Propellant management device and storage box for recoverable space launch vehicle

Abstract

The utility model provides a propellant management device capable of recycling a space carrier. The propellant management device comprises at least two circular transverse partition plates which are arranged on the inner wall of a storage box at intervals in the longitudinal direction of the space carrier storage box, and annular plates which are longitudinally arranged between the partition plates. Wherein the partition plate arranged on the bottom layer of the storage box is a first partition plate, the first partition plate is in a hollow circular ring shape, one end opening of the annular plate is in butt joint with the hollow circle of the first partition plate, and the end opening, in butt joint with the first partition plate, of the annular plate is matched with the hollow circle of the first partition plate. According to the device, storage of the propellant is achieved through simple parts.

Description

Technical Field

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

[0002] In a reusable space vehicle, a relatively complex propellant management device is usually configured using the principle of surface tension, and a liquid propellant management method is used in a microgravity environment. This method will lead to a significant increase in the structure and mass of the space vehicle, reducing the carrying capacity of the space vehicle.

[0003] In view of this, there is an urgent need to design a propellant management device and tank for a recoverable space vehicle that is simple in structure, lightweight and has a propellant retention function. Utility Model Content

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

[0005] The utility model provides a propellant management device for a recoverable space vehicle, comprising at least two circular transverse partitions arranged on the inner wall of the space vehicle tank at intervals along the longitudinal direction of the tank, and an annular plate arranged longitudinally between the partitions; wherein the partition arranged at the bottom layer of the tank is a first partition, the first partition is a hollow circular ring, one port of the annular plate is butt-jointed with the hollow circle of the first partition, and the port of the annular plate butt-jointed with the first partition matches the hollow circle of the first partition.

[0006] According to one embodiment of the utility model, the partition includes the first partition, the second partition and the third partition, and the ring plate includes the first ring plate and the second ring plate; the first partition, the second partition and the third partition are continuously spaced from bottom to top on the inner wall of the space vehicle tank, and the radial outer side of each partition is respectively contacted with the inner wall of the space vehicle; the hollow circle diameter of the first partition is the first diameter, and the first ring plate with the first diameter is arranged between the first partition and the second partition; the second ring plate with the first diameter is arranged between the second partition and the third partition.

[0007] According to an embodiment of the utility model, the height at which the first partition is arranged is the liquid level height of the propellant before the secondary ignition of the space vehicle.

[0008] According to an embodiment of the present invention, first small holes are provided on the plate surfaces of the first ring plate and the second ring plate.

[0009] According to an embodiment of the present invention, the diameter of the first small hole is determined according to the negative overload size, the lateral overload size and the engine flow rate.

[0010] According to an embodiment of the present invention, a second small hole is provided in the area between the radial outer side and the first diameter of the second partition plate.

[0011] According to an embodiment of the utility model, the third partition plate is provided with a second penetrating hole in a region within the first diameter.

[0012] According to an embodiment of the present invention, the diameter of the second small hole is determined according to the lateral overload size, the lateral overload size and the engine flow rate.

[0013] According to an embodiment of the utility model, the ring plate is a conical cylinder.

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

[0015] The propellant management device of the recoverable space vehicle in this embodiment generates sway damping through at least two transverse partitions and the longitudinal ring plates therebetween, so that most of the propellant in the gliding section is kept below the uppermost partition, effectively limiting the sway amplitude of the propellant and achieving propellant retention through simple components.

[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 recoverable space vehicle according to an embodiment of the utility model;

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

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

[0021] Figure 4 It is a schematic diagram of a second partition in a propellant management device of a recoverable space vehicle according to an embodiment of the utility model;

[0022] Figure 5 It is a schematic diagram of a third partition in a propellant management device of a recoverable space vehicle according to an embodiment of the utility model;

[0023] Figure 6 It is a schematic diagram of a ring plate in a propellant management device of a recoverable space vehicle according to an embodiment of the utility model.

[0024] Reference numerals:

[0025] 100 - partition plate, 101 - first partition plate, 102 - second partition plate, 103 - third partition plate, 200 - ring plate, 201 - first ring plate, 202 - second ring plate. DETAILED DESCRIPTION

[0026] 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.

[0027] 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.

[0028] 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.

[0029] 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.

[0030] 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.

[0031] Figure 1 It is a schematic diagram of a propellant management device for a recoverable space vehicle according to an embodiment of the utility model; Figure 2 is a schematic diagram of a propellant management device for a recoverable space vehicle according to another embodiment of the utility model; Figure 3 It is a schematic diagram of a first partition in a propellant management device of a recoverable space vehicle according to an embodiment of the utility model; Figure 4 It is a schematic diagram of a second partition in a propellant management device of a recoverable space vehicle according to an embodiment of the utility model; Figure 5 It is a schematic diagram of a third partition in a propellant management device of a recoverable space vehicle according to an embodiment of the utility model; Figure 6 It is a schematic diagram of a ring plate in a propellant management device of a recoverable space vehicle according to an embodiment of the utility model.

[0032] like Figure 1 As shown, the utility model provides a propellant management device for a recoverable space vehicle, comprising at least two circular transverse partitions 100 arranged on the inner wall of the tank X along the longitudinal direction of the space vehicle tank X, and an annular plate 200 arranged longitudinally between the partitions 100; wherein the partition 100 arranged at the bottom layer of the tank X is a first partition 101. The first partition 101 is a hollow annular shape, one port of the annular plate 200 is butted against the hollow circle of the first partition 101, and the port of the annular plate 200 butted against the first partition 101 matches the hollow circle of the first partition 101.

[0033] Specifically, the propellant management device of the recoverable space vehicle in this embodiment can effectively realize the positioning of the propellant in the tank X, provide sufficient propellant for the secondary start of the engine, and the propellant is in a non-air-entrained state. When the propellant in the tank X is under the combined effect of negative overload and lateral overload, such as the separation push rod of the space vehicle or the plume or attitude adjustment action of the second-stage engine, the propellant in the tank will produce a complex working condition of propellant sloshing. The propellant management device in this embodiment generates sloshing damping through at least two lateral partitions 100 and the longitudinal ring plate 200 therebetween, so that most of the propellant in the sliding section is kept below the uppermost partition 100, effectively limiting the sloshing amplitude of the propellant.

[0034] Among them, the propellant located below the first baffle 101 at the bottom layer of the tank X will sway under the negative overload and lateral overload, and the propellant will sway to the ring plate 200 through the hollow circle of the first baffle 101, and then reach the upper baffle 100 through the ring plate 200. The ring plate 200 and the upper baffle 100 are both provided with flow holes, and the swaying energy of the propellant is greatly consumed after passing through the above path. The propellant management device achieves the retention of propellant through fewer and simple components, effectively limits the swaying amplitude of the propellant, and keeps the drop in the air pillow pressure during the gliding process within an acceptable range.

[0035] like Figures 2 to 6 As shown, according to one embodiment of the utility model, the partition 100 includes a first partition 101, a second partition 102 and a third partition 103, and the ring plate 200 includes a first ring plate 201 and a second ring plate 202. The first partition 101, the second partition 102 and the third partition 103 are arranged on the inner wall of the space vehicle tank X in a continuous interval from bottom to top, and the radial outer side of each partition 100 is respectively arranged in contact with the inner wall of the space vehicle. The hollow circle diameter of the first partition 101 is the first diameter, and the first ring plate 201 with the first diameter is arranged between the first partition 101 and the second partition 102; the second ring plate 202 with the first diameter is arranged between the second partition 102 and the third partition 103.

[0036] According to an embodiment of the present invention, the height at which the first partition 101 is arranged is the liquid level height of the propellant before the secondary ignition of the space vehicle.

[0037] According to an embodiment of the present invention, first small holes are provided on the plate surfaces of the first ring plate 201 and the second ring plate 202 .

[0038] According to an embodiment of the present invention, the diameter of the first small hole is determined according to the negative overload size, the lateral overload size and the engine flow rate.

[0039] According to an embodiment of the present invention, the second partition plate 102 is provided with a second small hole penetrating the area between the radial outer side thereof and the first diameter.

[0040] According to an embodiment of the present invention, the third partition plate 103 is provided with a second penetrating hole in a region within the first diameter.

[0041] According to an embodiment of the present invention, the diameter of the second small hole is determined according to the lateral overload size, the lateral overload size and the engine flow rate.

[0042] According to an embodiment of the present invention, the ring plate 200 is a conical cylinder.

[0043] On the other hand, the present application also provides a tank X for a recoverable space vehicle, comprising the above-mentioned propellant management device for the recoverable space vehicle.

[0044] Specifically, as an embodiment of the present application, the partition 100 is divided into three, namely the first partition 101, the second partition 102 and the third partition 103; there are two ring plates 200 between the three partitions 100, namely the first ring plate 201 and the second ring plate 202. The height of the first partition 101 set at the tank X is the liquid level height of the propellant before the secondary ignition of the engine, which can effectively keep the propellant required for the secondary ignition at the bottom of the tank X. The flow holes of the first ring plate 201 and the second ring plate 202 are the first small holes that penetrate, and the opening diameter is determined according to the size of the negative overload, the lateral overload and the size of the engine flow. The flow holes of the second partition 102 and the third partition 103 are the second small holes that penetrate, and the opening diameter is determined according to the size of the lateral overload, the size of the lateral overload and the engine flow. The second small hole layout is annularly distributed, wherein the opening positions of the second small hole of the second partition 102 and the second small hole of the third partition 103 are staggered.

[0045] In this embodiment, the first ring plate 201 and the second ring plate 202 are circular cylinders, the diameters of the first ring plate 201 and the second ring plate 202 are the hollow circle diameters of the first partition plate 101, the two ends of the axis of the first ring plate 201 of the circular cylinder are respectively abutted against the hollow circle of the first partition plate 101 and the second partition plate 102, and the two ends of the axis of the second ring plate 202 of the circular cylinder are respectively abutted against the second partition plate 102 and the third partition plate 103. As another optional embodiment, the first ring plate 201 and / or the second ring plate 202 are conical cylinders, wherein the bottom diameter of the first ring plate 201 is the hollow circle diameter of the first partition plate 101, and the top diameter of the first ring plate 201 is greater than or less than the hollow circle diameter of the first partition plate 101. The two ends of the axis of the first ring plate 201 of the conical cylinder are respectively abutted against the hollow circle of the first partition plate 101 and the second partition plate 102 , and the two ends of the axis of the second ring plate 202 of the conical cylinder are respectively abutted against the second partition plate 102 and the third partition plate 103 .

[0046] In one embodiment, when the propellant below the first partition 101 sways, part of the propellant first passes through the hollow circle of the first partition 101 to reach the first ring plate 201, passes through the first small hole of the first ring plate 201 to reach the second partition 102, passes through the second small hole of the second partition 102 to reach the second ring plate 202, passes through the first small hole of the second ring plate 202 to reach the third partition 103, and passes through the second small hole of the third partition 103 to reach the air pillow on the upper layer of the tank X. After passing through the above path, the energy of the part of the propellant that sways is largely consumed, which effectively limits the sway amplitude of the propellant, so that the center of mass of the propellant changes less during flight, the exhaust is symmetrical and the interference force generated is smaller, and the safety and reliability of the secondary working section of the engine are improved.

[0047] In specific operation, before the second start of the engine, the tank X is pushed forward to the bottom for a short time using a forward push nozzle, so that part of the propellant that has shaken to the air pillow is relocated to the bottom of the tank X, making the liquid surface of the propellant more flat. In this process, for example, the gas mixed in the propellant can escape, thereby ensuring that the propellant is in a state without gas when the engine is ignited.

[0048] The propellant management device in this embodiment can ensure that most of the propellant always sinks to the bottom during the gliding process, reducing the contact area between the propellant and the air pillow space, which can effectively reduce the pressure drop of the first stage of the space vehicle during the gliding section and reduce the pressure replenishment demand. In addition, most of the propellant sinks to the bottom, which can make the center of mass of the propellant in the tank X change within the allowable range, and can reduce the interference of the propellant shaking on the rocket body posture during the flight.

[0049] 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 recoverable space vehicle, characterized in that: The invention comprises at least two circular transverse partitions arranged on the inner wall of the tank of the space vehicle at intervals along the longitudinal direction, and an annular plate arranged longitudinally between the partitions; The partition plate arranged at the bottom layer of the storage tank is the first partition plate, which is in the shape of a hollow circular ring. One port of the ring plate is connected to the hollow circle of the first partition plate, and the port of the ring plate connected to the first partition plate matches the hollow circle of the first partition plate.

2. The propellant management device for a recoverable space vehicle according to claim 1, characterized in that: The partition includes the first partition, the second partition and the third partition, and the ring plate includes the first ring plate and the second ring plate; The first baffle, the second baffle and the third baffle are arranged continuously and spaced from bottom to top on the inner wall of the space vehicle tank, and the radial outer sides of each baffle are respectively arranged in contact with the inner wall of the space vehicle; The hollow circle diameter of the first partition is a first diameter, and the first ring plate having the first diameter is arranged between the first partition and the second partition; The second ring plate having a first diameter is disposed between the second partition plate and the third partition plate.

3. The propellant management device for a recoverable space vehicle according to claim 2, characterized in that: The height at which the first partition is arranged is the liquid level height of the propellant before the secondary ignition of the space vehicle.

4. The propellant management device for a recoverable space vehicle according to claim 2, characterized in that: The first ring plate and the second ring plate are both provided with first small holes penetrating therethrough.

5. The propellant management device for a recoverable space vehicle according to claim 4, characterized in that: The diameter of the first small hole is determined according to the negative overload size, the lateral overload and the engine flow rate.

6. The propellant management device for a recoverable space vehicle according to claim 4, characterized in that: The second partition plate is provided with a second small hole penetrating through the area between the radial outer side and the first diameter.

7. The propellant management device for a recoverable space vehicle according to claim 6, characterized in that: The third partition plate is provided with a second small hole penetrating therethrough in an area within the first diameter.

8. The propellant management device for a recoverable space vehicle according to claim 7, characterized in that: The diameter of the second small hole is determined according to the negative overload size, the lateral overload size and the engine flow rate.

9. The propellant management device for a recoverable space vehicle according to claim 1, characterized in that: The ring plate is a conical cylinder.

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

Images