阅读说明：本技术 氢动力无人驾驶飞行器的储氢容器 (Hydrogen storage container of hydrogen-powered unmanned aerial vehicle ) 是由 亚历山大·恰巴克 于 2020-04-09 设计创作，主要内容包括：本发明公开了氢动力无人驾驶飞行器的储氢容器,涉及氢能源无人机燃料技术领域；为了解决无人机携带氢气有限问题；具体包括微管,所述微管为氢气存储单元,微管的外表面外壁涂覆有易熔材料,所述微管为圆柱形结构,大量尺寸相同的圆柱形微管组成有同一个微管矩阵,微管矩阵截面相同,六个尺寸相同的微管矩阵组成有第一多微管矩阵,四个以上尺寸相同的微管矩阵组成有第二多微管矩阵。本发明通过储氢容器替代现有的储氢瓶,用于给无人机燃料单元供电,可大幅度提高储氢密度,高压储氢,灵活放置,柔性连接等,在不改变飞行容器重量和外部尺寸条件下,解决无人机携带氢气有限、轻量化的问题,延长续航里程和飞行时间。(The invention discloses a hydrogen storage container of a hydrogen-powered unmanned aerial vehicle, and relates to the technical field of hydrogen energy unmanned aerial vehicle fuel; in order to solve the problem that the unmanned aerial vehicle is limited in hydrogen carrying capacity; the hydrogen storage device comprises micropipes, wherein the micropipes are hydrogen storage units, the outer wall of the outer surface of each micropipe is coated with a fusible material, each micropipe is of a cylindrical structure, a large number of cylindrical micropipes with the same size form a same micropipe matrix, the sections of the micropipe matrixes are the same, six micropipe matrixes with the same size form a first multi-micropipe matrix, and more than four micropipe matrixes with the same size form a second multi-micropipe matrix. The invention replaces the existing hydrogen storage bottle with the hydrogen storage container, is used for supplying power to the fuel unit of the unmanned aerial vehicle, can greatly improve the hydrogen storage density, store hydrogen under high pressure, is flexibly placed, is flexibly connected and the like, solves the problems of limited and light hydrogen carried by the unmanned aerial vehicle under the condition of not changing the weight and the external dimension of the flying container, and prolongs the endurance mileage and the flying time.)

1. The hydrogen storage container of the hydrogen-powered unmanned aerial vehicle comprises micropipes and is characterized in that the micropipes are hydrogen storage units, fusible materials are coated on the outer surface outer walls of the micropipes, the micropipes are cylindrical structures, a large number of cylindrical micropipes with the same size form a same micropipe matrix (3), the sections of the micropipe matrices (3) are the same, six micropipe matrices (3) with the same size form a first multi-micropipe matrix (1), and more than four micropipe matrices (3) with the same size form a second multi-micropipe matrix (2).

2. The hydrogen storage vessel of the hydrogen powered unmanned aerial vehicle of claim 1, wherein the microtubes are made of glass, quartz or basalt, and the microtubes have a diameter of 200 μm.

3. The hydrogen storage vessel of a hydrogen powered unmanned aerial vehicle of claim 2, wherein the fusible material is epoxy glue or epoxy rubber.

4. The hydrogen storage container of the hydrogen powered unmanned aerial vehicle of claim 3, wherein the micro tube is a hydrogen storage container of an independent unit, and the hydrogen storage container in the shape of the micro tube is placed in the center of the unmanned aerial vehicle frame.

5. The hydrogen storage container of the hydrogen powered unmanned aerial vehicle of claim 1, wherein the hydrogen storage containers of the first multi-microtubule matrix (1) are symmetrically placed on the frame with the center of the unmanned aerial vehicle as the center and are vertically distributed.

6. The hydrogen storage container of the hydrogen powered unmanned aerial vehicle of claim 5, wherein the hydrogen storage container of the second multi-micro-tube matrix (2) is symmetrically arranged on the frame by taking the center of the unmanned aerial vehicle as a center, and is distributed in a horizontal quadrangle or polygon shape, and the second multi-micro-tube matrix (2) is welded on the outer wall of the frame through metal.

7. The hydrogen storage container for the hydrogen-powered unmanned aerial vehicle as claimed in claim 6, wherein the hydrogen storage container is in the shape of a wound core tube, one or more flexible micro tubes are wound on the surface of the core tube, and the wound core tube is welded to the outer wall of the airframe by metal and is horizontally fixed.

8. The hydrogen storage vessel of a hydrogen powered unmanned aerial vehicle of claim 7, wherein the metal weld is a material that is adhesive and gas impermeable to both glass and core winding, and is In50 Sn.

9. The hydrogen storage vessel of a hydrogen-powered unmanned aerial vehicle as claimed in claim 4, wherein the ratio of the wall thickness of the microtube to the radius of the microtube at the constant section portion is 0.1% to 10%, and the wall thickness of the microtube is less than 10mkm or less than 2 mkm.

10. The hydrogen storage vessel of a hydrogen powered unmanned aerial vehicle of claim 9, wherein the hydrogen storage vessel made of microtubes and microtubes structure is made into a structure of any shape by welding or bonding process.

Technical Field

The invention relates to the technical field of hydrogen energy unmanned aerial vehicle fuel, in particular to a hydrogen storage container of a hydrogen-powered unmanned aerial vehicle.

Background

The aircraft is composed of a multistage telescopic cylinder, a sealing container, a light source, an electric field and a propeller, wherein a hydrogen energy unmanned aerial vehicle generally adopts a fuel cell or a hydrogen fuel engine as a power device, the density of liquid hydrogen is 845 times that of gaseous hydrogen at normal temperature and normal pressure, and the volume energy density of the liquid hydrogen is more than 10 times that of the gaseous hydrogen in compression storage, so most of the hydrogen energy unmanned aerial vehicles in the world currently adopt a liquid hydrogen storage method, the liquid hydrogen storage needs to cool the hydrogen to-253 ℃ to be liquid, and then the liquid hydrogen is stored in a high-vacuum heat insulation container for use, the inner layer of the traditional hydrogen storage container generally adopts a metal material with good hydrogen resistance, such as stainless steel, due to the high requirement of heat insulation design, the weight of the storage container is mainly consumed in the heat insulation design, a microtube structure container can be used as a maintenance and gas storage system under the emergency condition of the aircraft, and, In the aspect of pressure control, proper charging and discharging pressure must be maintained, and the pressure is generally 0.1-1.0 MPa.

Through retrieval, the Chinese patent with the application number of CN201811186277.2 discloses a hydrogen pile electric aircraft, which comprises a proton exchange membrane hydrogen pile, a power storage battery pack, a high-pressure hydrogen storage tank, a high-pressure gas potential energy recovery power generation special pressure reducing valve, a permanent magnet brushless driving motor set and a matched intelligent driving electric control system. The hydrogen pile electric aircraft in the patent has the following defects: if can not form the high pressure in square unmanned aerial vehicle's hollow frame, just can not store up a large amount of hydrogen in inside.

Disclosure of Invention

The invention aims to solve the defects in the prior art and provides a hydrogen storage container of a hydrogen-powered unmanned aerial vehicle.

In order to achieve the purpose, the invention adopts the following technical scheme:

the hydrogen storage container of the hydrogen-powered unmanned aerial vehicle comprises microtubes, wherein the microtubes are hydrogen storage units, the outer walls of the outer surfaces of the microtubes are coated with fusible materials, the microtubes are cylindrical structures, a large number of cylindrical microtubes with the same size form a same microtube matrix, the sections of the microtube matrices are the same, six microtube matrices with the same size form a first multi-microtube matrix, and more than four microtube matrices with the same size form a second multi-microtube matrix.

Preferably: the micro-tube is made of glass, quartz or basalt, and the diameter of the micro-tube is 200 microns.

Preferably: the fusible material is epoxy glue or epoxy rubber.

Preferably: the micro-pipe is a hydrogen storage container of an independent unit, and the hydrogen storage container in the shape of the micro-pipe is placed in the center of the unmanned aerial vehicle frame.

Preferably: the hydrogen storage containers of the first multi-microtubule matrix are symmetrically arranged on the rack by taking the center of the unmanned aerial vehicle as the center and are vertically distributed.

Preferably: the hydrogen storage containers of the second multi-micro-tube matrix are symmetrically arranged on the rack by taking the center of the unmanned aerial vehicle as the center and are distributed in a horizontal quadrangle or polygon shape, and the second multi-micro-tube matrix is welded on the outer wall of the rack through metal.

Preferably: the hydrogen storage container is in a winding core pipe shape, one or more flexible micro pipes are wound on the surface of the core pipe, and the winding core pipe is welded on the outer wall of the rack through metal and is horizontally fixed.

Preferably: the material of the metal welding is a material which has adhesive force to glass and a winding core material and is airtight, and the material is In50 Sn.

Preferably: the ratio of the wall thickness of the microtube to the radius of the microtube at the constant section part is 0.1-10%, and the wall thickness of the microtube is less than 10mkm or less than 2 mkm.

Preferably: the hydrogen storage container made of the microtubes and the multi-microtubes is made into a structure with any shape through a welding or bonding process.

The invention has the beneficial effects that: the micro-tube or multi-micro-tube structure is distributed at each part of the hydrogen storage container, is connected to a hydrogen supply system through a flexible micro-tube bundle and then enters a fuel unit of a power device, the flexible micro-tube and the multi-micro-tube can also be used as a high-pressure hydrogen conveying pipeline from a storage place to the fuel unit, a connecting sleeve is not needed when a route is laid and a turn is needed, because the multi-micro-tube structure is composed of a large number of independent micro-tubes, each micro-tube container for storing hydrogen is an independent unit, the problem that the unmanned aerial vehicle is limited and light in weight when carrying hydrogen is solved, if one micro-tube is damaged, other micro-tubes are not influenced, no danger can occur, and the container of the glass micro-tube structure can safely store the gas under the high-pressure state of more than or equal to 100MPa, the possibility of instantly discharging a large amount of hydrogen into the air under the condition that part of the microtube units have accidents is reduced, and the safety of high-pressure gas storage is improved.

Drawings

FIG. 1 is a schematic diagram of a first multi-microtube matrix structure of a hydrogen storage vessel of a hydrogen powered unmanned aerial vehicle according to the present invention;

FIG. 2 is a schematic diagram of a second multi-microtube matrix structure of a hydrogen storage vessel of a hydrogen powered unmanned aerial vehicle according to the present invention;

FIG. 3 is a schematic view of a micro-tube matrix structure of a hydrogen storage vessel of the hydrogen powered unmanned aerial vehicle according to the present invention;

fig. 4 is a schematic structural view of a hydrogen storage container of the hydrogen powered unmanned aerial vehicle according to the present invention.

In the figure: 1 a first multi-microtubule matrix, 2 a second multi-microtubule matrix, 3 a microtubule matrix, 4 a hydrogen storage vessel.

Detailed Description

The technical solution of the present patent will be described in further detail with reference to the following embodiments.

Reference will now be made in detail to embodiments of the present patent, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are exemplary only for the purpose of explaining the present patent and are not to be construed as limiting the present patent.

In the description of this patent, it is to be understood that the terms "center," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientations and positional relationships indicated in the drawings for the convenience of describing the patent and for the simplicity of description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are not to be considered limiting of the patent.

In the description of this patent, it is noted that unless otherwise specifically stated or limited, the terms "mounted," "connected," and "disposed" are to be construed broadly and can include, for example, fixedly connected, disposed, detachably connected, disposed, or integrally connected and disposed. The specific meaning of the above terms in this patent may be understood by those of ordinary skill in the art as appropriate.