CN116794967A - On-orbit service type spacecraft software system - Google Patents
On-orbit service type spacecraft software system Download PDFInfo
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- CN116794967A CN116794967A CN202310705786.6A CN202310705786A CN116794967A CN 116794967 A CN116794967 A CN 116794967A CN 202310705786 A CN202310705786 A CN 202310705786A CN 116794967 A CN116794967 A CN 116794967A
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- 238000002474 experimental method Methods 0.000 claims abstract description 7
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Abstract
The invention belongs to the technical field of aerospace craft software systems, and particularly relates to an on-orbit service type aerospace craft software system which comprises an on-orbit operation module, a data and task management module and a service management module, wherein the on-orbit operation module comprises an attitude control sub-module, an orbit control sub-module and an object approaching and on-orbit operation sub-module, the data and task management module comprises an environment maintenance sub-module, a power supply management sub-module, a data management sub-module, a communication management sub-module, a fusion and fault processing sub-module and a reconstruction and upgrading sub-module, and the service management module comprises a large data management sub-module, an aircraft experiment management sub-module and a sensitive environment control sub-module. The invention realizes multi-level redundancy and fault diagnosis by combining the three-mode redundancy computer electronic system, and ensures the high reliability of the aerospace system.
Description
Technical Field
The invention belongs to the technical field of aerospace craft software systems, and particularly relates to an on-orbit service type aerospace craft software system.
Background
With the rapid development of commercial aerospace, spacecraft targeted for on-orbit service have received increasing attention, such as space debris removal, on-orbit construction, on-orbit maintenance, target capture, and the like. With the development of technology, the demands for service functions increase, and operations to be performed become more and more complex. The software management of the traditional satellite is distinguished according to a subsystem, which comprises the following steps: the remote measurement and control, thermal control, energy, orbit, attitude, acquisition, load and the like are focused on the satellite platform by the management mode, and the management capability of the load is not strong, so that the system cannot adapt to the current on-orbit service targets.
The fault monitoring and health management of the satellite system are realized on the basis of data acquisition, state monitoring and health evaluation, data of the platform and data flows of all components are concerned, the fusion of device redundancy and functions is rarely considered, the platform and the load are completely isolated, and the optimal operation mode of the system cannot be automatically acquired.
At present, commercial aerospace starts to adopt low-cost industrial-grade devices, the reliability of electronic system hardware is improved through a redundancy scheme, but the processing capacity of automatic fault and diagnosis needs to be improved by combining software management.
Disclosure of Invention
In order to solve the technical problems, the invention provides an on-orbit service type spacecraft software system, which aims at serving various loads of aerospace and divides the software system into three modules: the on-orbit operation module, the data and task management module and the service management module are used for designing software fusion and fault diagnosis based on redundancy of industrial devices and data fusion of various buses to form a software system.
The invention is realized in this way, and provides an on-orbit service type spacecraft software system, which comprises an on-orbit operation module, a data and task management module and a service management module, wherein:
the on-orbit operation module comprises an attitude control sub-module, a track control sub-module and a target approaching and on-orbit operation sub-module, wherein the attitude control sub-module is used for completing high-precision attitude alignment, the track control sub-module is used for completing orbital transfer and orbit maneuver, and the target approaching and on-orbit operation sub-module is used for calling the attitude control sub-module and the track control sub-module to implement high-speed autonomous attitude and orbit combined control;
the data and task management module comprises an environment maintenance sub-module, a power supply management sub-module, a data management sub-module, a communication management sub-module, a fusion and fault processing sub-module and a reconstruction and upgrading sub-module, wherein each sub-module of the data and task management module is provided with a fault monitoring function, the environment maintenance sub-module is used for monitoring and controlling the operation parameters of the spacecraft, the power supply management sub-module is used for monitoring and controlling the power supply condition of the spacecraft, the data management sub-module is used for storing and updating data and programs and realizing redundancy backup of the data, the communication management sub-module is used for carrying out data interaction, verification and control instruction sending under different communication modes of each single machine, the fusion and fault processing sub-module is used for carrying out fusion analysis on fault monitoring data of each sub-module of the data and the task management module, and the reconstruction and upgrading sub-module is used for reconstructing and upgrading the computing system; the computing system is an on-orbit operation module, a data and task management module and a service management module;
the service management module comprises a big data management sub-module, an aircraft experiment management sub-module and a sensitive environment control sub-module, wherein the big data management sub-module is used for carrying out centralized storage, packaging and transmission on-orbit test data of loads, the aircraft experiment management sub-module is used for driving actions in the on-orbit experiment process and planning tasks, and the sensitive environment control sub-module is used for carrying out monitoring and control on environments and guaranteeing the requirements on the working environment of the loads.
Preferably, the on-orbit operation module, the data and task management module and the service management module communicate with external standalone and hardware units through buses.
Further preferably, the bus communication mode is CAN or SPI or I2C.
Compared with the prior art, the invention has the advantages that:
the invention provides a software system of an on-orbit service type spacecraft, which takes a service object as a center, designs the spacecraft software system into different levels and comprises the following components: the system comprises an on-orbit operation module, a data and task management module and a service management module. And the functional sub-modules and the single machine of the platform are uniformly managed, and a three-module redundant computer electronic system is combined, so that multi-level redundancy and fault diagnosis are realized, and the high reliability of the aerospace system is ensured.
Drawings
FIG. 1 is a schematic diagram of the software system of an on-orbit service type spacecraft provided by the invention;
FIG. 2 is an application diagram of a software system of an on-orbit service type spacecraft provided by the invention in one embodiment;
fig. 3 is a multi-layer fault diagnosis software system of the on-orbit service type spacecraft provided by the invention.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
Referring to FIG. 1, in one embodiment of the present invention, an on-orbit service type spacecraft software system is presented, which is suitable for low-cost commercial aerospace and task requirements of multiple service objects.
As shown in fig. 2, in one embodiment of the present invention, the on-track operations module, the data and task management module, and the service management module connect different stand-alone and hardware units and communicate with each other using a bus of CAN, SPI, I C or the like, using redundant industrial-level devices. Specific:
the track control device controls the propulsion of different thrusts to realize different track change or auxiliary gesture adjustment, collects sensing and switching state information, designs pressure sensing, temperature sensing, valve switching and the like into a redundant distribution array, processes the redundant information of a single machine of the unit in fusion fault diagnosis, and ensures the use of key components.
And the gesture control performs data fusion on the gesture high-precision device and the low-precision array device, acquires high-precision gesture determination by combining navigation positioning information, performs fusion on the high-cost gesture control device and the low-cost device, and completes the optimal gesture control scheme by combining power supply management information in different flight phases.
The power supply management is used for managing high-power devices, combining task requirements and optimizing energy sources; the switch of the primary power supply and the secondary power supply is controlled by combining service management and task requirements; and (3) implementing automatic power-on and sailboard unfolding control in the separation and track-entering stage.
The communication management combines the key communication devices including a measurement and control data transmission integrated machine and a redundant backup of navigation communication, and controls the communication of ground telemetry control, positioning and orbit determination and relative navigation of relative targets. The communication data and the data and states of each module are centralized in data management through bus communication, and are stored and calculated in a backup mode in a three-mode redundant calculation array. Under the condition of task faults or modification, supporting the software reconstruction of the spacecraft, storing the software codes uploaded by communication in three computing arrays, and respectively performing actions such as reading and restarting the reconstructed data to complete the data reconstruction.
According to different service object requirements, the system is mainly divided into three modules, and large data storage forwarding, test process control and sensitive environment control are respectively realized, and the driving and collecting modules are redundant and backed up, so that the system can adapt to more service objects and has higher reliability.
As shown in fig. 2, the hardware systems included under each management module of the spacecraft respectively include a single-machine array, power supply configuration and redundancy of a driving module, as shown in fig. 3, each sub-module software has corresponding data alarm, and the early warning signals are intensively processed in a fusion and fault processing unit; firstly, redundant data is arbitrated, a fault part is restarted, the fault part is judged to be in an unrepairable state, a backup scheme is isolated, isomorphic backup replacement or heterogeneous type replacement, such as a reaction flywheel fault, cannot be repaired after restarting, and the flywheel is closed by executing energy control, so that the fault part is replaced by a low-thrust propeller or magnetic rod attitude control scheme.
Claims (3)
1. An on-orbit service type spacecraft software system, which is characterized by comprising an on-orbit operation module, a data and task management module and a service management module, wherein:
the on-orbit operation module comprises an attitude control sub-module, a track control sub-module and a target approaching and on-orbit operation sub-module, wherein the attitude control sub-module is used for completing high-precision attitude alignment, the track control sub-module is used for completing orbital transfer and orbit maneuver, and the target approaching and on-orbit operation sub-module is used for calling the attitude control sub-module and the track control sub-module to implement high-speed autonomous attitude and orbit combined control;
the data and task management module comprises an environment maintenance sub-module, a power supply management sub-module, a data management sub-module, a communication management sub-module, a fusion and fault processing sub-module and a reconstruction and upgrading sub-module, wherein each sub-module of the data and task management module is provided with a fault monitoring function, the environment maintenance sub-module is used for monitoring and controlling the operation parameters of the spacecraft, the power supply management sub-module is used for monitoring and controlling the power supply condition of the spacecraft, the data management sub-module is used for storing and updating data and programs and realizing redundancy backup of the data, the communication management sub-module is used for carrying out data interaction, verification and control instruction sending under different communication modes of each single machine, the fusion and fault processing sub-module is used for carrying out fusion analysis on fault monitoring data of each sub-module of the data and the task management module, and the reconstruction and upgrading sub-module is used for reconstructing and upgrading the computing system;
the service management module comprises a big data management sub-module, an aircraft experiment management sub-module and a sensitive environment control sub-module, wherein the big data management sub-module is used for carrying out centralized storage, packaging and transmission on-orbit test data of loads, the aircraft experiment management sub-module is used for driving actions in the on-orbit experiment process and planning tasks, and the sensitive environment control sub-module is used for carrying out monitoring and control on environments and guaranteeing the requirements on the working environment of the loads.
2. The on-orbit service spacecraft software system according to claim 1, wherein said on-orbit operations module, said data and task management module and said service management module communicate with external standalone and hardware units via buses.
3. The on-orbit service type spacecraft software system according to claim 1, wherein the bus communication mode is CAN or SPI or I2C.
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| CN202310705786.6A CN116794967A (en) | 2023-06-15 | 2023-06-15 | On-orbit service type spacecraft software system |
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| CN202310705786.6A CN116794967A (en) | 2023-06-15 | 2023-06-15 | On-orbit service type spacecraft software system |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104182304A (en) * | 2014-08-12 | 2014-12-03 | 西北工业大学 | Universal multi-mode redundant pico/nano satellite on-board computer system |
| CN111106757A (en) * | 2019-11-20 | 2020-05-05 | 平高集团有限公司 | Power electronic transformer system based on MMC and hierarchical control system architecture thereof |
| CN112785183A (en) * | 2021-01-31 | 2021-05-11 | 中国人民解放军63963部队 | Health management system framework for layered fusion type vehicle teams |
| CN116203903A (en) * | 2023-03-01 | 2023-06-02 | 北京科技大学 | Space-time root diagnosis method for quality abnormality in hot continuous rolling process |
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- 2023-06-15 CN CN202310705786.6A patent/CN116794967A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104182304A (en) * | 2014-08-12 | 2014-12-03 | 西北工业大学 | Universal multi-mode redundant pico/nano satellite on-board computer system |
| CN111106757A (en) * | 2019-11-20 | 2020-05-05 | 平高集团有限公司 | Power electronic transformer system based on MMC and hierarchical control system architecture thereof |
| CN112785183A (en) * | 2021-01-31 | 2021-05-11 | 中国人民解放军63963部队 | Health management system framework for layered fusion type vehicle teams |
| CN116203903A (en) * | 2023-03-01 | 2023-06-02 | 北京科技大学 | Space-time root diagnosis method for quality abnormality in hot continuous rolling process |
Non-Patent Citations (4)
| Title |
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| 何礼富主编: "《软件工程与项目管理》", 31 May 2009, 长沙：国防科技大学出版社, pages: 166 - 167 * |
| 兰盛昌;孙蕊;邬树楠;王继河;徐国栋;: "基于SoC的"微型核"星载电子系统设计", 哈尔滨工业大学学报, no. 07, pages 1026 - 1030 * |
| 宫江雷;韩笑冬;张金辉;邓兵;杨凯飞;李翔;: "基于模型化配置的星务自主控制软件设计与应用", 空间控制技术与应用, no. 03 * |
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