CN112208801B - Mars detector double-component multi-gear thruster configuration and layout method and system - Google Patents
Mars detector double-component multi-gear thruster configuration and layout method and system Download PDFInfo
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Abstract
The invention provides a mars detector bipropellant multi-gear thruster configuration and layout method and a system, comprising the following steps: step S1: acquiring the selection result information of the bottom plate centralized layout scheme; step S2: acquiring the information of the grading main and standby matching result; step S3: constructing a combined working mode of the 3-gear thruster to finish the length coordination installation of the force arm of the thruster; step S4: based on the overall configuration and layout of the detector, balancing the reasonable layout position and the design cost of the thruster, considering the constraint of the mechanical environment of the detector on the layout position of the thruster, the influence of plume and working heat of the thruster, and combining the layout state of single-machine equipment to determine the layout position of the thruster; step S5: and acquiring configuration and layout information of the two-component multi-gear thruster of the Mars detector. The invention fully considers the layout space of the Mars detector and the limitation of system resources, solves the problem of the layout of the thruster under the resource constraint and meets the working requirement of attitude and orbit control of the detector.
Description
Technical Field
The invention relates to the technical field of deep space exploration, in particular to a configuration and layout method and system of a double-component multi-gear thruster of a Mars detector.
Background
The Mars exploration project is one of the important hot contents in the current deep space exploration field. The realization of the task is that interplanetary flight is carried out by taking a Mars detector as a detection main body under the support of other engineering systems. The thruster is an important device for realizing the attitude and orbit control of the mars probe, and the layout configuration of the thruster is particularly important.
According to the layout scheme of the conventional earth satellite, thrusters are generally arranged at the central positions of the vertexes or edges of a platform, and are configured by adopting a high-thrust 2-gear configuration and a low-thrust 2-gear configuration, so that the requirement of attitude and orbit control main and standby control is met, and the satellite platform reserves a relatively abundant layout space to avoid plume and heat influence.
Patent document CN109367821A discloses a GEO orbit satellite thruster configuration, which is composed of 1 far-point engine and 16 attitude control thrusters, wherein 1 far-point engine is positioned in the center of a satellite bottom plate, and a thrust vector is parallel to a star-Z axis; 8 attitude control thrusters in the 16 attitude control thrusters are arranged on the bottom plate, and 8 attitude control thrusters are arranged on the east side and the west side of the satellite. The invention realizes the function requirements by adopting a small number of thrusters and a compact layout configuration mode, simultaneously considers the realization of the backup function, meets the requirements of satellite orbital transfer and three-axis attitude control, has higher redundancy, can simplify the trend of a connecting pipeline of the thrusters, is convenient for the installation implementation and measurement of the thrusters on the satellite, and reduces the influence of the plume of the thrusters on the satellite. There is still room for improvement in structure and performance.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a configuration and layout method and a system of a double-component multi-gear thruster of a Mars detector.
The invention provides a configuration and layout method of a double-component multi-gear thruster of a Mars detector, which comprises the following steps:
step S1: acquiring the selection result information of the bottom plate centralized layout scheme according to the mars detection overall configuration parameter information and the mars detection overall layout parameter information;
step S2: acquiring grading main and standby matching result information according to Mars detection task target parameter information;
step S3: analyzing the requirement of interference torque and the constraint of installation position based on the requirement of attitude and orbit control task, constructing a combined working mode of 3 grades of thrusters, and finishing the length coordination installation of the force arm of the thrusters;
step S4: based on the overall configuration and layout of the detector, balancing the reasonable layout position and the design cost of the thruster, considering the constraint of the mechanical environment of the detector on the layout position of the thruster, the influence of plume and working heat of the thruster, and combining the layout state of single-machine equipment to determine the layout position of the thruster;
step S5: and acquiring configuration and layout information of the two-component multi-gear thruster of the Mars detector.
Preferably, the step S1 includes: step S1.1: acquiring the plume of the thruster and the information of the research result of the work heat influence according to the Mars detection overall configuration parameter information and the Mars detection overall layout parameter information; step S1.2: and acquiring the statistical carding information of the layout resources of the thruster according to the plume of the thruster and the information of the research result of the work heat influence.
Preferably, the step S1 further includes:
step S1.3: according to the statistical carding information of the layout resources of the thruster and the connection characteristic parameters of the pipelines of the two-component propulsion system, acquiring the information of the benefit and disadvantage analysis result of the centralized layout mode of the bottom plate of the thruster;
step S1.4: and acquiring the selection result information of the bottom plate centralized layout scheme according to the benefit and disadvantage analysis result information of the thruster bottom plate centralized layout mode.
Preferably, the step S2 includes:
step S2.1: starting from a Mars detection task target and a technical scheme, according to Mars detection task target parameter information, thruster configuration demand information and thruster design index parameter information are obtained.
Preferably, the step S2 further includes:
step S2.2: the requirements of three-axis attitude and orbit control capability in the whole process of a task are analyzed, constraints of thrust, thrust and configuration quantity of thrusters are formed, and stepped main-standby matching of 1 thruster 3000N, 8 thrusters 120N and 12 thrusters 25N is formed by combining resource limitations of weight and power consumption of a detector system.
The invention provides a mars detector two-component multi-gear thruster configuration and layout system, which comprises:
module M1: acquiring the selection result information of the bottom plate centralized layout scheme according to the mars detection overall configuration parameter information and the mars detection overall layout parameter information;
module M2: acquiring grading main and standby matching result information according to Mars detection task target parameter information;
module M3: analyzing the requirement of interference torque and the constraint of installation position based on the requirement of attitude and orbit control task, constructing a combined working mode of 3 grades of thrusters, and finishing the length coordination installation of the force arm of the thrusters;
module M4: based on the overall configuration and layout of the detector, balancing the reasonable layout position and the design cost of the thruster, considering the constraint of the mechanical environment of the detector on the layout position of the thruster, the influence of plume and working heat of the thruster, and combining the layout state of single-machine equipment to determine the layout position of the thruster;
module M5: and acquiring configuration and layout information of the two-component multi-gear thruster of the Mars detector.
Preferably, said module M1 comprises:
module M1.1: acquiring the plume of the thruster and the information of the research result of the work heat influence according to the Mars detection overall configuration parameter information and the Mars detection overall layout parameter information;
module M1.2: and acquiring the statistical carding information of the layout resources of the thruster according to the plume of the thruster and the information of the research result of the work heat influence.
Preferably, the module M1 further includes:
module M1.3: according to the statistical carding information of the layout resources of the thruster and the connection characteristic parameters of the pipelines of the two-component propulsion system, acquiring the information of the benefit and disadvantage analysis result of the centralized layout mode of the bottom plate of the thruster;
module M1.4: and acquiring the selection result information of the bottom plate centralized layout scheme according to the benefit and disadvantage analysis result information of the thruster bottom plate centralized layout mode.
Preferably, said module M2 comprises:
module M2.1: starting from a Mars detection task target and a technical scheme, according to Mars detection task target parameter information, thruster configuration demand information and thruster design index parameter information are obtained.
Preferably, the module M2 further includes:
module M2.2: the requirements of three-axis attitude and orbit control capability in the whole process of a task are analyzed, constraints of thrust, thrust and configuration quantity of thrusters are formed, and stepped main-standby matching of 1 thruster 3000N, 8 thrusters 120N and 12 thrusters 25N is formed by combining resource limitations of weight and power consumption of a detector system.
Compared with the prior art, the invention has the following beneficial effects:
1. the configuration and layout method of the Mars detector double-component multi-gear thruster provided by the invention is different from the configuration and layout scheme of the traditional satellite thruster, and the Mars detector double-component multi-gear thruster is generally arranged at the central position of each vertex or each edge of a platform and is configured by 2 gears of large thrust and small thrust. The method fully considers the layout space of the Mars detector and the system resource limitation, solves the problem of the layout of the thruster under the resource constraint through the design matched with the characteristics of a two-component system, the three-axis attitude and orbit control capability requirement, the attitude and orbit control working mode and the layout of single-machine equipment, and meets the working requirement of the attitude and orbit control of the detector;
2. the method has the advantages of simple principle, novel thought and clear process, not only embodies the maturity of technical application, but also shows the flexibility and the innovativeness of application, is an important solution for realizing the layout configuration of the two-component thruster in subsequent Mars detection tasks and other deep space detection tasks under the conditions of high configuration requirement, strong layout constraint and the like, is closely combined with actual engineering, and has high engineering guidance and direct application value;
3. the method is directly oriented to the mars detection task, fully considers the technical characteristics and difficulties of the deep space detection task in the process, and performs matching design of system configuration and working modes by utilizing the favorable condition that a propulsion system is tiled at the bottom of a detector compared with a near-earth space task, thereby meeting the requirements of engineering tasks and optimizing system resource configuration. After the method is provided, the engineering means of thruster configuration and layout in other deep space exploration tasks represented by a Mars exploration task are expanded, and different requirements of subsequent deep space exploration tasks are met.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
fig. 1 is a schematic diagram of a configuration and layout method of a two-component multi-gear thruster of a mars probe according to the present invention.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
The invention provides a configuration and layout method of a double-component multi-gear thruster of a Mars detector, which comprises the following steps:
step S1: acquiring the selection result information of the bottom plate centralized layout scheme according to the mars detection overall configuration parameter information and the mars detection overall layout parameter information;
step S2: acquiring grading main and standby matching result information according to Mars detection task target parameter information;
step S3: analyzing the requirement of interference torque and the constraint of installation position based on the requirement of attitude and orbit control task, constructing a combined working mode of 3 grades of thrusters, and finishing the length coordination installation of the force arm of the thrusters;
step S4: based on the overall configuration and layout of the detector, balancing the reasonable layout position and the design cost of the thruster, considering the constraint of the mechanical environment of the detector on the layout position of the thruster, the influence of plume and working heat of the thruster, and combining the layout state of single-machine equipment to determine the layout position of the thruster;
step S5: and acquiring configuration and layout information of the two-component multi-gear thruster of the Mars detector.
Specifically, in one embodiment, a configuration and layout method of a double-component multi-gear thruster of a mars detector is a novel method provided based on the characteristics of work requirements, attitude and orbit control requirements, safety requirements of the whole thruster, layout constraints of large parts, design requirements of plume avoidance and thermal radiation of the thruster and the like of a deep space exploration task propulsion system. The method has the advantages that the requirements of high specific impulse and high thrust of a mars detector and the mars attitude and orbit control safety requirements are met by means of centralized layout of a bottom plate of the thruster and stepped master-slave configuration of 1 3000N, 8 120N and 12 25N thrusters and coordination of the length of a force arm of the thruster, the technical problems that layout space constraint of the mars detector is severe, pipelines of a two-component propulsion system are complex and have high requirements on system resources, plume of the thruster and working heat influence are difficult to avoid and the like are effectively solved, and the configuration and layout of the deep-space two-component thruster are completed on the premise that the thruster effectively works in orbit. The method for the centralized layout of the double-component thruster on the bottom plate can be matched with 2 fuels, 2 oxidants and 4 gas cylinders which are tiled at the bottom of the detector, and 21 thrusters are effectively connected through an annular pipeline around a bearing cylinder, so that the layout limitation caused by the structural design of the bearing cylinder and a parallelepiped in the center of a detector platform is avoided. Meanwhile, the plume direction of the thruster points to the same hemispherical space, and the constraint of each large part expanded on the rail is effectively avoided. Moreover, the configuration and layout of the 3-gear thruster with coordinated force arms are adopted, so that 2 120N thrusters in two orthogonal directions can control interference torque in a main-standby mode when 3000N rail control works; when 4 120N rail control devices work, 2 25N devices in the orthogonal direction can control interference torque by main and standby devices; 4 transverse 25N thrusters can realize forward and reverse attitude rolling of the detector by a main thruster and a backup thruster.
Preferably, the step S1 includes: step S1.1: acquiring the plume of the thruster and the information of the research result of the work heat influence according to the Mars detection overall configuration parameter information and the Mars detection overall layout parameter information; step S1.2: and acquiring the statistical carding information of the layout resources of the thruster according to the plume of the thruster and the information of the research result of the work heat influence.
Preferably, the step S1 further includes:
step S1.3: according to the statistical carding information of the layout resources of the thruster and the connection characteristic parameters of the pipelines of the two-component propulsion system, acquiring the information of the benefit and disadvantage analysis result of the centralized layout mode of the bottom plate of the thruster;
step S1.4: and acquiring the selection result information of the bottom plate centralized layout scheme according to the benefit and disadvantage analysis result information of the thruster bottom plate centralized layout mode.
Preferably, the step S2 includes:
step S2.1: starting from a Mars detection task target and a technical scheme, according to Mars detection task target parameter information, thruster configuration demand information and thruster design index parameter information are obtained.
Preferably, the step S2 further includes:
step S2.2: the requirements of three-axis attitude and orbit control capability in the whole process of a task are analyzed, constraints of thrust, thrust and configuration quantity of thrusters are formed, and stepped main-standby matching of 1 thruster 3000N, 8 thrusters 120N and 12 thrusters 25N is formed by combining resource limitations of weight and power consumption of a detector system.
The invention provides a mars detector two-component multi-gear thruster configuration and layout system, which comprises:
module M1: acquiring the selection result information of the bottom plate centralized layout scheme according to the mars detection overall configuration parameter information and the mars detection overall layout parameter information;
module M2: acquiring grading main and standby matching result information according to Mars detection task target parameter information;
module M3: analyzing the requirement of interference torque and the constraint of installation position based on the requirement of attitude and orbit control task, constructing a combined working mode of 3 grades of thrusters, and finishing the length coordination installation of the force arm of the thrusters;
module M4: based on the overall configuration and layout of the detector, balancing the reasonable layout position and the design cost of the thruster, considering the constraint of the mechanical environment of the detector on the layout position of the thruster, the influence of plume and working heat of the thruster, and combining the layout state of single-machine equipment to determine the layout position of the thruster;
module M5: and acquiring configuration and layout information of the two-component multi-gear thruster of the Mars detector.
Preferably, said module M1 comprises:
module M1.1: acquiring the plume of the thruster and the information of the research result of the work heat influence according to the Mars detection overall configuration parameter information and the Mars detection overall layout parameter information;
module M1.2: and acquiring the statistical carding information of the layout resources of the thruster according to the plume of the thruster and the information of the research result of the work heat influence.
Preferably, the module M1 further includes:
module M1.3: according to the statistical carding information of the layout resources of the thruster and the connection characteristic parameters of the pipelines of the two-component propulsion system, acquiring the information of the benefit and disadvantage analysis result of the centralized layout mode of the bottom plate of the thruster;
module M1.4: and acquiring the selection result information of the bottom plate centralized layout scheme according to the benefit and disadvantage analysis result information of the thruster bottom plate centralized layout mode.
Preferably, said module M2 comprises:
module M2.1: starting from a Mars detection task target and a technical scheme, according to Mars detection task target parameter information, thruster configuration demand information and thruster design index parameter information are obtained.
Preferably, the module M2 further includes:
module M2.2: the requirements of three-axis attitude and orbit control capability in the whole process of a task are analyzed, constraints of thrust, thrust and configuration quantity of thrusters are formed, and stepped main-standby matching of 1 thruster 3000N, 8 thrusters 120N and 12 thrusters 25N is formed by combining resource limitations of weight and power consumption of a detector system.
Specifically, in one embodiment, a mars detector two-component multi-gear thruster configuration and layout method comprises the following steps:
step 1: the overall configuration and layout of the detector are inspected, and the layout feasibility of the two-component thruster is determined;
step 2: analyzing the requirement of attitude and orbit control task, and determining the configuration of a thruster;
and step 3: and analyzing the requirement of the interference torque and the constraint of the installation position, and determining the length of the force arm of the thruster.
And 4, step 4: and determining the layout position of the thruster according to the plume of the thruster and the working heat influence.
Step 1: the characteristics of the overall configuration and layout of the Mars probe are fully considered, plume and working heat influence of the thruster are researched, available layout resources of the thruster are counted and carded, the characteristic of pipeline connection of a two-component propulsion system is considered, the advantage and disadvantage analysis of a centralized layout mode of a bottom plate of the thruster is completed, and the feasibility of centralized layout of the bottom plate is clarified;
step 2: starting from a mars detection task target and a technical scheme, knowing the configuration requirement and design index parameters of a thruster, analyzing the three-axis attitude and orbit control capability requirement of the whole task process, forming the constraints of specific impulse, thrust and configuration quantity of the thruster, and forming 3-gear main and standby matching of 1 thruster 3000N, 8 thrusters 120N and 12 thrusters 25N by combining the resource limitations of the weight and power consumption of a detector system;
and step 3: analyzing the requirement of interference torque and the constraint of a mounting position based on the requirement of an attitude and orbit control task, designing a combined working mode of a 3-gear thruster, and determining the length of a force arm of the thruster;
and 4, step 4: based on the overall configuration and layout of the detector, the reasonable layout position and the design cost of the thruster are balanced, the constraint of the mechanical environment of the detector on the layout position of the thruster, the influence of plume and working heat of the thruster are fully considered, and the layout position of the thruster is determined by combining the layout state of single-machine equipment.
The configuration and layout method of the Mars detector double-component multi-gear thruster provided by the invention is different from the configuration and layout scheme of the traditional satellite thruster, and the Mars detector double-component multi-gear thruster is generally arranged at the central position of each vertex or each edge of a platform and is configured by 2 gears of large thrust and small thrust. The method fully considers the layout space of the Mars detector and the system resource limitation, solves the problem of the layout of the thruster under the resource constraint through the design matched with the characteristics of a two-component system, the three-axis attitude and orbit control capability requirement, the attitude and orbit control working mode and the layout of single-machine equipment, and meets the working requirement of the attitude and orbit control of the detector; the method has the advantages of simple principle, novel thought and clear process, not only embodies the maturity of technical application, but also shows the flexibility and the innovativeness of application, is an important solution for realizing the layout configuration of the two-component thruster in subsequent Mars detection tasks and other deep space detection tasks under the conditions of high configuration requirement, strong layout constraint and the like, is closely combined with actual engineering, and has high engineering guidance and direct application value; the method is directly oriented to the mars detection task, fully considers the technical characteristics and difficulties of the deep space detection task in the process, and performs matching design of system configuration and working modes by utilizing the favorable condition that a propulsion system is tiled at the bottom of a detector compared with a near-earth space task, thereby meeting the requirements of engineering tasks and optimizing system resource configuration. After the method is provided, the engineering means of thruster configuration and layout in other deep space exploration tasks represented by a Mars exploration task are expanded, and different requirements of subsequent deep space exploration tasks are met.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (4)
1. A configuration and layout method for a two-component multi-gear thruster of a Mars probe is characterized by comprising the following steps:
step S1: acquiring the selection result information of the bottom plate centralized layout scheme according to the mars detection overall configuration parameter information and the mars detection overall layout parameter information;
step S2: acquiring grading main and standby matching result information according to Mars detection task target parameter information;
step S3: analyzing the requirement of interference torque and the constraint of installation position based on the requirement of attitude and orbit control task, constructing a combined working mode of 3 grades of thrusters, and finishing the length coordination installation of the force arm of the thrusters;
step S4: based on the overall configuration and layout of the detector, balancing the reasonable layout position and the design cost of the thruster, considering the constraint of the mechanical environment of the detector on the layout position of the thruster, the influence of plume and working heat of the thruster, and combining the layout state of single-machine equipment to determine the layout position of the thruster;
step S5: acquiring configuration and layout information of a two-component multi-gear thruster of the Mars detector;
the step S1 includes:
step S1.1: acquiring the plume of the thruster and the information of the research result of the work heat influence according to the Mars detection overall configuration parameter information and the Mars detection overall layout parameter information;
step S1.2: acquiring thruster layout resource statistics and carding information according to the thruster plume and the work heat influence research result information;
the step S2 includes:
step S2.1: acquiring thruster configuration demand information and thruster design index parameter information according to the Mars detection task target parameter information;
the step S2 further includes:
step S2.2: the requirements of three-axis attitude and orbit control capability in the whole process of a task are analyzed, constraints of thrust, thrust and configuration quantity of thrusters are formed, and stepped main-standby matching of 1 thruster 3000N, 8 thrusters 120N and 12 thrusters 25N is formed by combining resource limitations of weight and power consumption of a detector system.
2. The mars probe two-component multi-step thruster configuration and layout method as claimed in claim 1, wherein the step S1 further comprises:
step S1.3: according to the statistical carding information of the layout resources of the thruster and the connection characteristic parameters of the pipelines of the two-component propulsion system, acquiring the information of the benefit and disadvantage analysis result of the centralized layout mode of the bottom plate of the thruster;
step S1.4: and acquiring the selection result information of the bottom plate centralized layout scheme according to the benefit and disadvantage analysis result information of the thruster bottom plate centralized layout mode.
3. A mars detector bipropellant multi-gear thruster configuration and layout system is characterized by comprising:
module M1: acquiring the selection result information of the bottom plate centralized layout scheme according to the mars detection overall configuration parameter information and the mars detection overall layout parameter information;
module M2: acquiring grading main and standby matching result information according to Mars detection task target parameter information;
module M3: analyzing the requirement of interference torque and the constraint of installation position based on the requirement of attitude and orbit control task, constructing a combined working mode of 3 grades of thrusters, and finishing the length coordination installation of the force arm of the thrusters;
module M4: based on the overall configuration and layout of the detector, balancing the reasonable layout position and the design cost of the thruster, considering the constraint of the mechanical environment of the detector on the layout position of the thruster, the influence of plume and working heat of the thruster, and combining the layout state of single-machine equipment to determine the layout position of the thruster;
module M5: acquiring configuration and layout information of a two-component multi-gear thruster of the Mars detector;
the module M1 includes:
module M1.1: acquiring the plume of the thruster and the information of the research result of the work heat influence according to the Mars detection overall configuration parameter information and the Mars detection overall layout parameter information;
module M1.2: acquiring thruster layout resource statistics and carding information according to the thruster plume and the work heat influence research result information;
the module M2 includes:
module M2.1: acquiring thruster configuration demand information and thruster design index parameter information according to the Mars detection task target parameter information;
the module M2 further includes:
module M2.2: the requirements of three-axis attitude and orbit control capability in the whole process of a task are analyzed, constraints of thrust, thrust and configuration quantity of thrusters are formed, and stepped main-standby matching of 1 thruster 3000N, 8 thrusters 120N and 12 thrusters 25N is formed by combining resource limitations of weight and power consumption of a detector system.
4. The Mars finder two-component multi-stage thruster configuration and layout system of claim 3, wherein said module M1 further comprises:
module M1.3: according to the statistical carding information of the layout resources of the thruster and the connection characteristic parameters of the pipelines of the two-component propulsion system, acquiring the information of the benefit and disadvantage analysis result of the centralized layout mode of the bottom plate of the thruster;
module M1.4: and acquiring the selection result information of the bottom plate centralized layout scheme according to the benefit and disadvantage analysis result information of the thruster bottom plate centralized layout mode.
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000190899A (en) * | 1997-11-25 | 2000-07-11 | Trw Inc | Thruster system for control of spacecraft attitude and speed |
| CN102358437A (en) * | 2011-08-08 | 2012-02-22 | 北京控制工程研究所 | Layout method for 10 N thrusters of high orbit satellite platform |
| CN102649481A (en) * | 2012-04-23 | 2012-08-29 | 上海卫星工程研究所 | 8-thruster layout designing method based on double-moment rectangular pyramid |
| CN105197257A (en) * | 2015-08-31 | 2015-12-30 | 中国空间技术研究院 | Thruster layout method for truss type GEO (geostationary orbit) satellite adopting subdivision optimization design |
| CN105883008A (en) * | 2014-12-15 | 2016-08-24 | 中国空间技术研究院 | Satellite thruster layout method |
| CN106428651A (en) * | 2016-11-29 | 2017-02-22 | 上海卫星工程研究所 | Space-based large-diameter multi-constrained extrasolar terrestrial planet detector structure |
| CN108609207A (en) * | 2018-03-12 | 2018-10-02 | 上海卫星工程研究所 | A kind of Mars probes high resolution camera layout and assembling method |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8489260B2 (en) * | 2008-12-16 | 2013-07-16 | California Institute Of Technology | Method and apparatus for powered descent guidance |
| CN101941529B (en) * | 2010-09-08 | 2013-04-17 | 北京理工大学 | Layout method for micro attitude and orbit control thruster array |
| US20160048612A1 (en) * | 2014-08-14 | 2016-02-18 | U.S.A. As Represented By The Administrator Of The National Aeronautics And Space Administration | Method and Software Tool for Evaluation and Automated Generation of Space Habitat Interior Layouts |
| CN106628260B (en) * | 2016-11-17 | 2018-11-23 | 上海卫星工程研究所 | A kind of layout design method of the coplanar double copies of spacecraft thruster |
-
2020
- 2020-10-22 CN CN202011140995.3A patent/CN112208801B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000190899A (en) * | 1997-11-25 | 2000-07-11 | Trw Inc | Thruster system for control of spacecraft attitude and speed |
| CN102358437A (en) * | 2011-08-08 | 2012-02-22 | 北京控制工程研究所 | Layout method for 10 N thrusters of high orbit satellite platform |
| CN102649481A (en) * | 2012-04-23 | 2012-08-29 | 上海卫星工程研究所 | 8-thruster layout designing method based on double-moment rectangular pyramid |
| CN105883008A (en) * | 2014-12-15 | 2016-08-24 | 中国空间技术研究院 | Satellite thruster layout method |
| CN105197257A (en) * | 2015-08-31 | 2015-12-30 | 中国空间技术研究院 | Thruster layout method for truss type GEO (geostationary orbit) satellite adopting subdivision optimization design |
| CN106428651A (en) * | 2016-11-29 | 2017-02-22 | 上海卫星工程研究所 | Space-based large-diameter multi-constrained extrasolar terrestrial planet detector structure |
| CN108609207A (en) * | 2018-03-12 | 2018-10-02 | 上海卫星工程研究所 | A kind of Mars probes high resolution camera layout and assembling method |
Non-Patent Citations (1)
| Title |
|---|
| 载人火星探测任务方案构想;朱新波，谢华，徐亮，陆希;《上海航天》;20140225;全文 * |
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