Liquid hydrogen release structure for responding to aircraft distress

Abstract

The application relates to the technical field of aviation structures, and discloses a liquid hydrogen release structure for coping with the distress of an aircraft, which comprises a discharge pipe connected to a wing, and a protection assembly connected to the discharge pipe, wherein the protection assembly comprises a plurality of blocking bodies and a driving part; the plurality of blocking bodies are uniformly distributed along the axial direction of the discharge pipe; the blocking bodies comprise a plurality of blocking plates which are uniformly distributed on the circumferential side of the discharge pipe; the first end of each blocking plate close to the outlet of the discharge pipe is hinged to the outer wall of the discharge pipe, and each blocking plate is in close contact with the outer wall of the discharge pipe so as to block the heat source in the wing; the driving part comprises a plurality of connecting rods which are uniformly distributed on the circumferential side of the discharge pipe, and the center line of each connecting rod is parallel to the length extension direction of the outer wall of the discharge pipe; the number and position of the connecting rods correspond to the number and position of the plurality of blocking plates included in the blocking bodies; and the second end of each blocking plate corresponding to the connecting rod is hinged to the connecting rod. The application can improve the release rate of liquid hydrogen when the aircraft is in distress and forced to land.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aviation structure, and particularly relates to a liquid hydrogen release structure for coping with distress of an aircraft. BACKGROUND

[0002] Liquid hydrogen has high energy density, and its calorific value can reach 142 MJ / kg, far exceeding 43 MJ / kg of aviation kerosene, which can greatly improve the thrust and endurance time of the aircraft and achieve efficient combustion and greatly reduce the overall mass of the aircraft. Therefore, in recent years, domestic and foreign aviation power manufacturers use liquid hydrogen as a new type of power energy for aviation. Since the boiling point of liquid hydrogen is extremely low, usually-253°C, liquid hydrogen is usually stored in an adiabatic double-layer vacuum adiabatic fuel tank. The fuel tank is usually arranged at the rear of the fuselage and extends to the wings on both sides. The fuel tank is connected to the engine through a pipeline to provide stable fuel for the flight of the aircraft. When the aircraft suddenly fails in the air and needs to make an emergency landing, in order to avoid the weight of the aircraft exceeding the rated support threshold of the landing gear, or the attitude of the aircraft out of control in the air, the unused additional liquid hydrogen usually needs to be quickly released in the air to reduce the total mass of the fuselage and balance the balance attitude of the center of gravity of the aircraft.

[0003] The current common liquid hydrogen release structure of the aircraft includes two groups, and the two groups of liquid hydrogen release structures are usually arranged at the wing tails of the two wings. The release structure includes a release pressure pump in communication with the fuel tank and a discharge pipe in communication with the liquid outlet end of the pressure pump. The other end of the discharge pipe extends to the outside of the wing. Since the stored liquid hydrogen needs to have strong heat insulation, the high temperature inside the wing is easy to be transferred to the fuel tank through the discharge pipe. In order to avoid the heat transfer of the discharge pipe to the fuel tank to affect its stability, a blocking sleeve body for blocking external heat sources as much as possible is usually sleeved on the discharge pipe. The blocking sleeve body usually has a protective layer, a heat insulation layer and a close inner layer close to the outer wall of the discharge pipe arranged from the outermost to the innermost. When the aircraft is in distress and needs to release liquid hydrogen, the pressure pump is opened to release the liquid hydrogen through the discharge pipe. The liquid hydrogen entering the discharge pipe in communication with the outside will absorb heat, and its temperature will gradually approach the boiling point. When the liquid hydrogen flow gradually approaches the outlet of the discharge pipe, its temperature can reach the boiling point. The liquid hydrogen is completely vaporized in this process to complete the discharge.

[0004] However, the existing blocking sleeve body can provide certain heat insulation protection for the discharge pipe to ensure that the temperature of the fuel tank tends to be stable. However, the large amount of heat blocked by the existing blocking sleeve body will undoubtedly slow down the speed of the liquid hydrogen absorbing heat and vaporizing in the discharge pipe, thereby reducing the overall discharge speed of the liquid hydrogen. This makes it difficult for the aircraft in distress to complete the rapid discharge of the predetermined amount of liquid hydrogen fuel, thereby increasing the difficulty of the emergency landing and the risk of safety accidents. SUMMARY

[0005] The application provides a liquid hydrogen release structure for responding to an aircraft distress, which can improve the release rate of liquid hydrogen when the aircraft distresses and forces landing.

[0006] The application provides a liquid hydrogen release structure for responding to an aircraft distress, which comprises a discharge pipe connected to a wing, and a protection assembly connected to the discharge pipe, wherein the protection assembly comprises a plurality of blocking bodies and a driving part, the plurality of blocking bodies are uniformly distributed along the axial direction of the discharge pipe, each blocking body comprises a plurality of blocking plates which are uniformly distributed on the lateral side of the discharge pipe, the first end of each blocking plate close to the outlet of the discharge pipe is hinged to the outer wall of the discharge pipe, and each blocking plate is in close contact with the outer wall of the discharge pipe to block the heat source in the wing, the driving part comprises a plurality of connecting rods which are uniformly distributed on the lateral side of the discharge pipe, the center line of each connecting rod is parallel to the length extension direction of the outer wall of the discharge pipe, the number and position of the connecting rods correspond to the number and position of the blocking plates included in the blocking body, the second end of each blocking plate corresponding to the connecting rod is hinged to the connecting rod, and when one blocking plate rotates under the action of a driving force, the corresponding connecting rod can drive other blocking plates to rotate synchronously, so that the outer wall of the discharge pipe is exposed to the high-temperature environment in the wing.

[0007] Preferably, the end of the discharge pipe close to the fuel tank is fixedly connected with a fixed pipe, the outer part of the fixed pipe is sleeved with a connecting sleeve, and the connecting sleeve is connected with a driving part for synchronously driving the rotation of the blocking plates.

[0008] Preferably, the connecting sleeve is connected with a fan for blowing the high-temperature hot gas in the wing to one side of the discharge pipe.

[0009] Preferably, the caliber of the discharge pipe increases from the end close to the fuel tank to the end close to the outlet.

[0010] Preferably, the discharge pipe is a polyhedral structure, and the shape of each blocking plate is consistent with the shape of the corresponding outer pipe wall of the discharge pipe.

[0011] Preferably, each blocking plate is hinged to the corresponding connecting rod through a fixedly connected hinge support and a horizontally extended hinge shaft.

[0012] Preferably, the position of the second end of each blocking plate is fixedly connected with a guide plate for guiding the hot gas flow driven by the fan to one side of the discharge pipe, and the length of each guide plate decreases from the side close to the outlet of the discharge pipe to the side close to the fuel tank.

[0013] Preferably, the driving part comprises a plurality of support rods and a plurality of driving members, each support rod corresponds to the position and number of each connecting rod, the driving member comprises a sliding block and a horizontal screw rod threadedly connected in the middle, the screw rod is rotationally connected with the connecting sleeve at both ends, the sliding block is slidingly connected with the connecting sleeve, one end of the support rod is hinged with the sliding block, and the other end is hinged with the corresponding and adjacent hinge shaft, and the screw rod rotates under the action of external driving force to drive the sliding block to slide horizontally towards the side close to the connecting rod, and the support rod drives each baffle to deflect.

[0014] Preferably, the driving member further comprises an inner tooth ring and a plurality of gears, the gears are fixedly sleeved on the same end of each screw rod, and the inner tooth ring is sleeved outside each gear and is in meshing connection with each gear.

[0015] Preferably, each baffle is hinged with the outer wall of the discharge pipe through a hinged support, the end close to the fuel tank and the end away from the fuel tank of each baffle are both provided with chamfers, and the inclined surfaces of the two chamfers are parallel.

[0016] Compared with the prior art, the beneficial effects of the present application are that: on the basis of being able to realize the heat insulation effect of the discharge pipe, the present application can also accelerate the rate of conversion of liquid hydrogen into hydrogen gas, and improve the discharge power, so as to reduce the residue of liquid hydrogen in the fuel tank and the pipeline, and reduce the risk probability of safety hidden danger.

[0017] In terms of structure, the baffles originally designed as protective heat insulation are designed as a plurality of combined arrangements and can deflect, so that when each baffle is in the state of being attached to the discharge pipe, the auxiliary heat insulation effect of the discharge pipe can be realized to ensure the stability of the liquid hydrogen fuel tank, when the aircraft suddenly fails in the air and needs to make an emergency landing, by controlling each baffle to rotate synchronously towards the end close to the discharge pipe outlet, the outer wall of the discharge pipe is exposed to the high-temperature environment inside the wing, so that the heat exchange between the liquid hydrogen and the hot gas flow outside the discharge pipe is realized, thereby improving the efficiency of liquid hydrogen vaporization, as the deflection angle of each baffle increases, the exposed area of the discharge pipe increases, the liquid hydrogen absorbs more heat, the vaporization speed is faster, and the rate of liquid hydrogen vaporization can even be doubled.

[0018] At the same time, the power of hydrogen gas released from the discharge pipe outlet is greatly increased, thereby realizing the effect of more rapidly discharging liquid hydrogen to the external environment, so that the aircraft in distress can quickly complete the discharge of the predetermined amount of liquid hydrogen fuel, reduce the gravity of the aircraft itself, reserve enough time for emergency landing, and reduce the risk of safety accidents. BRIEF DESCRIPTION OF DRAWINGS

[0019] Figure 1 A left side view of a part of a cross-sectional structure of a liquid hydrogen release structure for coping with aircraft distress according to an embodiment of the present application is provided.

[0020] Figure 2For Figure 1 Partial enlarged view of part A in the middle;

[0021] Figure 3 Structure schematic diagram of a second state of a liquid hydrogen release structure for coping with aircraft distress provided by the embodiment of the present application;

[0022] Figure 4 For Figure 3 Partial enlarged view of part B in the middle;

[0023] Figure 5 Front view structure schematic diagram of a polygonal discharge pipe in a liquid hydrogen release structure for coping with aircraft distress provided by the embodiment of the present application;

[0024] Figure 6 Partial front view structure schematic diagram of a liquid hydrogen release structure for coping with aircraft distress provided by the embodiment of the present application;

[0025] Figure 7 Front view structure schematic diagram of a discharge pipe same pipe diameter embodiment in a liquid hydrogen release structure for coping with aircraft distress provided by the embodiment of the present application;

[0026] Figure 8 Left side view structure schematic diagram of a discharge pipe same pipe diameter embodiment in a liquid hydrogen release structure for coping with aircraft distress provided by the embodiment of the present application.

[0027] BRIEF DESCRIPTION OF THE DRAWINGS

[0028] 1, discharge pipe; 2, protection assembly; 21, barrier body; 211, barrier plate; 22, driving part; 221, connecting rod; 3, fixed pipe; 4, connecting sleeve; 5, driving part; 51, support rod; 52, driving piece; 521, sliding block; 522, screw rod; 523, inner tooth ring; 524, gear; 6, fan; 7, hinged support; 71, hinge shaft; 8, guide plate; 9, hinged support. DETAILED DESCRIPTION

[0029] One specific embodiment of the present application will be described in detail below with reference to the accompanying drawings, but it should be understood that the protection scope of the present application is not limited by the specific embodiment.

[0030] In the description of the present application, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "axial", "radial", "circumferential" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the technical solutions of the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation of the present application.

[0031] With reference to Figure 1 , Figure 2 and Figure 3 , the present application provides a liquid hydrogen release structure for coping with aircraft distress, comprising a discharge pipe 1 connected in the wing, the discharge pipe 1 is connected with a protection assembly 2, the protection assembly 2 comprises: a plurality of sets of blocking bodies 21 and a driving part 22, the plurality of sets of blocking bodies 21 are uniformly distributed along the axial direction of the discharge pipe 1, the blocking body 21 comprises a plurality of blocking plates 211, which are uniformly distributed on the peripheral side of the discharge pipe 1, the first end of the blocking plate 211 close to the outlet of the discharge pipe 1 is hinged to the outer wall of the discharge pipe 1, and each blocking plate 211 is fitted to the outer wall surface of the discharge pipe 1 to block the heat source in the wing, the driving part 22 comprises a plurality of connecting rods 221 uniformly distributed on the peripheral side of the discharge pipe 1, and the center line of each connecting rod 221 is parallel to the length extension direction of the outer wall of the discharge pipe 1, the number and position of the connecting rods 221 correspond one-to-one to the number and position of the plurality of blocking plates 211 included in the blocking body 21, the second end of each blocking plate 211 corresponding to the connecting rod 221 is hinged to the connecting rod 221, and under the action of the driving force, one of the blocking plates 211 can drive other blocking plates 211 to rotate synchronously through the corresponding connecting rod 221, so that the outer wall of the discharge pipe 1 is exposed to the high-temperature environment in the wing.

[0032] In the above embodiments, the present application can not only achieve the heat insulation effect of the discharge pipe 1, but also accelerate the conversion rate of liquid hydrogen to hydrogen gas, and improve the discharge power, so as to reduce the residual liquid hydrogen in the fuel tank and the pipeline, and reduce the risk probability of safety hidden danger.

[0033] In terms of structure, the barrier 21 originally designed as a protective thermal insulation is designed as a structure capable of being arranged in combination and being deflected, and when each barrier plate 211 is in a state of being attached to the discharge pipe 1, an auxiliary thermal insulation effect on the discharge pipe 1 can be achieved to ensure the stability of the liquid hydrogen fuel tank. When the aircraft suddenly fails in the air and needs to make an emergency landing, by controlling each barrier plate 211 to rotate synchronously towards the end close to the outlet of the discharge pipe 1, the outer wall of the discharge pipe 1 is exposed to the high-temperature environment in the wing, so that the heat exchange between the liquid hydrogen and the hot air flow outside the discharge pipe 1 is realized, thereby improving the efficiency of the liquid hydrogen vaporization. Specifically, the present application ingeniously utilizes the large amount of heat generated by the friction between the wing and the air during high-altitude flight and the heat generated by the operation of the equipment in the wing, and the heat generated continuously is transmitted to the exposed outer wall of the discharge pipe 1 by means of heat radiation and hot air flow. The liquid hydrogen flowing through the discharge pipe 1 absorbs the heat after heat conduction and exchange of the discharge pipe 1, thereby realizing heat transfer in a cycle. The structure of the present application increases the rate at which the liquid hydrogen absorbs heat, and the temperature of the liquid hydrogen increases at a higher speed, and the temperature of the liquid hydrogen approaches the boiling point continuously, and the volume of the liquid hydrogen expands rapidly, thereby accelerating the rate of the liquid hydrogen from liquid state to gaseous state. Under standard sea level conditions, the discharge flow rate is increased from the original speed of about 12 kg / s to a speed greater than or equal to 28 kg / s. Specifically, as the deflection angle of each barrier plate 211 increases, the exposed area of the discharge pipe 1 increases, the liquid hydrogen absorbs more heat, and the vaporization speed increases, and the vaporization rate of the liquid hydrogen can even be doubled.

[0034] At the same time, after the liquid hydrogen is vaporized into hydrogen gas, the volume expands rapidly, and the more heat it absorbs, the more hydrogen gas it produces, and the larger the volume expansion. This volume expansion will generate a certain pressure difference in the discharge pipe 1, thereby greatly increasing the power of the hydrogen gas released from the outlet of the discharge pipe 1. When the pressure difference is larger, the speed of hydrogen gas discharge is faster, thereby achieving the effect of discharging liquid hydrogen to the outside environment more quickly, so that the aircraft in distress can quickly complete the discharge of the predetermined amount of liquid hydrogen fuel, thereby reducing the gravity of the aircraft itself, reserving enough time for emergency landing, and reducing the risk of safety accidents.

[0035] Specifically, the pipe material needs to be selected from low-temperature resistant alloys, such as austenitic stainless steel, aluminum alloy or composite material, to prevent low-temperature embrittlement and hydrogen embrittlement effect.

[0036] Further, referring to Figure 1 and Figure 3 , the end of the discharge pipe 1 close to the fuel tank is fixedly connected with a fixed pipe 3, the outside of the fixed pipe 3 is sleeved with a connecting sleeve 4, and the connecting sleeve 4 is connected with a driving part 5 for synchronously driving the rotation of each barrier plate 211.

[0037] In the above embodiment, the deflection of each baffle plate 211 can be synchronously controlled by the driving part 5, thereby realizing an automatic control mode. The fixed tube 3 and the connecting sleeve 4 support the driving part 5.

[0038] Further, referring to Figure 1 and Figure 3 , the connecting sleeve 4 is connected with a fan 6 for blowing the high-temperature hot gas in the wing to one side of the discharge pipe 1.

[0039] In the above embodiment, the flow speed of the hot gas in the wing can be greatly improved by the fan 6, so that the heat can quickly flow to the outer wall of the discharge pipe 1. Not only the efficiency of the vaporization of the liquid hydrogen is improved by applying heat to the exposed outer wall of the discharge pipe 1, but also the temperature in the wing is reduced after heat exchange, thereby avoiding the influence of the stability of the structure due to the excessively high temperature in the internal of the aircraft wing. Furthermore, the hot gas flow will form a vortex after being stirred by the fan 6 between any two baffle plates 211, which slows down the kinetic energy of the hot gas flow. The hot gas flow can sufficiently increase the temperature of the discharge pipe 1, and the cold gas flow is formed after the temperature of the hot gas flow is reduced after heat exchange. Since the cold gas flow is heavier than the hot gas flow, it will also flow downward and move toward the heating area of the wing and cool the heating area, thereby forming a cold-heat alternating circulation state.

[0040] Further, referring to Figure 1 and Figure 4 , the diameter of the discharge pipe 1 gradually increases from the end close to the fuel tank to the end close to the outlet.

[0041] In the above embodiment, the structure can increase the exposed surface of the discharge pipe 1 compared with a straight pipe type, thereby providing a better environment for the vaporization of the liquid hydrogen. In combination with the effect of the fan 6, as shown in Figure 8 , the hot gas flow can more quickly and fully contact the outer wall of the discharge pipe 1, thereby further improving the vaporization of the liquid hydrogen. By setting the tapered structure, the pressure in the discharge pipe 1 can be slightly reduced, without affecting the normal discharge speed range of the hydrogen gas, thereby realizing the sufficient heat exchange and vaporization effect of the liquid hydrogen in the discharge pipe 1.

[0042] Further, referring to Figure 5 , Figure 6 and Figure 7 , the discharge pipe 1 is a polyhedral structure, and the shape of each baffle plate 211 is consistent with the shape of the corresponding outer pipe wall of the discharge pipe 1.

[0043] In the above embodiment, by limiting the multi-polygon structure of the exhaust pipe 1, compared with the circular pipe of the cylinder structure, the exposed area is further increased under the specified size, compared with the cylinder structure, the heat exchange area of the liquid hydrogen can be increased, so that the sufficient heat absorption vaporization effect of the liquid hydrogen can be realized.

[0044] Further, referring to Figure 2 , each barrier plate 211 is hinged to the corresponding connecting rod 221 through the fixed connection of the hinge support 7 and the horizontally extending hinge shaft 71.

[0045] In the above embodiment, as shown in Figure 2 and Figure 4 , the hinge support 7 is a bent structure, when each barrier plate 211 is closed with the surface of the exhaust pipe 1, the hinge shaft 71 extends outward, and the hinge shaft 71 horizontally penetrates the connecting rod 221 and rotates the connection.

[0046] Further, referring to Figure 1 and Figure 2 , each barrier plate 211 is fixedly connected with a guide plate 8 at the second end for guiding the hot gas flow driven by the fan 6 to one side of the exhaust pipe 1, the length of each guide plate 8 decreases from the side close to the outlet of the exhaust pipe 1 to the side of the fuel tank.

[0047] In the above embodiment, by setting the guide plate 8, the hot gas flow can be guided to the outer surface of the corresponding exhaust pipe 1, by limiting the length of each guide plate 8 from the side close to the outlet of the exhaust pipe 1 to the side of the fuel tank, as shown in Figure 1 , the hot gas flow can flow through each position of the exhaust pipe 1.

[0048] Further, referring to Figure 2 and Figure 4 , the driving part 5 includes a plurality of support rods 51 and a plurality of driving parts 52, each support rod 51 corresponds to the position and number of each connecting rod 221, the driving part 52 includes a sliding block 521 and a horizontally threaded rod 522 screwed therein, both ends of the threaded rod 522 are rotatably connected with the connecting sleeve 4, the sliding block 521 is slidingly connected with the connecting sleeve 4, one end of the support rod 51 is hinged with the sliding block 521, the other end is hinged with the corresponding and adjacent hinge shaft 71, and the support rod 51 drives each barrier plate 211 to deflect under the rotation of the threaded rod 522 under the action of the external driving force.

[0049] Further, referring to Figure 2 , Figure 3 and Figure 4The driving member 52 further comprises an inner tooth ring 523 and a plurality of gears 524, the gears 524 are fixedly sleeved on the same end of each screw rod 522, the inner tooth ring 523 is sleeved outside each gear 524 and is engaged with each gear 524, and the inner tooth ring 523 is driven by a motor.

[0050] In the above embodiment, through the inner tooth ring 523 and the gears 524, the motor for driving the rotation of the inner tooth ring 523 is a micro motor, the motor housing is fixed, the output shaft is fixedly connected with the matching gear structure engaged with the inner tooth ring 523, and the rotation of the motor output shaft is driven by the engagement of the inner tooth ring 523 to realize the driving effect, and the specific rotation mode is not limited to the micro motor provided in the embodiment.

[0051] Further, referring to Figure 2 Each blocking plate 211 is hinged to the outer wall of the discharge pipe 1 through the hinge support 9, the end close to the fuel tank and the end away from the fuel tank of each blocking plate 211 are both provided with chamfers, and the inclined surfaces of the two chamfers are parallel.

[0052] In the above embodiment, the chamfer can further guide the hot air flow.

[0053] The above disclosure is only a few specific embodiments of the present application, but the embodiments of the present application are not limited to this, any changes that can be thought of by those skilled in the art should fall within the protection scope of the present application.

Claims

1. A liquid hydrogen release structure for responding to an emergency of an aircraft, comprising a discharge pipe connected to a wing, characterized in that, The discharge pipe is connected with a protection assembly, and the protection assembly comprises: A plurality of barrier bodies are uniformly distributed along the axial direction of the discharge pipe, and each barrier body comprises a plurality of barrier plates which are uniformly distributed on the peripheral side of the discharge pipe, and a first end of each barrier plate close to the outlet of the discharge pipe is hinged to the outer wall of the discharge pipe. A driving part comprises a plurality of connecting rods which are uniformly distributed on the peripheral side of the discharge pipe, and the center line of each connecting rod is parallel to the length extension direction of the outer wall of the discharge pipe, and the number and position of the connecting rods correspond to the number and position of the plurality of barrier plates included in the barrier body, and the second end of each barrier plate corresponding to the connecting rod is hinged to the connecting rod, and each barrier plate is in close contact with the outer wall of the discharge pipe, so as to block the heat source in the wing, and when one of the barrier plates rotates under the action of a driving force, other barrier plates can be driven to rotate synchronously through the corresponding connecting rod, so that the outer wall of the discharge pipe is exposed to the high-temperature environment in the wing.

2. A liquid hydrogen release structure for responding to a distress of an aircraft according to claim 1, wherein The end of the discharge pipe close to the fuel tank is fixedly connected with a fixed pipe, the outer part of the fixed pipe is sleeved with a connecting sleeve, and the connecting sleeve is connected with a driving part for synchronously driving the rotation of each barrier plate.

3. A liquid hydrogen release structure for use in responding to an emergency of an aircraft as defined in claim 2, wherein The connecting sleeve is connected with a fan for blowing the high-temperature hot gas in the wing to one side of the discharge pipe.

4. A liquid hydrogen release structure for use in responding to an emergency of an aircraft as defined in claim 3, wherein The caliber of the discharge pipe gradually increases from the end close to the fuel tank to the end close to the outlet.

5. A liquid hydrogen release structure for responding to a distress of an aircraft as defined in claim 3, wherein The discharge pipe has a polyhedral structure, and the shape of each barrier plate is consistent with the shape of the corresponding outer wall of the discharge pipe.

6. A liquid hydrogen release structure for responding to a distress of an aircraft as defined in claim 2, wherein, Each barrier plate is hinged to the corresponding connecting rod through a fixed hinged support and a horizontally extending hinge shaft.

7. A liquid hydrogen release structure for use in responding to an emergency of an aircraft as defined in claim 3, wherein The position of the second end of each barrier plate is fixedly connected with a guide plate for guiding the airflow driven by the fan to one side of the discharge pipe, and the length of each guide plate gradually decreases from the side close to the outlet of the discharge pipe to the side close to the fuel tank.

8. A liquid hydrogen release structure for use in responding to an emergency of an aircraft as defined in claim 6, wherein The driving part comprises a plurality of support rods and a plurality of driving members, each support rod corresponds to the position and number of each connecting rod, the driving member comprises a sliding block and a horizontal screw rod which is threadedly connected in the middle, the two ends of the screw rod are rotationally connected with the connecting sleeve, the sliding block is slidingly connected with the connecting sleeve, one end of the support rod is hinged to the sliding block, and the other end is hinged to the corresponding and adjacent hinge shaft, and the screw rod rotates under the action of an external driving force, so as to drive the sliding block to slide horizontally close to the connecting rod, and the support rod drives each barrier plate to deflect.

9. A liquid hydrogen release structure for use in responding to an aircraft emergency as defined in claim 8 wherein, The driving member further comprises an inner tooth ring and a plurality of gears, the gears are fixedly sleeved on the same end of each screw rod, the inner tooth ring is sleeved on the outside of each gear and is in meshing connection with each gear, and the inner tooth ring is driven by a motor.

10. A liquid hydrogen release structure for responding to a distress situation of an aircraft as defined in claim 1, wherein Each barrier plate is hinged to the outer wall of the discharge pipe through a hinged support, and the end close to the fuel tank and the end away from the fuel tank of the barrier plate are both provided with chamfers, and the inclined surfaces of the two chamfers are parallel.

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