Rocket low-temperature propellant supercooling pipeline and filling system
By setting up a spiral heat exchange pipeline and a multi-layer heat exchange structure in the rocket low-temperature propellant supercooling pipeline, combined with the insulation layer, the problem of low-temperature propellant evaporation is solved, efficient cooling and retention of propellant is achieved, and rocket launch is reduced cost.
Patent Information
- Application Number
- CN202422946900.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-02
- Publication Date
- 2024-12-31
- Estimated Expiration
- 2034-12-02
AI Technical Summary
Low-temperature propellants are prone to evaporation during storage, transport and filling, resulting in loss of propellants, and the prior art is difficult to effectively reduce their evaporation.
Design a rocket cryogenic propellant supercooling pipeline, including the main pipe and a spiral first heat exchange pipeline, for transporting coolant to cool the propellant, and reduce evaporation through a multi-layer heat exchange structure and insulation layer, including convexity A top cover and a third heat exchange pipe to improve heat exchange area and efficiency.
It effectively reduces the evaporation of low-temperature propellant, improves the retention rate of propellant, reduces the rocket launch cost, and improves the multiple ignition capacity of propellant.
Smart Images
Figure CN222276803U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the field of rocket filling, in particular to a rocket cryogenic propellant supercooling pipeline and a filling system. Background Art
[0002] Rocket propellants mainly include solid propellants, liquid propellants and solid-liquid mixed propellants. Solid rockets cannot be re-ignited and the recovery technology is relatively complicated. Therefore, the current rocket recovery technology at home and abroad mainly revolves around liquid rockets.
[0003] Cryogenic propellants have the following advantages: First, high specific impulse. Cryogenic propellants have low combustion temperatures, small specific heat capacity, and fast movement speed of combustion product molecules, which enables unit mass of propellant to generate greater thrust; second, high density, so that the same volume of tanks can store more propellants, thereby increasing the rocket's payload; third, high safety. Cryogenic propellants have low combustion temperatures, relatively stable combustion products, and are not prone to explosions and other dangerous situations; fourth, environmental protection. Cryogenic propellants generally do not contain toxic and harmful substances in their combustion products, and have less interference with the environment; fifth, they can be ignited multiple times. By controlling the liquid entering the combustion chamber, multiple ignitions of the engine can be achieved. However, cryogenic propellants need to be kept in liquid form for a long time at extremely low ambient temperatures. During the storage, transportation, and filling processes, cryogenic propellants are prone to evaporation, resulting in propellant loss.
[0004] In order to reduce the evaporation of cryogenic propellant, it is particularly important to design a rocket cryogenic propellant supercooling pipeline. Utility Model Content
[0005] The utility model aims to overcome the deficiencies of the prior art and provide a rocket cryogenic propellant supercooling pipeline and a filling system.
[0006] The utility model provides a rocket cryogenic propellant supercooling pipeline, comprising: a main pipeline and a first heat exchange pipeline, wherein the first heat exchange pipeline is arranged inside the main pipeline; the first heat exchange pipeline is spirally arranged along the axial direction of the main pipeline, and the first heat exchange pipeline is spaced apart from the inner side surface of the main pipeline; the main pipeline is used to transport cryogenic propellant, and the first heat exchange pipeline is used to transport coolant to cool the cryogenic propellant in the main pipeline.
[0007] According to an embodiment of the utility model, it also includes a second heat exchange pipe, which is a straight pipe; along the axial direction of the first heat exchange pipe, the second heat exchange pipe runs through the inner space spirally wrapped by the first heat exchange pipe; the second heat exchange pipe is used to transport coolant.
[0008] According to an embodiment of the utility model, it comprises a plurality of first heat exchange pipes with different spiral outer diameters; the first heat exchange pipes with smaller outer diameters are arranged in the inner space spirally surrounded by the first heat exchange pipes with larger outer diameters, and are arranged at intervals from each other.
[0009] According to one embodiment of the utility model, the inlet of the first heat exchange pipe is arranged close to the outlet of the main pipe, and the outlet of the first heat exchange pipe is arranged close to the inlet of the main pipe, so that the coolant in the first heat exchange pipe and the propellant in the main pipe flow in the opposite direction.
[0010] According to an embodiment of the present invention, along the flow direction of the propellant in the main pipeline, the spiral density of the first heat exchange pipeline gradually increases.
[0011] According to one embodiment of the utility model, outward convex top covers are provided at both ends of the main pipeline; the outward convex top cover is provided with an opening for low-temperature propellant to flow in or out; a third heat exchange pipeline is provided near the inner side surface of the outward convex top cover, and the third heat exchange pipeline is connected with the first heat exchange pipeline to transport the coolant.
[0012] According to one embodiment of the utility model, the third heat exchange pipe includes a first circular tube and a second circular tube arranged at intervals along the axial direction of the main pipe, and the first circular tube and the second circular tube are arranged in parallel; the first circular tube and the second circular tube are provided with a plurality of branch pipes along their circumferential direction, and the two ends of the branch pipes are respectively connected to the first circular tube and the second circular tube; the third heat exchange pipe as a whole is adapted to the inner side surface of the outward convex top cover.
[0013] According to an embodiment of the utility model, a heat-insulating layer is arranged on the outer side of the main pipeline, and the heat-insulating layer adopts polyurethane foam material to insulate the main pipeline.
[0014] According to an embodiment of the utility model, a vacuum layer is provided between the thermal insulation layer and the main pipeline to insulate the main pipeline.
[0015] On the other hand, the utility model provides a rocket cryogenic propellant supercooling filling system, comprising the above-mentioned supercooling pipeline and a cryogenic propellant storage unit; the inlet of the main pipeline is connected to the cryogenic propellant storage unit, and the outlet of the main pipeline is connected to the rocket tank, so as to cool the cryogenic propellant supplied by the cryogenic propellant storage unit and then fill it into the rocket tank.
[0016] According to the carrier rocket tank bottom heat treatment supercooling pipeline of the utility model, by arranging the first heat exchange pipeline inside the main pipeline, the low-temperature propellant can be cooled to reduce the evaporation of the low-temperature propellant.
[0017] 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
[0018] 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.
[0019] Figure 1 This is a perspective view of a rocket cryogenic propellant supercooling pipeline according to an embodiment of the utility model;
[0020] Figure 2 This is a three-dimensional diagram of a rocket cryogenic propellant supercooling pipeline according to an embodiment of the utility model;
[0021] Figure 3 It is a cross-sectional view of a rocket cryogenic propellant supercooling pipeline according to one embodiment of the utility model;
[0022] Figure 4 It is a three-dimensional diagram of a first heat exchange pipe of an embodiment of the utility model;
[0023] Figure 5 This is a three-dimensional diagram of a rocket cryogenic propellant supercooling pipeline according to an embodiment of the utility model;
[0024] Figure 6 It is a three-dimensional diagram of a third heat exchange pipe of an embodiment of the utility model;
[0025] Figure 7 is a cross-sectional view of a third heat exchange pipe of an embodiment of the utility model;
[0026] Figure 8 A three-dimensional diagram of a supercooling pipeline for transporting cryogenic propellant of a rocket according to an embodiment of the utility model.
[0027] Description of reference numerals:
[0028] 1-main pipeline; 2-first heat exchange pipeline; 3-outward convex top cover; 4-second heat exchange pipeline; 5-connecting part; 6-vacuum layer; 7-insulation layer; 8-third heat exchange pipeline; 31-opening; 81-first circular tube; 82-second circular tube; 83-branch pipe. DETAILED DESCRIPTION
[0029] 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.
[0030] 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.
[0031] 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.
[0032] 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 do not specifically refer to the meaning of order or sequence, and should not be regarded as limiting. Similar terms are used throughout the description to represent similar elements.
[0033] In the process of describing the present utility model below, in certain scene descriptions, only "rocket", "launch vehicle", "spacecraft", "space launch vehicle" or "missile" may be used. This is only for the convenience of description, and its connotation is not limited to the specific words used. Generally, the rocket of the present utility model includes not only space launch vehicles for carrying satellites or spacecraft or other probes, but also various types of missiles, rockets and other weapons for carrying military payloads, as well as similar products that can send payloads into the air. When interpreting the above specific words, those skilled in the art shall not limit the rocket to only one of the space launch vehicles or missiles based on the specific words used to describe the scene, thereby narrowing the scope of protection of the present utility model.
[0034] 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.
[0035] Figure 1 This is a perspective view of a rocket cryogenic propellant supercooling pipeline according to an embodiment of the utility model; Figure 2 This is a three-dimensional diagram of a rocket cryogenic propellant supercooling pipeline according to an embodiment of the utility model; Figure 3 It is a cross-sectional view of a rocket cryogenic propellant supercooling pipeline according to one embodiment of the utility model; Figure 4 It is a three-dimensional diagram of a first heat exchange pipe of an embodiment of the utility model; Figure 5 This is a three-dimensional diagram of a rocket cryogenic propellant supercooling pipeline according to an embodiment of the utility model; Figure 6 It is a three-dimensional diagram of a third heat exchange pipe of an embodiment of the utility model; Figure 7 is a cross-sectional view of a third heat exchange pipe of an embodiment of the utility model; Figure 8 A three-dimensional diagram of a supercooling pipeline for transporting cryogenic propellant of a rocket according to an embodiment of the utility model.
[0036] like Figure 1-3 As shown, the utility model provides a rocket cryogenic propellant supercooling pipeline, comprising: a main pipeline 1 and a first heat exchange pipeline 2, wherein the first heat exchange pipeline 2 is arranged inside the main pipeline 1. The first heat exchange pipeline 2 is spirally arranged along the axial direction of the main pipeline 1, and the first heat exchange pipeline 2 is spaced apart from the inner side surface of the main pipeline 1. The main pipeline 1 is used to transport cryogenic propellant, and the first heat exchange pipeline 2 is used to transport coolant to cool the cryogenic propellant in the main pipeline 1.
[0037] The supercooling pipeline of this embodiment can cool the cryogenic propellant and reduce the evaporation loss of the cryogenic propellant by arranging the spiral first heat exchange pipeline 2 inside the main pipeline 1.
[0038] According to one embodiment of the utility model, in addition to the main pipeline 1 and the first heat exchange pipeline 2, the subcooling pipeline also includes a second heat exchange pipeline 4, and the second heat exchange pipeline 4 is a straight pipe. Along the axial direction of the first heat exchange pipeline 2, the second heat exchange pipeline 4 runs through the inner space of the first heat exchange pipeline 2 spirally wrapped. The second heat exchange pipeline 4 is used to transport the coolant.
[0039] The supercooling pipe of this embodiment can effectively increase the heat exchange area between the cryogenic propellant and the coolant, and improve the heat exchange efficiency. For example, the second heat exchange pipe 4 can be connected to the first heat exchange pipe 2, or be independently provided.
[0040] According to an embodiment of the present invention, the supercooling pipe includes a plurality of first heat exchange pipes 2 with different spiral outer diameters. The first heat exchange pipes 2 with smaller outer diameters are arranged in the inner space spirally surrounded by the first heat exchange pipes 2 with larger outer diameters and are arranged at intervals from each other.
[0041] According to one embodiment of the utility model, the inlet of the first heat exchange pipe 2 is arranged close to the outlet of the main pipe 1, and the outlet of the first heat exchange pipe 2 is arranged close to the inlet of the main pipe 1, so that the coolant in the first heat exchange pipe 2 and the propellant in the main pipe 1 flow in the opposite direction.
[0042] In this embodiment, the flow direction of the coolant in the first heat exchange pipe 2 is opposite to the flow direction of the propellant in the main pipe, which can improve the cooling effect of the propellant.
[0043] like Figure 4 As shown, according to one embodiment of the present invention, along the flow direction of the propellant in the main pipeline 1, the spiral density of the first heat exchange pipeline 2 gradually increases.
[0044] In this embodiment, for example, increasing the spiral density of the first heat exchange pipe 2 near the outlet of the main pipe 1 can effectively improve the cooling effect of the propellant at the outlet of the main pipe 1 .
[0045] like Figure 5-7 As shown, according to one embodiment of the utility model, both ends of the main pipeline 1 are provided with an outward convex cover 3. The outward convex cover 3 is provided with an opening 31 for the cryogenic propellant to flow in or out. A third heat exchange pipeline 8 is provided near the inner side of the outward convex cover 3, and the third heat exchange pipeline 8 is connected with the first heat exchange pipeline 2 to transport the coolant.
[0046] The supercooling pipe of this embodiment can increase the heat exchange area between the cryogenic propellant and the coolant and improve the heat exchange efficiency by providing an outward convex top cover 3 and providing a third heat exchange pipe 8 near the outward convex top cover 3. For example, the third heat exchange pipe 8 can be connected to the first heat exchange pipe 2 and / or the second heat exchange pipe 4.
[0047] like Figure 6 and 7As shown, according to one embodiment of the utility model, the third heat exchange pipe 8 includes a first round pipe 81 and a second round pipe 82 arranged axially spaced apart from each other along the main pipe 1, and the first round pipe 81 and the second round pipe 82 are arranged in parallel. The first round pipe 81 and the second round pipe 82 are provided with a plurality of branch pipes 83 along their circumferential direction, and the two ends of the branch pipe 83 are respectively connected to the first round pipe 81 and the second round pipe 82. The third heat exchange pipe 8 as a whole is adapted to the inner side surface of the convex top cover 3.
[0048] The supercooling pipe of this embodiment can further increase the heat exchange area between the coolant and the propellant and improve the cooling effect by providing a third heat exchange pipe 8 that is compatible with the inner side surface of the convex top cover 3 and providing an overall cooling structure of parallel pipes and branch pipes.
[0049] like Figure 3 As shown, according to one embodiment of the utility model, a heat-insulating layer 7 is arranged on the outer side of the main pipeline 1 , and the heat-insulating layer 7 is made of polyurethane foam material to insulate the main pipeline 1 .
[0050] In this embodiment, the thermal insulation layer 7 can reduce the heat exchange between the cryogenic propellant and the external environment, thereby ensuring the cooling effect of the cryogenic propellant.
[0051] like Figure 3 As shown, according to one embodiment of the present utility model, a vacuum layer 6 is provided between the insulation layer 7 and the main pipeline 1 to insulate the main pipeline 1 .
[0052] The supercooling pipeline of this embodiment can further reduce the heat exchange between the cryogenic propellant and the external environment by adding the vacuum layer 6.
[0053] On the other hand, the utility model provides a rocket cryogenic propellant supercooling filling system, comprising the above-mentioned supercooling pipeline and the cryogenic propellant storage unit. The inlet of the main pipeline 1 is connected to the cryogenic propellant storage unit, and the outlet of the main pipeline 1 is connected to the rocket tank, so as to cool the cryogenic propellant supplied by the cryogenic propellant storage unit and then fill it into the rocket tank.
[0054] The supercooled filling system of this embodiment can effectively reduce propellant evaporation and lower the launch cost of the rocket by providing a supercooling pipe to cool the cryogenic propellant.
[0055] like Figure 8 As shown, the openings 31 at both ends of the convex top cover 3 are respectively provided with detachable connecting parts 5. Both ends of the connecting part 5 are connected, and are used to communicate with the cryogenic propellant storage unit and the rocket tank to fill the rocket tank.
[0056] The above-mentioned embodiments of the present invention can be combined with each other and have corresponding technical effects.
[0057] 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 rocket cryogenic propellant supercooling pipeline, characterized in that: include: A main pipeline and a first heat exchange pipeline, wherein the first heat exchange pipeline is arranged inside the main pipeline; the first heat exchange pipeline is spirally arranged along the axial direction of the main pipeline, and the first heat exchange pipeline is spaced apart from the inner side surface of the main pipeline; the main pipeline is used to transport cryogenic propellant, and the first heat exchange pipeline is used to transport coolant to cool the cryogenic propellant in the main pipeline.
2. The subcooling pipe according to claim 1, characterized in that: It also includes a second heat exchange pipe, which is a straight pipe. Along the axial direction of the first heat exchange pipe, the second heat exchange pipe runs through the inner space of the first heat exchange pipe spirally wrapped. The second heat exchange pipe is used to transport coolant.
3. The subcooling pipe according to claim 1, characterized in that: It comprises a plurality of first heat exchange pipes with different spiral outer diameters; the first heat exchange pipes with smaller outer diameters are arranged in the inner space spirally surrounded by the first heat exchange pipes with larger outer diameters, and are arranged at intervals from each other.
4. The subcooling pipe according to claim 1, characterized in that: The inlet of the first heat exchange pipe is arranged close to the outlet of the main pipe, and the outlet of the first heat exchange pipe is arranged close to the inlet of the main pipe, so that the coolant in the first heat exchange pipe and the propellant in the main pipe flow in the opposite direction.
5. The subcooling pipe according to claim 1, characterized in that: Along the flow direction of the propellant in the main pipeline, the spiral density of the first heat exchange pipeline gradually increases.
6. The subcooling pipe according to claim 1, characterized in that: Outwardly convex top covers are arranged at both ends of the main pipeline; the outwardly convex top covers are provided with openings for low-temperature propellant to flow in or out; a third heat exchange pipeline is arranged near the inner side surface of the outwardly convex top cover, and the third heat exchange pipeline is connected with the first heat exchange pipeline to transport coolant.
7. The subcooling pipe according to claim 6, characterized in that: The third heat exchange pipe includes a first circular tube and a second circular tube which are spaced apart along the axial direction of the main pipe, and the first circular tube and the second circular tube are arranged in parallel; the first circular tube and the second circular tube are provided with a plurality of branch tubes along their circumferential direction, and the two ends of the branch tubes are respectively connected to the first circular tube and the second circular tube; the third heat exchange pipe as a whole is adapted to the inner side surface of the outward convex top cover.
8. The subcooling pipe according to claim 1, characterized in that: A heat-insulating layer is arranged on the outer side of the main pipeline, and the heat-insulating layer is made of polyurethane foam material.
9. The subcooling pipe according to claim 8, characterized in that: A vacuum layer is arranged between the thermal insulation layer and the main pipeline.
10. A rocket cryogenic propellant supercooling filling system, characterized in that: It comprises a supercooling pipeline and a cryogenic propellant storage unit as described in any one of claims 1 to 9; the inlet of the main pipeline is connected to the cryogenic propellant storage unit, and the outlet of the main pipeline is connected to a rocket tank, so as to cool the cryogenic propellant supplied by the cryogenic propellant storage unit and then fill it into the rocket tank.