CN114872936A - Satellite orbit control power system - Google Patents
Satellite orbit control power system Download PDFInfo
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- CN114872936A CN114872936A CN202210809656.2A CN202210809656A CN114872936A CN 114872936 A CN114872936 A CN 114872936A CN 202210809656 A CN202210809656 A CN 202210809656A CN 114872936 A CN114872936 A CN 114872936A
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- valve
- power system
- main frame
- satellite
- engine
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- 239000007788 liquid Substances 0.000 claims abstract description 40
- 239000003380 propellant Substances 0.000 claims abstract description 39
- 239000007789 gas Substances 0.000 claims description 107
- 239000012530 fluid Substances 0.000 claims description 18
- 229910052751 metal Inorganic materials 0.000 claims description 17
- 239000002184 metal Substances 0.000 claims description 17
- 238000004891 communication Methods 0.000 claims description 10
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 6
- 239000001307 helium Substances 0.000 claims description 3
- 229910052734 helium Inorganic materials 0.000 claims description 3
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 claims description 3
- 229910052757 nitrogen Inorganic materials 0.000 claims description 3
- 230000010354 integration Effects 0.000 abstract description 8
- 238000007599 discharging Methods 0.000 description 10
- 238000009434 installation Methods 0.000 description 8
- 229910000838 Al alloy Inorganic materials 0.000 description 5
- OAKJQQAXSVQMHS-UHFFFAOYSA-N Hydrazine Chemical compound NN OAKJQQAXSVQMHS-UHFFFAOYSA-N 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000740 bleeding effect Effects 0.000 description 1
- 238000007084 catalytic combustion reaction Methods 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- HDZGCSFEDULWCS-UHFFFAOYSA-N monomethylhydrazine Chemical compound CNN HDZGCSFEDULWCS-UHFFFAOYSA-N 0.000 description 1
- 229910052755 nonmetal Inorganic materials 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/242—Orbits and trajectories
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/244—Spacecraft control systems
Abstract
The invention relates to a satellite orbit control power system, which comprises a main frame, a high-pressure gas cylinder, a storage tank and an engine, wherein the high-pressure gas cylinder, the storage tank and the engine are respectively arranged on the main frame; the gas path valve assembly is used for controlling gas to flow to the storage tank so as to extrude the propellant; a liquid path valve assembly is arranged between the engine and the storage tank and used for controlling the flow of the propellant to the engine to generate thrust. The satellite orbit control power system provided by the invention has the advantages of high integration level, simple and compact structure, capability of generating larger thrust, capability of meeting the requirements of orbit change and orbit release of a medium-sized satellite, and capability of solving the problems of complex structure and limited thrust of the conventional satellite power system.
Description
Technical Field
The invention belongs to the technical field of space vehicles, and particularly relates to a satellite orbit control power system.
Background
With the vigorous development of aerospace industry in China, satellites are widely applied to the fields of communication, ground remote measurement and the like. The power system of the satellite performs tasks of putting the satellite into a working orbit, performing orbit conversion and attitude adjustment according to the task requirements of the satellite, and leaving the orbit.
In the prior art, most of power systems applied to medium-sized satellites are high in cost and complex in structure, and a variable/off-orbit power system specially aiming at the medium-sized satellites is not provided, so that the problems of high off-orbit difficulty and slow off-orbit of the medium-sized satellites are caused by limited thrust of the power systems at the end of the service life of the medium-sized satellites. Therefore, it is urgent to develop a power system for changing/derailing for medium-sized satellites.
Disclosure of Invention
The invention aims to solve the problems of complex structure and limited thrust of a satellite power system. The purpose is realized by the following technical scheme:
the invention provides a satellite orbit control power system, which comprises a main frame, a high-pressure gas cylinder, a storage box and an engine, wherein the high-pressure gas cylinder, the storage box and the engine are respectively arranged on the main frame, and the high-pressure gas cylinder is used for storing gas; the gas path valve assembly is used for controlling the gas to flow to the storage tank so as to extrude the propellant; a liquid path valve assembly is arranged between the engine and the storage tank and used for controlling the propellant to flow to the engine to generate thrust, and the liquid path valve assembly are both arranged in the main frame.
According to the satellite orbit control power system provided by the embodiment of the invention, the high-pressure gas cylinder, the storage box and the engine are all arranged on the main frame, so that the integration level of the satellite orbit control power system is improved; the high-pressure gas cylinder is communicated with the storage tank through the gas circuit valve assembly, the storage tank is communicated with the engine through the liquid circuit valve assembly, gas in the high-pressure gas cylinder can flow into the storage tank through the control of the gas circuit valve assembly and extrude propellant in the storage tank, so that the propellant can enter the engine through the control of the liquid circuit valve assembly, and the gas circuit valve assembly and the liquid circuit valve assembly are both arranged in the main frame, so that the integration level of the satellite orbit control power system is further improved.
In addition, in some embodiments of the present invention, the high pressure gas cylinder and the tank are installed inside the main frame near opposite sides of the main frame, respectively, and the engine is installed at the bottom of the main frame.
In some embodiments of the present invention, the gas circuit valve assembly includes a high pressure solenoid valve, a pressure reducing valve and a check valve which are sequentially communicated through a pipeline, the high pressure solenoid valve is communicated with the high pressure gas cylinder, and the check valve is communicated with the tank.
In some embodiments of the present invention, the satellite orbit control power system further comprises an inflation valve and a first joint, the inflation valve is communicated between the high pressure gas cylinder and the high pressure solenoid valve through the first joint, and the inflation valve is used for inflating or deflating the high pressure gas cylinder.
In some embodiments of the present invention, the satellite tracking power system further comprises a high pressure sensor and a second joint, the second joint is communicated between the first joint and the high pressure solenoid valve, and the high pressure sensor is communicated with the second joint to detect air pressure.
In some embodiments of the invention, the fluid line valve assembly comprises a fill drain valve, a fluid line solenoid valve and a third connector, the fill drain valve and the fluid line solenoid valve being connected to the tank through the third connector.
In some embodiments of the invention, the satellite orbital control power system further comprises a hydraulic pressure sensor in communication with the third joint to detect hydraulic pressure.
In some embodiments of the invention, the engine comprises a thrust chamber, and one end of the liquid path solenoid valve, which is far away from the third joint, is communicated to the thrust chamber.
In some embodiments of the invention, the main frame is provided as a metal housing in a rectangular parallelepiped shape.
In some embodiments of the invention, the gas is provided as nitrogen or helium.
Drawings
Various additional advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like parts are designated by like reference numerals throughout the drawings.
In the drawings:
fig. 1 is a first schematic structural diagram of a satellite orbit control power system according to an embodiment of the invention;
fig. 2 is a schematic structural diagram of a satellite orbit control power system according to an embodiment of the invention.
The reference symbols in the drawings denote the following:
100. a satellite orbit control power system;
10. a main frame; 11. a metal housing;
20. a high pressure gas cylinder;
30. a storage tank;
40. an engine; 41. a thrust chamber;
511. a first joint; 512. a second joint; 52. an inflation valve; 53. a high pressure sensor; 54. a high-pressure solenoid valve; 55. a pressure reducing valve; 56. a one-way valve;
61. filling and discharging valves; 62. a liquid path solenoid valve; 63. a third joint; 64. liquid path pressure sensor.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
It is to be understood that the terminology used herein is for the purpose of describing particular example embodiments only, and is not intended to be limiting. As used herein, the singular forms "a", "an" and "the" may be intended to include the plural forms as well, unless the context clearly indicates otherwise. The terms "comprises," "comprising," "including," and "having" are inclusive and therefore specify the presence of stated features, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, steps, operations, elements, components, and/or groups thereof.
Although the terms first, second, third, etc. may be used herein to describe various elements, components, regions, layers and/or sections, these elements, components, regions, layers and/or sections should not be limited by these terms. These terms may be only used to distinguish one element, component, region, layer or section from another region, layer or section. Terms such as "first," "second," and other numerical terms when used herein do not imply a sequence or order unless clearly indicated by the context. Thus, a first element, component, region, layer or section discussed below could be termed a second element, component, region, layer or section without departing from the teachings of the example embodiments.
For convenience of description, spatially relative terms, such as "inner", "outer", "lower", "below", "upper", "above", and the like, may be used herein to describe one element or feature's relationship to another element or feature as illustrated in the figures. Such spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "below" or "beneath" other elements or features would then be oriented "above" or "over" the other elements or features. Thus, the example term "below … …" can include both an orientation of above and below.
As shown in fig. 1 and 2, an embodiment of the present invention provides a satellite orbit control power system 100, where the satellite orbit control power system 100 includes a main frame 10, a high-pressure gas cylinder 20, a storage tank 30, and an engine 40, the high-pressure gas cylinder 20, the storage tank 30, and the engine 40 are respectively mounted on the main frame 10, and the high-pressure gas cylinder 20 is used for storing gas; the storage tank 30 is used for storing propellant, and an air path valve assembly is arranged between the storage tank 30 and the high-pressure gas cylinder 20 and is used for controlling the gas in the high-pressure gas cylinder 20 to flow to the storage tank 30 so as to extrude the propellant; a fluid path valve assembly is provided between the engine 40 and the tank 30 for controlling the flow of propellant to the engine 40 to generate thrust.
According to the satellite orbit control power system 100 provided by the embodiment of the invention, the high-pressure gas cylinder 20, the storage box 30 and the engine 40 are all arranged on the main frame 10, so that the integration level of the satellite orbit control power system 100 is improved; the high-pressure gas cylinder 20 is communicated with the storage tank 30 through the gas circuit valve assembly, the storage tank 30 is communicated with the engine 40 through the liquid circuit valve assembly, gas in the high-pressure gas cylinder 20 can flow into the storage tank 30 through the control of the gas circuit valve assembly to extrude propellant in the storage tank 30, so that the propellant enters the engine 40 through the control of the liquid circuit valve assembly, and the gas circuit valve assembly and the liquid circuit valve assembly are both arranged in the main frame 10, so that the integration level of the satellite orbit control power system 100 is further improved.
In the present embodiment, the high pressure gas cylinder 20, the storage tank 30, and the engine 40 are all disposed in the main frame 10, and the shape of the main frame 10 may be a prism or a cylinder, which is not particularly limited in the present embodiment. In an alternative embodiment, as shown in fig. 1 and 2, the main frame 10 is shaped as a rectangular parallelepiped to facilitate installation of internal structures, and on this basis, the high pressure gas cylinder 20 and the storage tank 30 are both installed inside the main frame 10, as shown in fig. 1, the high pressure gas cylinder 20 and the storage tank 30 are respectively disposed near two opposite sides of the main frame 10, for example, may be respectively disposed near two side edges of the main frame 10 at two ends of a diagonal line, thereby facilitating arrangement of other components inside the main frame 10, substantially improving the internal space utilization of the main frame 10, and improving the structural integration, and the engine 40 is installed at the bottom of the main frame 10 to facilitate inflow of propellant in the storage tank 30 from high to low, i.e., ensuring that the propellant fully enters the engine 40, and improving the thrust of the engine 40.
Further, the high pressure gas cylinder 20 and the tank 30 may be mounted on the main frame 10 by fasteners such as brackets, clamp coupling bolts, screws, etc. to ensure stability of the overall structure; the main frame 10 may be provided as a metal frame or a non-metal frame, and for example, the main frame 10 may be provided as an aluminum alloy frame, or, as shown in fig. 2, the main frame 10 may be provided as a metal housing 11, such as an aluminum alloy housing, which facilitates the installation of the internal structure while ensuring the reliability and light weight of the main frame 10. On this basis, the high-pressure gas cylinder 20 and the tank 30 are both mounted inside an aluminum alloy case, and the engine 40 is mounted on the bottom of the aluminum alloy case, and it is understood that the thrust chamber 41 in the engine 40 at least partially protrudes from the bottom of the aluminum alloy case and generates thrust by burning a propellant.
As shown in fig. 1, in the present embodiment, an air passage valve assembly is disposed between the tank 30 and the high-pressure gas cylinder 20, and the air passage valve assembly is also mounted in the main frame 10 and may be disposed in a space between the high-pressure gas cylinder 20 and the tank 30; a liquid path valve assembly is arranged between the engine 40 and the storage tank 30, the liquid path valve assembly is also arranged in the main frame 10, can be arranged in the space between the high-pressure gas cylinder 20 and the storage tank 30 and is positioned above the engine 40, and each component in the gas path valve assembly and the liquid path valve assembly can also be arranged on the main frame 10 through a bracket or a hoop, and a fastening piece such as a bolt, a screw and the like is combined to ensure the stability of the whole structure. In this embodiment, the gas circuit valve assembly and the liquid circuit valve assembly are integrally installed in the main frame 10, so that the integration level of the satellite orbit control power system 100 is improved, the disorder of pipelines is avoided, the overall structure is further simplified, the gas circuit valve assembly arranged in a centralized manner is convenient for high-pressure gas to rapidly flow into the storage tank 30 to extrude propellant, and the liquid circuit valve assembly arranged in a centralized manner is convenient for the propellant to rapidly and fully enter the engine 40, so that the thrust of the engine 40 is improved.
On the basis of the above embodiments, the high pressure gas cylinder 20 stores gas therein, and the gas can reach a specific pressure in the high pressure gas cylinder 20 to form high pressure gas, and in some embodiments of the present invention, the high pressure gas is set to be nitrogen or helium; the tank 30 stores therein a propellant, which is a liquid propellant, and may be, for example, anhydrous hydrazine, methylhydrazine, monopropyl-3, or the like, and the present embodiment is not particularly limited to the types of high-pressure gas and propellant.
Further, as shown in fig. 1, the satellite orbit control power system 100 further includes an inflation valve 52, and the inflation valve 52 is in communication with the high pressure gas cylinder 20 for inflating the high pressure gas cylinder 20 or deflating the high pressure gas cylinder 20. The charging valve 52 can be connected to the high pressure gas cylinder 20 through a pipeline alone, or can be connected to the gas circuit valve assembly, when the charging valve 52 is connected to the gas circuit valve assembly, the number of pipelines can be reduced, and the structure can be further simplified, and the following embodiments will describe the installation manner of the charging valve 52 by combining the specific structure of the gas circuit valve assembly.
Further, as shown in fig. 1, the satellite tracking power system 100 further includes a high pressure sensor 53, and the high pressure sensor 53 is communicated with the high pressure gas cylinder 20 or a pipeline in the air valve assembly, and is used for detecting the gas pressure in the high pressure gas cylinder 20 or the pipeline. The high-pressure sensor 53 may be separately communicated with the high-pressure gas cylinder 20 through a pipeline, or may be communicated with the gas circuit valve assembly, when the high-pressure sensor 53 is communicated with the gas circuit valve assembly, the number of pipelines may be reduced, and the structure may be further simplified, and the following embodiments will describe the installation manner of the high-pressure sensor 53 in combination with the specific structure of the gas circuit valve assembly.
With continued reference to fig. 1, in some embodiments of the present invention, the air passage valve assembly includes a plurality of pipelines, and a high pressure solenoid valve 54, a pressure reducing valve 55 and a check valve 56 sequentially connected through the plurality of pipelines, wherein one end of the high pressure solenoid valve 54 is connected to the high pressure air bottle 20, the other end of the high pressure solenoid valve 54 is connected to the pressure reducing valve 55, one end of the pressure reducing valve 55 far from the high pressure solenoid valve 54 is connected to the check valve 56, and the other end of the check valve 56 is connected to the tank 30. That is, a pipeline is disposed between each adjacent two of the high pressure gas cylinder 20, the high pressure solenoid valve 54, the pressure reducing valve 55, the check valve 56 and the storage tank 30, and a plurality of pipelines are adaptively arranged according to the internal space of the main frame 10, and the pipeline may be a straight pipeline according to actual conditions, or may be a bent pipeline or an arc pipeline.
On the basis of the above embodiment, the satellite orbit control power system 100 further comprises a first connector 511 and a second connector 512, wherein the first connector 511 is used for communicating the inflation valve 52 with the pipeline of the air valve assembly, and the second connector 512 is used for communicating the high pressure sensor 53 with the pipeline of the air valve assembly. In this embodiment, the first connector 511 and the second connector 512 are installed on the pipeline of the air valve assembly, and the pipeline of the air valve assembly is used to realize multi-structure integration, thereby making full use of the internal space of the main frame 10 and simplifying the structure.
In an alternative embodiment, as shown in fig. 1, the first connector 511 and the second connector 512 are both provided as three-way connectors, and the first connector 511 and the second connector 512 are sequentially communicated with a pipeline between the high-pressure gas cylinder 20 and the high-pressure solenoid valve 54, that is, a first end of the first connector 511 (three-way connector) is communicated with the high-pressure gas cylinder 20, a second end opposite to the first end is communicated with the pipeline, and a third end is communicated with the charging valve 52; a first end of the second joint 512 (three-way joint) communicates with the above-mentioned pipe, a second end provided opposite to the first end communicates with the high-pressure solenoid valve 54, and a third end communicates with the high-pressure sensor 53.
Therefore, before the satellite orbit control power system 100 works, the second end of the first connector 511 is closed, the first end of the first connector 511 is communicated with the third end, and high-pressure gas can be filled into the high-pressure gas cylinder 20 from the gas filling valve 52 and the first connector 511; during the operation of the satellite orbit control power system 100, the third end of the first joint 511 is closed, the first end is communicated with the second end, high-pressure gas flows out from the high-pressure gas cylinder 20 and flows through the second joint 512 via the first joint 511, and the high-pressure sensor 53 connected to the second joint 512 can detect the gas pressure; then, the high-pressure gas flows through the high-pressure solenoid valve 54, and under the condition that the high-pressure solenoid valve 54 is opened, the high-pressure gas sequentially flows through the pressure reducing valve 55 and the check valve 56 through a pipeline, wherein the pressure reducing valve 55 is used for reducing the pressure of the high-pressure gas to the gas pressure required for extruding the propellant in the storage tank 30, and the reduced-pressure gas flows into the storage tank 30 through the check valve 56.
On the basis of the above embodiment, as shown in fig. 1, the pipeline of the gas path valve assembly located between the high pressure gas cylinder 20 and the first connector 511 is connected to the top of the high pressure gas cylinder 20, and extends upward and then extends along the horizontal direction, taking the main frame 10 as the metal housing 11 as an example, as shown in fig. 1, the first connector 511 is close to the side wall of the main frame 10, as shown in fig. 2, the inflation valve 52 connected to the first connector 511 is partially exposed out of the metal housing 11, and the inflation valve 52 can be connected to the metal housing 11 through a fastener such as a bolt or a screw, so as to ensure stability; the pipeline connected to the second end of the first joint 511 extends downwards first, bends near the bottom of the metal shell 11 and then extends upwards until being communicated with the second joint 512; the pipeline connected to the second end of the second joint 512 extends upwards and then extends towards one side close to the high-pressure gas cylinder 20 along the horizontal direction until the pipeline is communicated with the high-pressure electromagnetic valve 54; the pressure reducing valve 55, the check valve 56 and the rest of the pipes are located above the high pressure gas cylinder 20, arranged along the circumferential direction of the main frame 10, and extend toward the tank 30 until communicating from the top of the tank 30 to the tank 30.
In the embodiment, the inflation valve 52 is partially exposed out of the metal shell 11, so as to facilitate inflation or deflation of the high-pressure gas cylinder 20; the high-pressure gas cylinder 20, the position overall arrangement of pipeline and each part and storage tank 30 among the gas circuit valve subassembly is clear reasonable, make full use of the installation space that main frame 10 provided, make overall structure simple and clear, be convenient for maintain, and through the pipeline setting that will be close to storage tank 30 in storage tank 30 top, and communicate with storage tank 30's top, guaranteed that gaseous top-down gets into storage tank 30, fully extrude the propellant in the storage tank 30, make the propellant can fully flow into in the engine 40, and then fully burn and improve thrust.
In some embodiments of the present invention, as shown in fig. 1, the fluid circuit valve assembly includes a fill and bleed valve 61, a fluid circuit solenoid valve 62 and a plurality of conduits, wherein the fluid circuit solenoid valve 62 is in communication between the reservoir 30 and the engine 40, and the fill and bleed valve 61 is in communication with the reservoir 30 for filling the reservoir 30 with propellant or for bleeding propellant from the reservoir 30. The filling and discharging valve 61 may be separately communicated with the tank 30 through a pipeline, or may be communicated with a pipeline between the tank 30 and the liquid path electromagnetic valve 62, when the filling and discharging valve 61 is communicated with the pipeline, the number of pipelines can be reduced, and the structure can be further simplified, and the following embodiment will describe the installation manner of the filling and discharging valve 61 in combination with the specific structure of the liquid path valve assembly.
In some embodiments of the present invention, the satellite orbiting power system 100 further includes a liquid path pressure sensor 64, the liquid path pressure sensor 64 is in communication with the pipeline in the liquid path valve assembly for detecting the pressure of the liquid propellant in the pipeline, and the following embodiments will describe the installation manner of the liquid path pressure sensor 64 with reference to the specific structure of the liquid path valve assembly.
With continued reference to fig. 1, in some embodiments of the present invention, the fluid path valve assembly includes a third connector 63, the third connector 63 is a four-way connector, the third connector 63 can be disposed below the tank 30, and a first end of the third connector 63 (four-way connector) is in communication with the bottom of the tank 30 to facilitate the outflow of propellant; the second end is communicated with the filling and discharging valve 61 directly or through a pipeline; the third end is communicated with the liquid path pressure sensor 64 directly or through a pipeline; the fourth end is in communication with a fluid line solenoid valve 62, either directly or via a conduit, the fluid line solenoid valve 62 being in communication with the engine 40 via a conduit.
Therefore, before the satellite orbit control power system 100 works, the third end and the fourth end of the third joint 63 can be closed, the first end of the third joint 63 is communicated with the second end, the propellant can be filled into the storage tank 30 from the filling and discharging valve 61 and the third joint 63, during the work of the satellite orbit control power system 100, the second end of the third joint 63 is closed, the first end is communicated with the third end and the fourth end, the propellant flows out of the storage tank 30 and flows through the third joint 63, and the liquid pressure sensor 64 connected to the third joint 63 can detect the liquid pressure; when the fluid solenoid valve 62 connected to the third connector 63 is in an open condition, propellant can flow into the engine 40 through the fluid solenoid valve 62.
On the basis of the above embodiment, as shown in fig. 1, the pipeline of the fluid path valve assembly located between the tank 30 and the third joint 63 is connected to the bottom of the tank 30, and extends horizontally to communicate with the third joint 63, taking the main frame 10 as the metal housing 11 as an example, as shown in fig. 1, the third joint 63 is close to the bottom of the main frame 10, the pipeline connected to the second end of the third joint 63 extends along the horizontal direction, as shown in fig. 2, a part of the filling and discharging valve 61 connected to the third joint 63 is exposed out of the metal housing 11, the filling and discharging valve 61 may be located on the same side of the metal housing 11 as the inflation valve 52, and the filling and discharging valve 61 may be connected to the metal housing 11 by a fastener such as a bolt or a screw, so as to ensure stability; the pipeline connected to the third end of the third joint 63 extends towards the side far away from the storage tank 30 along the horizontal direction until the pipeline is communicated with the liquid path pressure sensor 64; the pipeline connected to the fourth end of the third joint 63 extends upwards until the pipeline is communicated with the liquid solenoid valve 62; the pipe connected between the fluid passage solenoid valve 62 and the engine 40 is bent downward.
Further, in some embodiments of the present invention, the engine 40 includes a solenoid valve and a thrust chamber 41, an end of the liquid path solenoid valve 62 away from the third joint 63 is connected to the thrust chamber 41 through a pipeline, and the solenoid valve of the engine 40 may be connected to the pipeline between the liquid path solenoid valve 62 and the thrust chamber 41 directly or through a pipeline to control the flow of the propellant in the pipeline. As shown in fig. 1, the engine 40 may be mounted at the bottom of the main frame 10 by a bracket, a bolt, a screw, or other fasteners, and the thrust chamber 41 of the engine 40 partially or completely extends out of the main frame 10, as shown in fig. 2, taking the main frame 10 as the metal housing 11 as an example, and the thrust chamber 41 is partially or completely located outside the bottom plate of the metal housing 11.
In the embodiment, the filling and discharging valve 61 is partially exposed out of the metal shell 11, so that the propellant can be filled into and discharged from the storage tank 30 conveniently; the position layout of pipelines and all parts in the storage tank 30 and the liquid path valve assembly and the engine 40 is clear and reasonable, the installation space provided by the main frame 10 is fully utilized, the whole structure is simple and clear, the maintenance is convenient, and the liquid propellant pipelines are arranged below the storage tank 30 and communicated with the top of the engine 40, so that the liquid propellant flows into the engine 40 from top to bottom, and the thrust is improved by full combustion.
In summary, in the satellite orbit control system provided in this embodiment, the high-pressure gas is charged into the high-pressure gas cylinder 20 through the charging valve 52, so that the high-pressure gas in the high-pressure gas cylinder 20 reaches a specific pressure; propellant is filled into the reservoir 30 through a fill and bleed valve 61; during operation, the high-pressure solenoid valve 54 in the gas path valve assembly is opened, the high-pressure gas flows through the pressure reducing valve 55 to reduce the pressure, then enters the storage tank 30 through the check valve 56, so that the propellant in the storage tank 30 is extruded out, the liquid path solenoid valve 62 in the liquid path valve assembly is opened, the solenoid valve of the engine 40 is opened before the propellant enters the engine 40, and the propellant enters the thrust chamber 41 for catalytic combustion, so that the thrust is generated.
The satellite orbit control system provided by the embodiment has the characteristics of reasonable and compact structure, light weight, low cost and high thrust, is higher in specific impulse compared with a cold air power system, is simpler and more reliable compared with a two-component power system, can meet the requirements of medium-sized satellite orbit changing and off-orbit, can be delivered as a complete product, and has a very wide application space.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are also included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (10)
1. The satellite orbit control power system is characterized by comprising a main frame, a high-pressure gas cylinder, a storage box and an engine, wherein the high-pressure gas cylinder, the storage box and the engine are respectively arranged on the main frame, and the high-pressure gas cylinder is used for storing gas; the gas path valve assembly is used for controlling the gas to flow to the storage tank so as to extrude the propellant; a liquid path valve assembly is arranged between the engine and the storage tank and used for controlling the propellant to flow to the engine to generate thrust, and the liquid path valve assembly are both arranged in the main frame.
2. The satellite-orbiting power system of claim 1 wherein the high pressure gas cylinder and the tank are mounted inside the main frame adjacent to opposite sides of the main frame, respectively, and the motor is mounted to the bottom of the main frame.
3. The satellite orbit control power system according to claim 1, wherein the gas circuit valve assembly comprises a high pressure solenoid valve, a pressure reducing valve and a one-way valve which are sequentially communicated through a pipeline, the high pressure solenoid valve is communicated with the high pressure gas cylinder, and the one-way valve is communicated with the storage tank.
4. The satellite orbit control power system of claim 3, further comprising an inflation valve and a first joint, wherein the inflation valve is communicated between the high pressure gas cylinder and the high pressure solenoid valve through the first joint, and the inflation valve is used for inflating or deflating the high pressure gas cylinder.
5. The satellite-orbiting power system of claim 4 further comprising a high pressure sensor and a second connector, said second connector communicating between said first connector and said high pressure solenoid valve, said high pressure sensor communicating with a second connector to detect air pressure.
6. The satellite orbital control power system of claim 1, wherein the fluid path valve assembly comprises a fill drain valve, a fluid path solenoid valve, and a third connector, the fill drain valve and the fluid path solenoid valve being connected to the tank through the third connector.
7. The satellite orbiting power system of claim 6 further comprising a hydraulic pressure sensor in communication with the third joint to detect hydraulic pressure.
8. The satellite-orbiting power system of claim 7 wherein the engine includes a thrust chamber, and an end of the fluid line solenoid valve remote from the third connector communicates to the thrust chamber.
9. The satellite orbital control power system according to claim 1, wherein the main frame is provided as a rectangular parallelepiped metal housing.
10. The satellite-orbiting power system of claim 1 wherein the gas is provided as nitrogen or helium.
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