CN110920935A - Plug-and-play intelligent core system - Google Patents
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- CN110920935A CN110920935A CN201911313074.XA CN201911313074A CN110920935A CN 110920935 A CN110920935 A CN 110920935A CN 201911313074 A CN201911313074 A CN 201911313074A CN 110920935 A CN110920935 A CN 110920935A
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- 238000007726 management method Methods 0.000 claims description 35
- 238000004364 calculation method Methods 0.000 claims description 10
- 238000009432 framing Methods 0.000 claims description 5
- 238000013523 data management Methods 0.000 claims description 3
- 238000002347 injection Methods 0.000 claims description 3
- 239000007924 injection Substances 0.000 claims description 3
- 238000004458 analytical method Methods 0.000 claims description 2
- 230000010354 integration Effects 0.000 abstract description 8
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
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Abstract
A plug-and-play intelligent core system solves the problem of low integration speed of the existing satellite products, and belongs to the field of satellite design. The invention comprises a central computer, a reconfigurable module, a nonstandard interface module, a reconfigurable module, a standard interface module and a measurement and control module: the central computer is used for realizing satellite affair management, attitude and orbit control, power management, thermal control management and protocol driving of the satellite; the reconfigurable module is simultaneously connected with the central computer and the non-standard interface module and is used for reconfiguring the data protocol of the non-standard interface module into a standard bus protocol and further connecting the standard bus protocol with the central computer through a universal bus, so that the plug and play of the non-standard interface module are realized; the non-standard interface module is used for connecting a single machine component of the non-standard interface; the standard interface module is connected with the central computer through a universal bus and is used for connecting a single machine component of a non-standard interface; and the measurement and control module is connected with the central computer and is used for realizing the functions of remote measurement and control of the whole satellite.
Description
Technical Field
The invention relates to an integrated system, in particular to a high-integration plug-and-play intelligent core system, and belongs to the field of satellite design.
Background
With the development trend of satellite microminiaturization, higher requirements are put forward on the integration level of the satellite. The microsatellite is limited in aspects of quality, power consumption and the like, so that the platform quality is reduced, the platform power consumption is reduced, and the method is very important for improving the loading capacity of the microsatellite. In addition, with the development of aerospace commercialization, higher requirements are put on the integration speed of satellites. Commercial aerospace adopts more COTS devices, and often does not have a uniform communication protocol, so that the integration speed of satellite products is restricted.
Disclosure of Invention
Aiming at the problem of low integration speed of the existing satellite product, the invention provides a high-integration plug-and-play intelligent core system.
The invention relates to a plug-and-play intelligent core system, which comprises a central computer, a reconfigurable module, a nonstandard interface module, a reconfigurable module, a standard interface module and a measurement and control module, wherein the central computer comprises a central computer, the reconfigurable module comprises a plurality of modules, the central computer comprises a plurality of modules, and the central computer comprises:
the central computer is used for realizing satellite affair management, attitude and orbit control, power management, thermal control management and protocol driving of the satellite;
the reconfigurable module is simultaneously connected with the central computer and the non-standard interface module and is used for reconfiguring the data protocol of the non-standard interface module into a standard bus protocol and further connecting the standard bus protocol with the central computer through a universal bus, so that the plug and play of the non-standard interface module are realized;
the non-standard interface module is used for connecting a single machine component of the non-standard interface;
the standard interface module is connected with the central computer through a universal bus and is used for connecting a single machine component of a non-standard interface;
and the measurement and control module is connected with the central computer and is used for realizing the functions of remote measurement and control of the whole satellite.
Preferably, the central computer is configured to receive telemetry data of each stand-alone component through a general bus, complete framing of whole satellite telemetry, and download the framing to the measurement and control module, and is further configured to receive a remote injection instruction forwarded by the measurement and control module, perform instruction analysis, and forward the analyzed instruction to other stand-alone components through the general bus.
Preferably, the central computer implements satellite affair management of the satellite, including data management, task management and time management.
Preferably, the central computer implements attitude and orbit control of the satellite, including attitude determination, attitude calculation, attitude control, orbit calculation, and orbit control of the satellite.
Preferably, the central computer implements power management of the satellite, including implementing whole-satellite power distribution management, ampere-hour meter calculation and single battery balancing.
Preferably, the central computer implements thermal control management of the satellite, including implementing an active thermal control function of the whole satellite.
Preferably, the system further comprises a power supply and distribution module which is used for converting the primary bus voltage of the whole satellite into the voltage required by the central computer, the measurement and control module and the reconfigurable module.
The plug-and-play intelligent core system with high integration level integrates a satellite system, attitude and orbit control, power management and other systems, greatly simplifies satellite hardware configuration, reduces satellite weight and lowers satellite cost. Meanwhile, the intelligent core system realizes plug and play of different interface devices by using the reconfigurable unit, and the integration speed of satellite products is increased.
Drawings
Fig. 1 is a schematic diagram of the principle of the present invention.
Detailed Description
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 only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.
The invention is further described with reference to the following drawings and specific examples, which are not intended to be limiting.
The plug-and-play intelligent core system of the embodiment comprises a central computer, a reconfigurable module, a nonstandard interface module, a reconfigurable module, a standard interface module and a measurement and control module:
the central computer is used for realizing satellite affair management, attitude and orbit control, power management, thermal control management and protocol driving of the satellite;
the reconfigurable module is simultaneously connected with the central computer and the non-standard interface module and is used for reconfiguring the data protocol of the non-standard interface module into a standard bus protocol and further connecting the standard bus protocol with the central computer through a universal bus, so that the plug and play of the non-standard interface module are realized;
the non-standard interface module is used for connecting a single machine component of the non-standard interface;
the standard interface module is connected with the central computer through a universal bus and is used for connecting a single machine component of a non-standard interface;
and the measurement and control module is connected with the central computer and is used for realizing the functions of remote measurement and control of the whole satellite.
In the existing satellite design, a housekeeping system, an attitude and orbit control system, a power supply management system and a thermal control management system are all provided with independent computer systems, and all the systems are connected through a hardware bus. The intelligent core system provided by the embodiment integrates the housekeeping management, the attitude and orbit control, the power supply management and the thermal control management into one computer system, realizes the independent operation of each functional module in a thread mode, and reduces 3 computer units and corresponding cable and shell structures without considering the backup condition. The central computer of the embodiment integrates the central computer, the measurement and control module, the reconfigurable module and the power supply and distribution module into one case, and adopts the connectors between boards to perform data communication, thereby reducing communication cables between systems and simultaneously reducing independent shell structures. The intelligent core system of the embodiment realizes the plug and play of the standard interface module by using the equipment identification protocol, realizes the plug and play of the nonstandard interface module by using the reconfigurable module, and greatly improves the system integration speed.
The central computer of the embodiment receives the telemetering data of each single machine component through the general bus, completes the framing of the whole satellite telemetering, and transmits the framing to the measurement and control module through the PCM interface. The central computer receives the remote control injection instruction forwarded by the measurement and control module through the PCM interface, analyzes the instruction, and forwards the analyzed instruction to other single machine components through the general bus or directly executes the instruction related to the central computer.
The protocol driver of the embodiment is used for realizing the autonomous recognition function of the universal bus and realizing the plug and play of the standard interface module. The method specifically comprises the following steps: and dynamically allocating ID to the standard module according to the unique equipment identification code of the standard module, and realizing the autonomous identification of the central machine and the single machine component, thereby realizing the rapid access of the standard module.
The central computer of the embodiment realizes the satellite affair management of the satellite, including data management, task management and time management.
The central computer of the embodiment realizes attitude and orbit control of the satellite, including attitude determination, attitude calculation, attitude control, orbit calculation and orbit control of the satellite. The method specifically comprises the following steps: determining the current attitude and orbit by acquiring the attitude and orbit information of the sensor and the actuating mechanism after the star management processing; and calculating attitude control and track control parameters according to the current control mode or instruction, and driving the actuating mechanism.
The central computer of the embodiment implements power management of the satellite, including implementing whole-satellite power distribution management, ampere-hour meter calculation and single battery balancing. The method specifically comprises the following steps: according to task execution or instructions, directly driving the OC chip to control the on-off of each single machine component; directly acquiring information such as bus voltage, bus current, load current, solar array current and the like through an ADC chip, and carrying out ampere-hour meter calculation; and directly acquiring the voltage of each single battery through an ADC chip, and carrying out balance calculation on the single batteries.
The central computer of the embodiment realizes the thermal control management of the satellite, including the active thermal control function of the whole satellite. The method specifically comprises the following steps: the temperature information of each active temperature control point is directly acquired through the ADC chip, and the output and the turn-off of the heating sheet are directly driven according to the threshold of the active temperature control switch.
The system of the embodiment further comprises a power supply and distribution module which is used for converting the primary bus voltage of the whole satellite into various voltages such as 1.2V, 3.3V, 5V and 12V required by the central computer, the measurement and control module and the reconfigurable module, and ensuring the normal operation of each functional module. The intelligent core system of the embodiment uses the common power distribution module to provide power distribution for the central computer, the measurement and control module and the reconfigurable module, and 2 power supply and distribution modules are saved.
Although the invention herein has been described with reference to particular embodiments, it is to be understood that these embodiments are merely illustrative of the principles and applications of the present invention. It is therefore to be understood that numerous modifications may be made to the illustrative embodiments and that other arrangements may be devised without departing from the spirit and scope of the present invention as defined by the appended claims. It should be understood that features described in different dependent claims and herein may be combined in ways different from those described in the original claims. It is also to be understood that features described in connection with individual embodiments may be used in other described embodiments.
Claims (7)
1. The plug-and-play intelligent core system is characterized by comprising a central computer, a reconfigurable module, a nonstandard interface module, a reconfigurable module, a standard interface module and a measurement and control module:
the central computer is used for realizing satellite affair management, attitude and orbit control, power management, thermal control management and protocol driving of the satellite;
the reconfigurable module is simultaneously connected with the central computer and the non-standard interface module and is used for reconfiguring the data protocol of the non-standard interface module into a standard bus protocol and further connecting the standard bus protocol with the central computer through a universal bus, so that the plug and play of the non-standard interface module are realized;
the non-standard interface module is used for connecting a single machine component of the non-standard interface;
the standard interface module is connected with the central computer through a universal bus and is used for connecting a single machine component of a non-standard interface;
and the measurement and control module is connected with the central computer and is used for realizing the functions of remote measurement and control of the whole satellite.
2. The plug-and-play intelligent core system of claim 1, wherein the central computer is configured to receive telemetry data of each stand-alone component via a universal bus, complete framing of whole satellite telemetry, download to the measurement and control module, receive a remote injection instruction forwarded by the measurement and control module, perform instruction analysis, and forward the analyzed instruction to other stand-alone components via the universal bus.
3. The plug-and-play intelligent core system of claim 1, wherein said central computer implements satellite services management including data management, task management, time management.
4. The plug-and-play intelligent core system of claim 1, wherein said central computer implements attitude and orbit control of the satellite, including attitude determination, attitude calculation, attitude control, orbit calculation, and orbit control of the satellite.
5. The plug-and-play smart core system of claim 1, wherein said central computer implements satellite power management, including whole-satellite power distribution management, ampere-hour computing, and cell battery balancing.
6. The plug-and-play intelligent core system of claim 1, wherein said central computer implements thermal management of the satellite, including implementing a whole-satellite active thermal management function.
7. The plug-and-play smart core system of claim 1, further comprising a power supply and distribution module for converting a voltage of a primary bus of the whole star to a voltage required by the central computer, the measurement and control module, and the reconfigurable module.
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| CN201911313074.XA CN110920935A (en) | 2019-12-18 | 2019-12-18 | Plug-and-play intelligent core system |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111891398A (en) * | 2020-08-13 | 2020-11-06 | 中国人民解放军国防科技大学 | Elastic universal intelligent satellite hardware system architecture |
| CN112035384A (en) * | 2020-08-28 | 2020-12-04 | 西安微电子技术研究所 | Satellite-borne information processing system, method, equipment and readable storage medium |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5978578A (en) * | 1997-01-30 | 1999-11-02 | Azarya; Arnon | Openbus system for control automation networks |
| US20050060317A1 (en) * | 2003-09-12 | 2005-03-17 | Lott Christopher Martin | Method and system for the specification of interface definitions and business rules and automatic generation of message validation and transformation software |
| US6873886B1 (en) * | 2002-11-27 | 2005-03-29 | The United States Of America As Represented By The Secretary Of The Navy | Modular mission payload control software |
| CN202160096U (en) * | 2011-08-17 | 2012-03-07 | 浪潮电子信息产业股份有限公司 | Power conversion board with non-standard interface |
| CN102662904A (en) * | 2012-04-06 | 2012-09-12 | 哈尔滨工业大学 | Plug-and-play system based on controller area network (CAN) bus and design method thereof |
| EP2570921A1 (en) * | 2011-06-14 | 2013-03-20 | Siemens Aktiengesellschaft | Devices and method for exchanging data |
| CN205910547U (en) * | 2016-08-03 | 2017-01-25 | 深圳航天东方红海特卫星有限公司 | Star of integration carries integration electronic system |
| CN109359083A (en) * | 2018-09-27 | 2019-02-19 | 浙江大学 | The hardware implementation method of restructural series bus controller in a kind of chip |
| CN110002005A (en) * | 2019-03-04 | 2019-07-12 | 哈尔滨工业大学 | A kind of restructural micro-nano satellite system architecture and satellite system reconstructing method |
| CN110471341A (en) * | 2019-08-15 | 2019-11-19 | 中国空间技术研究院 | A kind of spaceborne intelligent menu mode Integrated Electronic System |
-
2019
- 2019-12-18 CN CN201911313074.XA patent/CN110920935A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5978578A (en) * | 1997-01-30 | 1999-11-02 | Azarya; Arnon | Openbus system for control automation networks |
| US6873886B1 (en) * | 2002-11-27 | 2005-03-29 | The United States Of America As Represented By The Secretary Of The Navy | Modular mission payload control software |
| US20050060317A1 (en) * | 2003-09-12 | 2005-03-17 | Lott Christopher Martin | Method and system for the specification of interface definitions and business rules and automatic generation of message validation and transformation software |
| EP2570921A1 (en) * | 2011-06-14 | 2013-03-20 | Siemens Aktiengesellschaft | Devices and method for exchanging data |
| CN202160096U (en) * | 2011-08-17 | 2012-03-07 | 浪潮电子信息产业股份有限公司 | Power conversion board with non-standard interface |
| CN102662904A (en) * | 2012-04-06 | 2012-09-12 | 哈尔滨工业大学 | Plug-and-play system based on controller area network (CAN) bus and design method thereof |
| CN205910547U (en) * | 2016-08-03 | 2017-01-25 | 深圳航天东方红海特卫星有限公司 | Star of integration carries integration electronic system |
| CN109359083A (en) * | 2018-09-27 | 2019-02-19 | 浙江大学 | The hardware implementation method of restructural series bus controller in a kind of chip |
| CN110002005A (en) * | 2019-03-04 | 2019-07-12 | 哈尔滨工业大学 | A kind of restructural micro-nano satellite system architecture and satellite system reconstructing method |
| CN110471341A (en) * | 2019-08-15 | 2019-11-19 | 中国空间技术研究院 | A kind of spaceborne intelligent menu mode Integrated Electronic System |
Non-Patent Citations (5)
| Title |
|---|
| 张景楠等: "微小卫星星务分系统的硬件设计与实现", 《电子设计工程》 * |
| 徐祎，杨晓静，王懋: "《通信原理与系统》", 30 September 2012, 国防工业出版社 * |
| 朱烜硕: "基于CAN总线的卫星即插即用系统的设计与实现", 《中国优秀硕士学位论文全文数据库工程科技Ⅱ辑》 * |
| 杨晶: "基于FPGA的UART接口协议转换模块设计", 《中国优秀硕士学位论文全文数据库信息科技辑》 * |
| 邹吉炜: "空间即插即用电子系统关键技术研究", 《中国优秀硕士学位论文全文数据库工程科技Ⅱ辑》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111891398A (en) * | 2020-08-13 | 2020-11-06 | 中国人民解放军国防科技大学 | Elastic universal intelligent satellite hardware system architecture |
| CN111891398B (en) * | 2020-08-13 | 2022-03-11 | 中国人民解放军国防科技大学 | Elastic universal intelligent satellite hardware system architecture |
| CN112035384A (en) * | 2020-08-28 | 2020-12-04 | 西安微电子技术研究所 | Satellite-borne information processing system, method, equipment and readable storage medium |
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Application publication date: 20200327 |