CN113323771A - Modular power system for spacecraft and power propulsion method - Google Patents
Modular power system for spacecraft and power propulsion method Download PDFInfo
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- CN113323771A CN113323771A CN202110759356.3A CN202110759356A CN113323771A CN 113323771 A CN113323771 A CN 113323771A CN 202110759356 A CN202110759356 A CN 202110759356A CN 113323771 A CN113323771 A CN 113323771A
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- 238000000034 method Methods 0.000 title claims abstract description 7
- 239000003380 propellant Substances 0.000 claims abstract description 153
- 238000001125 extrusion Methods 0.000 claims abstract description 39
- 230000006835 compression Effects 0.000 claims abstract description 15
- 238000007906 compression Methods 0.000 claims abstract description 15
- 230000007246 mechanism Effects 0.000 claims abstract description 8
- 239000007789 gas Substances 0.000 claims description 141
- 239000007800 oxidant agent Substances 0.000 claims description 10
- 239000000446 fuel Substances 0.000 claims description 8
- 239000012528 membrane Substances 0.000 claims description 3
- 239000002828 fuel tank Substances 0.000 claims 1
- 230000010355 oscillation Effects 0.000 claims 1
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 230000002708 enhancing effect Effects 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 238000012423 maintenance Methods 0.000 description 3
- 238000007599 discharging Methods 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000001590 oxidative effect Effects 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—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
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/401—Liquid propellant rocket engines
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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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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/50—Feeding propellants using pressurised fluid to pressurise the propellants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/56—Control
- F02K9/58—Propellant feed valves
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
A modular power system for a spacecraft and a method of power propulsion. The invention comprises the following components: an engine module located lowermost in the overall system; a propellant module is connected with the engine module; a compression module is connected to the propellant module; the load module is arranged above the extrusion module; the engine module, the propellant module, the extrusion module and the load module are fixedly connected through a support structure. The invention integrates all gas circuit valves, pipelines, high-pressure gas cylinders and the like into the extrusion module, integrates all propellant valves, pipelines, storage tanks and the like into the propellant module, and integrates the thrust chamber, the electromagnetic valve, the servo mechanism and the like into the engine module, thereby simplifying the structure of the power system, greatly improving the assembly efficiency of the power system, reducing the production cost, saving the space and enhancing the reliability and the maintainability of the system.
Description
The technical field is as follows:
the invention relates to a modular power system for a spacecraft and a power propulsion method.
Background art:
the space attitude and orbit control engine is widely applied to rocket upper stages and satellites and is the key to whether a flight task is successful or not. The bipropellant attitude and orbit control engine has the advantages of high specific impulse, high precision, multiple starting, wide thrust range and the like, and is widely applied to an aircraft power system. The two-component engine comprises a high-pressure gas cylinder, a storage tank, a thrust chamber, a valve, a pipeline and the like, and has the problems of multiple system components, complex pipeline layout, lower space utilization rate, complex installation, inconvenient maintenance and the like.
The invention content is as follows:
the invention aims to provide a modular power system and a power propulsion method for a spacecraft, which solve the problems of complex layout of a valve component and a pipeline of an air path system, low space utilization rate, complex installation and inconvenient maintenance.
The above purpose is realized by the following technical scheme:
a modular power system for a spacecraft, comprising:
an engine module located lowermost in the overall system;
a propellant module connected with the engine module;
a compression module connected with the propellant module;
a load module disposed above the extrusion module;
the engine module, the propellant module, the extrusion module and the load module are fixedly connected through a support structure.
Furthermore, the extrusion module comprises an annular gas cylinder, the annular gas cylinder is provided with a gas filling port, high-pressure gas in the annular gas cylinder reaches a first gas outlet of the extrusion module and a second gas outlet of the extrusion module through the combination of a valve and a sensor, the first gas outlet is connected with a third gas pipeline, and the second gas outlet is connected with a fourth gas pipeline.
Further, the first gas outlet reaches the extrusion gas first inlet of the propellant module through a gas third line;
the second gas outlet reaches the extrusion three-way inlet of the propellant module through a fourth gas line.
The modular power system for a spacecraft described, the propellant module comprising a first reservoir of propellant and a second reservoir of propellant;
the propellant first tank is provided with a first compressed gas inlet above, and the propellant reaches the first propellant inlet of the engine module from the propellant valve through a propellant first pipeline;
the inlet of the tee joint of the first propellant storage tank is connected with a tee joint, and the tee joint is provided with a first outlet of the tee joint and a second outlet of the tee joint;
the three-way first outlet is connected with an extrusion gas second inlet, the extrusion gas second inlet is connected with a propellant second storage tank, and propellant in the propellant second storage tank reaches a propellant second inlet of the engine module from a propellant valve through a propellant second pipeline;
and a second outlet of the tee joint is connected with one end of a second gas pipeline, the other end of the second gas pipeline is connected with a gas inlet of the engine module, and the propellant reaches the electromagnetic valve through the gas inlet.
Further, the first propellant inlet is a fuel inlet and the second propellant inlet is an oxidizer inlet.
Further, the first propellant reservoir is a fuel reservoir and the second propellant reservoir is an oxidizer reservoir.
Further, the propellant valve consists of a charging and discharging valve, a membrane valve and a filter.
Further, the engine module comprises an engine, the engine is formed by fixedly connecting a thrust chamber and an electromagnetic valve through bolts, and the engine is connected with the supporting structure through a servo mechanism.
Further, the number of the servo mechanisms is at least 4, and the swinging of the engine along four directions is met.
A propulsion method using the modular power system for spacecraft of one of claims 1 to 9, high pressure gas being charged to the toroidal gas cylinder through a charging valve, the high pressure gas in the toroidal gas cylinder reaching the extrusion module first gas outlet and reaching the extrusion module second gas outlet through a valve and sensor combination, the two gases reaching the extrusion gas first inlet and the three-way inlet of the propellant module through a gas third line and a gas fourth line, respectively:
one path of gas enters a first propellant storage tank from a first extrusion gas inlet through a diaphragm valve, the propellant in the storage tank is extruded, and the propellant reaches a first propellant inlet of an engine module from a propellant valve through a first propellant pipeline; the other path of gas is divided into two paths after passing through the tee joint of the propellant module:
one path of the propellant flows into a first gas pipeline and a second extruded gas inlet through a first outlet of the tee joint, enters a second propellant storage tank through the diaphragm valve, extrudes the propellant in the storage tank, and reaches the second propellant inlet of the engine module from the propellant valve through the second propellant pipeline; the other path of gas flows into a gas second pipeline through a second outlet of the tee joint to reach a gas inlet of the engine module and finally reaches the electromagnetic valve;
the electromagnetic valve is opened and closed by controlling gas in the electromagnetic valve, so that the propellant is controlled to enter the thrust chamber through the first propellant inlet and the second propellant inlet, and the propellant is combusted in the thrust chamber to generate thrust.
The invention has the beneficial effects that:
the engine module, the propellant module, the extrusion module and the load module are connected and fixed through the supporting structure, and a complex power system is simplified into the engine module, the propellant module and the extrusion module. The system integrates all gas circuit valves, pipelines, high-pressure gas cylinders and the like into an extrusion module, integrates all propellant valves, pipelines, storage tanks and the like into a propellant module, and integrates a thrust chamber, an electromagnetic valve, a servo mechanism and the like into an engine module, so that the structure of the power system is simplified, the assembly efficiency of the power system is greatly improved, the production cost is reduced, the space is saved, and the reliability and the maintainability of the system are enhanced. The problems of complex layout of valve components and pipelines of the gas circuit system, low space utilization rate, complex installation and inconvenient maintenance are solved. The power system layout is more compact, the quality is effectively reduced, the reliability is obviously improved, and the power system has good applicability to the two-component liquid attitude and orbit control engine.
Description of the drawings:
FIG. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a schematic structural view of an extrusion module of the present invention.
Figure 3 is a schematic diagram of the construction of a propellant module of the present invention.
FIG. 4 is a schematic block diagram of an engine module according to the present invention.
Wherein the figures include the following reference numerals:
100. an engine module;
110. a thrust chamber;
120. an electromagnetic valve; 121. a first propellant inlet; 122. A second propellant inlet; 123. a gas inlet;
130. a servo mechanism;
200. a propellant module;
210. a first inlet for an extrusion gas;
220. a first reservoir of propellant;
230. a tee joint; 231. a three-way inlet; 232. a first outlet of the tee joint; 233. a second outlet of the tee joint;
240. a first gas pipeline and a second extrusion gas inlet;
250. a second conduit for gas;
260. a propellant first line;
270. a second line of propellant;
280. a propellant valve;
290. a second reservoir of propellant;
300. an extrusion module;
310. an inflation inlet;
320. a high pressure gas cylinder;
330. an extrusion module first gas outlet;
340. a third gas line;
350. a second gas outlet of the extrusion module;
360. a gas fourth line;
370. valves and sensors;
400. a load module;
666. a support structure.
The specific implementation mode is as follows:
in order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
The invention provides a modularized power system for a spacecraft, which comprises the following components in part by weight as shown in the attached figure 1: an engine module 100, a propellant module 200 and a compression module 300. The load module 400 is positioned above the compression module 300 and the engine module 100, propellant module 200, compression module 300 and load module 400 are secured together by a support structure 666.
The material of the supporting structure 666 is aluminum alloy, and the supporting structure is designed in a light weight mode, and the structural strength is guaranteed through triangular ribs.
As shown in fig. 2, the compression module 300 is composed of a gas charging port 310, a high pressure gas cylinder 320, a compression module first gas outlet 330, a gas third pipeline 340, a compression module second gas outlet 350, a gas fourth pipeline 360, and a valve and sensor 370.
A diaphragm valve may be, but is not limited to, disposed between the pressurized gas first inlet 210 and the propellant first reservoir 220;
the charging port 310 is connected with a high-pressure gas cylinder 320, and the high-pressure gas cylinder 320 can be annular or cylindrical and can be one or more;
the extrusion module first gas outlet 330 is connected with a gas third pipeline 340, and the other end of the gas third pipeline 340 is connected with the extrusion gas first inlet 210 of the propellant module 200;
the second gas outlet 350 of the extrusion module is connected with a fourth gas pipeline 360, and the other end of the fourth gas pipeline 360 is connected with the three-way inlet 231 of the propellant module 200;
the valve and sensor combination 370 primarily includes, but is not limited to, an electric burst valve, a pressure relief valve, a safety valve, a check valve, a pressure sensor, etc., for reducing the pressure of the high pressure gas to a level that can be used by the tank.
As shown in fig. 3, the propellant module 200 is composed of a first inlet 210 for extruding gas, a first tank 220 for propellant, a three-way 230, a three-way inlet 231, a first outlet 232 for three-way, a second outlet 233 for three-way, a first inlet 240 for gas and a second inlet 240 for extruding gas, a second pipeline 250 for gas, a first pipeline 260 for propellant, a second pipeline 270 for propellant, a valve 280 for propellant, and a second tank 290 for propellant.
The first gas line and the second extrusion gas inlet 240 are connected to the three-way first outlet 232; one end of the gas second pipeline 250 is connected with the third-way second outlet 233, and the other end is connected with the gas inlet 123 of the engine module; the propellant first line 260 is connected at one end to a propellant valve 280 and at the other end to the first propellant inlet 123 of the engine module; the propellant second line 270 is connected at one end to a propellant valve 280 and at the other end to the second propellant inlet 123 of the engine module.
The first propellant reservoir 220 is a fuel reservoir and the second propellant reservoir 290 is an oxidizer reservoir; the propellant first tank 220 and propellant second tank 290 may be, but are not limited to being, bolted to support structure 666; a diaphragm valve is provided between the first inlet 210 for pressurised gas and the first reservoir 220 for propellant.
The tee 230 can be, but is not limited to be, fixed on the support structure 666 by screws, and the tee 230 comprises three interfaces of a tee inlet 231, a tee first outlet 232 and a tee second outlet 233;
the first gas line and second extrusion gas inlet 240 is connected to the tee first outlet 232;
one end of the gas second pipeline 250 is connected with the third-way second outlet 233, and the other end is connected with the gas inlet 123 of the engine module;
the propellant first line 260 is connected at one end to a propellant valve 280 and at the other end to the first propellant inlet 123 of the engine module;
one end of the second propellant pipeline 270 is connected with a propellant valve 280, and the other end is connected with a second propellant inlet 123 of the engine module;
the propellant valves 280 have two sets, and each storage tank is provided with one set, and can be but not limited to be composed of a charging and discharging valve, a membrane valve and a filter.
As shown in fig. 4, the engine module 100 is composed of a thrust chamber 110, a solenoid valve 120, a first propellant inlet 121, a second propellant inlet 122, a gas inlet 123 and a servo 130; the thrust chamber 110 and the solenoid valve 120 may be, but not limited to, fixed by bolts to form an engine, and the engine is connected to the support structure 666 by the servo mechanism 130;
the servo mechanisms 130 can be, but are not limited to, four, and can meet the swinging of the engine along four directions;
the solenoid valve 120 may be, but is not limited to, a pneumatic valve, and the opening and closing of the engine is controlled by the solenoid valve 120;
the first propellant inlet 121 is a fuel inlet and the second propellant inlet 122 is an oxidizer inlet.
In this embodiment, the operating principle of the modular power system is as follows: high-pressure gas is filled into the annular gas cylinder 320 through the gas filling valve 310, the high-pressure gas in the annular gas cylinder 320 reaches the first gas outlet 330 of the extrusion module and reaches the second gas outlet 350 of the extrusion module through the valve and the sensor 370, and the two paths of gas reach the first extrusion gas inlet 210 and the three-way inlet 231 of the propellant module 200 through the third gas pipeline 340 and the fourth gas pipeline 360 respectively: a path of gas enters the propellant first reservoir 220 from the propellant first inlet 210 through the diaphragm valve, to squeeze fuel in the reservoir, from the propellant valve 280 through the propellant first line 260 to the propellant first inlet 121 of the engine module 100; the other path of gas is divided into two paths again after passing through the tee 230 of the propellant module 200: one path flows into the gas first pipeline and the extrusion gas second inlet 240 through the three-way first outlet 232, enters the propellant second tank 290 through the diaphragm valve, extrudes the oxidizer in the tank, and the oxidizer reaches the propellant second inlet 122 of the engine module 100 from the propellant valve 280 through the propellant second pipeline 270; the other gas flows into the gas second pipe 250 through the three-way second outlet 233 to reach the gas inlet 123 of the engine module and finally to the solenoid valve. The electromagnetic valve 120 is controlled to open and close by controlling the gas therein, so as to control the fuel and the oxidant to enter the thrust chamber, and the fuel and the oxidant are combusted in the thrust chamber to generate thrust.
From the above description, it can be seen that the above-described embodiments of the present invention achieve the following technical effects:
the engine module, the propellant module, the extrusion module and the load module are connected and fixed through the supporting structure, and a complex power system is simplified into the engine module, the propellant module and the extrusion module. The power system layout is more compact, the quality is effectively reduced, the reliability is obviously improved, and the power system has good applicability to the two-component liquid attitude and orbit control engine.
In the description of the present invention, it is to be understood that the orientation or positional relationship indicated by the orientation words such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal" and "top, bottom", etc. are usually based on the orientation or positional relationship shown in the drawings, and are only for convenience of description and simplicity of description, and in the case of not making a reverse description, these orientation words do not indicate and imply that the device or element being referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore, should not be considered as limiting the scope of the present invention; the terms "inner and outer" refer to the inner and outer relative to the profile of the respective component itself.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A modular power system for a spacecraft, comprising:
an engine module (100), the engine (100) module being located lowermost in the overall system;
a propellant module (200), the propellant module (200) being connected with the engine module (100);
a compression module (300), the compression module (300) being connected with the propellant module (200);
a load module (400), the load module (400) being disposed above the compression module (300);
the engine module (100), the propellant module (200), the compression module (300) and the load module (400) are fixedly connected by a support structure (666).
2. The modular power system for spacecraft of claim 1, wherein the compression module (300) comprises a ring cylinder (320), the ring cylinder (320) having a charging port (310), high pressure gas in the ring cylinder (320) passing through a valve and sensor combination (370) to a compression module first gas outlet (330) and to a compression module second gas outlet (350), the first gas outlet (330) being connected to a gas third line (340), the second gas outlet (350) being connected to a gas fourth line (360).
3. The modular power system for spacecraft of claim 2, wherein the first gas outlet (330) reaches the compressed gas first inlet (210) of the propellant module (200) through a gas third line (340);
the second gas outlet (350) reaches the three-way extrusion inlet (231) of the propellant module (200) via a fourth gas line (360).
4. The modular power system for spacecraft of claim 3, wherein the propellant module (200) comprises a first propellant tank (220) and a second propellant tank (290);
-above the propellant first tank (220) there is a first inlet (210) for pressurised gas, propellant from a propellant valve (280) through a propellant first line (260) to a propellant first inlet (121) of an engine module (100);
a tee joint inlet (231) of the first propellant storage tank (220) is connected with a tee joint, and the tee joint (230) is provided with a tee joint first outlet (232) and a tee joint second outlet (233);
the three-way first outlet (232) is connected to an extrusion gas second inlet (240), the extrusion gas second inlet (240) being connected to a propellant second tank (290), propellant in the propellant second tank (290) passing from a propellant valve (280) through a propellant second line (270) to a propellant second inlet (122) of the engine module (100);
the tee joint second outlet (233) is connected with one end of a second gas pipeline (250), the other end of the second gas pipeline (250) is connected with a gas inlet (123) of the engine module (100), and the propellant reaches the electromagnetic valve through the gas inlet (123).
5. The modular power system for spacecraft of claim 4, wherein the first propellant inlet (121) is a fuel inlet and the second propellant inlet (122) is an oxidizer inlet.
6. The modular power system for spacecraft of claim 4, wherein the first propellant tank (220) is a fuel tank and the second propellant tank (290) is an oxidizer tank.
7. The modular power system for spacecraft of claim 4, wherein the propellant valve (280) consists of a charge and discharge valve, a membrane valve, and a filter.
8. The modular power system for spacecraft of claim 4, wherein the engine module (100) comprises an engine consisting of a thrust chamber (110) and a solenoid valve (120) bolted together, the engine being connected to a support structure (666) by a servo mechanism (130).
9. The modular power system for spacecraft of claim 8, wherein said servomechanism (130) is at least 4, accommodating engine oscillation in four directions.
10. A propulsion method using a modular power system for spacecraft as claimed in one of claims 1 to 9, characterized in that high pressure gas is charged into the ring cylinder (320) through the charging valve (310), the high pressure gas in the ring cylinder (320) is passed through the valve and sensor combination (370) to the squeeze module first gas outlet (330) and to the squeeze module second gas outlet (350), and the two gases are passed through the gas third line (340) and the gas fourth line (360), respectively, to the squeeze gas first inlet (210) and the three-way inlet (231) of the propellant module (200):
a path of gas enters a first propellant tank (220) from a first propellant gas inlet (210) through a diaphragm valve, the propellant in the tank is compressed, and the propellant reaches a first propellant inlet (121) of the engine module (100) from a propellant valve (280) through a first propellant pipeline (260); the other path of gas is divided into two paths after passing through a tee joint (230) of the propellant module (200):
one path flows into a gas first pipeline and a squeezing gas second inlet (240) through a three-way first outlet (232), enters a propellant second storage tank (290) through a diaphragm valve, squeezes propellant in the storage tank, and reaches a propellant second inlet (122) of the engine module (100) from a propellant valve (280) through a propellant second pipeline (270); the other path of gas flows into a gas second pipeline (250) through a three-way second outlet (233) to reach a gas inlet (123) of the engine module and finally reach the electromagnetic valve;
the electromagnetic valve (120) is controlled to be opened and closed, so that the propellant is controlled to enter the thrust chamber through the first propellant inlet (121) and the second propellant inlet (122), and the propellant is combusted in the thrust chamber to generate thrust.
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| CN202110759356.3A CN113323771A (en) | 2021-07-06 | 2021-07-06 | Modular power system for spacecraft and power propulsion method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115339658A (en) * | 2022-08-15 | 2022-11-15 | 湖北航天技术研究院总体设计所 | Aircraft hydraulic power system and liquid engine support assembly thereof |
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| US5143327A (en) * | 1990-08-31 | 1992-09-01 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Integrated launch and emergency vehicle system |
| US6968676B1 (en) * | 2001-11-01 | 2005-11-29 | Krishnan Vinu B | Propulsion from combustion of solid propellant pellet-projectiles |
| RU2464208C1 (en) * | 2011-06-10 | 2012-10-20 | Николай Борисович Болотин | Multistage carrier rocket, liquid-propellant rocket engine, turbo pump unit and bank nozzle unit |
| 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 |
| CN109911247A (en) * | 2019-03-13 | 2019-06-21 | 北京星际荣耀空间科技有限公司 | Rocket and its propellant tank |
| CN111120147A (en) * | 2019-12-13 | 2020-05-08 | 上海空间推进研究所 | Multistage liquid fuel gas pressurization system and use method thereof |
| CN110979738A (en) * | 2019-12-23 | 2020-04-10 | 北京宇航推进科技有限公司 | Pressure-drop type integrated power system and power propulsion method |
| CN212313906U (en) * | 2020-05-22 | 2021-01-08 | 北京宇航天驰动力科技有限公司 | Modularized single-component propulsion system suitable for spacecraft |
| CN215256505U (en) * | 2021-07-06 | 2021-12-21 | 北京宇航推进科技有限公司 | Modular power system for a spacecraft |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115339658A (en) * | 2022-08-15 | 2022-11-15 | 湖北航天技术研究院总体设计所 | Aircraft hydraulic power system and liquid engine support assembly thereof |
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