CN211230643U - Propellant attitude and orbit control integrated propulsion system and carrier rocket - Google Patents
Propellant attitude and orbit control integrated propulsion system and carrier rocket Download PDFInfo
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- CN211230643U CN211230643U CN201922053023.XU CN201922053023U CN211230643U CN 211230643 U CN211230643 U CN 211230643U CN 201922053023 U CN201922053023 U CN 201922053023U CN 211230643 U CN211230643 U CN 211230643U
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- 239000003380 propellant Substances 0.000 title claims abstract description 94
- 239000007788 liquid Substances 0.000 claims abstract description 66
- 239000000446 fuel Substances 0.000 claims description 27
- 239000007800 oxidant agent Substances 0.000 claims description 27
- 230000001590 oxidative effect Effects 0.000 claims description 19
- 238000006073 displacement reaction Methods 0.000 claims description 12
- 230000007423 decrease Effects 0.000 claims description 6
- 239000006200 vaporizer Substances 0.000 claims description 2
- 230000010354 integration Effects 0.000 abstract description 7
- 238000000034 method Methods 0.000 description 7
- 230000008569 process Effects 0.000 description 6
- 230000000694 effects Effects 0.000 description 3
- 239000012530 fluid Substances 0.000 description 2
- 230000033228 biological regulation Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000005429 filling process Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
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Abstract
The utility model discloses a propellant attitude and orbit control integration propulsion system and carrier rocket. The attitude and orbit control integrated propulsion system comprises a pressurization unit, a propellant storage unit, a propellant distribution unit, a orbit control engine and an attitude control engine which are sequentially connected through pipelines. The propellant distribution unit comprises a main pipeline, a rail control pipeline and an attitude control pipeline which are connected with the propellant storage unit, wherein one end of the rail control pipeline, which is far away from the main pipeline, is connected with the rail control engine, and one end of the attitude control pipeline, which is far away from the main pipeline, is connected with the attitude control engine. Wherein the attitude control pipeline is provided with a liquid-gas replacement device, so that the liquid propellant passing through the attitude control pipeline is gasified and then supplied to the attitude control engine. The utility model discloses an attitude and orbit accuse integration propulsion system and carrier rocket make the propellant that gets into in the attitude control engine be the gaseous state through setting up the liquid gas replacement device on attitude accuse supply line, guarantee carrier rocket's attitude control engine reliable work.
Description
Technical Field
The utility model relates to a liquid rocket engine technical field, concretely relates to propellant attitude and orbit control integration propulsion system and carrier rocket.
Background
In the process of filling the propellant into the pipeline and in the standby process of the liquid rocket engine, the propellant and the pipeline system have obvious heat exchange, so that the propellant is partially gasified and supplied in a gas-liquid two-phase state, and the reliable work of the engine is not facilitated. The problem is particularly remarkable in the attitude control engine with small flow and random work, and the application of the propellant in the attitude and orbit control propulsion system is restricted.
Therefore, in order to solve the problems of gas-liquid two-phase supply of the propellant, unfavorable reliable operation of the engine and the like, a posture and orbit control propulsion system which can make the engine operate more stably and reliably is needed.
SUMMERY OF THE UTILITY MODEL
To the above-mentioned technical problem among the correlation technique, an aspect of the utility model provides a propellant attitude and orbit accuse integration propulsion system, through optimizing propellant supply scheme, can make the track control engine with the liquid propellant supply, the attitude control engine is with the gaseous propellant supply, the effectual influence that has reduced above-mentioned problem to attitude and orbit accuse engine has improved engine operational reliability.
One aspect of the utility model provides a propellant attitude and orbit control integration propulsion system. A propellant attitude and orbit control integrated propulsion system comprises a pressurization unit, a propellant storage unit, a propellant distribution unit and an engine module which are sequentially connected through pipelines. Wherein the engine module includes a track control engine and an attitude control engine. The propellant distribution unit comprises a main pipeline connected with the propellant storage unit, a rail control pipeline connected with the main pipeline and an attitude control pipeline, wherein one end of the rail control pipeline, which is far away from the main pipeline, is connected with the rail control engine, and one end of the attitude control pipeline, which is far away from the main pipeline, is connected with the attitude control engine. Wherein the attitude control pipeline is provided with a liquid-gas replacement device, so that the liquid propellant passing through the attitude control pipeline is gasified and then supplied to the attitude control engine.
The liquid-gas replacement device is used for replacing all liquid propellants flowing through the attitude control pipeline with gas and supplying the gas to the attitude control pipeline.
In one embodiment, the liquid-gas displacement device comprises a flow regulator, an evaporator and a gas cylinder which are sequentially arranged on the attitude control pipeline, wherein the outlet end of the flow regulator is connected with the inlet end of the evaporator, the outlet end of the evaporator is connected with the inlet end of the gas cylinder, and the outlet end of the gas cylinder is connected with the attitude control engine. Wherein, in this embodiment, the flow regulator is configured to automatically regulate the flow of propellant into the evaporator; the vaporizer is used to convert the liquid propellant into a gaseous state for entry into the cylinder.
In one embodiment, the flow regulator is configured to automatically open after the pressure in the gas cylinder drops to a certain degree, and the opening degree of the flow regulator is adjustable, so that the opening degree of the flow regulator gradually decreases to close along with the gradual rise of the pressure in the gas cylinder during the gradual filling process of the gas propellant in the gas cylinder.
The liquid flowing through the liquid-gas displacement device is automatically regulated by the flow regulator to enter the evaporator, the evaporator completely gasifies the liquid and then fills the liquid into the gas cylinder, when the gas cylinder is gradually filled with gas propellant, the pressure of the gas cylinder gradually rises, and at the moment, the opening degree of the flow regulator is gradually reduced to be closed along with the gradual rise of the pressure of the gas cylinder.
In one embodiment, a sensing element is arranged in the flow regulator and used for sensing the pressure change of the gas cylinder; after the sensing element senses that the pressure of the gas cylinder is gradually reduced to a preset specific value, the flow regulator is automatically started, and liquid propellant is pushed into the evaporator; and after the sensing element senses that the pressure in the gas cylinder rises to a preset specific value, the flow regulator is automatically closed.
In one embodiment, the gas cylinder is configured to not charge at an initial state, and the gas cylinder is automatically charged during pressurization of the system.
In the above embodiment, the propellant storage unit comprises a first tank and a second tank, the propellant dispensing unit comprises a first dispensing unit and a second dispensing unit, the first tank is connected to the first dispensing unit, the second tank is connected to the second dispensing unit; the first distribution unit and the second distribution unit are arranged in parallel and are respectively used for supplying one of fuel and oxidant to the attitude control engine and the track control engine.
In one embodiment, the first distribution unit comprises a first main pipeline connected with the first tank, a first rail control pipeline connected with the first main pipeline, and a first attitude control pipeline; the first distribution unit is connected with the first storage tank through the first main pipeline; the first distribution unit is used for distributing the propellant in the first storage tank to the first rail control pipeline and the first attitude control pipeline.
In one embodiment, the second distribution unit comprises a second main pipeline connected to the second tank, a second rail control pipeline connected to the second main pipeline, and a second attitude control pipeline. The second distribution unit is connected with the second storage tank through the second main pipeline, and the second distribution unit is used for distributing the propellant in the second storage tank to the second rail control pipeline and the second attitude control pipeline.
In one embodiment, the first attitude control circuit is connected to an inlet of the attitude control engine for supplying one of a liquid fuel and a liquid oxidizer to the attitude control engine, and the second attitude control circuit is connected to another inlet of the attitude control engine for supplying the other of the liquid fuel and the liquid oxidizer to the attitude control engine.
In one embodiment, the first rail control line is connected to an inlet of the rail control engine for supplying one of liquid fuel and liquid oxidant to the rail control engine, and the second rail control line is connected to another inlet of the rail control engine for supplying the other of liquid fuel and liquid oxidant to the rail control engine.
Another aspect of the present invention is to provide a launch vehicle comprising any of the propellant attitude and trajectory control integrated propulsion systems described in the embodiments above.
The embodiment of the utility model provides an attitude and orbit accuse integration propulsion system and launch vehicle through set up liquid gas replacement device in the pipeline, has solved the problem that the attitude control engine can not reliably work when propellant gas-liquid double-phase state supplies.
Those skilled in the art will recognize additional features and advantages upon reading the detailed description, and upon viewing the accompanying drawings.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a first overall schematic view of a posture and orbit control integrated propulsion system according to an embodiment of the present invention.
Fig. 2 is a schematic view of a liquid-gas displacement apparatus according to an embodiment of the present invention.
Figure 3 is a second overall schematic view of a posture and orbit control integrated propulsion system according to an embodiment of the present invention.
Detailed Description
The technical solution of the present invention is further explained by the following embodiments with reference to the accompanying drawings. Spatially relative terms such as "below," "… below," "lower," "above," "… above," "upper," and the like are used for convenience in describing the positioning of one element relative to a second element and are intended to encompass different orientations of the device in addition to different orientations than those illustrated in the figures. Further, for example, the phrase "one element is over/under another element" may mean that the two elements are in direct contact, or that there is another element between the two elements. Furthermore, terms such as "first", "second", and the like, are also used to describe various elements, regions, sections, etc. and should not be taken as limiting. Like terms refer to like elements throughout the description.
One aspect of the utility model provides an attitude and orbit control integration propulsion system and carrier rocket. Referring to fig. 1, an attitude and orbit control integrated propulsion system comprises a pressurization unit 1, a propellant storage unit 2, a propellant distribution unit 3 and an engine module 4 which are connected in sequence through pipelines. The engine module 4 includes a track control engine 41 and an attitude control engine 42. The propellant distribution unit 3 includes a main pipeline 31 connected to the propellant storage unit 2, a rail control pipeline 32 connected to the main pipeline 31, and an attitude control pipeline 33, wherein the attitude control pipeline 33 is provided with a liquid-gas displacement device 300, so that the liquid propellant passing through the attitude control pipeline 33 is completely gasified and then supplied to the attitude control engine 42. The end of the rail control pipe 32 remote from the main pipe 31 is connected to the rail control engine 41, and the end of the attitude control pipe 33 remote from the main pipe 31 is connected to the attitude control engine 42.
Above-mentioned utility model's embodiment makes the liquid propellant who stores in storage tank 2 under the pressure effect of pressurizing unit 1 through setting up liquid gas replacement device 300 at gesture accuse pipeline 33, and the propellant that will store in storage tank 2 gets into rail accuse pipeline 32 and gesture accuse pipeline 33 respectively by main line 31, can make the propellant that flows through gesture accuse pipeline 33 turn into the gaseous state and supply to gesture control engine 42 by liquid gas replacement device 300, improves gesture control engine 42 job stabilization nature. Instead, the propellant flowing through the rail control line 32 directly enters the rail control engine 41 in a liquid state.
Referring to fig. 1 and 2, in one embodiment, the liquid-gas displacement device 300 includes a flow regulator 331, an evaporator 332, and a gas cylinder 333, which are sequentially disposed in the attitude control circuit 33. Wherein the outlet end of the flow regulator 331 is connected with the inlet end of the evaporator 332, the outlet end of the evaporator 332 is connected with the inlet end of the gas cylinder 333, and the outlet end of the gas cylinder 333 is connected with the attitude control motor 42. In this embodiment, the flow regulator 331 is used to automatically regulate the flow of propellant into the evaporator 332; the evaporator 32 is used for converting the liquid propellant into a gas state and then propelling the gas cylinder 333; the gas cylinder 333 is used to store vaporized propellant.
The liquid-gas replacement device can also be formed by connecting a flow regulator, an evaporator, a gas cylinder and a pipeline, namely, the flow regulator is connected with the evaporator and the gas cylinder through the pipeline. As previously mentioned, the flow regulator automatically regulates the flow of propellant into the evaporator, which converts the liquid propellant to the gaseous state, and the gas cylinder, which stores the gaseous propellant.
In one embodiment, the flow regulator 331 is configured to automatically open after the pressure in the gas cylinder 333 drops to a certain level, and the opening of the flow regulator 331 is adjustable such that the opening of the flow regulator 331 gradually decreases to close as the pressure in the gas cylinder 333 gradually increases during the process of gradually filling the gas propellant in the gas cylinder 333.
Specifically, the fluid flowing through the liquid-gas replacement device 300 is automatically adjusted by the flow regulator 331 to enter the evaporator 332, and the fluid is gasified by the evaporator 332 and then filled into the gas cylinder 333. The pressure of the gas cylinder 333 gradually increases during the process of the gas cylinder 333 being gradually filled with the propellant gas, and the opening degree of the flow regulator 331 gradually decreases to close along with the gradual increase of the pressure of the gas cylinder 333.
The liquid-gas replacement device can enable the propellant entering the evaporator to be stably gasified and improve the performance of a propulsion system by configuring the flow regulator into the flow of the automatic regulation pipeline.
In one embodiment, a sensing element is provided within the flow regulator 331 for sensing pressure changes of the gas cylinder 333. After the sensing element senses that the pressure of the gas cylinder 333 is gradually reduced to a preset specific value, the flow regulator 331 is automatically turned on to push the liquid propellant into the evaporator 332. When the sensing element senses that the pressure in the gas cylinder 333 is increased to a preset specific value, the flow regulator is automatically closed. The embodiment of the utility model discloses an install sensing element in flow regulator 331, can sense gas cylinder 333 along with gaseous full of and the value of the pressure variation of discharge process, after the pressure value in gas cylinder 333 rises to the specific value that sets up in advance, flow regulator 331 self-closing stops to supply liquid to evaporimeter 332. Similarly, when the discharge pressure of the gas in the gas cylinder 333 gradually decreases to a predetermined value, the flow regulator is automatically turned on to continue supplying liquid into the evaporator 332, and so on until the operation is finished.
For example, the flow regulator may be an opening-adjustable valve, and the sensing element transmits a sensed pressure signal to the controller under the control of the controller, and the controller performs an operation of opening, closing, or opening the valve according to a comparison between a received pressure value and a set value.
In one embodiment, the gas cylinder 333 is configured to not charge during an initial state and the gas cylinder 333 is automatically charged during pressurization of the system. The specific process is as follows: the gas of the pressurizing unit 1 enters the propellant storage unit 2 to pressurize the liquid propellant, and the liquid propellant is filled to the inlet of the flow regulator 331 and the inlet of the rail-controlled engine 41 under the pressurizing effect; the flow regulator 331 is automatically turned on, and the liquid propellant is vaporized and filled in the gas cylinder 333 through the flow regulator 331 into the evaporator 332. As the vaporized propellant increases, the pressure in the gas cylinder 333 increases, and the opening of the flow regulator 331 decreases until it closes, at which time the propulsion system is operational.
When the attitude control engine 42 is operated, the gaseous propellant in the gas cylinder 333 is supplied to the attitude control engine 42. With the continuous consumption of the propellant, the pressure of the propellant in the gas cylinder 333 is reduced, after the pressure reaches a specific value, the flow regulator 331 is automatically opened, the liquid propellant from the propellant storage unit 2 enters the evaporator 332 and is gasified, the gasified propellant is filled in the gas cylinder 333, after the pressure of the propellant in the gas cylinder 333 rises to the specific value, the flow regulator 331 is closed, and the steps are repeated until the system operation is finished.
Referring to fig. 3, in one embodiment the propellant storage unit comprises a first tank 2-1 and a second tank 2-2, the propellant dispensing unit comprises a first dispensing unit and a second dispensing unit, the first tank 2 is connected to the first dispensing unit and the second tank 2-2 is connected to the second dispensing unit. The first distribution unit and the second distribution unit are disposed in parallel therebetween, and are used to supply one of fuel and oxidant to the attitude control engine 42 and the track control engine 41, respectively. Referring to fig. 3, an embodiment of the present invention provides for two tanks for storing one of the fuel and oxidizer and two dispensing units for dispensing one of the aforementioned propellants and then pushing the same to the engine module, respectively, between the booster unit and the engine module. The second tank stores the other of the fuel and the oxidizer, and the second dispensing unit is used for dispensing the other propellant and then pushing the other propellant to the engine module. Wherein both the first distribution unit and the second distribution unit may comprise the liquid-gas replacement device according to any one of the preceding embodiments.
In one embodiment, the first distribution unit includes a first main pipeline 31-1 connected to the first tank 2-1, a first rail control pipeline 32-1 connected to the first main pipeline 31-1, and a first attitude control pipeline 333-1. The first distribution unit is connected with the first storage tank 2-1 through a first main pipeline 31-1, and the first distribution unit is used for distributing the propellant in the first storage tank 2-1 to a first rail control pipeline 32-1 and a first attitude control pipeline 33-1. Wherein in this embodiment the first rail control line is directly connected to the inlet of the rail controlled engine, propelling propellant to the rail controlled engine. The first attitude control pipeline may include a liquid-gas displacement device, such that the propellant passing through the first attitude control pipeline is gasified by the liquid-gas displacement device and then propels the inlet of the attitude control engine.
In one embodiment, the second distribution unit includes a second main pipeline 31-2 connected to the second tank 2-2, a second rail control pipeline 32-2 connected to the second main pipeline 31-2, and a second attitude control pipeline 33-2. The second distribution unit is connected to the second tank 2-2 via a second main line 31-2, and the second distribution unit is configured to distribute the propellant in the second tank 2-2 to a second rail control line 32-2 and a second attitude control line 33-2. In this embodiment, the second attitude control pipeline is directly connected to the inlet of the track control engine to push the propellant to the track control engine, and the second attitude control pipeline may include a liquid-gas displacement device, so that the propellant passing through the first attitude control pipeline is gasified by the liquid-gas displacement device and then pushed to the inlet of the attitude control engine.
With continued reference to FIG. 3, in one embodiment, a first attitude control circuit 33-1 is coupled to an inlet of attitude control motor 42 for supplying one of liquid fuel and liquid oxidant to attitude control motor 42, and a second attitude control circuit 33-2 is coupled to another inlet of attitude control motor 42 for supplying the other of liquid fuel and liquid oxidant to attitude control motor 42. In this embodiment, in order to ensure the normal operation of the attitude control engine 42, it is necessary to consume both the fuel and the oxidant, so the first attitude control pipeline 33-1 and the second attitude control pipeline 33-2 are respectively connected to two inlets of the attitude control engine 42, the first attitude control pipeline 33-1 is used for providing one of the liquid fuel and the liquid oxidant for the attitude control engine 42, and the second attitude control pipeline 33-2 is used for providing one of the liquid fuel and the liquid oxidant for the attitude control engine 42.
For example, in the case of multiple attitude control engines, a first attitude control conduit 33-1 may be connected to one inlet of each of the attitude control engines, and a second attitude control conduit 33-2 may be connected to another inlet of each of the attitude control engines.
In one embodiment, a first rail control line 32-1 is coupled to an inlet of the rail control engine 41 for providing one of liquid fuel and liquid oxidizer to the rail control engine 42, and a second rail control line 32-2 is coupled to another inlet of the rail control engine 41 for providing the other of liquid fuel and liquid oxidizer to the rail control engine 41.
In this embodiment, in order to ensure the normal operation of the track control engine 41, it is necessary to consume both the fuel and the oxidant, so the first and second rail control pipelines 32-1 and 32-2 are respectively connected to two inlets of the track control engine 41, the first rail control pipeline 32-1 gasifies one of the liquid fuel and the liquid oxidant by the liquid-gas displacement device and supplies the gasified one of the liquid fuel and the liquid oxidant to one inlet of the track control engine 41, and the second rail control pipeline 32-2 gasifies the other of the liquid fuel and the liquid oxidant by the liquid-gas displacement device and supplies the gasified one of the liquid fuel and the liquid oxidant to the other inlet of the track control engine 41.
In the above embodiment, the first attitude control pipeline and the second attitude control pipeline may be provided with a liquid-gas replacement device to ensure that the oxidant and the fuel supplied to the attitude control engine are in a gaseous state, so that the attitude control engine can work more reliably.
Another aspect of the utility model provides a carrier rocket can be through the liquid gas replacement device in above-mentioned embodiment, will fill oxidant and fuel to the attitude control engine in and be gaseous state, guarantee the reliable work of attitude control engine.
The above embodiments of the present invention can be combined with each other, and have corresponding technical effects.
The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. 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 low-temperature propellant attitude and orbit control integrated propulsion system is characterized by comprising: the system comprises a pressurizing unit, a propellant storage unit, a propellant distribution unit and an engine module which are sequentially connected through pipelines; wherein the engine module includes a track control engine and an attitude control engine;
the propellant distribution unit comprises a main pipeline connected with the propellant storage unit, a rail control pipeline connected with the main pipeline and an attitude control pipeline, wherein one end of the rail control pipeline, which is far away from the main pipeline, is connected with the rail control engine, and one end of the attitude control pipeline, which is far away from the main pipeline, is connected with the attitude control engine;
wherein the attitude control pipeline is provided with a liquid-gas replacement device, so that the liquid propellant passing through the attitude control pipeline is gasified and then supplied to the attitude control engine.
2. The attitude and orbit control integrated propulsion system according to claim 1, wherein the liquid-gas displacement device comprises a flow regulator, an evaporator and a gas cylinder which are sequentially arranged on the attitude control pipeline, wherein an outlet end of the flow regulator is connected with an inlet end of the evaporator, an outlet end of the evaporator is connected with an inlet end of the gas cylinder, and an outlet end of the gas cylinder is connected with the attitude control engine;
wherein the flow regulator is configured to automatically regulate the flow of propellant into the evaporator; the vaporizer is used to convert the liquid propellant into a gaseous state for entry into the cylinder.
3. The attitude and orbit control integrated propulsion system of claim 2, wherein the flow regulator is configured to automatically open after a certain pressure drop in the gas cylinder, and the flow regulator is adjustable in opening such that the flow regulator opening gradually decreases to close as the pressure in the gas cylinder gradually increases during the gradual filling of the gas propellant in the gas cylinder.
4. An attitude and orbit control integrated propulsion system according to claim 3, wherein a sensing element is arranged in the flow regulator and is used for sensing pressure changes of the gas cylinder; after the sensing element senses that the pressure of the gas cylinder is gradually reduced to a preset specific value, the flow regulator is automatically started, and liquid propellant is pushed into the evaporator; and after the sensing element senses that the pressure in the gas cylinder rises to a preset specific value, the flow regulator is automatically closed.
5. The attitude and orbit control integrated propulsion system of claim 2, wherein the gas cylinder is configured to not inflate during an initial state and to automatically inflate during system pressurization.
6. An attitude and orbit control integrated propulsion system according to any of claims 1 to 5, characterised in that the propellant storage unit comprises a first tank and a second tank, the propellant dispensing unit comprises a first dispensing unit and a second dispensing unit, the first tank is connected to the first dispensing unit and the second tank is connected to the second dispensing unit; the first distribution unit and the second distribution unit are arranged in parallel and are respectively used for supplying one of fuel and oxidant to the attitude control engine and the track control engine.
7. The attitude and orbit control integrated propulsion system of claim 6, wherein the first distribution unit comprises a first main pipeline connected with the first storage tank, a first orbit control pipeline connected with the first main pipeline, and a first attitude control pipeline; the first distribution unit is connected with the first storage tank through the first main pipeline; the first distribution unit is used for distributing the propellant in the first storage tank to the first rail control pipeline and the first attitude control pipeline;
the second distribution unit comprises a second main pipeline connected with the second storage tank, a second rail control pipeline connected with the second main pipeline and a second attitude control pipeline; the second distribution unit is connected with the second storage tank through the second main pipeline; the second distribution unit is used for distributing the propellant in the second storage tank to the second rail control pipeline and the second attitude control pipeline.
8. An attitude and orbit control integrated propulsion system according to claim 7, wherein the first attitude control conduit is connected to the attitude control engine inlet for supplying one of fuel and oxidant to the attitude control engine, and the second attitude control conduit is connected to the other attitude control engine inlet for supplying the other of fuel and oxidant to the attitude control engine.
9. An attitude and orbit control integrated propulsion system according to claim 8, wherein the first orbital control conduit is connected to an inlet of the orbit control engine for supplying one of liquid fuel and liquid oxidizer to the orbit control engine, and the second orbital control conduit is connected to another inlet of the orbit control engine for supplying the other of liquid fuel and liquid oxidizer to the orbit control engine.
10. A launch vehicle comprising a posture and orbit control integrated propulsion system as claimed in any one of claims 1 to 9.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201922053023.XU CN211230643U (en) | 2019-11-25 | 2019-11-25 | Propellant attitude and orbit control integrated propulsion system and carrier rocket |
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| CN201922053023.XU CN211230643U (en) | 2019-11-25 | 2019-11-25 | Propellant attitude and orbit control integrated propulsion system and carrier rocket |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112412660A (en) * | 2020-12-03 | 2021-02-26 | 西安航天动力研究所 | Space power system combining extrusion and electric pump auxiliary pressurization |
| CN112777001A (en) * | 2021-01-25 | 2021-05-11 | 中国人民解放军国防科技大学 | Micro-nano satellite accompanied with orbit entry |
| CN112983679A (en) * | 2021-05-06 | 2021-06-18 | 星河动力(北京)空间科技有限公司 | Carrier rocket upper-stage propulsion system and carrier rocket |
| CN114408222A (en) * | 2021-12-20 | 2022-04-29 | 上海空间推进研究所 | Pneumatic supercharged engine system |
-
2019
- 2019-11-25 CN CN201922053023.XU patent/CN211230643U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112412660A (en) * | 2020-12-03 | 2021-02-26 | 西安航天动力研究所 | Space power system combining extrusion and electric pump auxiliary pressurization |
| CN112777001A (en) * | 2021-01-25 | 2021-05-11 | 中国人民解放军国防科技大学 | Micro-nano satellite accompanied with orbit entry |
| CN112983679A (en) * | 2021-05-06 | 2021-06-18 | 星河动力(北京)空间科技有限公司 | Carrier rocket upper-stage propulsion system and carrier rocket |
| CN114408222A (en) * | 2021-12-20 | 2022-04-29 | 上海空间推进研究所 | Pneumatic supercharged engine system |
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Effective date of registration: 20240527 Address after: No.13, Ronghua South Road, Daxing Economic and Technological Development Zone, Beijing Patentee after: Blue Arrow Space Technology Co.,Ltd. Country or region after: China Address before: Room L501, 5th Floor, R&D Building, No. 456, Aerospace South Road, National Civil Aerospace Industry Base, Xi'an City, Shaanxi Province 710077 Patentee before: SHAANXI LANDSPACE TECHNOLOGY Co.,Ltd. Country or region before: China |