阅读说明：本技术 一种用于氢能飞机的储氢罐体安装支架结构 (Hydrogen storage tank mounting support structure for hydrogen energy aircraft ) 是由 张永杰 陈巨 于 2021-10-19 设计创作，主要内容包括：本发明属于飞行器技术领域,涉及一种用于氢能飞机的储氢罐体安装支架结构,至少两个支撑体,间隔设置；连接杆,至少有一个,位于相邻的两个支撑体之间,连接杆的两端分别与相邻的两个支撑体垂直固定；其中,支撑体包括：第一环片；第二环片,和第一环片通过连接件连接,第二环片和第一环片拼合后成整环；支撑结构,设置在第二环片上,用于实现对储氢罐体的支撑。本发明本体质量小,可满足飞机的轻量化要求,同时可承受飞机起飞、着陆和飞行时候遇到的冲击载荷,并且限制储氢罐体的各个方向的自由度,以保证储氢罐体不和飞机发生相对运动,从而导致飞机重心变化,安装支架和储氢罐体结构上设置的缓冲结构,使得其整体具有缓冲能力,可靠性高。(The invention belongs to the technical field of aircrafts, and relates to a hydrogen storage tank mounting bracket structure for a hydrogen energy aircraft, which comprises at least two support bodies arranged at intervals; at least one connecting rod is positioned between the two adjacent supporting bodies, and two ends of each connecting rod are respectively and vertically fixed with the two adjacent supporting bodies; wherein, the support body includes: a first ring segment; the second ring piece is connected with the first ring piece through a connecting piece, and the second ring piece and the first ring piece are spliced to form an integral ring; and the supporting structure is arranged on the second ring piece and used for supporting the hydrogen storage tank body. The invention has the advantages that the weight of the body is small, the requirement of the airplane on light weight can be met, impact load encountered during takeoff, landing and flying of the airplane can be borne, the freedom degree of the hydrogen storage tank body in each direction is limited, the hydrogen storage tank body is prevented from moving relative to the airplane, the gravity center of the airplane is changed, and the installation support and the buffering structure arranged on the hydrogen storage tank body structure ensure that the whole body has buffering capacity and high reliability.)

1. A hydrogen storage tank mounting bracket structure for a hydrogen-powered aircraft, comprising:

at least two supporting bodies which are arranged at intervals;

at least one connecting rod is positioned between the two adjacent supporting bodies, and two ends of each connecting rod are respectively and vertically fixed with the two adjacent supporting bodies;

wherein the support body includes:

a first ring segment (1);

the second ring piece (2) is connected with the first ring piece (1) through a connecting piece (4), and the second ring piece (2) and the first ring piece (1) are spliced to form a whole ring;

and the supporting structure is arranged on the second ring piece (2) and used for supporting the hydrogen storage tank body (6).

2. A hydrogen storage tank mounting bracket structure for a hydrogen-powered aircraft according to claim 1, characterized in that said support structure comprises two sets of symmetrically arranged resilient shock-absorbing support structures (5).

3. A hydrogen storage tank mounting bracket structure for a hydrogen-powered aircraft according to claim 2, characterized in that said elastic shock-absorbing support structure (5) comprises:

the connecting block (5-1) is fixed with the second ring piece (2);

the cylinder body (5-2) is vertically arranged, is positioned on one side, away from the second ring piece (2), of the connecting block (5-1), and is fixed with the connecting block (5-1);

the support (5-3) comprises a base body and a rod body arranged above the base body, the rod body is vertically arranged, and one end of the rod body, which is far away from the base body, is inserted into the barrel body (5-2);

the elastic piece (5-4) is sleeved on the cylinder body (5-2) and clamped between the seat body and the connecting block (5-1).

4. A hydrogen storage tank mounting bracket structure for a hydrogen-powered aircraft according to claim 1, characterized in that the first ring plate (1) and the second ring plate (2) are L-shaped in cross-section.

5. A hydrogen storage tank mounting bracket structure for a hydrogen-powered aircraft according to claim 4, characterized in that the thickness of the first ring segment (1) is smaller than the thickness of the second ring segment (2).

6. A hydrogen storage tank mounting bracket structure for a hydrogen-powered aircraft according to claim 1, further comprising a lateral limiting structure provided on the hydrogen storage tank (6).

7. A hydrogen storage tank mounting bracket structure for a hydrogen-powered aircraft according to claim 6, characterized in that the transverse limiting structure comprises at least two baffles (7) symmetrically arranged, one end of each baffle (7) is fixed with the hydrogen storage tank (6), and the distance between two baffles (7) is matched with the distance between two adjacent support bodies.

8. A hydrogen storage tank mounting bracket structure for a hydrogen-powered aircraft according to claim 7, characterized in that the baffle plate (7) is provided with at least one lightening hole.

9. A hydrogen storage tank mounting bracket structure for a hydrogen powered aircraft as claimed in claim 1, wherein there are three of said tie rods and they are evenly spaced between two supports.

Technical Field

The invention belongs to the technical field of aircrafts, and particularly relates to a hydrogen storage tank mounting support structure for a hydrogen energy aircraft.

Background

The traditional fuel aviation develops to the present day, the technical aspects are mature, and the fuel engine and the fuel tank system of the airplane tend to be perfect. However, in the world with increasingly scarce global energy, low-carbon economy is in a rapidly developing environment, and the aviation field with huge fuel consumption has to be changed to adapt to the global large trend.

Hydrogen is the best energy found by human beings at present, and the advantages of huge reserves, high efficiency, no pollution and no emission are increasingly paid more and more attention from various countries, and the hydrogen can be generated by adopting electrolyzed water in a simple acquisition mode, so that the hydrogen can provide continuous energy for the human beings.

To date, the airlines' good and research institutes in some countries have introduced their own solutions for validating aircraft on hydrogen energy sources:

for example, the hydrogen storage device of the sparrow testing machine flying by Chinese bushels has the structure that the hydrogen storage tank is designed to be consistent with the size of a machine body, a skin of the machine body is used for wrapping a hydrogen storage tank body, a support structure is not adopted, the machine body is equivalent to the hydrogen storage tank, and wings and other parts are arranged on the hydrogen storage tank body. The load of the airplane during landing is transferred from the landing frame to the airplane body, and is equivalent to the load directly acting on the hydrogen storage tank body. According to the structure, most of the airplane body is filled with the hydrogen storage tank, in the flying process of the airplane body, acting force applied to the airplane body can directly act on the hydrogen storage tank through the skin without buffering, and serious consequences such as deformation leakage and even explosion of the hydrogen storage tank can be caused when large load is faced.

And a high-pressure hydrogen storage tank is adopted for quickly charging the airplane, and a plurality of small hydrogen storage tanks are arranged on the back row seats of the airplane in an overlapped mode and are arranged together by using a simple fixing device. However, it does not take into account the problem of crash when they are placed together, and the aircraft is subjected to a lot of loads during flight, resulting in acceleration of the aircraft in all directions, which may cause the hydrogen tanks to interact, as well as risk of deformation of the hydrogen tanks; in addition, since the hydrogen storage devices of the submachine 8-300 aircraft are all arranged at the rear of the aircraft body, and the weight of the hydrogen storage devices is larger than that of a fuel storage system, different from the fuel of a traditional fuel-powered aircraft, the weight of the hydrogen storage devices is deviated from the center of gravity of the aircraft, so that the stability of the aircraft is reduced, and the balance of the center of gravity of the aircraft is needed, and more weight cost can be paid.

Disclosure of Invention

In view of the above, the present invention provides a mounting bracket structure for a hydrogen storage tank of a hydrogen powered aircraft to solve the above-mentioned technical problems.

The technical scheme of the invention is as follows:

a hydrogen storage tank mounting bracket structure for a hydrogen powered aircraft, comprising:

at least two supporting bodies which are arranged at intervals;

at least one connecting rod is positioned between the two adjacent supporting bodies, and two ends of each connecting rod are respectively and vertically fixed with the two adjacent supporting bodies;

wherein the support body includes:

a first ring segment;

the second ring piece is connected with the first ring piece through a connecting piece, and the second ring piece and the first ring piece are spliced to form a whole ring;

and the supporting structure is arranged on the second ring piece and used for supporting the hydrogen storage tank body.

Preferably, the support structure comprises two sets of elastic shock-absorbing support structures which are symmetrically arranged.

Preferably, the elastic shock-absorbing support structure includes:

the connecting block is fixed with the second ring plate;

the cylinder is vertically arranged, is positioned on one side of the connecting block, which is far away from the second ring piece, and is fixed with the connecting block;

the support comprises a base body and a rod body arranged above the base body, the rod body is vertically arranged, and one end of the rod body, which is far away from the base body, is inserted into the barrel body;

the elastic piece is sleeved on the cylinder body and clamped between the seat body and the connecting block.

Preferably, the first ring piece and the second ring piece are L-shaped in cross section.

Preferably, the thickness of the first ring piece is smaller than the thickness of the second ring piece.

Preferably, the hydrogen storage tank further comprises a transverse limiting structure, and the transverse limiting structure is arranged on the hydrogen storage tank body.

Preferably, the transverse limiting structure comprises at least two baffles which are symmetrically arranged, one end of each baffle is fixed with the hydrogen storage tank body, and the distance between the two baffles is matched with the distance between the two adjacent supporting bodies.

Preferably, the baffle plate is provided with at least one lightening hole.

Preferably, the number of the connecting rods is three, and the connecting rods are uniformly distributed between the two supporting bodies.

The invention provides a hydrogen storage tank body mounting bracket structure for a hydrogen energy aircraft, which adopts an L-shaped beam with a simple structure as a support body to carry out structural bearing design, uses a structure of the support body formed by a first ring sheet and a second ring sheet to fix the radial freedom degree of the hydrogen storage tank body, transfers all loads of takeoff, landing and flying of the aircraft to the hydrogen storage tank through the support body, uses a connecting rod to connect adjacent support bodies for fixing the support bodies, and is favorable for improving the stability degree of the bracket by a triangular stable structure formed by the connecting rod; meanwhile, the structure that the hydrogen storage tank body is connected by using the mounting support structure avoids the direct action of the load of the machine body on the hydrogen storage tank body. The elastic shock absorption supporting structure is fixed below the two supporting bodies, so that impact load on the machine body and the hydrogen storage tank body is greatly reduced, the stability of the structure is enhanced, and too much weight is not increased; the transverse limiting structure arranged on the hydrogen storage tank body limits the axial freedom degree of the hydrogen storage tank, the mode completes the limitation of the axial freedom degree of the hydrogen storage tank body with the minimum weight cost, and single load is transferred under the conditions of takeoff of an airplane and the like. The invention can bear the load of the hydrogen storage tank body in the flying process, and limits the freedom degree of the hydrogen storage tank body in each direction so as to ensure that the hydrogen storage tank body does not move relative to the airplane, thereby ensuring the stability of the center of gravity of the airplane. The elastic damping support structure arranged on the mounting support and the hydrogen storage tank body structure enables the whole body to have buffering capacity and can bear impact load encountered during takeoff, landing and flying of an airplane. The support provided by the invention is used as a structure on an airplane, the weight of the body is small, the light weight requirement of the structure can be met, the practicability is strong, and the support is worthy of popularization.

Drawings

FIG. 1 is a schematic view of the present invention in use;

FIG. 2 is a schematic view of a portion of the present invention in the configuration of FIG. 1;

FIG. 3 is a partial schematic view of the present invention 2;

FIG. 4 is a cross-sectional view of a portion of the structure of FIG. 2 of the present invention;

FIG. 5 is a partial schematic view of the present invention 3;

FIG. 6 is a partial schematic view of the present invention 4;

FIG. 7 is a partial schematic view of the present invention 5;

fig. 8 is a left side view of the partial structural schematic 5 of the present invention.

Detailed Description

The invention provides a mounting bracket structure of a hydrogen storage tank for a hydrogen energy aircraft, which is described below with reference to the structural schematic diagrams of figures 1 to 8.

Example 1

A hydrogen storage tank body mounting bracket structure for a hydrogen energy aircraft comprises two supporting bodies which are arranged at intervals, three connecting rods are arranged between the two supporting bodies, and two ends of each connecting rod are respectively and vertically fixed with the two adjacent supporting bodies, as shown in figures 1 and 2.

Wherein, three connecting rod specification is the same, because the bearing load that the connecting rod participated in is less, so the intensity requirement to the connecting rod is not high, three connecting rod adopt thin wall steel pipe connect can, the triangle stable structure that three connecting rod formed has strengthened the structural stability of installing support when bearing the impact load when the aircraft lands greatly.

As shown in fig. 1, 2 and 6, the support body comprises a first ring piece 1 and a second ring piece 2, the second ring piece 2 and the first ring piece 1 are connected through a connecting piece 4 and then are spliced into an integral ring, the connecting piece 4 comprises a bolt 4-1 and a nut 4-2, and the bolt 4-1 is fastened by the nut 4-2 after penetrating through the second ring piece 2 and the first ring piece 1. And a support structure is arranged on the second ring piece 2 and used for supporting the hydrogen storage tank body 6.

Wherein, the cross-section of first ring piece 1 and second ring piece 2 is the L type for the mounting bracket is big with the contact surface of hydrogen storage tank body, and the whole aluminum alloy that adopts of mounting bracket designs simultaneously, makes the whole light in weight of mounting bracket, and intensity is high. Secondly, the thickness of the first ring piece is smaller than that of the second ring piece, and the thicknesses of the first ring piece 1 and the second ring piece 2 are designed to be different, so that the weight of the support is reduced as far as possible under the condition that the overall strength of the structure reaches the standard.

More specifically, as shown in fig. 1 and 2, the support structure includes two sets of elastic shock-absorbing support structures 5 arranged symmetrically.

As shown in fig. 3, 4 and 5, the elastic damping support structure 5 includes a connection block 5-1 fixed to the second ring 2, a vertically arranged cylinder 5-2 is provided below the connection block 5-1, and one end of the cylinder 5-2 is fixed to the connection block 5-1. A support 5-3 is arranged below the cylinder 5-2, the support 5-3 comprises a seat body and a rod body arranged above the seat body, the rod body is vertically arranged, and one end of the rod body, which is far away from the seat body, is inserted into the cylinder 5-2; the barrel 5-2 is sleeved with an elastic part 5-4, and the elastic part 5-4 is clamped between the seat body and the connecting block 5-1 and used for realizing integral shock absorption and buffering.

Wherein the elastic member 5-4 is preferably a hard spring, which plays a role of shock absorption.

The elastic damping support structures 5 are totally four and are respectively positioned at the lower sides of the two support bodies, the hollow cylinders welded on the bases, the rod bodies and the cylinder bodies 5-2 form a sleeve structure for limiting the freedom degree of the hard springs, so that the hard springs can only stretch along the direction of the cylinder bodies 5-2 to achieve a stable effect, and the base body is welded with the ground of the machine body to play a role in fixing the whole support.

Furthermore, in order to prevent the axial position of the hydrogen storage tank body on the mounting bracket structure from changing, a transverse limiting structure is arranged on the hydrogen storage tank body 6 to limit the freedom degree of the hydrogen storage tank body along the tank body direction. The transverse limiting structure is contacted with the second ring piece on the mounting support structure, and the two planes are mutually coupled to transfer load.

As shown in fig. 7 and 8, the transverse limiting structure comprises at least two baffles 7 which are symmetrically arranged and used for transmitting loads in positive and negative directions, one end of each baffle 7 is fixed with the hydrogen storage tank body 6, and the distance between the two baffles 7 is matched with the distance between two adjacent supporting bodies.

Furthermore, two digging holes are adopted on the baffle 7 for reducing weight, and after strength checking is carried out, the weight of the mounting bracket is reduced under the condition of ensuring the structural strength of the baffle 7.

The hydrogen storage tank mounting support structure for the hydrogen energy aircraft can bear the load of the hydrogen storage tank in the flight process, and limits the freedom degree of the hydrogen storage tank in each direction so as to ensure that the hydrogen storage tank does not move relative to the aircraft, thereby ensuring the stability of the gravity center of the aircraft. The elastic damping support structure arranged on the mounting support and the hydrogen storage tank body structure enables the whole body to have buffering capacity and can bear impact load encountered during takeoff, landing and flying of an airplane. The support provided by the invention is used as a structure on an airplane, the weight of the body is small, the light weight requirement of the structure can be met, the practicability is strong, and the support is worthy of popularization.

The above disclosure is only for the preferred embodiments of the present invention, but the embodiments of the present invention are not limited thereto, and any variations that can be made by those skilled in the art are intended to fall within the scope of the present invention.