of an aircraft body in the aircraft, each pair is provided with the vertical frame, an upper wall plate is movably connected with the vertical frames and detachably connected with the slide rail frames, and the vertical frames are arranged on the upper wall plate. The device is used for realizing emergency disengagement. The sliding rail frame and the vertical frame are arranged and are structurally matched with the upper wall plate to jointly complete the separation behavior under the emergency condition, the sliding rail frame and the vertical frame are arranged above a passenger cabin and are symmetrically arranged along the left side and the right side, and when the hydrogen storage tank encounters an impact load of emergency landing, the hydrogen storage tank can fly out towards the two sides of a machine body along a supporting frame of the sliding rail frame through emergency separation; and the hydrogen storage tank is prevented from compressing the living space of passenger cabin members downwards, so that the safety of passengers is ensured.

Description

Technical Field

[0001] The utility model belongs to the field of hydrogen energy aircraft, and specifically relates to a hydrogen energy aircraft hydrogen storage tank arrangement structure and a hydrogen energy aircraft. Background Art

[0002] Compared with traditional aviation fuel, hydrogen energy has the advantages of high energy density (about three times that of aviation kerosene), pollution-free emissions, huge reserves, simple acquisition methods, and renewable nature.

[0003] However, there are several unavoidable problems in using liquid hydrogen as a power source for civil airliners. First, liquid hydrogen needs to be stored in a pressurized container, so the hydrogen storage tank is preferably a sphere, cylinder or elliptical column. Therefore, due to the space limitation of the wing, the hydrogen storage tank is not suitable for the wing tank layout of conventional civil airliners, which will bring about changes in the overall layout plan of civil aircraft.

[0004] According to the existing design scheme, the hydrogen tank can be arranged at the tail section of the fuselage, the top of the fuselage or the wing external hanger, etc. Among them, the scheme of arranging the hydrogen tank on the top of the fuselage has a small change to the conventional layout of civil aircraft, and has a large adjustment space for the center of gravity of the aircraft. It is a more competitive overall layout scheme. However, placing the hydrogen tank on the top of the aircraft makes it more difficult to meet the airworthiness compliance of crashworthiness. For aircraft crash conditions that may cause the occupants to survive, according to CCAR-25-R4 "General Principles of Emergency Landing Situations Article 25.561", the layout of the hydrogen tank must ensure that it does not infringe on the survival space of the occupants on board during the downward limit inertial load of 6.0g.

[0005] In response to the crashworthiness problem caused by the placement of hydrogen storage tanks on top of the fuselage, Airbus International Patent GB2591253 (A) discloses a liquid hydrogen tank placement scheme for hydrogen-powered aircraft. The typical fuselage cross-section is designed to be in the shape of a double flap, and the liquid hydrogen storage tank is placed on the upper side of the fuselage, in the area between the double flaps. The structure includes a support wall that runs through the passenger cabin and the cargo hold. If this design needs to meet airworthiness requirements, the strength of the hydrogen storage tank support structure must be enhanced. This ensures that the hydrogen storage tank on top does not occupy the passenger cabin space in the event of an emergency landing or other crash conditions. Its drawbacks are that the hydrogen storage tank has a small storage space; it does not involve the destruction and separation of the structure from the crash; and it includes a hydrogen storage tank support wall that runs through the passenger cabin.

[0006] Compared with the patent CN113844661A of NJTU, a hydrogen storage tank mounting bracket structure for hydrogen-powered aircraft has at least two support bodies, which are arranged at intervals; at least one connecting rod is located between two adjacent support bodies, and the two ends of the connecting rod are respectively fixed vertically to the two adjacent support bodies; wherein the support body includes: a first ring piece; a second ring piece, which is connected to the first ring piece by a connecting piece, and the second ring piece and the first ring piece are assembled into a whole ring; a supporting structure is arranged on the second ring piece to support the hydrogen storage tank body. However, the energy absorption of the spring structure is limited and cannot meet the energy absorption requirements of a 6g downward crash of a large civil airliner.

[0007] In contrast, a liquid hydrogen storage tank in patent CN109296932A has an insulating inner layer on its outer peripheral wall, an outer tank on its outer peripheral wall, a placement plate fixedly connected to the bottom of the outer tank, reinforcing ribs fixedly connected to both sides of the placement plate, shock-absorbing plates fixedly connected to both ends of the bottom of the placement plate, and the placement plate fixedly connected to a base through the shock-absorbing plates. It includes reinforcing ribs, shock-absorbing plates, sleeves, shock-absorbing springs, pistons and piston rods. The problem is the same as that of the patent of NPU, the energy absorption of the spring structure is limited and does not involve the layout plan on the aircraft.

[0008] Compare with the liquid hydrogen storage tank in patent CN109296932A, the outer peripheral wall of the heat-insulating inner layer is provided with an insulating inner layer, the outer peripheral wall of the heat-insulating inner layer is provided with an outer tank, the bottom of the outer tank is fixedly connected with a placement plate, the two sides of the placement plate are fixedly connected with reinforcing ribs, the two ends of the bottom of the placement plate are fixedly connected with shock-absorbing plates, and the placement plate is fixedly connected with a base through the shock-absorbing plates. It contains reinforcing ribs, shock-absorbing plates, sleeves, shock-absorbing springs, pistons and piston rods. The problem is the same as the patent of NPU. The energy absorption of the spring structure is limited and does not involve the layout plan on the aircraft. The position of the liquid hydrogen tank is in the middle or front and rear of the cabin in the heading direction. At the same time, the patent does not involve how the structure of the hydrogen storage tank is separated when the aircraft crashes. Utility Model Content

[0009] The utility model provides a hydrogen storage tank arrangement structure for a hydrogen energy aircraft and a hydrogen energy aircraft, so as to solve the problems in the prior art that the hydrogen storage tank has an unreasonable structure, interferes with the arrangement of the passenger cabin, and cannot meet the crash energy absorption requirements of large civil airliners.

[0010] In order to achieve the above purpose, the utility model proposes the following technical solutions:

[0011] A hydrogen energy aircraft hydrogen storage tank arrangement structure, the arrangement structure is located above the aircraft cabin, and includes a slide rail structure and a plurality of vertical frames;

[0012] The slide rail structure includes a plurality of slide rail pairs, each of which includes a symmetrically arranged slide rail frame, one end of which is connected to the bottom of the vertical frame;

[0013] An upper wall plate is arranged between the other end of the slide rail frame and the top of the vertical frame;

[0014] The upper wall plate is movably connected to the vertical frame and detachably connected to the slide rail frame;

[0015] One end of the slide rail frame connected to the vertical frame is higher than one end of the slide rail frame connected to the upper wall plate.

[0016] Preferably, slide rail frame partitions are provided between the slide rail frames, and vertical frame partitions are provided between the vertical frames.

[0017] Preferably, the slide rail frame is provided with a first safety pin and a slide rail trolley, and the hydrogen storage tank is connected to the support frame through the slide rail trolley and fixed by the first safety pin.

[0018] Preferably, a second safety pin is provided between the hydrogen storage tank and the vertical frame, and the second safety pin is used to fix the hydrogen storage tank to the aircraft and to disconnect it in an emergency.

[0019] Preferably, the distances between the pairs of slide rails are equal.

[0020] Preferably, an arc-shaped fuselage frame is arranged between the vertical frame and the slide rail frame, and the upper wall panel connects the vertical frame and the support frame through the fuselage frame.

[0021] Preferably, the fuselage frame and the slide rail frame are connected by ear fasteners. When the aircraft crashes, the ear fasteners are disconnected, and the fuselage frame and the upper wall panel are lifted up.

[0022] Preferably, an integral reinforcement plate is provided between the vertical frame, the slide rail frame and the upper wall plate.

[0023] Preferably, when the aircraft crashes, the integral reinforcement plate and the upper wall plate are separated.

[0024] A hydrogen energy aircraft comprises a hydrogen energy aircraft hydrogen storage tank arrangement structure.

[0025] The utility model is beneficial in that:

[0026] A hydrogen tank arrangement structure is proposed, including the arrangement of a slide rail frame and a vertical frame, which are structurally matched with the upper wall plate to jointly complete the detachment behavior in an emergency situation. Considering the crashworthiness problems that may be encountered in this overall layout, it is arranged above the cabin and symmetrically arranged along the left and right sides. When the hydrogen tank encounters the impact load of an emergency landing, it can fly out to both sides of the fuselage through the emergency separation of the support frame along the slide rail frame, thereby avoiding the hydrogen tank compressing the living space of the cabin members downward, thereby ensuring the safety of the passengers. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] The drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation on the present invention.

[0028] In the figure:

[0029] Figure 1 This is a schematic diagram of the fuselage cross section of a hydrogen-powered aircraft;

[0030] Figure 2 This is a schematic diagram of the layout of hydrogen storage tanks for hydrogen-powered aircraft;

[0031] Figure 3 This is a partial enlarged schematic diagram of the layout of hydrogen storage tanks for hydrogen-powered aircraft;

[0032] Figure 4 This is a schematic diagram of the force analysis of the hydrogen storage tank layout;

[0033] Figure 5 This is a schematic diagram of the disconnection of the hydrogen storage tank and the frame safety pin;

[0034] Figure 6 This is a schematic diagram of the disconnection of the safety pin of the hydrogen storage tank and the slide rail frame;

[0035] Figure 7 Schematic diagram of the connection between the upper and lower wall panels of the hydrogen storage tank;

[0036] Figure 8 Schematic diagram for emergency disconnection and ejection of hydrogen storage tanks. DETAILED DESCRIPTION

[0037] The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments. It should be noted that the embodiments and features in the embodiments of the present invention can be combined with each other without conflict.

[0038] The following detailed descriptions are all exemplary descriptions, and are intended to provide further detailed descriptions of the present invention. Unless otherwise specified, all technical terms used in the present invention have the same meanings as those generally understood by those skilled in the art to which the present invention belongs. The terms used in the present invention are only intended to describe specific embodiments, and are not intended to limit the exemplary embodiments according to the present invention.

[0039] See also Figure 1 As shown, the present invention provides a hydrogen storage tank arrangement structure for a hydrogen energy aircraft, wherein the hydrogen energy aircraft comprises a passenger cabin 2, a cargo hold 3 and a hydrogen storage tank area, wherein the cargo hold 3 is located below the passenger cabin 2, and the hydrogen storage tank area is located on the top of the passenger cabin 2, and is covered with fuselage wall panels on the periphery, together forming the fuselage of the hydrogen energy aircraft, and the present invention is arranged on the hydrogen storage tank area on the hydrogen energy aircraft.

[0040] The hydrogen energy aircraft hydrogen storage tank arrangement structure includes a hydrogen storage tank 4, a slide rail structure and a plurality of vertical frames 6;

[0041] The slide rail structure includes a plurality of slide rail pairs, each of which includes two symmetrically arranged slide rail frames 5. The vertical frame 6 is arranged at the top of the slide rail pair, and one end of the slide rail frame 5 is arranged at the bottom of the vertical frame 6 to form a track for the hydrogen storage tank 4 to slide down after being disconnected; an arc-shaped fuselage frame is arranged between the other end of the slide rail frame 5 and the top of the corresponding vertical frame 6, and an upper wall panel 7 is arranged on the fuselage frame to form a closed fuselage to withstand the pressurized load.

[0042] The distances between the slide rails are equal, and they form a frame for placing the hydrogen storage tank 4 together with the vertical frame 6.

[0043] One end of the slide rail frame 5 located at the bottom of the vertical frame 6 is higher than one end of the slide rail frame 5 located at the upper wall plate 7 .

[0044] like Figure 2 As shown, a slide rail frame partition 9 is fixed between the slide rail frames 5 , and a vertical frame partition 10 is fixed between the vertical frames 6 .

[0045] The hydrogen storage tank 4 is connected to the slide rail frame 5 through a slide rail trolley, and the hydrogen storage tank 4 is fixed by a first safety pin. A second safety pin is provided between the hydrogen storage tank 4 and the vertical frame 6 for realizing emergency disconnection.

[0046] The fuselage frame and the slide rail frame 5 are connected by ear fasteners, and the fuselage frame and the vertical frame 6 are movably connected. When a crash occurs, the fuselage frame together with the upper wall panel 7 is lifted up and disconnected from the ear fasteners. At this time, the second safety pin between the hydrogen storage tank 4 and the vertical frame 6 is disconnected, and the first safety pin on the slide rail trolley is also disconnected, and the hydrogen storage tank 4 is separated from the fuselage.

[0047] The upper wall panel 7 and the lower wall panel 1 are combined to form the fuselage wall panel. The upper wall panel 7 is arranged on the fuselage frame to cover the hydrogen storage tank area; the lower wall panel is arranged on the lower layer of the fuselage to cover the passenger cabin 2 and the cargo cabin 3.

[0048] like Figure 3 As shown, an integral reinforcement plate 8 is provided between the hydrogen storage tanks 4, and the integral reinforcement plate is located between the vertical frame 6, the support frame of the slide rail frame 5 and the upper wall plate 7. On the one hand, it can isolate multiple hydrogen storage tanks 4 in the longitudinal direction to avoid mutual interference during emergency disconnection, and on the other hand, it can also strengthen the rigidity of the vertical frame 6 and transfer the load transferred from the hydrogen storage tank 4 to the vertical frame 6 to the fuselage structure.

[0049] When the fuselage frame is lifted up together with the upper wall panel 7 , the integral reinforcement plate 8 is also separated from the upper wall panel 7 and remains fixed between the vertical frame 6 and the slide rail frame 5 .

[0050] In a specific embodiment, the cross-section of the hydrogen storage tank 4 is elliptical or circular.

[0051] In a specific embodiment, the hydrogen storage tanks 4 on both sides of the vertical frame 6 are symmetrically distributed.

[0052] In a specific embodiment, the first safety pin and the second safety pin can be a tension pin or a shear pin.

[0053] The stress analysis of the hydrogen tank when the aircraft proposed in the present invention is subjected to the typical crash load (6g downward) specified in airworthiness clause 25.561 is as follows: Figure 4 As shown, the hydrogen storage tank arranged on the left side of the fuselage is used as an example for explanation:

[0054] Due to the inclination angle of the slide rail frame 5, the 6g downward gravity Ftotal of the hydrogen storage tank 4 is decomposed into F1 parallel to the slide rail frame 5 and F2 perpendicular to the slide rail frame 5. The force of the slide rail frame 5 on the hydrogen storage tank 4 includes the vertical support reaction force F52 and the tangential force F51 provided by the emergency disconnection shear pin. The force of the vertical frame 6 on the hydrogen storage tank 4 is mainly the support reaction force F6 perpendicular to the reference line of the vertical frame 6 provided by the safety pin (stretching pin or shear pin) (through the means of nail hole clearance fit, U-shaped groove, etc., the vertical frame 6 does not bear the load parallel to the reference line of the vertical frame 6 to simplify the force transmission). F51, F52 and F6 can jointly bear the 6g gravity load of the hydrogen storage tank 4 to achieve the balance of force and moment.

[0055] The specific process of the present invention is as follows:

[0056] like Figure 5 The aircraft is in a normal state. When a crash occurs, the hydrogen storage tank 4 is subjected to a downward impact load of 6g. The strength design of the emergency disconnect pin causes the second safety pin between the hydrogen storage tank 4 and the vertical frame 6 to be destroyed first, and the hydrogen storage tank 4 and the vertical frame 6 are disconnected.

[0057] like Figure 6 As shown, the first safety pin between the hydrogen storage tank 4 and the slide rail frame 5 will bear a greater load, thereby causing the first safety pin to be damaged;

[0058] like Figure 7 As shown, when the connection between the hydrogen storage tank 4 and the vertical frame 6 and the slide rail frame 5 is broken, the hydrogen storage tank 4 is no longer connected to the body, so it will slide downward along the tangential direction of the slide rail and break through the connection between the upper wall plate 7 and the lower wall plate 1 in the hydrogen storage tank area, thereby achieving complete separation of the hydrogen storage tank 4;

[0059] like Figure 8 As shown, the hydrogen storage tank 4 is disconnected and ejected in an emergency.

[0060] Supplementary explanation: Referring to the emergency disconnection design of the engine suspension, according to the emergency disconnection related provisions in CS25 and the recommended acceptable compliance method description, for the emergency disconnection design of the engine suspension, it is necessary to analyze the disconnection sequence from the initial disconnection point to the complete separation of the engine from the wing, and the subsequent ejection trajectory does not need to be analyzed. Therefore, it is believed that the trajectory of the hydrogen storage tank after it flies out of the fuselage in this proposal does not need to be analyzed;

[0061] At the same time, the mass of liquid hydrogen in a liquid hydrogen storage tank generally does not exceed 25%, so the design of a disconnectable safety pin in the empty hydrogen state can ensure that the full hydrogen storage tank is not disconnected during the normal operation cycle. Finally, the double-layer vacuum insulation hydrogen storage tank must meet the verification of the fireproof flame combustion test and drop test. It can ensure safety after disconnection.

[0062] The present invention also provides an aircraft, which adopts the above-mentioned hydrogen storage tank arrangement structure.

[0063] The present invention provides a solution for the overall layout of hydrogen energy aircraft hydrogen storage tanks arranged on the upper side of the fuselage to meet the airworthiness clause CCAR-25-R4 "Emergency Landing Situation Article 25.561", thereby preventing the hydrogen storage tank 4 from damaging the integrity of the cabin during emergency landing and avoiding injury to passengers;

[0064] Compared with the existing technical solutions, especially the solution of Airbus international patent GB2591253 (A), the present invention does not affect the layout of the cabin, and there is no need to set up additional load-bearing walls / pillars and other structures in the cabin; the storage space of the hydrogen storage tank 4 is increased; in addition, by breaking off and throwing the hydrogen storage tank to the side and below, the load-bearing requirements of the body structure are reduced compared to directly bearing the 6g inertial load of the hydrogen storage tank 4, and the structural weight reduction can be achieved.

[0065] It is known from common technical knowledge that the present invention can be implemented by other embodiments that do not deviate from its spirit or essential features. Therefore, the embodiments disclosed above are only illustrative in all respects and are not exclusive. All changes within the scope of the present invention or within the scope equivalent to the present invention are included in the present invention.

[0066] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the utility model rather than to limit it. Although the utility model is described in detail with reference to the above embodiments, ordinary technicians in the relevant field should understand that the specific implementation methods of the utility model can still be modified or replaced by equivalents, and any modification or equivalent replacement that does not depart from the spirit and scope of the utility model should be included in the scope of protection of the claims of the utility model.

Claims

1. A hydrogen energy aircraft hydrogen storage tank arrangement structure, characterized in that: The arrangement structure is located above the aircraft cabin and includes a slide rail structure and a plurality of vertical frames; The slide rail structure includes a plurality of slide rail pairs, each of which includes a symmetrically arranged slide rail frame, one end of which is connected to the bottom of the vertical frame; An upper wall plate is arranged between the other end of the slide rail frame and the top of the vertical frame; The upper wall plate is movably connected to the vertical frame and detachably connected to the slide rail frame; One end of the slide rail frame connected to the vertical frame is higher than one end of the slide rail frame connected to the upper wall plate.

2. A hydrogen energy aircraft hydrogen storage tank arrangement structure as claimed in claim 1, characterized in that: Slide rail frame partitions are arranged between the slide rail frames, and vertical frame partitions are arranged between the vertical frames.

3. A hydrogen energy aircraft hydrogen storage tank arrangement structure as claimed in claim 1, characterized in that: The slide rail frame is provided with a first safety pin and a slide rail trolley, and the hydrogen storage tank is connected to the support frame through the slide rail trolley and is fixed by the first safety pin.

4. A hydrogen energy aircraft hydrogen storage tank arrangement structure as claimed in claim 1, characterized in that: A second safety pin is provided between the hydrogen storage tank and the vertical frame, and the second safety pin is used for fixing the hydrogen storage tank to fix the aircraft and for emergency disconnection.

5. The hydrogen storage tank arrangement structure for a hydrogen energy aircraft according to claim 1, characterized in that: The distances between the pairs of slide rails are equal.

6. A hydrogen energy aircraft hydrogen storage tank arrangement structure as claimed in claim 1, characterized in that: An arc-shaped fuselage frame is arranged between the vertical frame and the slide rail frame, and the upper wall plate is connected with the vertical frame and the support frame through the fuselage frame.

7. A hydrogen energy aircraft hydrogen storage tank arrangement structure as claimed in claim 6, characterized in that: The fuselage frame and the slide rail frame are connected by ear fasteners. When the aircraft crashes, the ear fasteners are disconnected, and the fuselage frame and the upper wall panel are lifted up.

8. The hydrogen storage tank arrangement structure for a hydrogen energy aircraft according to claim 1, characterized in that: An integral reinforcement plate is arranged between the vertical frame, the slide rail frame and the upper wall plate.

9. A hydrogen energy aircraft hydrogen storage tank arrangement structure as claimed in claim 8, characterized in that: When the aircraft crashes, the integral reinforcement plate and the upper wall plate are separated.

10. A hydrogen-powered aircraft, characterized in that: The hydrogen-powered aircraft comprises a hydrogen-powered aircraft hydrogen storage tank arrangement structure according to any one of claims 1-9.

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