CN109763913B - Dual component propellant storage and supply system and space vehicle - Google Patents
Dual component propellant storage and supply system and space vehicle Download PDFInfo
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- CN109763913B CN109763913B CN201910042393.5A CN201910042393A CN109763913B CN 109763913 B CN109763913 B CN 109763913B CN 201910042393 A CN201910042393 A CN 201910042393A CN 109763913 B CN109763913 B CN 109763913B
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- 239000003380 propellant Substances 0.000 title claims abstract description 68
- 230000009977 dual effect Effects 0.000 title description 7
- 239000007800 oxidant agent Substances 0.000 claims abstract description 178
- 239000000446 fuel Substances 0.000 claims abstract description 176
- 230000001590 oxidative effect Effects 0.000 claims abstract description 130
- 238000007599 discharging Methods 0.000 claims abstract description 17
- 238000001125 extrusion Methods 0.000 claims abstract description 5
- 238000002955 isolation Methods 0.000 claims description 42
- 239000002775 capsule Substances 0.000 claims description 9
- 239000002828 fuel tank Substances 0.000 claims description 7
- 230000009471 action Effects 0.000 claims description 3
- 230000004888 barrier function Effects 0.000 claims description 2
- 230000000712 assembly Effects 0.000 claims 1
- 238000000429 assembly Methods 0.000 claims 1
- 230000010354 integration Effects 0.000 abstract description 6
- 230000000694 effects Effects 0.000 abstract description 2
- 230000002349 favourable effect Effects 0.000 abstract 1
- 239000000306 component Substances 0.000 description 58
- 239000007788 liquid Substances 0.000 description 12
- 238000005192 partition Methods 0.000 description 12
- 238000010586 diagram Methods 0.000 description 8
- 238000003466 welding Methods 0.000 description 7
- 238000007789 sealing Methods 0.000 description 6
- 239000000463 material Substances 0.000 description 5
- 238000000034 method Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
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- Fuel Cell (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The present application provides a two-component propellant storage and supply system and an aerospace vehicle, the two-component propellant storage and supply system comprising: a tank housing, a fuel assembly, an oxidant assembly, and a plenum assembly; the fuel component and the oxidant component are reversely arranged in the storage tank shell, and an air cavity space is formed between the fuel component and the oxidant component; the external air charging equipment charges a 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 system can obviously reduce the envelope size and the structural weight of the system, improve the integration level of the system, be favorable for realizing the purposes of integrating, miniaturizing and lightening the dual-component propellant storage and supply system, and can obviously improve the performance of the attitude and orbit control engine system of the aerospace craft.
Description
Technical Field
The application belongs to the technical field of attitude and orbit control engines, and particularly relates to a dual-component propellant storage and supply system and a space vehicle.
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 of the space and weight of the attitude and orbit control engine system and is an important determining factor for influencing the performance of the attitude and orbit control engine system. The existing two-component propellant 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, a mounting structure and the like, wherein under the condition of smaller space range and lighter structural mass, propellant is loaded as much as possible, and the realization of propellant supply without gas inclusion is a key technology of the propellant storage and supply system.
As shown in fig. 1 and 2, the existing two-component propellant storage and supply system comprises: and a serial type layout mode and a parallel type layout mode. The inventors of the present application found during the development process that: the two conventional layout modes have the problems of low space utilization rate, larger envelope size, complex installation structure, larger structure weight and the like. Along with development of aerospace technology and upgrading of application requirements, requirements of miniaturization, integration and light weight of the spacecraft are increasingly highlighted, and a conventional layout mode of a two-component propellant storage and supply system cannot meet current application requirements, so that application of the attitude and orbit control engine is limited.
Disclosure of Invention
To overcome, at least to some extent, the problems associated with the related art, the present application provides a two-component propellant storage and supply system and an aerospace vehicle.
According to a first aspect of embodiments of the present application, there is provided a two-component propellant storage and supply system comprising:
a tank housing, a fuel assembly, an oxidant assembly, and a plenum assembly;
the fuel component and the oxidant component are reversely arranged in the storage tank shell, and an air cavity space is formed between the fuel component and the oxidant component;
the external inflation equipment is used for inflating a pressurizing working medium into the air cavity space through the pressurizing assembly;
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.
A two-component propellant storage and supply system as described above, the fuel assembly comprising a fuel bellows assembly and a fuel cap; the oxidant assembly comprises an oxidant bellows assembly and an oxidant seal head;
the fuel bellows assembly and the oxidizer bellows assembly are disposed in the reservoir housing in opposite directions; the air cavity space is formed between the fuel bellows assembly and the oxidizer bellows assembly;
the fuel seal head is arranged at one side of the fuel film box component far away from the oxidant film box component, a fuel path isolation valve and a charging and discharging valve are arranged on the fuel seal head, and the fuel component is connected with the thruster module through the fuel path isolation valve and a fuel pipeline;
the oxidant head sets up the oxidant bellows subassembly is kept away from the one side of fuel bellows subassembly, be provided with oxidant way isolation valve and add the exhaust valve on the oxidant head, the oxidant subassembly pass through oxidant way isolation valve and oxidant pipeline with the thruster module is connected.
A two-component propellant storage and supply system as described above, the fuel bellows assembly comprising a fuel bellows and a fuel cap; the oxidant bellows assembly includes an oxidant bellows and an oxidant header;
in the tank case, the fuel bellows is provided on one side of the tank case in a longitudinal direction of the tank case, and the oxidizer bellows is provided on the other side of the tank case in the longitudinal direction of the tank case;
one side of the fuel film box, which is close to the oxidant film box, is fixedly connected with the fuel top cover, and the opposite side of the fuel film box is fixedly connected with the fuel seal head;
one side of the oxidant diaphragm capsule, which is close to the fuel diaphragm capsule, is fixedly connected with the oxidant top cover, and the opposite side of the oxidant diaphragm capsule is fixedly connected with the oxidant end socket.
A two-component propellant storage and supply system as described above, the fuel cap being recessed inwardly of the fuel bellows and the oxidant cap being recessed inwardly of the oxidant bellows; the air cavity space between the fuel top cover and the oxidant top cover is an ellipsoidal or spherical space.
The two-component propellant storage and supply system comprises a fuel seal head, a fuel seal head and a fuel top cover, wherein 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 film 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 head is matched with the shape of the oxidant top cover, the oxidant head protrudes towards the outside of the oxidant diaphragm capsule, and the protruding direction of the oxidant head is consistent with the recessed direction of the oxidant top cover.
A dual component propellant storage and supply system as described above is located between the fuel assembly and the oxidizer assembly with an inflation valve disposed on the reservoir housing, and the pressurization assembly is connected to the inflation valve.
A two-component propellant storage and supply system as described above, the pressurizing assembly comprising a high pressure gas cylinder, a gas path isolation valve and a gas flow distributor; the inlet of the high-pressure gas cylinder is connected with the charging valve, and the outlet of the high-pressure gas cylinder is connected with the air flow distributor through the air path isolation valve.
The dual component 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.
A two-component propellant storage and supply system as described above, the tank housing further being provided with a safety valve.
A two-component propellant storage and supply system as described above is located in the tank housing with a compartmentalized barrier disposed at the air cavity space formed between the fuel assembly and the oxidizer assembly.
Further, the cabin partition board is arranged on the central axis of the storage box shell in the width direction, and two ends of the cabin partition board are fixedly connected with the storage box shell.
According to a second aspect of embodiments of the present application, there is also provided an aerospace vehicle comprising a two-component propellant storage and supply system as described in any one of the preceding.
According to the above specific embodiments of the present application, at least the following advantages are achieved: according to the dual-component propellant storage and supply system, the fuel assembly and the oxidant assembly are reversely arranged in the same storage tank shell, one fuel sealing head and one oxidant sealing head can be saved, the mounting structure between the fuel assembly and the oxidant assembly is saved, and the enveloping size and the structural weight of the dual-component propellant storage and supply system can be remarkably reduced. In addition, by disposing the pressurizing assembly in the air cavity space formed between the fuel assembly and the oxidizer assembly, the integration of the two-component propellant storage and supply system can be further enhanced, reducing its envelope size.
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 scope of the invention as claimed.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description, serve to explain the principles of the application.
Fig. 1 is a schematic diagram of a prior art tandem two-component propellant storage and supply system.
Fig. 2 is a schematic diagram of a prior art parallel two-component propellant storage and supply system.
Fig. 3 is a schematic diagram 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.
Fig. 4 is a schematic diagram of a connection structure between a two-component propellant storage and supply system and a thruster module according to a second embodiment of the present disclosure.
Reference numerals illustrate:
1. a tank housing; 11. an inflation valve; 12. a safety valve; 13. a compartment partition;
2. a fuel assembly; 21. a fuel bellows assembly; 211. a fuel bellows; 212. a fuel top cover; 22. a fuel head; 23. a fuel path isolation valve and a charging and discharging valve; 24. a fuel line;
3. an oxidizer assembly; 31. an oxidizer bellows assembly; 311. an oxidizer capsule; 312. an oxidant cap; 32. an oxidant head; 33. an oxidant path isolation valve and a charging and discharging valve; 34. an oxidant line;
4. a pressurizing assembly; 41. a high pressure gas cylinder; 42. an air path isolation valve; 43. an air flow distributor; 44. a pressure regulator;
5. a thruster module;
10. a fuel tank; 20. an oxidant reservoir; 30. a liquid path isolation valve.
Detailed Description
For the purposes of clarity, technical solutions and advantages of embodiments of the present application, the following drawings and detailed description will clearly illustrate the spirit of the disclosure of the present application, and any person skilled in the art, after having the knowledge of the embodiments of the present application, may make changes and modifications by the techniques taught by the present application, without departing from the spirit and scope of the present application.
The exemplary embodiments of the present application and their description are for the purpose of explaining the present application, but are not limiting of the present application. In addition, the same or similar reference numerals are used for the same or similar parts in the drawings and the embodiments.
The terms "first," "second," …, and the like, as used herein, do not denote a particular order or sequence, nor are they intended to limit the application to distinguishing between elements or operations that are described in the same technical language.
With respect to directional terms used herein, for example: upper, lower, left, right, front or rear, etc., are merely references to the directions of the drawings. Thus, directional terminology is used for purposes of illustration and is not intended to be limiting.
As used herein, the terms "comprising," "including," "having," "containing," and the like are intended to be inclusive and mean an inclusion, but not limited to.
As used herein, "and/or" includes any or all combinations of such things.
Reference herein to "a plurality" includes "two" and "more than two"; the term "plurality of sets" as used herein includes "two sets" and "more than two sets".
The terms "about," "approximately" and the like as used herein are used to modify any quantity or error that could be slightly varied without the slight variation or error altering its nature. In general, the range of slight variations or errors modified by such terms 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 above mentioned values can be adjusted according to the actual requirements, and are not limited thereto.
Certain terms used to describe the application will be discussed below, or elsewhere in this specification, to provide additional guidance to those skilled in the art in connection with the description of the application.
Fig. 1 is a schematic diagram of a prior art tandem two-component propellant storage and supply system. As shown in fig. 1, the existing tandem two-component propellant storage and supply system includes 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. The fuel tank 10 and the oxidizer tank 20 are disposed in series in the system. The high-pressure gas cylinder 41 is connected with 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 respectively, liquid path isolation valves 30 are arranged at outlets of the fuel storage tank 10 and the oxidant storage tank 20, and the two liquid path isolation valves 30 are connected with the thruster module 5 through pipelines.
Fig. 2 is a schematic diagram of a prior art parallel two-component propellant storage and supply system. As shown in fig. 2, the existing parallel two-component propellant storage and supply system includes 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. The fuel tank 10 and the oxidizer tank 20 are disposed in parallel in the system. The high-pressure gas cylinder 41 is connected with 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 respectively, liquid path isolation valves 30 are arranged at outlets of the fuel storage tank 10 and the oxidant storage tank 20, and the two liquid path isolation valves 30 are connected with the thruster module 5 through pipelines.
The two-component propellant storage and supply system provided by the application can effectively solve the problems of large envelope size, low space utilization rate, heavy structural quality and the like of the two-component propellant storage and supply system in the conventional layout mode.
The dual component propellant storage and supply system of the present application includes a tank housing, a fuel assembly, an oxidizer assembly, and a pressurization assembly.
The fuel assembly and the oxidizer assembly are disposed in the tank housing in opposite directions, with an air cavity space formed between the fuel assembly and the oxidizer assembly.
An inflation valve is disposed on the tank housing between the fuel assembly and the oxidizer assembly. The pressurizing assembly is connected with the charging valve. The external air charging equipment can charge the pressurizing working medium into the pressurizing assembly through the air charging 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 dual component propellant storage and supply system of the present application is used by first filling the fuel assembly with fuel, filling the oxidizer assembly with oxidizer, and then sealing the storage. The fuel assembly and the oxidant assembly respectively and correspondingly function as sealing and isolating fuel and oxidant.
And charging a pressurizing working medium into the pressurizing assembly, and then sealing and storing. Wherein the pressurizing working medium is specifically a pressurizing gas working medium.
When the dual-component propellant storage and supply system works, the pressurizing assembly fills pressurizing working medium into an air cavity space formed between the fuel assembly and the oxidant assembly. In this state, the fuel assembly and the oxidizer assembly can isolate both the fuel and the oxidizer from the pressurized gas working medium, thereby ensuring that both the propellants are liquid and are not entrained 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 dual-component propellant storage and supply system can effectively solve the problems of large envelope size, low space utilization rate and heavy structural quality of the conventional layout mode of the existing dual-component propellant storage and supply system, is beneficial to achieving the aims of integration, miniaturization and light weight of the dual-component propellant storage and supply system, and can remarkably improve the performance of the attitude and orbit control engine system of the aerospace craft.
Example 1
Fig. 3 is a schematic diagram 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. As shown in fig. 3, the two-component propellant storage and supply system includes a tank housing 1, a fuel assembly 2, an oxidizer assembly 3, and a pressurization assembly 4.
Wherein the fuel assembly 2 comprises a fuel bellows assembly 21 and a fuel cap 22. The oxidizer assembly 3 includes an oxidizer bellows assembly 31 and an oxidizer head 32.
The fuel bellows assembly 21 and the oxidizer bellows assembly 31 are disposed in the reservoir housing 1 in opposite directions. An air cavity space is formed between the fuel bellows assembly 21 and the oxidizer bellows assembly 31.
The fuel seal head 22 is arranged at one side of the fuel film box component 21 far away from the oxidant film box component 31, and the fuel film box component 21 and the fuel seal head 22 form a closed cavity, namely the fuel cavity. The fuel head 22 is provided with a fuel path isolation valve and a charge/discharge valve 23. The fuel containing cavity is connected with the thruster module 5 through a fuel line isolation valve and a fuel line 24; and filling or discharging fuel liquid into the fuel accommodating cavity through the filling and discharging valve.
The oxidant seal 32 is disposed on a side of the oxidant bellows assembly 31 away from the fuel bellows assembly 21, and the oxidant bellows assembly 31 and the oxidant seal 32 form another closed cavity, i.e. the oxidant cavity. The oxidizer head 32 is provided with an oxidizer path isolation valve and a charge/discharge valve 33. The oxidant chamber is connected to the thruster module 5 by means of an oxidant line isolation valve and an oxidant line 34. And filling or discharging the oxidant liquid into the oxidant containing cavity through a filling and discharging valve.
Specifically, the tank housing 1, the fuel head 22, and the oxidant head 32 are all made of a metal material. The material of the tank housing 1 is primary compatible with the stored fuel or oxidant. The material of the fuel head 22 is compatible with the stored fuel stage. The material of the oxidant header 32 is primary compatible with the stored oxidant.
The tank shell 1 and the fuel seal 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 charging and discharging valve 23 are fixedly arranged on the fuel seal head 22 in a welding mode. The oxidant path isolation valve and the charging and discharging valve 33 are fixedly arranged on the oxidant head 32 by a welding mode.
Further, the fuel bellows assembly 21 includes a fuel bellows 211 and a fuel cap 212. The oxidizer bellows assembly 31 includes an oxidizer bellows 311 and an oxidizer cap 312.
In the tank case 1, a fuel bellows 211 is provided on one side of the tank case 1 in the longitudinal direction of the tank case 1, and an oxidizer bellows 311 is provided on the other side of the tank case 1 in the longitudinal direction of the tank case 1. One side of the fuel bellows 211, which is adjacent to the oxidizer bellows 311, is fixedly connected to the fuel cap 212, and the opposite side is fixedly connected to the fuel head 22. One side of the oxidant bellows 311, which is adjacent to the fuel bellows 211, is fixedly connected to the oxidant cap 312, and the opposite side is fixedly connected to the oxidant head 32.
Specifically, the fuel bellows 211 and the oxidizer bellows 311 are each made of a metal material. The material of the fuel bellows 211 is compatible with the stored fuel stage. The material of the oxidizer bellows 311 is primary compatible with the stored oxidizer.
Specifically, the fuel bellows 211 and the fuel top cover 212 may be connected by welding. The oxidizer bellows 311 and the oxidizer cap 312 may be connected by welding.
Preferably, the fuel cap 212 is recessed inside the fuel bellows 211 and the oxidant cap 312 is recessed inside the oxidant bellows 311. The air cavity space between the fuel cap 212 and the oxidant cap 312 is specifically 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 cap 22 is matched with the shape of the fuel top cover 212, the fuel cap 22 protrudes to the outside of the fuel bellows 211, and the protruding direction of the fuel cap 22 is consistent with the recessed direction of the fuel top cover 212.
The shape of the oxidant head 32 is matched with that of the oxidant top cover 312, the oxidant head 32 protrudes towards the outside of the oxidant bellows 311, and the protruding direction of the oxidant 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 path isolation valve 42, and a gas flow distributor 43. The inlet of the high-pressure gas cylinder 41 is connected with the charging valve 11, and the outlet thereof is connected with the air flow distributor 43 through the air passage isolation valve 42. Specifically, the pressurizing assembly 4 may be fixedly connected inside or outside the tank housing 1 by a mounting bracket.
Between the fuel assembly 2 and the oxidizer assembly 3, an inflation valve 11 is provided on the tank housing 1. The pressurizing assembly 4 is connected with an inflation valve 11. The external charging device can charge the pressurizing assembly 4 with pressurizing working medium through the charging valve 11. Specifically, the external charging device charges the high-pressure gas cylinder 41 with a pressurized gas working medium through the charging valve 11.
When the dual-component propellant storage and supply system works, the gas path isolation valve 42 is opened according to an external control instruction, and high-pressure gas stored in the high-pressure gas cylinder 41 is uniformly injected into an air cavity space formed between the fuel assembly 2 and the oxidant assembly 3 through the gas path isolation valve 42 and the air flow distributor 43.
During the draining process, the fuel bellows assembly 21 and the oxidizer bellows assembly 31 gradually move to both sides of the tank housing 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 cap 22 and the oxidant cap 312 is attached to the oxidant cap 32.
In addition, the pressurizing assembly 4 further includes a pressure regulator 44, and the pressure regulator 44 is disposed between the air path isolation valve 42 and the air flow distributor 43, and is connected to the air path isolation valve 42 and the air flow distributor 43. The pressure regulator 44 is used to regulate the high-pressure gas output from the high-pressure gas cylinder 41 to a gas of a pressure required for the system.
When the pressure regulator 44 is not provided, the dual component propellant storage and supply system of the present application operates in a drop pressure mode of operation.
In this embodiment, the tank housing 1 is further provided with a safety valve 12 for ensuring the safety of the operation of the two-component propellant storage and supply system.
Specifically, the inflation valve 11 and the safety valve 12 are both fixed to the tank case 1 by welding.
Compared with the conventional layout mode of the traditional two-component propellant storage and supply system, the two-component propellant storage and supply system disclosed by the application has the advantages that one fuel seal head 22 and one oxidant seal head 32 can be saved by sharing the structural form of one storage tank shell 1 through the fuel assembly 2 and the oxidant assembly 3, the mounting structure between the fuel storage tank and the oxidant storage tank can be saved, and the envelope size and the structural weight of the two-component propellant storage and supply system can be remarkably reduced. In addition, by disposing the pressurizing assembly 4 in the air cavity space, the integration of the two-component propellant storage and supply system can be further improved, and the envelope size thereof can be reduced.
Example two
Fig. 4 is a schematic diagram of a connection structure between a two-component propellant storage and supply system and a thruster module according to a second embodiment of the present disclosure. The basic structure of the two-component propellant storage and supply system provided in this embodiment is the same as in the first embodiment and will not be described in detail here. The difference is that: a compartment partition 13 is added to the tank housing 1.
As shown in fig. 4, a bulkhead 13 is provided in the tank case 1 at an air chamber space formed between the fuel assembly 2 and the oxidizer assembly 3. The compartment partition 13 is perpendicular to the longitudinal axis of the tank housing 1. The partition 13 is used as a redundant structure for sealing and isolating the fuel diaphragm box assembly 21 and the oxidant diaphragm box assembly 31, and isolates the fuel and the oxidant from being mixed and reacted under the condition that the fuel diaphragm box assembly 21 and the oxidant diaphragm box assembly 31 have fault leakage, so that the intrinsic safety and the reliability of the system are improved.
Accordingly, two air flow distributors 43 are provided, which are respectively and correspondingly arranged in the air cavity space formed by the partition 13 and the fuel top cover 212 and the air cavity space formed by the partition 13 and the oxidant top cover 312. The safety valve 12 is also provided with two storage tank shells 1 which are respectively arranged at two sides of the dividing partition 13.
Preferably, the partition 13 is disposed on a central axis of the tank housing 1 in the width direction, both ends of the partition 13 are fixedly connected with the tank housing 1, and the partition 13 bisects the air cavity space.
Example III
The third embodiment of the present application also provides an aerospace vehicle comprising any one of the two-component propellant storage and supply systems of the first and second embodiments.
The foregoing is merely illustrative of the specific embodiments of this application and any equivalent variations and modifications can be made by those skilled in the art without departing from the spirit and principles of this application.
Claims (9)
1. A two-component propellant storage and supply system comprising:
a tank housing, a fuel assembly, an oxidant assembly, and a plenum assembly;
the fuel component and the oxidant component are reversely arranged in the storage tank shell, and an air cavity space is formed between the fuel component and the oxidant component;
the external inflation equipment is used for inflating a pressurizing working medium into the air cavity space through the pressurizing assembly;
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 fuel assembly comprises a fuel bellows assembly and a fuel seal head; the oxidant assembly comprises an oxidant bellows assembly and an oxidant seal head;
the fuel bellows assembly and the oxidizer bellows assembly are disposed in the reservoir housing in opposite directions; the air cavity space is formed between the fuel bellows assembly and the oxidizer bellows assembly;
the fuel bellows assembly includes a fuel bellows and a fuel cap; the oxidant bellows assembly includes an oxidant bellows and an oxidant header;
in the tank case, the fuel bellows is provided on one side of the tank case in a longitudinal direction of the tank case, and the oxidizer bellows is provided on the other side of the tank case in the longitudinal direction of the tank case;
one side of the fuel film box, which is close to the oxidant film box, is fixedly connected with the fuel top cover, and the opposite side of the fuel film box is fixedly connected with the fuel seal head;
one side of the oxidant diaphragm capsule, which is close to the fuel diaphragm capsule, is fixedly connected with the oxidant top cover, and the opposite side of the oxidant diaphragm capsule is fixedly connected with the oxidant end socket;
a safety valve is also arranged on the storage tank shell;
the fuel tank is characterized in that the fuel tank is positioned between the fuel assembly and the oxidant assembly, an inflation valve is arranged on the tank shell, and the pressurizing assembly is connected with the inflation valve.
2. The two-component propellant storage and supply system of claim 1 wherein the fuel cap is disposed on a side of the fuel bellows assembly remote from the oxidizer bellows assembly, the fuel cap being provided with a fuel line isolation valve and a fill and drain valve, the fuel assembly being connected to the thruster module by a fuel line isolation valve and a fuel line;
the oxidant head sets up the oxidant bellows subassembly is kept away from the one side of fuel bellows subassembly, be provided with oxidant way isolation valve and add the exhaust valve on the oxidant head, the oxidant subassembly pass through oxidant way isolation valve and oxidant pipeline with the thruster module is connected.
3. The two-component propellant storage and supply system of claim 2, wherein the fuel cap is recessed inwardly of the fuel bellows and the oxidizer cap is recessed inwardly of the oxidizer bellows; the air cavity space between the fuel top cover and the oxidant top cover is an ellipsoidal or spherical space.
4. A two-component propellant storage and supply system as claimed in claim 3, wherein the fuel cap is shaped to match the shape of the fuel cap, the fuel cap projecting outwardly of the fuel bellows, the direction of the fuel cap projection being coincident with the direction of the fuel cap recess;
the shape of the oxidant head is matched with the shape of the oxidant top cover, the oxidant head protrudes towards the outside of the oxidant diaphragm capsule, and the protruding direction of the oxidant head is consistent with the recessed direction of the oxidant top cover.
5. The two-component propellant storage and supply system of claim 1 wherein the pressurizing assembly comprises a high pressure gas cylinder, a gas path isolation valve and a gas flow distributor; the inlet of the high-pressure gas cylinder is connected with the charging valve, and the outlet of the high-pressure gas cylinder is connected with the air flow distributor through the air path isolation valve.
6. The two-component propellant storage and supply system of claim 5, wherein the pressurization assembly further comprises a pressure regulator disposed between and connected to the gas path isolation valve and the gas flow distributor.
7. A two-component propellant storage and supply system as claimed in any one of claims 1 to 6, wherein a compartmentalized barrier is provided in the tank housing at the air cavity space formed between the fuel and oxidant assemblies.
8. The two-component propellant storage and supply system of claim 7 wherein the bulkhead is disposed on a widthwise centerline of the tank housing, both ends of the bulkhead being fixedly connected to the tank housing.
9. An aerospace vehicle comprising a two-component propellant storage and supply system according to any one of claims 1 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910042393.5A CN109763913B (en) | 2019-01-17 | 2019-01-17 | Dual component propellant storage and supply system and space vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910042393.5A CN109763913B (en) | 2019-01-17 | 2019-01-17 | Dual component propellant storage and supply system and space vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109763913A CN109763913A (en) | 2019-05-17 |
| CN109763913B true CN109763913B (en) | 2024-03-26 |
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Family Applications (1)
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| CN111924138B (en) * | 2020-09-21 | 2021-01-01 | 蓝箭航天空间科技股份有限公司 | Special diaphragm box inflation and pressure measurement device for low-temperature aerospace carrier |
| CN112211750B (en) * | 2020-10-19 | 2021-12-14 | 北京天兵科技有限公司 | Rocket engine ignition agent storage and supply device |
| CN114233520B (en) * | 2021-12-10 | 2023-04-25 | 北京航空航天大学 | Attitude and orbit control integrated propulsion system for supercharging electric pump and spacecraft |
| CN114607527B (en) * | 2022-03-23 | 2023-09-05 | 北京航天雷特机电工程有限公司 | Temperature control conveying system for propellant of space engine |
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