CN209818182U - Bipropellant storage and supply system and spacecraft - Google Patents
Bipropellant storage and supply system and spacecraft Download PDFInfo
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- CN209818182U CN209818182U CN201920074417.0U CN201920074417U CN209818182U CN 209818182 U CN209818182 U CN 209818182U CN 201920074417 U CN201920074417 U CN 201920074417U CN 209818182 U CN209818182 U CN 209818182U
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Abstract
The utility model provides a bipropellant stores and supply system and space carrier, bipropellant stores and supply system includes: a tank housing, a fuel assembly, an oxidizer assembly, and a pressurization assembly; the fuel assembly and the oxidant assembly are reversely arranged in the storage box shell, and an air cavity space is formed between the fuel assembly and the oxidant assembly; the external inflating equipment inflates the pressurizing working medium into the air cavity space through the pressurizing assembly; under the extrusion effect of the pressurized working medium, the fuel assembly is used for discharging fuel to the thruster module, and the oxidant assembly is used for discharging oxidant to the thruster module. The utility model discloses can show the envelope size and the structure weight of reduction system, improve the integrated level of system, help realizing that bipropellant stores and the supply system integrates, miniaturized and lightweight target, can show the performance that improves space shuttle posture rail accuse engine system.
Description
Technical Field
The utility model belongs to the technical field of attitude and orbit accuse engine, concretely relates to bipropellant stores and supply system and space carrier.
Background
The attitude and orbit control engine system is a core component of the aerospace craft, and the propellant storage and supply system occupies most space and weight of the attitude and orbit control engine system and is an important determinant influencing the performance of the attitude and orbit control engine system. The existing bipropellant storage and supply system mainly comprises a fuel storage tank, an oxidant storage tank, a high-pressure gas cylinder, a gas path isolation valve, a pressure regulator, a liquid path isolation valve, a gas-liquid path pipeline, an installation structure and the like, wherein under the condition of a small space range and light structural mass, the key technology of the propellant storage and supply system is that propellant is loaded as much as possible and propellant supply without gas inclusion is realized.
As shown in fig. 1 and 2, the conventional bipropellant storage and supply system comprises: series and parallel layouts. The inventor of the utility model finds in the research and development process: the two conventional layout modes have the problems of low space utilization rate, large envelope size, complex mounting structure, large structural weight and the like. With the development of aerospace technology and the upgrading of application requirements, the requirements of spacecraft miniaturization, integration and light weight are increasingly highlighted, and the conventional layout mode of a bipropellant storage and supply system cannot meet the current application requirements, so that the application of a posture and orbit control engine is limited.
Disclosure of Invention
To overcome, at least to some extent, the problems of the related art, the present invention provides a bipropellant storage and supply system and an aerospace vehicle.
According to a first aspect of embodiments of the present invention, the present invention provides a bipropellant storage and supply system, comprising:
a tank housing, a fuel assembly, an oxidizer assembly, and a pressurization assembly;
the fuel assembly and the oxidant assembly are reversely arranged in the tank shell, and an air cavity space is formed between the fuel assembly and the oxidant assembly;
the external inflating equipment is used for inflating a pressurizing working medium into the air cavity space through the pressurizing assembly;
and under the extrusion action of the pressurized working medium, the fuel assembly is used for discharging fuel to the thruster module, and the oxidant assembly is used for discharging oxidant to the thruster module.
The bipropellant storage and supply system as described above, the fuel assembly comprising a fuel capsule assembly and a fuel head; the oxidant assembly comprises an oxidant diaphragm box assembly and an oxidant seal head;
the fuel membrane cartridge assembly and the oxidant membrane cartridge assembly are oppositely arranged in the tank shell; the air cavity space is formed between the fuel capsule assembly and the oxidizer capsule assembly;
the fuel seal head is arranged on one side of the fuel membrane box assembly, which is far away from the oxidant membrane box assembly, a fuel path isolation valve and a charging and discharging valve are arranged on the fuel seal head, and the fuel assembly is connected with the thruster module through the fuel path isolation valve and a fuel pipeline;
the oxidant seal head is arranged on one side, far away from the fuel diaphragm capsule component, of the oxidant diaphragm capsule component, an oxidant path isolation valve and a charging and discharging valve are arranged on the oxidant seal head, and the oxidant component is connected with the thruster module through the oxidant path isolation valve and an oxidant pipeline.
The bipropellant storage and supply system as described above, the fuel capsule assembly comprising a fuel capsule and a fuel cap; the oxidant diaphragm capsule assembly comprises an oxidant diaphragm capsule and an oxidant top cover;
in the tank housing, the fuel membrane cassette is disposed on one side of the tank housing in a length direction of the tank housing, and the oxidant membrane cassette is disposed on the other side of the tank housing in the length direction of the tank housing;
one side of the fuel membrane box, which is close to the oxidant membrane box, is fixedly connected with the fuel top cover, and the opposite side of the fuel membrane box is fixedly connected with the fuel seal head;
one side of the oxidant membrane box, which is close to the fuel membrane box, is fixedly connected with the oxidant top cover, and the opposite side of the oxidant membrane box is fixedly connected with the oxidant seal head.
The bipropellant storage and supply system as described above, said fuel cap being recessed inwardly of said fuel capsule and said oxidizer cap being recessed inwardly of said oxidizer capsule; the air cavity space between the fuel top cover and the oxidant top cover is an ellipsoid or spherical space.
In the bipropellant storage and supply system, the shape of the fuel seal head is matched with that of the fuel top cover, the fuel seal head protrudes towards the outside of the fuel membrane box, and the protruding direction of the fuel seal head is consistent with the recessed direction of the fuel top cover;
the shape of the oxidant seal head is matched with that of the oxidant top cover, the oxidant seal head protrudes towards the outside of the oxidant diaphragm capsule, and the protruding direction of the oxidant seal head is consistent with the recessed direction of the oxidant top cover.
The bipropellant storage and supply system as described above, located between the fuel assembly and oxidizer assembly, with an inflation valve provided on the tank housing; the pressurizing assembly comprises a high-pressure gas cylinder, a gas path isolating valve and a gas flow distributor; the inlet of the high-pressure gas cylinder is connected with the inflation valve, and the outlet of the high-pressure gas cylinder is connected with the airflow distributor through the gas path isolation valve.
The bipropellant propellant storage and supply system as described above, the pressurizing assembly further comprising a pressure regulator disposed between and connected to the gas path isolation valve and the gas flow distributor.
The bipropellant propellant storage and supply system as described above is located in the tank housing with a compartmentalized bulkhead positioned in the air cavity space formed between the fuel assembly and oxidizer assembly.
Furthermore, the subdivision partition plate is arranged on a central axis of the storage box shell in the width direction, and two ends of the subdivision partition plate are fixedly connected with the storage box shell.
According to a second aspect of embodiments of the present invention, there is also provided an aerospace vehicle comprising any of the bipropellant storage and supply systems described above.
According to the above embodiments of the present invention, at least the following advantages are obtained: the utility model discloses bipropellant stores and supply system can save a fuel head and an oxidant head through with fuel assembly and the reverse setting of oxidant subassembly in same storage tank casing, saves the mounting structure between fuel assembly and the oxidant subassembly, can show envelope size and the structure weight that reduces bipropellant storage and supply system. In addition, by arranging the pressurizing assembly in the air cavity space formed between the fuel assembly and the oxidizer assembly, the integration level of the bipropellant storage and supply system can be further improved, and the envelope size of the bipropellant storage and supply system can be reduced.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the invention, as claimed.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of the specification of the invention, illustrate embodiments of the invention and together with the description, serve to explain the principles of the invention.
Fig. 1 is a schematic diagram of a prior art in-line bi-component propellant storage and supply system.
Fig. 2 is a schematic diagram of the structure of a prior parallel type bipropellant storage and supply system.
Fig. 3 is a schematic view of a connection structure between a bipropellant storage and supply system and a thruster module according to an embodiment of the present invention.
Fig. 4 is a schematic view of a connection structure between a two-component propellant storage and supply system and a thruster module according to an embodiment of the present invention.
Description of reference numerals:
1. a tank housing; 11. an inflation valve; 12. a safety valve; 13. a subdivision partition plate;
2. a fuel assembly; 21. a fuel membrane cartridge assembly; 211. a fuel film cartridge; 212. a fuel cap; 22. A fuel seal head; 23. fuel line isolation valves and additional discharge valves; 24. a fuel line;
3. an oxidant assembly; 31. an oxidant diaphragm capsule assembly; 311. an oxidant bellows; 312. an oxidant cap; 32. sealing the oxidant end; 33. an oxidant path isolation valve and an additional exhaust valve; 34. an oxidant line;
4. a pressurizing assembly; 41. a high pressure gas cylinder; 42. a gas path isolation valve; 43. an airflow distributor; 44. a pressure regulator;
5. a thruster module;
10. a fuel storage tank; 20. an oxidant storage tank; 30. liquid path isolating valve.
Detailed Description
To make the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the spirit of the present invention will be described in detail with reference to the accompanying drawings, and any person skilled in the art can change or modify the techniques taught by the present invention without departing from the spirit and scope of the present invention after understanding the embodiments of the present invention.
The exemplary embodiments and descriptions of the present invention are provided to explain the present invention, but not to limit the present invention. Additionally, the same or similar numbered elements/components used in the drawings and the embodiments are used to represent the same or similar parts.
As used herein, the terms "first," "second," …, etc. do not denote any order or sequential importance, nor are they used to limit the invention, but rather are used to distinguish one element from another or from another element or operation described in the same technical language.
With respect to directional terminology used herein, for example: up, down, left, right, front or rear, etc., are simply directions with reference to the drawings. Accordingly, the directional terminology used is intended to be illustrative and is not intended to be limiting of the present teachings.
As used herein, the terms "comprising," "including," "having," "containing," and the like are open-ended terms that mean including, but not limited to.
As used herein, "and/or" includes any and all combinations of the described items.
References to "plurality" herein include "two" and "more than two"; reference to "multiple sets" herein includes "two sets" and "more than two sets".
As used herein, the terms "substantially", "about" and the like are used to modify any slight variation in quantity or error that does not alter the nature of the variation. In general, the range of slight variations or errors that such terms modify may be 20% in some embodiments, 10% in some embodiments, 5% in some embodiments, or other values. It should be understood by those skilled in the art that the aforementioned values can be adjusted according to actual needs, and are not limited thereto.
Certain words used to describe the invention are discussed below or elsewhere in this specification to provide additional guidance to those skilled in the art in describing the invention.
Fig. 1 is a schematic diagram of a prior art in-line bi-component propellant storage and supply system. As shown in fig. 1, the prior art in-line two-component propellant storage and supply system comprises a fuel tank 10, an oxidizer tank 20, a high pressure gas cylinder 41, a gas path isolation valve 42, a pressure regulator 44, a liquid path isolation valve 30 and a thruster module 5. A fuel reservoir 10 and an oxidant reservoir 20 are provided in series in the system. The high-pressure gas cylinder 41 is respectively connected with the inlets of the fuel storage tank 10 and the oxidant storage tank 20 through a gas path isolation valve 42 and a pressure regulator 44, the outlets of the fuel storage tank 10 and the oxidant storage tank 20 are respectively provided with a liquid path isolation valve 30, and the two liquid path isolation valves 30 are respectively connected with the thruster module 5 through pipelines.
Fig. 2 is a schematic diagram of the structure of a prior parallel type bipropellant storage and supply system. As shown in fig. 2, the prior art parallel type bipropellant storage and supply system comprises a fuel tank 10, an oxidizer tank 20, a high pressure gas cylinder 41, a gas path isolation valve 42, a pressure regulator 44, a liquid path isolation valve 30 and a thruster module 5. A fuel tank 10 and an oxidant tank 20 are provided in parallel in the system. The high-pressure gas cylinder 41 is respectively connected with the inlets of the fuel storage tank 10 and the oxidant storage tank 20 through a gas path isolation valve 42 and a pressure regulator 44, the outlets of the fuel storage tank 10 and the oxidant storage tank 20 are respectively provided with a liquid path isolation valve 30, and the two liquid path isolation valves 30 are respectively connected with the thruster module 5 through pipelines.
The utility model provides a bipropellant agent stores and supply system can effectively solve the bipropellant agent of current conventional layout mode and stores and the big, space utilization of envelope size and the heavy scheduling problem of quality of structure that supply system exists.
The utility model discloses bipropellant stores and supply system includes tank shell, fuel assembly, oxidant subassembly and pressure boost subassembly.
The fuel assembly and the oxidizer assembly are oppositely disposed in the tank housing with an air cavity space formed therebetween.
And an inflation valve is arranged on the tank shell and is positioned between the fuel assembly and the oxidant assembly. The pressurizing assembly is connected with the inflation valve. The external inflation equipment can charge the pressurization working medium into the pressurization assembly through the inflation valve. The pressurizing assembly is used for charging pressurizing working medium into the air cavity space.
Under the extrusion effect of the pressurized working medium, the fuel assembly is used for discharging fuel to the thruster module, and the oxidant assembly is used for discharging oxidant to the thruster module.
The utility model discloses bipropellant stores and before the use of supply system or deliver, annotates fuel in to fuel assembly earlier, to annotating the oxidant in the oxidant assembly, later sealed storage. The fuel assembly and the oxidant assembly respectively play a role in sealing and isolating the fuel and the oxidant.
And charging the pressurizing working medium into the pressurizing assembly, and then sealing and storing. Wherein the pressurized working medium is specifically a pressurized gas working medium.
The utility model discloses bipropellant stores and supply system during operation, and pressure boost subassembly fills into pressure boost working medium to the air cavity space that forms between fuel assembly and the oxidant subassembly. In this state, the fuel assembly and the oxidizer assembly can isolate the two propellants, namely the fuel and the oxidizer, from the pressurized gas working medium, thereby ensuring that the propellants are both in a liquid state and are not mixed with gas.
Under the extrusion action of the pressurized gas working medium, the fuel assembly discharges fuel to the thruster module, and the oxidant assembly discharges oxidant to the thruster module.
The utility model discloses bipropellant stores and supply system can effectively solve the problem that envelope size is big, space utilization is low, construction quality is heavy that current bipropellant stores and supply system conventional layout mode exists, helps realizing that bipropellant stores and supply system integrates, miniaturized and lightweight target, can show the performance that improves space shuttle posture rail accuse engine system.
Example one
Fig. 3 is a schematic view of a connection structure between a bipropellant storage and supply system and a thruster module according to an embodiment of the present invention. As shown in fig. 3, the bipropellant storage and supply system includes a tank housing 1, a fuel assembly 2, an oxidizer assembly 3, and a booster assembly 4.
Wherein the fuel assembly 2 includes a fuel membrane cartridge assembly 21 and a fuel head 22. The oxidizer assembly 3 comprises an oxidizer diaphragm capsule assembly 31 and an oxidizer end cap 32.
The fuel cartridge assembly 21 and the oxidizer cartridge assembly 31 are oppositely disposed in the tank case 1. A gas cavity space is formed between the fuel capsule assembly 21 and the oxidizer capsule assembly 31.
The fuel seal head 22 is arranged on one side of the fuel diaphragm capsule assembly 21 far away from the oxidant diaphragm capsule assembly 31, and the fuel diaphragm capsule assembly 21 and the fuel seal head 22 form a closed cavity which is a fuel cavity. The fuel seal head 22 is provided with a fuel path isolation valve and a charge and discharge valve 23. The fuel containing cavity is connected with the thruster module 5 through a fuel path isolation valve and a fuel path 24, and fuel liquid is filled into or discharged from the fuel containing cavity through a charging and discharging valve.
The oxidant seal head 32 is arranged on one side of the oxidant diaphragm capsule assembly 31 far away from the fuel diaphragm capsule assembly 21, and the oxidant diaphragm capsule assembly 31 and the oxidant seal head 32 form another closed cavity which is an oxidant cavity. The oxidant seal head 32 is provided with an oxidant path isolation valve and an additional exhaust valve 33. The oxidant chamber is connected to the thruster module 5 by an oxidant line isolation valve and an oxidant line 34. And the oxidant liquid is filled or discharged into the oxidant containing cavity through the charging and discharging valve.
Specifically, the tank shell 1, the fuel head 22 and the oxidant head 32 are all made of metal materials. The material of the tank housing 1 is compatible with the stored fuel or oxidant stage. The material of the fuel head 22 is primarily compatible with the stored fuel. The material of the oxidant head 32 is compatible with the stored oxidant stage.
The tank shell 1 and the fuel head 22 are connected by welding or flange connection. The tank shell 1 and the oxidant seal head 32 are connected by welding or flange connection.
The fuel path isolation valve and the adding and discharging valve 23 are fixedly arranged on the fuel seal head 22 in a welding mode. The oxidant path isolation valve and the charge and discharge valve 33 are fixedly arranged on the oxidant seal head 32 in a welding mode.
Further, the fuel membrane cartridge assembly 21 includes a fuel membrane cartridge 211 and a fuel head cover 212. Oxidizer capsule assembly 31 includes oxidizer capsule 311 and oxidizer cap 312.
In the tank case 1, the fuel membrane cartridge 211 is provided on one side of the tank case 1 in the longitudinal direction of the tank case 1, and the oxidant membrane cartridge 311 is provided on the other side of the tank case 1 in the longitudinal direction of the tank case 1. The side of the fuel capsule 211 adjacent to the oxidant capsule 311 is fixedly attached to the fuel head 212 and the opposite side is fixedly attached to the fuel head 22. The oxidant membrane casing 311 is fixedly connected to the oxidant cap 312 on the side close to the fuel membrane casing 211, and fixedly connected to the oxidant cap 32 on the opposite side.
Specifically, the fuel diaphragm 211 and the oxidant diaphragm 311 are both made of a metal material. The material of the fuel capsule 211 is primarily compatible with the stored fuel. The material of the oxidant bellows 311 is compatible with the stored oxidant stage.
Specifically, the fuel bellows 211 and the fuel cap 212 may be connected by welding. The oxidant bellows 311 and the oxidant cap 312 may be connected by welding.
Preferably, fuel cap 212 is recessed into the interior of fuel capsule 211 and oxidant cap 312 is recessed into the interior of oxidant capsule 311. The gas chamber space between fuel head 212 and oxidant head 312 is embodied as an ellipsoidal or spherical space.
The pressurizing assembly 4 can be arranged in the ellipsoidal or spherical space, so that the integration level of the system is further improved, and the envelope size of the system is reduced.
In addition, the shape of the fuel head 22 is matched with the shape of the fuel cap 212, the fuel head 22 protrudes to the outside of the fuel film box 211, and the protruding direction of the fuel head 22 is consistent with the recessed direction of the fuel cap 212.
The shape of the oxidant seal head 32 is matched with that of the oxidant top cover 312, the oxidant seal head 32 protrudes towards the outside of the oxidant film box 311, and the protruding direction of the oxidant seal head 32 is consistent with the recessed direction of the oxidant top cover 312.
The pressurizing assembly 4 includes a high-pressure gas cylinder 41, a gas passage isolation valve 42, and a gas flow distributor 43. The inlet of the high pressure gas cylinder 41 is connected to the charging valve 11, and the outlet thereof is connected to the gas flow distributor 43 through the gas path isolation valve 42. Specifically, the plenum assembly 4 may be fixedly attached inside or outside the tank housing 1 by mounting brackets.
An inflation valve 11 is provided on the tank housing 1 between the fuel assembly 2 and the oxidizer assembly 3. The pressurizing assembly 4 is connected with an inflation valve 11. The external inflation device can charge the pressurizing working medium into the pressurizing assembly 4 through the inflation valve 11. Specifically, the external charging device charges the pressurized gas working medium into the high-pressure gas cylinder 41 through the charging valve 11.
The utility model discloses bipropellant stores and supply system during operation, and gas circuit isolating valve 42 is opened according to external control instruction, and the high-pressure gas who stores in the high-pressure gas cylinder 41 evenly spouts in the air cavity space that forms between fuel assembly 2 and the oxidant subassembly 3 through gas circuit isolating valve 42 and air distributor 43.
In the liquid discharging process, the fuel diaphragm capsule assembly 21 and the oxidant diaphragm capsule assembly 31 gradually move towards two sides of the storage tank shell 1 until the propellant is exhausted or the control valve of the downstream thruster module 5 is closed; when the propellant is exhausted, the fuel cap 212 is attached to the fuel head 22 and the oxidizer cap 312 is attached to the oxidizer head 32.
In addition, the pressure increasing assembly 4 further comprises a pressure regulator 44, and the pressure regulator 44 is arranged between the gas path isolation valve 42 and the gas flow distributor 43 and is connected with the gas path isolation valve 42 and the gas flow distributor 43. The pressure regulator 44 is used for regulating the high-pressure gas output by the high-pressure gas cylinder 41 into gas at the pressure required by the system.
When pressure regulator 44 is not provided, the present two-pack propellant storage and supply system operates in a pressure let-down mode of operation.
In this embodiment, to ensure the safety of the operation of the bipropellant storage and supply system, the tank housing 1 is also provided with a safety valve 12.
Specifically, the inflation valve 11 and the safety valve 12 are fixed to the tank case 1 by welding.
Compared with the conventional layout mode of the traditional bipropellant storage and supply system, the bipropellant storage and supply system can save a fuel seal head 22 and an oxidant seal head 32 through the structural form that the fuel assembly 2 and the oxidant assembly 3 share one tank shell 1, save the installation structure between the fuel tank and the oxidant tank, and obviously reduce the enveloping size and the structural weight of the bipropellant storage and supply system. In addition, by arranging the pressurizing assembly 4 in the air cavity space, the integration level of the bipropellant storage and supply system can be further improved, and the envelope size of the bipropellant storage and supply system can be reduced.
Example two
Fig. 4 is a schematic view of a connection structure between a two-component propellant storage and supply system and a thruster module according to an embodiment of the present invention. The basic structure of the bipropellant storage and supply system provided in this embodiment is the same as that of the first embodiment, and will not be described in detail herein. The difference lies in that: a compartment divider 13 is added to the tank casing 1.
As shown in fig. 4, a subdivision partition 13 is provided in the tank casing 1 at the air chamber space formed between the fuel assemblies 2 and the oxidizer assemblies 3. The compartment divider 13 is perpendicular to the longitudinal axis of the tank shell 1. The compartment partition plate 13 is used as a redundant structure for sealing and isolating the fuel membrane box assembly 21 and the oxidant membrane box assembly 31, and under the condition that the fuel membrane box assembly 21 and the oxidant membrane box assembly 31 are in fault and leak, the fuel and the oxidant are isolated, so that the fuel and the oxidant cannot be mixed and react, and the intrinsic safety and the reliability of the system are improved.
Accordingly, the two air flow distributors 43 are provided, and are respectively provided in the air chamber space formed by the compartment partition 13 and the fuel head cover 212 and the air chamber space formed by the compartment partition 13 and the oxidant head cover 312. Two safety valves 12 are also provided, one on each tank housing 1 on each side of the subdivision partition 13.
Preferably, the subdivision partition plate 13 is arranged on the central axis of the width direction of the storage tank shell 1, two ends of the subdivision partition plate 13 are fixedly connected with the storage tank shell 1, and the subdivision partition plate 13 bisects the air cavity space.
EXAMPLE III
The third embodiment of the present invention further provides an aerospace vehicle, which includes any one of the first and second embodiments of the two-component propellant storage and supply systems.
The foregoing is only an illustrative embodiment of the present invention, and any equivalent changes and modifications made by those skilled in the art without departing from the spirit and principles of the present invention should fall within the protection scope of the present invention.
Claims (10)
1. A bipropellant storage and supply system, comprising:
a tank housing, a fuel assembly, an oxidizer assembly, and a pressurization assembly;
the fuel assembly and the oxidant assembly are reversely arranged in the tank shell, and an air cavity space is formed between the fuel assembly and the oxidant assembly;
the external inflating equipment is used for inflating a pressurizing working medium into the air cavity space through the pressurizing assembly;
and under the extrusion action of the pressurized working medium, the fuel assembly is used for discharging fuel to the thruster module, and the oxidant assembly is used for discharging oxidant to the thruster module.
2. The bipropellant storage and supply system of claim 1, wherein the fuel assembly comprises a fuel capsule assembly and a fuel head; the oxidant assembly comprises an oxidant diaphragm box assembly and an oxidant seal head;
the fuel membrane cartridge assembly and the oxidant membrane cartridge assembly are oppositely arranged in the tank shell; the air cavity space is formed between the fuel capsule assembly and the oxidizer capsule assembly;
the fuel seal head is arranged on one side of the fuel membrane box assembly, which is far away from the oxidant membrane box assembly, a fuel path isolation valve and a charging and discharging valve are arranged on the fuel seal head, and the fuel assembly is connected with the thruster module through the fuel path isolation valve and a fuel pipeline;
the oxidant seal head is arranged on one side, far away from the fuel diaphragm capsule component, of the oxidant diaphragm capsule component, an oxidant path isolation valve and a charging and discharging valve are arranged on the oxidant seal head, and the oxidant component is connected with the thruster module through the oxidant path isolation valve and an oxidant pipeline.
3. The bipropellant propellant storage and supply system of claim 2, wherein the fuel capsule assembly comprises a fuel capsule and a fuel cap; the oxidant diaphragm capsule assembly comprises an oxidant diaphragm capsule and an oxidant top cover;
in the tank housing, the fuel membrane cassette is disposed on one side of the tank housing in a length direction of the tank housing, and the oxidant membrane cassette is disposed on the other side of the tank housing in the length direction of the tank housing;
one side of the fuel membrane box, which is close to the oxidant membrane box, is fixedly connected with the fuel top cover, and the opposite side of the fuel membrane box is fixedly connected with the fuel seal head;
one side of the oxidant membrane box, which is close to the fuel membrane box, is fixedly connected with the oxidant top cover, and the opposite side of the oxidant membrane box is fixedly connected with the oxidant seal head.
4. The bipropellant storage and supply system of claim 3, wherein said fuel cap is recessed inwardly of said fuel capsule, and said oxidizer cap is recessed inwardly of said oxidizer capsule; the air cavity space between the fuel top cover and the oxidant top cover is an ellipsoid or spherical space.
5. The bipropellant storage and supply system of claim 4, wherein the fuel header is shaped to match the shape of a fuel cap, the fuel header protruding outward of the fuel capsule in a direction that coincides with the fuel cap recess;
the shape of the oxidant seal head is matched with that of the oxidant top cover, the oxidant seal head protrudes towards the outside of the oxidant diaphragm capsule, and the protruding direction of the oxidant seal head is consistent with the recessed direction of the oxidant top cover.
6. The bipropellant storage and supply system of claim 1, wherein an inflation valve is disposed on the tank housing between the fuel assembly and oxidizer assembly; the pressurizing assembly comprises a high-pressure gas cylinder, a gas path isolating valve and a gas flow distributor; the inlet of the high-pressure gas cylinder is connected with the inflation valve, and the outlet of the high-pressure gas cylinder is connected with the airflow distributor through the gas path isolation valve.
7. The bipropellant propellant storage and supply system of claim 6, wherein the pressurization assembly further comprises a pressure regulator disposed between and connected to a gas path isolation valve and a gas flow divider.
8. The bipropellant propellant storage and supply system of any of claims 1 to 7, wherein a compartmentalized bulkhead is located in the tank housing at the air cavity space formed between the fuel assembly and oxidizer assembly.
9. The bipropellant propellant storage and supply system of claim 8, wherein the subdivision partition is disposed on a widthwise central axis of the tank housing, both ends of the subdivision partition being fixedly connected to the tank housing.
10. An aerospace vehicle comprising a bipropellant storage and supply system as claimed in any one of claims 1 to 9.
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| CN201920074417.0U CN209818182U (en) | 2019-01-17 | 2019-01-17 | Bipropellant storage and supply system and spacecraft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109763913A (en) * | 2019-01-17 | 2019-05-17 | 北京蓝箭空间科技有限公司 | Bipropellant propulsion developing agent storage and supply system and space launch vehicle |
| CN111928104A (en) * | 2020-10-09 | 2020-11-13 | 北京星际荣耀空间科技有限公司 | Liquid oxymethane rocket supercharging device and liquid oxymethane rocket |
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2019
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109763913A (en) * | 2019-01-17 | 2019-05-17 | 北京蓝箭空间科技有限公司 | Bipropellant propulsion developing agent storage and supply system and space launch vehicle |
| CN109763913B (en) * | 2019-01-17 | 2024-03-26 | 蓝箭航天空间科技股份有限公司 | Dual component propellant storage and supply system and space vehicle |
| CN111928104A (en) * | 2020-10-09 | 2020-11-13 | 北京星际荣耀空间科技有限公司 | Liquid oxymethane rocket supercharging device and liquid oxymethane rocket |
| CN111928104B (en) * | 2020-10-09 | 2020-12-22 | 北京星际荣耀空间科技有限公司 | Liquid oxymethane rocket supercharging device and liquid oxymethane rocket |
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