Composite material wound titanium metal diaphragm tank

Abstract

The application relates to the technical field of propellant storage and supply, in particular to a composite material wound titanium metal diaphragm storage tank, which comprises a shell, a metal diaphragm and a supporting ring, wherein the shell comprises a gas cavity shell and a liquid cavity shell which are welded together; the metal diaphragm is arranged in the interior of the gas cavity shell; a gas cavity is formed between the outer side of the metal diaphragm and the gas cavity shell; a liquid cavity is formed between the inner side of the metal diaphragm and the liquid cavity shell; the supporting ring is arranged in the interior of the gas cavity and is welded and fixed with the metal diaphragm and the gas cavity shell respectively; and a heat insulation coating is arranged between the gas cavity side of the metal diaphragm and the supporting ring. The application realizes the forming of the composite layer of the storage tank by winding reinforcing fibers on the outer side of the storage tank and high-temperature solidification, thereby improving the pressure resistance of the storage tank, reducing the weight of the storage tank, avoiding the influence of high temperature on the propellant, and enabling the high-temperature gas to be successfully extruded to deform the metal diaphragm, so that the propellant without air inclusion is provided for the engine.

Description

Technical Field

[0001] This application relates to the field of propellant storage and supply technology, and more specifically, to a composite material wound titanium metal diaphragm storage tank. Background Technology

[0002] Propulsion tanks are essential pressure vessels commonly used in spacecraft such as satellites, rockets, missiles, and spacecraft. Their main function is to store and supply liquid propellants (including fuel and oxidizer) and high-pressure gases, which are the working media of the propulsion system. Therefore, propulsion tanks account for a large proportion of the mass and volume of the spacecraft's propulsion system, and their performance directly affects the spacecraft's lifespan, pre-packaging performance, accuracy, and launch maneuverability.

[0003] Metal diaphragm tanks are currently the most advanced liquid fuel propellant tanks used in space systems. They are mainly composed of a metal shell and an internal metal diaphragm. There are no non-metallic materials inside, so they are not sensitive to temperature and acceleration. They are more advantageous for spacecraft that frequently change orbits, adjust attitudes frequently, and have high maneuverability.

[0004] With the development of aerospace and weaponry technology, higher and higher requirements are being placed on the performance of aircraft, as well as on the performance of traditional metal diaphragm propellant tanks. In order to reduce the weight of the propellant tank, the structure of the tank needs to be designed to be lightweight. In addition, in order to improve the overall specific impulse of the propulsion system, the hot gas generated by combustion needs to be introduced into the gas chamber of the propellant tank through the gas guide pipe, thereby improving the gas utilization rate and increasing the overall specific impulse of the propulsion system. Summary of the Invention

[0005] This application provides a composite material wound titanium metal diaphragm tank, which can reduce the weight of the tank and deform the internal metal diaphragm under the pressure of high-temperature gas, so as to achieve normal propellant storage and supply.

[0006] To achieve the above objectives, this application provides a composite material wound titanium metal diaphragm storage tank, comprising a shell, a metal diaphragm, and a support ring, wherein: the shell comprises a gas cavity shell and a liquid cavity shell welded together; the metal diaphragm is disposed inside the gas cavity shell; a gas cavity is formed between the outer side of the metal diaphragm and the gas cavity shell; a liquid cavity is formed between the inner side of the metal diaphragm and the liquid cavity shell; the support ring is disposed inside the gas cavity and is welded and fixed to the metal diaphragm and the gas cavity shell respectively; a heat insulation coating is provided between the gas cavity side of the metal diaphragm and the support ring.

[0007] Furthermore, it also includes a first composite layer, which is spirally wound around the outside of the shell.

[0008] Furthermore, the first composite layer includes reinforcing fibers and a high-temperature resin, wherein: the reinforcing fibers are T1000, T800, T700, or T300; the high-temperature resin is polyimide; and the curing regime of the first composite layer is high-temperature curing, with a curing temperature of 250°C.

[0009] Furthermore, it also includes a mounting flange, which is formed using TC4 and is circumferentially wound around the outside of the first composite layer by the second composite layer.

[0010] Furthermore, the location of the mounting flange's winding area is a flexible, adaptive structure.

[0011] Furthermore, the second composite layer includes reinforcing fibers and a high-temperature resin, wherein: the reinforcing fibers are T1000, T800, T700, or T300; the high-temperature resin is polyimide; and the curing regime of the second composite layer is high-temperature curing, with a curing temperature of 250°C.

[0012] Furthermore, the metal diaphragm is spherical-conical in shape, with a wall thickness of 1mm-2mm, and is made of high-purity titanium (TA1ELI).

[0013] The composite material wound titanium metal diaphragm storage tank provided by the present invention has the following beneficial effects:

[0014] This application improves the pressure resistance of the propellant tank by wrapping reinforcing fibers around the outside of the tank and curing it at high temperature to form a composite layer, while reducing the weight of the tank. The application also sprays heat-insulating material on the side of the internal metal diaphragm gas cavity to block the heat generated by the high-temperature gas in the gas cavity, avoiding the influence of high temperature on the propellant. This allows the high-temperature gas to smoothly compress and deform the metal diaphragm, providing the engine with propellant that does not get trapped. Attached Figure Description

[0015] The accompanying drawings, which form part of this application, are used to provide a further understanding of the application and to make other features, objects, and advantages of the application more apparent. The illustrative embodiments and descriptions of this application are used to explain the application and do not constitute an undue limitation of the application. In the drawings:

[0016] Figure 1 This is a schematic diagram of a composite material wound titanium metal diaphragm storage tank according to an embodiment of this application;

[0017] Figure 2 This is a partial enlarged view of a composite material wound titanium metal diaphragm storage tank provided according to an embodiment of this application;

[0018] Figure 3 This is a schematic diagram of the second composite layer winding region provided according to an embodiment of this application;

[0019] Figure 4This is a schematic diagram of the mounting flange provided according to an embodiment of this application;

[0020] In the figure: 1-Gas chamber shell, 2-Liquid chamber shell, 3-Metal diaphragm, 4-Support ring, 5-Heat insulation coating, 6-First composite layer, 7-Mounting flange, 8-Second composite layer, 9-Wrapping area. Detailed Implementation

[0021] To enable those skilled in the art to better understand the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present application, and not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative effort should fall within the scope of protection of the present application.

[0022] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this application are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate for the embodiments of this application described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0023] In this application, the terms "upper," "lower," "left," "right," "front," "rear," "top," "bottom," "inner," "outer," "middle," "vertical," "horizontal," "lateral," and "longitudinal" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. These terms are primarily for the purpose of better describing this application and its embodiments, and are not intended to limit the indicated device, element, or component to having a specific orientation, or to be constructed and operated in a specific orientation.

[0024] Furthermore, in addition to indicating location or positional relationship, some of the aforementioned terms may also have other meanings. For example, the term "above" may also be used in some cases to indicate a certain dependency or connection relationship. Those skilled in the art can understand the specific meaning of these terms in this application based on the specific circumstances.

[0025] In addition, the term "multiple" should mean two or more.

[0026] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. This application will now be described in detail with reference to the accompanying drawings and embodiments.

[0027] like Figure 1-2 As shown, this application provides a composite material wound titanium metal diaphragm storage tank, including a shell, a metal diaphragm 3, and a support ring 4, wherein: the shell includes a gas cavity shell 1 and a liquid cavity shell 2 welded together; the metal diaphragm 3 is disposed inside the gas cavity shell 1; a gas cavity is formed between the outer side of the metal diaphragm 3 and the gas cavity shell 1; a liquid cavity is formed between the inner side of the metal diaphragm 3 and the liquid cavity shell 2; the support ring 4 is disposed inside the gas cavity and is welded and fixed to the metal diaphragm 3 and the gas cavity shell 1 respectively; a heat insulation coating 5 is provided between the gas cavity side of the metal diaphragm 3 and the support ring 4.

[0028] Specifically, the composite material wound titanium metal diaphragm tank provided in this application embodiment is mainly used for the storage and supply of propellants in various aircraft propulsion systems. By setting a metal diaphragm 3 inside the tank, the tank is divided into a gas chamber and a liquid chamber. Reinforcing fibers are wound on the outside of the tank shell, and the composite layer of the tank is formed by high-temperature curing, thereby improving the pressure resistance of the tank and reducing its weight. Meanwhile, heat insulation material is sprayed on the gas chamber side of the metal diaphragm 3 inside the tank to block the heat generated by the high-temperature gas combustion into the gas chamber, avoiding the influence of high temperature on the propellant. This allows the high-temperature gas combustion to smoothly squeeze and deform the metal diaphragm 3, providing the engine with propellant without air entrapment. The shell constitutes the overall structure of the tank, including a gas chamber shell 1 and a liquid chamber shell 2 welded together. A metal diaphragm 3 is disposed inside the gas chamber shell 1, forming a gas chamber between its outer side and the gas chamber shell 1 for introducing high-temperature combustion gas. A liquid chamber is formed between the inner side of the metal diaphragm 3 and the liquid chamber shell 2 for filling with propellant. A support ring 4 is disposed between the outer side of the metal diaphragm 3 and the gas chamber shell 1 to support the metal diaphragm 3. When the liquid chamber is filled with propellant, the support ring 4 can support the metal diaphragm 3, keeping the metal diaphragm 3 in its initial state. A heat-insulating coating 5 is disposed between the gas chamber side of the metal diaphragm 3 and the support ring 4 to insulate against the heat generated by the high-temperature combustion gas inside the gas chamber, ensuring that the temperature of the propellant medium inside the liquid chamber is always within a safe range.

[0029] More specifically, in this embodiment, before receiving the working command, the gas chamber and liquid chamber need to be evacuated simultaneously, with a vacuum level generally around 10 Pa. After completion, propellant medium is filled into the liquid chamber. At this time, under the action of the support ring 4, the metal diaphragm 3 is always in its initial state. In this embodiment, the tank material is titanium metal, and the parts in contact with the propellant (shell and metal diaphragm 3) are all made of titanium alloy, which is highly compatible with the propellant, thus enabling long-term storage of the propellant. When the working command is received, high-temperature gas enters the gas chamber. Under the pressure of the high-temperature gas, the metal diaphragm 3 flips, squeezing the propellant medium inside the liquid chamber out of the tank and supplying it to the subsequently connected engine through pipelines. During this process, the heat insulation coating 5 between the gas chamber side of the metal diaphragm 3 and the support ring 4 isolates the heat generated by the high-temperature gas inside the gas chamber, ensuring that the temperature of the propellant medium inside the liquid chamber is always within a safe range.

[0030] Furthermore, it also includes a first composite layer 6, which is spirally wound around the outside of the shell.

[0031] Furthermore, the first composite layer 6 includes reinforcing fibers and high-temperature resin, wherein: the reinforcing fibers are T1000, T800, T700, or T300; the high-temperature resin is polyimide; and the curing regime of the first composite layer 6 is high-temperature curing, with a curing temperature of 250°C.

[0032] Specifically, a composite layer is wound around the outside of the tank shell, mainly to improve the tank's pressure resistance and reduce its overall weight. The first composite layer 6 is wound in a spiral manner to achieve geodesic winding. The first composite layer 6 is mainly composed of reinforcing fibers and high-temperature resin. The high-temperature resin is preferably polyimide, and the reinforcing fibers are selected from T1000, T800, T700, or T300 according to the actual situation. The first composite layer 6 is formed by high-temperature curing, and the curing temperature is preferably 250℃.

[0033] Furthermore, such as Figure 3-4 As shown, it also includes a mounting flange 7, which is formed by TC4 and is disposed on the outside of the first composite layer 6 by circumferential winding of the second composite layer 8.

[0034] Furthermore, the winding area 9 of the mounting flange 7 is a flexible structure that follows the movement.

[0035] Furthermore, the second composite layer 8 includes reinforcing fibers and high-temperature resin, wherein: the reinforcing fibers are T1000, T800, T700, or T300; the high-temperature resin is polyimide; and the curing regime of the second composite layer 8 is high-temperature curing, with a curing temperature of 250°C.

[0036] Specifically, the mounting flange 7 is mainly used for connecting and fixing the tank. The tank is assembled and fixed with the corresponding structure of the aircraft propulsion system through the mounting flange 7. Since the tank is required to withstand a large number of dynamic environmental test conditions, the mounting flange 7 is preferably made of TC4 and wound to the outside of the first composite layer 6 through the second composite layer 8. In order to improve the overall strength of the mounting flange 7, the winding area 9 of the mounting flange 7 is designed as a follow-up flexible structure, which is a thin-walled open comb-shaped cylindrical structure that can achieve flexible deformation. Thus, when the tank liner expands, it expands simultaneously with the liner, which can improve the resistance to dynamic environment of the mounting flange 7 and enhance the processability of the winding. In addition, in order to improve the consistency of the tank and maximize the strength of the composite material and improve the overall performance of the mounting flange 7, the material and curing method of the second composite layer 8 are the same as those of the first composite layer 6, but the winding method of the second composite layer 8 is different. It adopts circumferential winding and is set in the winding area 9 of the mounting flange 7, that is, the connection between the gas chamber shell 1 and the liquid chamber shell 2.

[0037] Furthermore, the metal diaphragm 3 is spherical-conical in shape, with a wall thickness of 1mm-2mm, and is made of high-purity titanium (TA1ELI). The metal diaphragm 3 is generally made of corrosion-resistant, high-strength, and easy-to-process / weld materials. In this application, high-purity titanium (TA1ELI) is preferred. The overall shape is spherical-conical, with the bottom welded to the support ring 4, dividing the tank interior into a gas chamber and a liquid chamber. The preferred wall thickness is 2mm.

[0038] Specifically, the composite material wound titanium metal diaphragm 3 storage tank provided in this application embodiment first sprays heat insulation material on the outside of the metal diaphragm 3 to form a heat insulation coating 5. Then, the bottom of the metal diaphragm 3 is welded to the support ring 4, and then welded to the gas chamber shell 1 as a whole, and then welded to the liquid chamber shell 2. After forming, the first composite layer 6 is spirally wound on the outside of the shell. Finally, the mounting flange 7 is circumferentially wound on the outside of the first composite layer 6 through the second composite layer 8 to realize the overall storage tank manufacturing. This solves the problem that conventional metal diaphragm 3 storage tanks are heavy and cannot achieve normal propellant supply by squeezing the metal diaphragm 3 with high-temperature gas. While reducing the overall weight of the storage tank, it also improves the overall performance of the storage tank.

[0039] The above description is merely a preferred embodiment of this application and is not intended to limit this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A composite overwrapped titanium metal liner tank characterized by, Includes a housing, a metal diaphragm, and a support ring, wherein: The housing comprises a gas cavity housing and a liquid cavity housing welded together; The metal diaphragm is disposed inside the air cavity housing; An air cavity is formed between the outer side of the metal diaphragm and the air cavity housing; A liquid cavity is formed between the inner side of the metal diaphragm and the liquid cavity housing; The support ring is disposed inside the air cavity and is welded and fixed to the metal diaphragm and the air cavity shell, respectively. A heat-insulating coating is provided between the air cavity side of the metal diaphragm and the support ring; It also includes a first composite layer, which is spirally wound around the outside of the housing; The first composite layer comprises reinforcing fibers and a high-temperature resin, wherein: The reinforcing fiber is T1000, T800, T700, or T300; The high-temperature resin is polyimide; The first composite layer is cured at high temperature, with a curing temperature of 250°C. It also includes a mounting flange, which is formed using TC4 and is circumferentially wound around the outside of the first composite layer by the second composite layer; The winding area of ​​the mounting flange is a flexible, follow-up structure; The second composite layer comprises reinforcing fibers and a high-temperature resin, wherein: The reinforcing fiber is T1000, T800, T700, or T300; The high-temperature resin is polyimide; The curing process for the second composite layer is high-temperature curing, with a curing temperature of 250°C.

2. The composite-wrapped titanium metal-skinned cryotank of claim 1, wherein, The metal diaphragm is spherical-conical in shape, with a wall thickness of 1mm-2mm, and is made of high-purity titanium (TA1ELI).

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