阅读说明：本技术 一种贮箱、低温推进剂集成流体系统和飞行器 (Storage tank, low-temperature propellant integrated fluid system and aircraft ) 是由 罗颢文 魏一 唐文 刘兴睿 张晓颖 熊宴斌 于 2021-10-08 设计创作，主要内容包括：本发明提供的贮箱和低温推进剂集成流体系统以及飞行器,包括：外壳体,包括冷却层和隔热层,所述冷却层设置在所述隔热层内侧；容纳腔,由所述外壳体围成,适于容纳推进剂流体；所述冷却层包括环绕所述容纳腔设置的冷却管,适于容纳低温流体。通过在贮箱的外壳体上分别设置冷却层和隔热层,内侧冷却层内的低温流体,通过吸收热量来保证容纳腔内的推进剂流体处于低温环境下,有效降低推进剂的蒸发量,同时结合隔热层的设置,隔离外壳体自外向内传递的热量,克服现有技术中贮箱隔热性能差,其容纳的推进剂蒸发损失大的缺陷。(The invention provides a tank and low-temperature propellant integrated fluid system and an aircraft, comprising: the outer shell comprises a cooling layer and a heat insulation layer, and the cooling layer is arranged on the inner side of the heat insulation layer; a containment chamber, bounded by the outer housing, adapted to contain a propellant fluid; the cooling layer includes a cooling tube disposed around the containment chamber and adapted to contain a cryogenic fluid. The outer shell of the storage tank is respectively provided with the cooling layer and the heat insulation layer, low-temperature fluid in the inner side cooling layer can be ensured to be in a low-temperature environment by absorbing heat, the evaporation capacity of propellant is effectively reduced, and meanwhile, the heat transmitted from outside to inside of the outer shell is isolated by combining the arrangement of the heat insulation layer, so that the defects that the heat insulation performance of the storage tank is poor and the evaporation loss of the propellant contained in the storage tank is large in the prior art are overcome.)

1. A tank, comprising:

the outer shell comprises a cooling layer (11) and a heat insulation layer, wherein the cooling layer (11) is arranged on the inner side of the heat insulation layer;

a containment chamber (15) enclosed by the outer casing, suitable for containing a propellant fluid;

the cooling layer (11) comprises a plurality of cooling pipes (111) arranged around the containing cavity (15), the cooling pipes (111) being adapted to contain a cryogenic fluid.

2. A tank according to claim 1, characterized in that said cooling pipes (111) are arranged in a uniformly spaced spiral along said containment chamber (15), said cryogenic fluid being adapted to flow unidirectionally along said cooling pipes (111).

3. A tank according to claim 1 or 2, characterized in that the thermally insulating layer comprises a graded layer (12), which graded layer (12) is arranged outside the cooling layer (11), the density of the thermally insulating layer increasing in a direction away from the cooling layer (11).

4. A tank according to claim 3, characterized in that said insulating layer further comprises a sprayed foam layer (13), said sprayed foam layer (13) being arranged between said cooling layer (11) and said graded layer (12).

5. A tank according to claim 4, characterized in that it further comprises a vacuum layer (14), said vacuum layer (14) being arranged inside said cooling layer (11), adjacent to said containment chamber (15).

6. A cryogenic propellant integrated fluid system comprising:

-at least two tanks according to any of claims 1 to 5, respectively a first tank (1) and a second tank (2), suitable for containing respectively a first fluid as propellant and a second fluid at a higher temperature than the first fluid, the cooling layers (11) of both the first tank (1) and the second tank (2) being placed in communication with the containing chamber (15) of the first tank (1);

a first power unit (4) which is communicated with the accommodating chambers (15) of the first storage tank (1) and the second storage tank (2);

an ignition part (5) arranged on the first power part (4) and suitable for starting the first power part (4);

the pressure control device comprises a first pressure control piece (7) and a second pressure control piece (8), wherein the first pressure control piece (7) is communicated with the ignition part (5) and a cooling layer (11) of the second storage box (2) respectively, and the second pressure control piece (8) is communicated with an accommodating cavity (15) of the ignition part (5) and the second storage box (2).

7. The cryogenic propellant integrated fluid system of claim 6, further comprising:

and the second power part (6) is respectively connected with the first pressure control piece (7) and the second pressure control piece (8) and is suitable for being matched with the first power part (4).

8. The cryogenic propellant integrated fluid system according to claim 6, further comprising a gas storage assembly comprising a first gas storage means (9) and a second gas storage means (10), the first gas storage means (9) being arranged at a downstream end of the first control pressure (7) and the second gas storage means (10) being arranged at a downstream end of the second control pressure (8).

9. Cryogenic propellant integrated fluid system according to any of claims 6-8, wherein the first tank (1) is further connected with a driving means (3), the driving means (3) being adapted to drive the first fluid from the receiving cavity (15) of the first tank (1) into the cooling layer (11) of the first tank (1).

10. The integrated fluid system for low temperature propellants according to claim 9, characterized in that the first control pressure member (7) and the second control pressure member (8) are booster pumps.

11. An aircraft comprising the cryogenic propellant integrated fluid system of any of claims 6 to 10.

Technical Field

The invention relates to the technical field of aerospace, in particular to a storage tank, a low-temperature propellant integrated fluid system and an aircraft.

Background

The consumption of battery and propellant carried by the conventional oxyhydrogen-powered upper-level aircraft increases rapidly with the on-track time and the number of starts, and the weight and volume consumption thereby becomes a bottleneck limiting the implementation of tasks.

At present, the prior art provides a scheme for integrally managing various fluids in a higher-level aircraft to fully utilize evaporated gaseous propellant generated by external heat leakage, which is called an integrated fluid system, and the system integrates original mutually independent subsystems, utilizes oxyhydrogen propellant and evaporated gas thereof in a main storage tank, combines the technology of an oxyhydrogen internal combustion engine, comprehensively manages fluids and energy sources on the aircraft, realizes an auxiliary power system with integrated functions, and effectively and comprehensively utilizes low-temperature propellant.

However, the above-mentioned prior art tank has poor heat insulating properties and a large evaporation loss of the propellant contained therein.

Disclosure of Invention

The technical problem underlying the present invention is therefore to overcome the poor thermal insulation of the tanks of the prior art oxyhydrogen-powered vehicles of the above class, and to provide a tank, a cryogenic propellant integrated fluid system and a vehicle.

The present invention provides a storage tank comprising: the outer shell comprises a cooling layer and a heat insulation layer, and the cooling layer is arranged on the inner side of the heat insulation layer; a containment chamber, bounded by the outer housing, adapted to contain a propellant fluid; the cooling layer includes a cooling tube disposed around the containment chamber and adapted to contain a cryogenic fluid.

The cooling pipes are spirally arranged along the containing cavity at uniform intervals, and the low-temperature fluid is suitable for flowing along the cooling pipes in a single direction.

The heat insulation layer comprises a gradient layer, the gradient layer is arranged on the outer side of the cooling layer, and the density of the heat insulation layer is gradually increased along the direction far away from the cooling layer.

The heat insulation layer further comprises a spraying foam layer, and the spraying foam layer is arranged between the cooling layer and the gradual change layer.

The storage box further comprises a vacuum layer, wherein the vacuum layer is arranged on the inner side of the cooling layer and is adjacent to the containing cavity.

The present invention also provides a cryogenic propellant integrated fluid system comprising: at least two of the above-mentioned tanks, respectively a first tank and a second tank, adapted to contain respectively a first fluid as propellant and a second fluid at a higher temperature than the first fluid, the cooling layers of both the first tank and the second tank being arranged in communication with the containing chamber of the first tank;

the first power part is respectively communicated with the accommodating cavities of the first storage tank and the second storage tank;

the ignition part is arranged on the first power part and is suitable for starting the first power part;

and the pressure control device comprises a first pressure control piece and a second pressure control piece, the first pressure control piece is respectively communicated with the ignition part and the cooling layer of the second storage box, and the second pressure control piece is communicated with the ignition part and the accommodating cavity of the second storage box.

The cryogenic propellant integrated fluid system further comprises: and the second power part is respectively connected with the first pressure control part and the second pressure control part and is suitable for being matched with the first power part.

The low-temperature propellant integrated fluid system further comprises a gas storage assembly, wherein the gas storage assembly comprises a first gas storage device and a second gas storage device, the first gas storage device is arranged at the downstream end of the first pressure control piece, and the second gas storage device is arranged at the downstream end of the second pressure control piece.

The first reservoir is further connected to a drive means adapted to drive the first fluid from the receiving chamber of the first reservoir into the cooling layer of the first reservoir.

The first pressure control part and the second pressure control part are booster pumps.

The invention provides an aircraft comprising the low-temperature propellant integrated fluid system.

The technical scheme of the invention has the following advantages:

1. the invention provides a storage tank, comprising: the outer shell comprises a cooling layer and a heat insulation layer, and the cooling layer is arranged on the inner side of the heat insulation layer; a containment chamber, bounded by the outer housing, adapted to contain a propellant fluid; the cooling layer includes a cooling tube disposed around the containment chamber and adapted to contain a cryogenic fluid.

The outer shell of the storage tank is respectively provided with the cooling layer and the heat insulation layer, low-temperature fluid in the inner side cooling layer can be ensured to be in a low-temperature environment by absorbing heat, the evaporation capacity of propellant is effectively reduced, and meanwhile, the heat transmitted from outside to inside of the outer shell is isolated by combining the arrangement of the heat insulation layer, so that the defects that the heat insulation performance of the storage tank is poor and the evaporation loss of the propellant contained in the storage tank is large in the prior art are overcome.

2. According to the storage tank provided by the invention, the cooling pipes are spirally arranged along the accommodating cavity at uniform intervals, and the low-temperature fluid is suitable for flowing along the cooling pipes in a single direction.

The setting is the heliciform and is holding the cooling tube that chamber evenly distributed set up, can realize on the one hand the even cooling to holding the chamber, has improved the temperature homogeneity that holds intracavity propellant fluid, and on the other hand, the cooling tube of heliciform setting can realize inside fluidic one-way flow when guaranteeing that the single tube has the area of coverage on a large scale, and then can take away the heat through the fluid of removal high-efficiently.

3. The heat insulation layer comprises a gradient layer, the gradient layer is arranged on the outer side of the cooling layer, and the density of the heat insulation layer is gradually increased along the direction far away from the cooling layer.

Through the insulating layer that sets up the density gradual change, can effectively reduce the weight of insulating layer, reduce the energy consumption of the aircraft that sets up the storage tank, the higher one side of density sets up with external adjacent simultaneously, can effectively reduce the heat conduction, the lower one side of gradual change layer density sets up with the cooling layer is adjacent simultaneously, can reduce the heat that this position goes out the gradual change layer, improves its required heat absorption capacity that heaies up, and then makes whole insulating layer play good heat-insulating effect.

4. The invention provides a low-temperature propellant integrated fluid system, wherein the first storage tank is also connected with a driving device, and the driving device is suitable for driving the first fluid to flow from a containing cavity of the first storage tank into a cooling layer of the first storage tank.

The arrangement is that on one hand, the first fluid flows into the cooling layer and is used as the low-temperature fluid and the propellant fluid at the same time, so that the composite use of the first fluid is realized, the types of the fluid in the system are reduced, and the system structure is simplified.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.

FIG. 1 is a schematic structural diagram of a cryogenic propellant integrated fluid system provided in an embodiment of the present invention;

FIG. 2 is a schematic and partially enlarged view of the internal portion of the reservoir of the cryogenic propellant integrated fluid system of FIG. 1;

FIG. 3 is a schematic view of the internal structure of the outer shell of the tank shown in FIG. 2;

FIG. 4 is a schematic structural view of a cooling tube of the outer shell of the tank of FIG. 3 and a schematic structural view of another embodiment;

description of reference numerals:

1-a first tank; 2-a second tank; 3-a drive device; 4-a first power section; 5-an ignition part; 6-a second power section; 7-a first control and compression part; 8-a second control and pressing piece; 9-a first gas storage device; 10-a second gas storage device; 11-a cooling layer; 111-a cooling tube; 12-a graded layer; 13-spraying a foam layer; 14-vacuum layer; 15-containing chamber.

Detailed Description

The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

In addition, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.

As shown in fig. 1 to 4, the present embodiment provides a tank including an outer shell and a housing chamber 15.

The outer shell is cylindrical, the shell wall of the outer shell comprises a cooling layer 11 and a heat insulation layer, and the cooling layer 11 is arranged on the inner side of the heat insulation layer and contains low-temperature fluid; the containment chamber 15 is surrounded by an outer casing, inside which a propellant fluid is contained, the temperature of which in the present embodiment is equal to or higher than the temperature of the cryogenic fluid.

The cooling layer 11 and the heat insulation layer are respectively arranged on the outer shell of the storage tank, low-temperature fluid in the inner side cooling layer 11 guarantees that propellant fluid in the accommodating cavity 15 is in a low-temperature environment through heat absorption, evaporation capacity of propellant is effectively reduced, meanwhile, heat transmitted from outside to inside of the outer shell is isolated by combining the arrangement of the heat insulation layer, and the defects that the storage tank in the prior art is poor in heat insulation performance and evaporation loss of the contained propellant is large are overcome.

The cooling layer 11 comprises a number of cooling tubes 111 arranged around the receiving cavity 15. The cross section of the cooling pipe 111 is not limited, and can be arranged in a prototype or a square shape, as a preferred embodiment, the cross section of the cooling pipe 111 is arranged alternately in a triangular shape and a trapezoidal shape, so that the cooling pipe 111 is arranged in a cylindrical accommodating space with the same size, compared with other shapes, the contact area between the cooling pipe 111 and an adjacent structure is increased, the mutual limiting is realized, and the installation stability of the cooling pipe 111 is enhanced.

In this embodiment, the cooling tubes 111 are arranged in a uniformly spaced spiral along the receiving chamber 15, and the cryogenic fluid is adapted to flow unidirectionally along the cooling tubes 111. The setting is the heliciform and is holding the cooling tube 111 that 15 evenly distributed set up in chamber, can realize the uniform cooling to holding chamber 15 on the one hand, has improved the temperature homogeneity that holds propellant fluid in the chamber 15, and on the other hand, the cooling tube 111 of heliciform setting can realize the one-way flow of inside fluid when guaranteeing that the single tube has the coverage area on a large scale, and then can take away the heat high-efficiently through the fluid of removal.

As an alternative embodiment, the plurality of cooling pipes 111 may be arranged in parallel rings along the circumference of the accommodating chamber 15, or in a cage shape connecting the top and bottom of the outer shell.

The heat insulation layer comprises a gradient layer 12, the gradient layer 12 is arranged on the outer side of the cooling layer 11, and the density of the heat insulation layer is gradually increased along the direction far away from the cooling layer 11. In the present embodiment, the graded layer 12 is divided into three layers, which are a low-density multilayer heat insulating unit, a medium-density multilayer heat insulating unit, and a high-density multilayer heat insulating unit, respectively. Specifically, the gradient layer 12 may be made of a polyurethane heat insulating material.

Through the insulating layer that sets up the density gradual change, can effectively reduce the weight of insulating layer, reduce the energy consumption of the aircraft that sets up the storage tank, the higher one side of density sets up with external adjacent simultaneously, can effectively reduce the heat conduction, the lower one side of gradual change layer 12 density sets up with cooling layer 11 is adjacent simultaneously, can reduce the heat that this position goes out gradual change layer 12, improve its required heat-absorbing capacity that heaies up, and then make whole insulating layer play good heat-insulating effect, in addition, the setting up of gradual change layer 12 can protect inside cooling layer 11, reduce the impact that the cooling layer received, improve overall structure's stability.

The thermal insulation layer further comprises a spray foam layer 13 and a vacuum layer 14, wherein the spray foam layer 13 is arranged between the cooling layer 11 and the gradient layer 12. The vacuum layer 14 is disposed inside the cooling layer 11, adjacent to the accommodation chamber 15. The spraying foam layer is arranged to play a role in heat insulation, and the spraying foam layer 13 is arranged in a fluid form in a spraying mode during installation, so that the outer gradual change layer 12 and the inner cooling layer 11 can be bonded and connected, and the stability of the whole structure is improved. On one hand, the vacuum layer is arranged, so that the cooling layer and the storage tank are internally used for exchanging heat only through heat radiation, the convection phenomenon is avoided, the heat loss is effectively reduced, the cold loss of the storage tank caused by a supporting structure heat bridge between the outer walls of all layers is avoided, and the quality of the low-temperature propellant is ensured.

The embodiment also provides a low-temperature propellant integrated fluid system which comprises two storage tanks, a first power part 4, an ignition part 5 and a pressure control device. As an alternative embodiment, the number of reservoirs may be multiple.

The two tanks are respectively a first tank 1 and a second tank 2, which can respectively contain a first fluid as a propellant and a second fluid with a temperature higher than that of the first fluid, in this embodiment, the first fluid is liquid hydrogen, the second fluid is liquid oxygen, and the temperature of the liquid oxygen is higher than the boiling point of the liquid hydrogen. As an alternative embodiment, the first fluid and the second fluid may be liquid oxygen, methane, or the like, respectively. In the present embodiment, the cooling layer 11 of both the first tank 1 and the second tank 2 is provided in communication with the housing chamber 15 of the first tank 1. The liquid oxygen in the containing cavity of the first storage tank flows into the cooling layer of the first storage tank, plays a role in heat insulation and heat preservation for the liquid oxygen at the inner side of the first storage tank, and after the liquid oxygen flows into the cooling layer of the second storage tank, the temperature of the liquid oxygen is lower than that of the liquid hydrogen in the second storage tank, so that the liquid oxygen further absorbs heat, and meanwhile plays a role in cooling and heat insulation for the liquid hydrogen in the second storage tank.

The first power part 4 is a main engine powered by hydrogen and oxygen, is respectively communicated with the accommodating cavities 15 of the first storage tank 1 and the second storage tank 2, and can directly supply liquid hydrogen and liquid oxygen from the two storage tanks; the ignition section 5, which is provided on the first power section 4, specifically an ignition torch, may start the main engine, which in this embodiment generates starting power by hydrogen and oxygen.

The pressure control device comprises a first pressure control piece 7 and a second pressure control piece 8, wherein the first pressure control piece 7 is respectively communicated with the ignition part 5 and the cooling layer 11 of the second storage box 2, and the second pressure control piece 8 is communicated with the ignition part 5 and the containing cavity 15 of the second storage box 2. The liquid oxygen in the cooling layer 11 of the second storage tank 2 absorbs heat and increases temperature to become oxygen in the process of flowing to the first pressure control piece, and the accommodating cavity 15 of the second storage tank 2 is provided with a gasification device, so that the liquid oxygen flowing out of the accommodating cavity 15 is gasified to become oxygen and then flows to the position of the second pressure control piece 8.

The pressure control device can accurately control the flow rate, pressure, and the like of the hydrogen and oxygen gas entering the ignition portion 5, and in the present embodiment, the first pressure control member 7 and the second pressure control member 8 are specifically a hydrogen booster pump and an oxygen booster pump.

The low-temperature propellant integrated fluid system further comprises a second power part 6, wherein the second power part 6 is specifically an attitude and orbit control engine which is respectively connected with the first pressure control piece 7 and the second pressure control piece 8, can take hydrogen and oxygen as power sources and is matched with the first power part 4 to control the flight attitude and the flight orbit of an aircraft provided with the low-temperature propellant integrated fluid system.

The low-temperature propellant integrated fluid system further comprises a gas storage assembly, the gas storage assembly comprises a first gas storage device 9 and a second gas storage device 10, specifically a hydrogen gas cylinder and an oxygen gas cylinder, the first gas storage device 9 is arranged at the downstream end of the first control pressing part 7, the second gas storage device 10 is arranged at the downstream end of the second control pressing part 8, hydrogen and oxygen can be stored respectively, and the hydrogen and oxygen can be supplied to the second power part and the igniter respectively when needed.

Furthermore, a driving device 3 is connected to the first storage tank 1, and the driving device 3 is specifically a liquid hydrogen circulating pump, and can drive the first fluid to flow into the cooling layer 11 of the first storage tank 1 from the accommodating cavity 15 of the first storage tank 1 and to continue to flow towards the cooling layer 11 of the second storage tank 2 and the first pressure control member 7.

The embodiment also provides an aircraft, particularly a launch vehicle, a space shuttle or a near-earth aircraft and the like, which comprises the low-temperature propellant integrated fluid system.

It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications of the invention may be made without departing from the spirit or scope of the invention.