Propellant management device and storage box of space launch vehicle

Abstract

The utility model provides a propellant management device of an aerospace vehicle, which comprises an anti-collapse cover plate, a propellant management device and a propellant management device, the partition plates are arranged on the inner wall of the storage tank above the anti-collapse cover plate at intervals in the height direction of the storage tank; the exhaust pipe is vertically arranged right above the anti-collapse cover plate, the height of the top of the exhaust pipe is slightly higher than that of the partition plate, and the anti-collapse cover plate and the partition plate are both provided with porous capillary screens. According to the device, propellant storage is achieved through a simple structure, and consumption of the propellant sinking to the bottom is reduced.

Description

Technical Field

[0001] The utility model relates to the field of aerospace tanks, in particular to a propellant management device and a tank for a space vehicle. Background Art

[0002] In reusable space vehicles, forward thrust is usually used to manage propellant in a microgravity space environment. This method will cause the space vehicle to consume too much attitude control propellant, reducing the space vehicle's carrying capacity.

[0003] In view of this, there is an urgent need to design a propellant management device and a tank for a space launch vehicle that has a simple structure and does not consume too much bottom-sinking propellant. Utility Model Content

[0004] The utility model aims to overcome the deficiencies of the prior art and provide a propellant management device and a tank for a space vehicle.

[0005] The utility model provides a propellant management device for a space vehicle, comprising: an anti-collapse cover plate, which is arranged on the bottom wall of a tank around a port of a tank delivery pipe; a partition plate, which is arranged on the inner wall of the tank above the anti-collapse cover plate at intervals in the height direction of the tank; an exhaust pipe, which is vertically arranged just above the anti-collapse cover plate, the top height of the exhaust pipe is slightly higher than the height of the partition plate, and the anti-collapse cover plate and the partition plate are both provided with porous capillary screens.

[0006] According to one embodiment of the present application, the height of the partition is set slightly lower than the liquid level of the propellant before the secondary ignition of the space vehicle, ensuring that the propellant liquid level covers the partition in the initial state.

[0007] According to one embodiment of the present application, the exhaust pipe is arranged at a central axis position of the tank.

[0008] According to one embodiment of the present application, the propellant management device and tank of the space launch vehicle also include: a first screen, which is arranged in a circle of a first diameter with the center of the partition as the center, and the first diameter is smaller than the diameter of the tank to ensure that the propellant liquid level in the initial state covers the first screen.

[0009] According to one embodiment of the present application, the propellant management device and tank of the space launch vehicle also include: a second screen, which is matched and arranged above the exhaust pipe, the diameter of the second screen is the inner diameter of the exhaust pipe, and the installation height of the second screen is flush with the installation height of the first screen to ensure that the propellant liquid level covers the second screen in the initial state.

[0010] According to one embodiment of the present application, the propellant management device and tank of the space vehicle further include: a third screen, which is formed by extending downward from the edge of the anti-collapse cover plate, and the third screen is located between the anti-collapse cover plate and the bottom wall of the tank.

[0011] According to one embodiment of the present application, the aperture of the first sieve is smaller than the aperture of the second sieve.

[0012] According to one embodiment of the present application, the bubble rupture point of the first screen is greater than the bubble rupture point of the second screen.

[0013] According to one embodiment of the present application, an angle between the plane of the anti-collapse cover plate and the exhaust pipe is greater than 90 degrees.

[0014] On the other hand, the present application also provides a tank of a space vehicle, comprising the above-mentioned propellant management device of the space vehicle.

[0015] The present application uses the first screen on the partition to isolate the gas and liquid of the propellant in the tank, thereby realizing the retention function of the propellant. The third screen and the anti-collapse cover can filter impurities in the tank on the one hand, and can serve as a thermal buffer zone to intercept local heat leakage on the other hand, and can block the bubbles generated by the downstream heat leakage from diffusing into the propellant in the tank, thereby rendering the retention function of the first screen ineffective; the anti-collapse cover is designed with a certain inclination angle, which is beneficial to prevent the bubbles generated downstream from gathering in the anti-collapse cover, ensuring that the propellant near the outlet below the anti-collapse cover is in a non-air-entrained state when the engine is started for the second time, thereby improving the safety and reliability of the secondary working section of the space vehicle engine.

[0016] It should be understood that the above general description and the following specific embodiments are only exemplary and illustrative and are not intended to limit the scope of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The following drawings are a part of the specification of the present utility model, which illustrate exemplary embodiments of the present utility model. The attached drawings and the description of the specification are used to explain the principle of the utility model.

[0018] Figure 1 It is a schematic diagram of a propellant management device for a space vehicle according to an embodiment of the utility model;

[0019] Figure 2 is a schematic diagram of a propellant management device for a space vehicle according to another embodiment of the utility model;

[0020] Figure 3 It is a schematic diagram of a screen in a propellant management device of a space vehicle according to an embodiment of the utility model.

[0021] Reference numerals:

[0022] 100 - anti-collapse cover plate, 101 - third screen, 200 - partition, 201 - first screen, 202 - second screen, 300 - exhaust pipe. DETAILED DESCRIPTION

[0023] The features and exemplary embodiments of various aspects of the present invention will be described in detail below. In order to make the purpose, technical solutions and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain the present invention and are used to illustrate the principles of the present invention, and are not configured to limit the present invention. In addition, the structural components in the drawings are not necessarily drawn to scale. For example, the sizes of some structural components or areas in the drawings may be enlarged for other structural components or areas to help understand the embodiments of the present invention.

[0024] The directional words appearing in the following description are all directions shown in the figures, and do not limit the specific structure of the embodiments of the utility model. In the description of the utility model, it should be noted that, unless otherwise specified, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be directly connected or indirectly connected through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above terms in the utility model can be understood according to the specific circumstances.

[0025] In addition, the terms "include", "comprise", "have" or any other variations thereof are intended to cover non-exclusive inclusion, so that a structure or component including a series of elements includes not only those elements, but also other mechanical elements that are not explicitly listed or inherent in the structure or component. In the absence of more restrictions, the elements defined by the sentence "include..." do not exclude the existence of other identical elements in the article or device including the elements.

[0026] Spatially related terms such as "below", "beneath", "under", "low", "above", "on", "high", etc. are used to facilitate description to explain the positioning of one element relative to a second element, indicating that these terms are intended to cover different orientations of the device in addition to orientations different from those shown in the figures. In addition, for example, "one element is above / below another element" can mean that the two elements are in direct contact, or that there are other elements between the two elements. In addition, terms such as "first", "second", etc. are also used to describe various elements, regions, parts, etc., and should not be regarded as limiting. Similar terms represent similar elements throughout the description.

[0027] For those skilled in the art, the present invention can be implemented without some of these specific details. The following description of the embodiments is only intended to provide a better understanding of the present invention by showing examples of the present invention.

[0028] Figure 1 It is a schematic diagram of a propellant management device for a space vehicle according to an embodiment of the utility model; Figure 2 is a schematic diagram of a propellant management device for a space vehicle according to another embodiment of the utility model; Figure 3 It is a schematic diagram of a screen in a propellant management device of a space vehicle according to an embodiment of the utility model.

[0029] like Figure 1 As shown, the utility model provides a propellant management device for a space launch vehicle, comprising: an anti-collapse cover plate 100, which is arranged on the bottom wall of the tank around the port of the tank delivery pipe; a partition plate 200, which is arranged on the inner wall of the tank above the anti-collapse cover plate 100 at intervals in the height direction of the tank; an exhaust pipe 300, which is vertically arranged directly above the anti-collapse cover plate 100, and the anti-collapse cover plate 100 and the partition plate 200 are both provided with porous capillary screens.

[0030] Specifically, Figure 3 As shown, a liquid film will be formed on the porous capillary screen surface of the anti-collapse cover plate 100 and the partition plate 200 after being infiltrated with the propellant. When there is a certain pressure difference on both sides of the gas-liquid interface, the gas-liquid interface on each pore will be curved at the microscopic level, and the liquid film will prevent the gas from passing through the screen, thereby achieving gas-liquid separation. Based on the setting of the porous capillary screen of the anti-collapse cover plate 100 and the partition plate 200 in the present application, the gas above the screen cannot enter the propellant below the screen, and at the same time, the propellant below the screen cannot pass through the screen into the air pillow above the screen, thereby playing the role of propellant retention.

[0031] Specifically, when there is heat leakage near the outlet of the tank in the space vehicle, gas will be generated in the propellant. Other reasons for the generation of gas in the propellant will not be described in detail herein. In the embodiment of the present application, the gas in the propellant will not pass through the screens on the anti-collapse cover 100 and the partition 200. The gas will rise along the exhaust pipe 300 in the middle of the anti-collapse cover 100 and gather under the screen inside the exhaust pipe 300. When the gas gathers to a certain amount, the bubbles will break through the screen inside the exhaust pipe 300 under the action of the bottom sinking force and be discharged into the air pillow. The screen on the anti-collapse cover 100 can prevent the gas from passing through, effectively preventing the gas in the propellant from affecting the screen on the partition 200, and ensuring the gas-liquid separation function of the screen of the partition 200.

[0032] like Figure 2As shown, according to one embodiment of the present application, the height of the partition 200 is set slightly lower than the liquid level of the propellant before the secondary ignition of the space vehicle.

[0033] According to one embodiment of the present application, the exhaust pipe 300 is disposed at the central axis position of the tank, for example, the exhaust pipe 300 may coincide with the central axis.

[0034] According to one embodiment of the present application, the propellant management device and tank of the space vehicle further include: a first screen 201, which is arranged in a circle with a first diameter having a center of the partition 200, wherein the first diameter is smaller than the diameter of the tank.

[0035] According to one embodiment of the present application, the propellant management device and tank of the space vehicle also include: a second screen 202, which is matched and arranged above the exhaust pipe 300, and the installation height of the second screen 202 is flush with the installation height of the first screen 201, and the first screen and the second screen are separated by the wall of the exhaust pipe.

[0036] According to one embodiment of the present application, the propellant management device and tank of the space vehicle further include: a third screen 101, which is formed by extending downward from the edge of the anti-collapse cover 100, wherein the third screen 101 is located between the anti-collapse cover 100 and the bottom wall of the tank.

[0037] According to one embodiment of the present application, the aperture of the first sieve 201 is smaller than the aperture of the second sieve 202 .

[0038] According to one embodiment of the present application, the bubble bursting point of the first sieve 201 is greater than the bubble bursting point of the second sieve 202 .

[0039] According to one embodiment of the present application, the angle between the plane of the anti-collapse cover plate 100 and the exhaust pipe 300 is greater than 90 degrees.

[0040] On the other hand, the present application also provides a tank of a space vehicle, comprising the above-mentioned propellant management device of the space vehicle.

[0041] Specifically, the first screen 201 on the partition 200 and the second screen 202 in the exhaust pipe 300 are both made of porous capillary materials, and the apertures of the first screen 201 and the second screen 202 are different. When the propellant infiltrates the first screen 201 and the second screen 202, the liquid film on the gas-liquid interface on the aperture presents a curved surface shape. Figure 3 As shown in Figure 1, assuming that the main curvature radius of the liquid film surface is R, the pressure difference on both sides of the liquid film is:

[0042] ΔP=P1-P2=2σ / R

[0043] In the above formula, σ is the surface tension coefficient of the liquid film medium. The maximum pressure difference that the liquid film on the porous capillary screen can withstand is called the bubble rupture point, and its value is usually determined by experiments. If the pressure difference on both sides of the aperture in the screen is lower than the corresponding bubble rupture point, the gas above the screen cannot pass through the aperture of the screen to reach the propellant below, thereby achieving gas-liquid separation and then achieving propellant retention.

[0044] The installation height of the partition 200 is set according to the propellant liquid level before the secondary start of the engine, so as to ensure that the propellant completely infiltrates the first screen 201 and the second screen 202 during the secondary start of the space vehicle. The porous capillary element set at the first diameter with the center of the partition 200 as the center of the outer wall of the exhaust pipe 300 is the first screen 201, and the porous capillary element inside the exhaust pipe 300 that is flush with the installation height of the first screen 201 is the second screen 202. The aperture of the first screen 201 is smaller than the aperture of the second screen 202, the bubble breaking point of the first screen 201 is greater than the bubble breaking point of the second screen 202, and the first screen 201 and the second screen 202 are separated by the wall of the exhaust pipe 300.

[0045] In a specific scenario, the propellant management device of the present application can still keep the propellant under the partition 200 under different accelerations. a 、a e 、a l They represent bottom acceleration, reverse acceleration and lateral acceleration respectively. e Under this condition, for the first screen 201 and the second screen 202, the pressure difference along their cross sections is 0, which makes it easy to achieve a stable gas-liquid interface. l In order to maintain the propellant inside the propellant management device, the bubble rupture point ΔP of the first screen 201 is required to be 筛1 >ρa l D1, D1 is the first diameter of the partition 200, and the bubble breaking point ΔP of the second screen 202 is required 筛2 >ρa l D2, D2 is the inner diameter of the exhaust pipe 300, and ρ is the density of the propellant.

[0046] When there is a bottom acceleration a a When the spacecraft is in a state of being ...

[0047] The propellant management device of the space vehicle in this application needs to make the best balance for this problem according to the full mission profile and the changes in acceleration in all directions, and seek the optimal design solution, that is, the bubble breaking point of the first screen 201 and the second screen 202 is optimally selected to ensure that the propellant management device can achieve both propellant retention and exhaust. The device can ensure that there is more propellant retention, and improve the safety and reliability of the secondary working section of the space vehicle engine.

[0048] In one embodiment, the angle between the plane of the anti-collapse cover plate 100 and the exhaust pipe 300 is greater than 90 degrees, and the anti-collapse cover plate 100 is a convex cone relative to the outlet of the delivery pipe, which is conducive to the bubbles generated in the downstream of the sliding section to float smoothly along the exhaust pipe 300 in the middle of the anti-collapse cover plate 100 under the action of the bottom force and penetrate the second screen 202 to be discharged into the air pillow, ensuring that the propellant near the outlet below the anti-collapse cover plate 100 is in a non-air-entrained state when the engine is started again. When the anti-collapse cover plate 100 is about to end the flight of the space vehicle, the liquid level of the tank propellant is shallow, the flow rate near the outlet of the delivery pipe is fast, and the flow rate near the tank wall is low. The middle liquid level will show a concave trend. The anti-collapse cover plate 100 can support the propellant near the outlet of the delivery pipe, reduce the radial velocity distribution difference, delay the air entrainment moment of the propellant at the outlet, reduce the volume of unusable propellant in the tank, and improve the carrying capacity of the space vehicle.

[0049] It should be noted that the third screen 101 plays the role of filtering impurities in the propellant in the tank, and can also serve as a thermal buffer to intercept local heat leakage, block the gas generated by downstream heat leakage from diffusing into the propellant in the tank, and avoid causing the retention function of the first screen 201 to fail.

[0050] The propellant management device of the space vehicle in this embodiment can ensure that most of the propellant always sinks to the bottom during the gliding process, and can effectively control the range of change of the propellant center of mass. In addition, with the propellant management device of this application, a smaller positive thrust can be used for exhaust before the engine is restarted, and the propellant consumption required for the engine to sink to the bottom during the gliding phase is relatively small, which is suitable for long-term gliding conditions. The device comprehensively considers the propellant management, exhaust function, filtering function and anti-collapse function of the gliding phase, and significantly improves the success rate of liquid space vehicle recovery.

[0051] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A propellant management device for a space vehicle, characterized in that: include: An anti-collapse cover plate is arranged on the bottom wall of the tank around the port of the tank delivery pipe; Partitions, which are arranged at intervals on the inner wall of the tank above the anti-collapse cover plate in the height direction of the tank; The exhaust pipe is vertically arranged just above the anti-collapse cover plate, and the top height of the exhaust pipe is slightly higher than the height of the partition plate. The anti-collapse cover plate and the partition plate are both provided with porous capillary screens.

2. The propellant management device for a space launch vehicle according to claim 1, characterized in that: The height at which the partition is arranged is slightly lower than the liquid level of the propellant before the secondary ignition of the space vehicle.

3. The propellant management device for a space launch vehicle according to claim 1, characterized in that: The exhaust pipe is arranged at the central axis position of the tank.

4. The propellant management device for a space launch vehicle according to claim 3, characterized in that: Also includes: The first screen is arranged in a circle with a first diameter and a center of the partition plate as the center, and the first diameter is smaller than the diameter of the storage tank.

5. The propellant management device for a space launch vehicle according to claim 4, characterized in that: Also includes: The second screen is matched and arranged above the exhaust pipe. The diameter of the second screen is the inner diameter of the exhaust pipe. The installation height of the second screen is flush with the installation height of the first screen. The first screen and the second screen are separated by the wall of the exhaust pipe.

6. The propellant management device for a space launch vehicle according to claim 5, characterized in that: Also includes: The third screen is formed by extending downward from the edge of the anti-collapse cover plate, and the third screen is located between the anti-collapse cover plate and the bottom wall of the storage tank.

7. The propellant management device for a space launch vehicle according to claim 6, characterized in that: The aperture of the first mesh is smaller than the aperture of the second mesh.

8. The propellant management device for a space launch vehicle according to claim 6, characterized in that: The bubble bursting point of the first screen is greater than the bubble bursting point of the second screen.

9. The propellant management device for a space launch vehicle according to claim 1, characterized in that: The angle between the plane of the anti-collapse cover plate and the exhaust pipe is greater than 90 degrees.

10. A tank for a space launch vehicle, characterized in that: A propellant management device for a space launch vehicle comprising the propellant management device as described in any one of claims 1 to 9.

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