Hydrogen-lithium electricity mixing device for aircraft

Abstract

The utility model discloses a hydrogen-lithium electricity mixing device for an aircraft, which relates to the technical field of aircrafts and comprises a fixed table, a buffer mechanism is mounted on the outer wall of the fixed table, a hydrogen system electric pile is mounted at the top of the buffer mechanism, a hydrogen system DC / DC2 is mounted at the top of the hydrogen system electric pile, and a hydrogen bottle is mounted on the outer wall of the fixed table. A fixing sleeve is installed on the outer wall of the hydrogen bottle, a busbar pipeline is installed on the outer wall of the hydrogen bottle, and a hydrogen system air compressor is installed at the bottom of the fixing table. The buffer mechanism is arranged, the fixing frame and the hydrogen system galvanic pile form a telescopic structure through the buffer spring, when the device is used, due to the fact that the aircraft can generate violent vibration in the takeoff or landing process, internal components are prone to being damaged, the vibration generated in the takeoff or landing process of the aircraft can be absorbed and buffered through the arrangement of the buffer spring, and the safety of the aircraft is improved. Internal components are protected, and the safety of the device is improved.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of aircraft technology, concretely is a hydrogen lithium mixed power device for aircraft. BACKGROUND

[0002] In modern aircraft, the power device mainly used by commercial and civil aircraft is aviation kerosene power device and lithium electric power device, and the current aviation kerosene power device produces tail gas when working, which pollutes the environment, is not clean energy, and petroleum is not renewable energy and will be used up one day, which is not a long-term solution, and the lithium electric power device also troubles people due to the problem of natural endurance length, in order to provide a new type of energy power device for the aircraft power device, and the hydrogen fuel cell engine has the advantages of no pollution, long endurance, hydrogen is renewable energy, hydrogen energy is one of the main development trends in the future, and the aircraft is prone to vibration when taking off or landing, and is closed, so a hydrogen lithium mixed power device for aircraft is needed.

[0003] The existing aircraft device cannot be buffered and protected and has poor heat dissipation effect when operating, and therefore a hydrogen lithium mixed power device for aircraft is urgently needed. UTILITY MODEL CONTENT

[0004] Therefore, the utility model aims at providing a hydrogen lithium mixed power device for aircraft to solve the problems of inability to buffer and protect and poor heat dissipation effect of the existing aircraft device during use.

[0005] To achieve the above-mentioned purpose, the utility model provides the following technical scheme: a hydrogen lithium mixed power device for aircraft, comprising a fixing table, and a buffer mechanism is installed on the outer wall of the fixing table.

[0006] A hydrogen system electric pile is installed on the top of the buffer mechanism, a hydrogen system DC / DC2 is installed on the top of the hydrogen system electric pile, a hydrogen bottle is installed on the outer wall of the fixing table, a fixing sleeve is installed on the outer wall of the hydrogen bottle, a busbar pipeline is installed on the outer wall of the hydrogen bottle, a hydrogen system air compressor is installed at the bottom of the fixing table, and an air path pipeline is installed on the outer wall of the hydrogen system air compressor.

[0007] A hydrogen system water pump is installed at the bottom of the fixing table, a first water path pipeline is installed on one side of the hydrogen system water pump, a second water path pipeline is installed on the other side of the hydrogen system water pump, a hydrogen system expansion water tank is installed on the outer wall of the second water path pipeline, a hydrogen system heat dissipation fan is installed on the side wall of the fixing table, a rotating shaft is installed on the outer wall of the hydrogen system heat dissipation fan, and a third water path pipeline is installed on the outer wall of the hydrogen system heat dissipation fan.

[0008] Preferably, the buffer mechanism comprises a fixing frame, a limiting rod and a buffer spring, the outer wall of the fixing table is provided with the fixing frame, the inner wall of the fixing frame is provided with the limiting rod, and the outer wall of the limiting rod is provided with the buffer spring.

[0009] Preferably, the fixing frame is welded with the fixing table, and the fixing frame and the fixing table form an extension structure through the buffer spring.

[0010] Preferably, the hydrogen cylinder is fixed to the tail end of the aircraft through a fixing sleeve in a threaded mode, and the hydrogen cylinder is connected with the hydrogen system electric pile through a busbar pipeline.

[0011] Preferably, the hydrogen system air compressor is fixed to the fixing table in a threaded mode, and the hydrogen system air compressor is connected with the hydrogen system electric pile through an air pipeline.

[0012] Preferably, the hydrogen system water pump is symmetrically arranged around the central axis of the fixing table, and the hydrogen system water pump is connected with the hydrogen system electric pile through a first water pipeline.

[0013] Preferably, the hydrogen system cooling fan is symmetrically arranged around the central axis of the fixing table, and the hydrogen system cooling fan is connected with the hydrogen system water pump through a third water pipeline.

[0014] Compared with the prior art, the utility model has the advantages that:

[0015] 1、The buffer mechanism is arranged, the fixing frame and the hydrogen system electric pile form an extension structure through the buffer spring, when the device is used, the aircraft will vibrate violently when taking off or landing, and internal components are prone to damage, the vibration generated when the aircraft takes off or lands can be absorbed and buffered through the arrangement of the buffer spring, internal components are protected, and the safety of the device is improved.

[0016] 2、The hydrogen system cooling fan is arranged, the hydrogen fuel cell system is highly integrated, especially the position of the hydrogen system cooling fan, the hydrogen system cooling fan is arranged, the rotor of the aircraft can cool the electric pile, so that the advantages of weight reduction and aesthetics are achieved, and the hydrogen system cooling fan can be angle-adjusted through the rotation shaft control, the size of the heat dissipation amount is controlled by adjusting the increase or decrease of the windward surface, and the practicability of the device is improved. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 It is a structure schematic view of the front appearance of the utility model;

[0018] Figure 2 It is a structure schematic view of the side appearance of the utility model;

[0019] Figure 3It is the structural schematic view of the buffer mechanism of the utility model.

[0020] Figure 4 It is the schematic view of the system electrical principle of the utility model.

[0021] In the drawing: 1, fixed platform;2, buffer mechanism;201, fixed frame;202, limit rod;203, buffer spring;3, hydrogen system electric pile;4, hydrogen system DC / DC2;5, hydrogen bottle;6, fixed sleeve;7, busbar pipeline;8, hydrogen system air compressor;9, air road pipeline;10, hydrogen system water pump;11, first water road pipeline;12, second water road pipeline;13, hydrogen system expansion water tank;14, hydrogen system cooling fan;15, rotating shaft;16, third water road pipeline. DETAILED DESCRIPTION

[0022] The technical scheme in the embodiments of the utility model will be described clearly and completely below in combination with the drawings in the embodiments of the utility model. The embodiments described below with reference to the drawings are exemplary and are only used for explaining the utility model and cannot be understood as limiting the utility model.

[0023] The embodiments will be described below according to the overall structure of the utility model.

[0024] Please refer to Figures 1-4 A hydrogen-lithium mixed power device for aircraft, including fixed platform 1, the outer wall of fixed platform 1 is installed with buffer mechanism 2, buffer mechanism 2 includes fixed frame 201, limit rod 202 and buffer spring 203, the outer wall of fixed platform 1 is installed with fixed frame 201, the inner wall of fixed frame 201 is installed with limit rod 202, the outer wall of limit rod 202 is installed with buffer spring 203, fixed frame 201 is welded with fixed platform 1, fixed frame 201 and fixed platform 1 constitute telescopic structure through buffer spring 203, through the buffer mechanism 2 set, fixed frame 201 and hydrogen system electric pile 3 constitute telescopic structure through buffer spring 203, when using the device, because the aircraft will produce violent vibration when taking off or landing, it is easy to cause internal components damage, and the setting of buffer spring 203 can absorb and buffer the vibration generated when the aircraft takes off or lands, protect internal components and increase the safety of the device.

[0025] Please refer to Figures 1-4The utility model provides a kind of hydrogen lithium mixed power device for aircraft, the top of buffer mechanism 2 is equipped with hydrogen system electric pile 3, the top of hydrogen system electric pile 3 is equipped with hydrogen system DC / DC 24, the outer wall of fixed platform 1 is equipped with hydrogen bottle 5, the outer wall of hydrogen bottle 5 is equipped with fixed sleeve 6, the outer wall of hydrogen bottle 5 is equipped with busbar pipeline 7, the bottom of fixed platform 1 is equipped with hydrogen system air compressor 8, the outer wall of hydrogen system air compressor 8 is equipped with air path pipeline 9, hydrogen bottle 5 is fixed in the tail end of aircraft by fixed sleeve 6 screw, hydrogen bottle 5 is connected with hydrogen system electric pile 3 by busbar pipeline 7, hydrogen system air compressor 8 is fixed in fixed platform 1 by screw, hydrogen system air compressor 8 is connected with hydrogen system electric pile 3 by air path pipeline 9.

[0026] Please refer to Figures 1-4 The utility model provides a kind of hydrogen lithium mixed power device for aircraft, the bottom of fixed platform 1 is equipped with hydrogen system water pump 10, one side of hydrogen system water pump 10 is equipped with first water path pipeline 11, the other side of hydrogen system water pump 10 is equipped with second water path pipeline 12, the outer wall of second water path pipeline 12 is equipped with hydrogen system expansion tank 13, the lateral wall of fixed platform 1 is equipped with hydrogen system cooling fan 14, the outer wall of hydrogen system cooling fan 14 is equipped with rotating shaft 15, the outer wall of hydrogen system cooling fan 14 is equipped with third water path pipeline 16, hydrogen system water pump 10 is symmetrically arranged with the center axis of fixed platform 1, hydrogen system water pump 10 is connected with hydrogen system electric pile 3 by first water path pipeline 11, hydrogen system cooling fan 14 is symmetrically arranged with the center axis of fixed platform 1, hydrogen system cooling fan 14 is connected with hydrogen system water pump 10 by third water path pipeline 16, by the setting of hydrogen system cooling fan 14, the system is highly integrated to hydrogen fuel cell system, especially the position of integrated hydrogen system cooling fan 14, the electric pile heat dissipation of the utility model fuel cell, the rotor of aircraft can be cooled to electric pile by the arrangement of hydrogen system cooling fan 14, so as to achieve the advantages, such as weight reduction, beautiful, and hydrogen system cooling fan 14 can be controlled by rotating shaft 15 Angle adjustment, the size of heat dissipation is controlled by the increase or decrease of windward surface, increase the practicability of device.

[0027] Working principle: in use, first of all, the device is moved to the desired position, then due to the aircraft will produce violent vibration when taking off or landing, easy to cause internal components damage, and the setting of the buffer spring 203, can absorb the vibration generated when the aircraft takes off or lands, protect internal components, increase the safety of the device, then through the arrangement of the hydrogen system cooling fan 14, let the rotor of the aircraft carry out heat dissipation to the electric pile, so as to achieve the advantages of weight reduction, beautiful, and the hydrogen system cooling fan 14 can be controlled by the shaft 15 to adjust the angle, by adjusting the increase or decrease of the windward surface to control the size of the heat dissipation, increase the practicability of the device, then the output of the hydrogen system electric pile 3 is directly connected with the input of the hydrogen system DC / DC 24, and the hydrogen system DC / DC 24 is internally integrated with FCU, precharge circuit, residual hydrogen discharge, auxiliary road output function, finally, the hydrogen system air compressor 8, the hydrogen system water pump 10 and the hydrogen system cooling fan 14 are connected with the auxiliary power supply interface of the hydrogen system DC / DC 24, the circuit system connection of the device is completed, and the device is used normally, so the use process of the device is completed, and the contents not described in detail in the specification belong to the prior art known to those skilled in the art.

[0028] The terms "center", "longitudinal", "transverse", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, which is only a simplified description for the convenience of describing the utility model, and does not indicate or imply that the indicated device or element must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the protection scope of the utility model.

[0029] Although the utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement to part of the technical features, any modification, equivalent replacement, improvement, etc. within the spirit and principle of the utility model should be included in the protection scope of the utility model.

Claims

1. A hydrogen-lithium hybrid power plant for an aircraft, comprising a fixed platform (1), characterized in that: The outer wall of the fixed platform (1) is provided with a buffer mechanism (2); The top of the buffer mechanism (2) is provided with a hydrogen system electric pile (3), the top of the hydrogen system electric pile (3) is provided with a hydrogen system DC / DC2 (4), the outer wall of the fixed platform (1) is provided with a hydrogen bottle (5), the outer wall of the hydrogen bottle (5) is provided with a fixing sleeve (6), the outer wall of the hydrogen bottle (5) is provided with a busbar pipeline (7), the bottom of the fixed platform (1) is provided with a hydrogen system air compressor (8), and the outer wall of the hydrogen system air compressor (8) is provided with an air pipeline (9); The bottom of the fixed platform (1) is provided with a hydrogen system water pump (10), one side of the hydrogen system water pump (10) is provided with a first water pipeline (11), the other side of the hydrogen system water pump (10) is provided with a second water pipeline (12), the outer wall of the second water pipeline (12) is provided with a hydrogen system expansion tank (13), the side wall of the fixed platform (1) is provided with a hydrogen system cooling fan (14), the outer wall of the hydrogen system cooling fan (14) is provided with a rotating shaft (15), and the outer wall of the hydrogen system cooling fan (14) is provided with a third water pipeline (16).

2. The hydrogen-lithium hybrid battery device for aircraft according to claim 1, characterized in that: The buffer mechanism (2) comprises a fixing frame (201), a limiting rod (202) and a buffer spring (203), the outer wall of the fixed platform (1) is provided with the fixing frame (201), the inner wall of the fixing frame (201) is provided with the limiting rod (202), and the outer wall of the limiting rod (202) is provided with the buffer spring (203).

3. The hydrogen-lithium hybrid power plant for aircraft as claimed in claim 2 wherein: The fixing frame (201) is welded with the fixed platform (1), and the fixing frame (201) and the fixed platform (1) form an extension structure through the buffer spring (203).

4. The hydrogen-lithium hybrid power plant for aircraft as claimed in claim 1 wherein: The hydrogen bottle (5) is threadedly fixed at the tail end of the aircraft through the fixing sleeve (6), and the hydrogen bottle (5) is connected with the hydrogen system electric pile (3) through the busbar pipeline (7).

5. The hydrogen-lithium hybrid power plant for aircraft as claimed in claim 1 wherein: The hydrogen system air compressor (8) is threadedly fixed with the fixed platform (1), and the hydrogen system air compressor (8) is connected with the hydrogen system electric pile (3) through the air pipeline (9).

6. The hydrogen-lithium hybrid power plant for aircraft as claimed in claim 1 wherein: The hydrogen system water pump (10) is centrally symmetrically arranged about the central axis of the fixed platform (1), and the hydrogen system water pump (10) is connected with the hydrogen system electric pile (3) through the first water pipeline (11).

7. The hydrogen-lithium hybrid power plant for aircraft as claimed in claim 1 wherein: The hydrogen system cooling fan (14) is centrally symmetrically arranged about the central axis of the fixed platform (1), and the hydrogen system cooling fan (14) is connected with the hydrogen system water pump (10) through the third water pipeline (16).

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