WO2015180000A1 - Comprehensive management system for platform and payload integrated satellite - Google Patents

Comprehensive management system for platform and payload integrated satellite Download PDF

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Publication number
WO2015180000A1
WO2015180000A1 PCT/CN2014/000992 CN2014000992W WO2015180000A1 WO 2015180000 A1 WO2015180000 A1 WO 2015180000A1 CN 2014000992 W CN2014000992 W CN 2014000992W WO 2015180000 A1 WO2015180000 A1 WO 2015180000A1
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integrated
board
control
module
management system
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PCT/CN2014/000992
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French (fr)
Chinese (zh)
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徐伟
金光
王绍举
朴永杰
徐拓奇
郑晓云
冯汝鹏
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中国科学院长春光学精密机械与物理研究所
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Publication of WO2015180000A1 publication Critical patent/WO2015180000A1/en

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    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B19/00—Programme-control systems
    • G05B19/02—Programme-control systems electric
    • G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
    • G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors

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  • the invention relates to the field of aerospace technology, in particular to an integrated management system for a platform load integrated satellite, which can realize integrated and high integration of a high performance small satellite platform and a load electronic system, and at the same time take into account the modularization and standardization functions of different types of small satellites. Expand task requirements.
  • the traditional satellite electronic system adopts a function-centered distributed design method, which assigns various functions to the on-board computer of the satellite management computer, attitude control computer, payload computer and other sub-systems that make up the satellite electronic system. .
  • This design method cannot integrate the electronic system of the load and the platform into overall planning and function, and the resource utilization rate is low.
  • the number of on-board computers is often huge and the volume, weight and power consumption of the electronic system are increased several times;
  • each onboard computer is customized on demand, does not have scalability, and is difficult to meet the needs of different types of tasks. It has low reusability, long development cycle and high R&D cost.
  • the present invention is directed to an integrated computer for a platform load integrated satellite to meet future high performance, high integration small satellite application requirements.
  • the invention provides an integrated management system for platform load integrated satellites, in order to solve the problems of low resource utilization and non-scalability of the existing satellite electronic system using the distributed on-board computer design method.
  • An integrated management system for integrated platform load satellites including an integrated integrated control unit and a standardized function expansion unit.
  • the standardized integrated expansion unit uses an external CAN bus to interconnect with an integrated integrated control unit;
  • the integrated integrated control unit is composed of an integrated management module, a communication interface module, a secondary power supply, and an arbitration logic control module.
  • the integrated management module is responsible for the whole star computing task and the scheduling task, and sends a pound control instruction to the communication interface module, and receives external information data transmitted through the communication interface module;
  • the communication interface module performs information exchange with the external interface according to the control command sent by the integrated management module. Mutual and transfer of external information data to the integrated management module;
  • the secondary power supply and arbitration logic control module is used to provide secondary power to the integrated integrated control unit and is responsible for providing arbitration control for the integrated management module;
  • the standardized function expansion unit includes an instruction control board, an active temperature control board, and a mechanism control board;
  • the instruction control board implements various OC commands; including ON/OFF command, camera control OC command, pyrotechnic control OC command, and star arrow separation stroke switch OC signal acquisition;
  • the active temperature control board is composed of a temperature acquisition module and a temperature control module.
  • the temperature acquisition module obtains temperature value digital information through the thermistor, the analog switch, the signal amplification and the A/D conversion, and the temperature control module according to the temperature value.
  • the quantity information is subjected to a full-scale closed-loop temperature control according to a predetermined thermal control strategy;
  • the mechanism control board drives the stepping motor according to the collected encoder information to realize the position control of the camera focusing and the biasing mechanism;
  • the present invention changes the traditional design method for the topology design of the platform load integrated satellite electronic system, and does not focus on functions, and assigns various functions to the onboard computer of each subsystem to complete. Rather, it transcends the boundaries between the sub-systems, adopts the idea of resource sharing, considers the platform load integrated satellite electronic system as a whole, and designs an integrated management system for platform-load integrated satellites, using a highly integrated integrated computer. Realize the electronic management of platform load integrated satellites.
  • the high-performance processor is used to realize the integrated control and management of the platform and the load; 2.
  • the dual-machine hot backup processor is implemented in Parallel data parallel computing and processing.
  • the management system of the invention realizes resource integration, reduces the number of single machines and components, integrates instructions, reduces instruction types and forwarding links, integrates telemetry, reduces redundant telemetry to increase bandwidth, integrates functions, reduces testing links and testing processes, and performs performance. Integration reduces device volume and power consumption.
  • FIG. 1 is a block diagram of an integrated integrated control unit architecture in an integrated management system for a platform load integrated satellite according to the present invention
  • FIG. 2 is a hardware block diagram of a parallel computing of dual CPUs in an integrated management system for a platform load integrated satellite according to the present invention
  • FIG. 3 is a standardization work in an integrated management system for a platform load integrated satellite according to the present invention. Can expand the block diagram of the unit structure;
  • FIG. 4 is a block diagram of a standardized design of an extension unit board in an integrated management system for a platform load integrated satellite according to the present invention
  • FIG. 5 is an exploded view showing the hardware structure of an integrated management system for a platform load integrated satellite according to the present invention
  • Fig. 6 (a) and (b) are schematic diagrams showing an integrated computer integrated and distributed layout in an integrated management system for a platform load integrated satellite according to the present invention.
  • an integrated management system for a platform load integrated satellite is composed of an integrated integrated control unit and a standardized function expansion unit.
  • the integrated minimum function of the star is integrated into an integrated integrated control unit; it is responsible for the autonomous task management and centralized information management of the whole star, and completes the calculation of the control and imaging related algorithms.
  • the integrated integrated control unit is composed of an integrated management module, a communication interface module, a secondary power supply and an arbitration logic control module, and is used for forming a core calculation and processing unit of the integrated satellite management;
  • the integrated management module is responsible for the whole star computing task and the scheduling task, and sends a pound control instruction to the communication interface module, and receives external information data transmitted through the communication interface module;
  • the communication interface module performs information interaction with the external interface according to the control instruction sent by the integrated management module, and transmits the external information data to the integrated management module;
  • the secondary power supply and arbitration logic control module is used to provide secondary power to the integrated integrated control unit and is responsible for providing arbitration control for the integrated management module;
  • the integrated management module adopts a high-performance dual-processor hot backup design, which is composed of a CPUA board 1, a CPUB board 2, a communication board A, a communication board B, a power supply, and an arbitration board. 5 and the bottom plate.
  • the CPUA and CPUB boards that are backed up each other use a high-performance domestic or imported SPARC V8 architecture 32-bit RISC embedded processor, complemented by clock circuits, memory and application-related peripheral circuits.
  • the dual CPUs transmit information and data through the high-speed serial bus and FIFO to realize point-to-point parallel computing, avoiding the redundant links brought by the shared global memory and parallel bus expansion design, and improving reliability.
  • the invention comprehensively considers the communication bus type of the platform load integrated satellite electronic system and the measurement and control response Inter-machine communication mode, two communication board functions for mutual backup include CAN bus communication, 1553B bus communication, RS422 bus communication, and remote telemetry synchronous communication.
  • the communication board adopts an anti-fuse type (or FLASH type) FPGA with high reliability for integrated design, which can effectively reduce the circuit scale of the hardware system and fully cover the external communication requirements of the small satellite integrated computer.
  • Specific resources include:
  • One-six-way CAN bus communication two-way integrated CAN and other units on the star, two-way control CAN and attitude control components interconnection, two-way expansion CAN and expansion unit interconnection;
  • two-way RS422 bus adopts standard asynchronous serial port design, realizes serial data communication according to UART protocol, and the size of sending and receiving buffer is adjustable.
  • the standardized function expansion unit described in this embodiment is used for extending the peripheral function requirements of each model satellite.
  • Standardized design method can be used to flexibly increase or decrease the number of modules according to the specific requirements of each type of task, to achieve rapid integration of integrated computers, integrated design and modular design to meet high-performance small satellite electronics module replacement and system upgrade. , functional expansion and other requirements, reduce research and development costs and shorten the development cycle.
  • the standardized function expansion unit and the integrated integrated control unit are interconnected by extending the CAN bus.
  • the standardized function expansion unit described in this embodiment is composed of an instruction output module 6, an active thermal control module 7, a mechanism control module 8, and an extended power supply module 9, etc., in combination with FIG. 3 and FIG. 4, each function expansion board adopts a single chip microcomputer ( When the PCB layout size is limited and the function density of the board needs to be increased, the CAN bus can be used to construct the CAN bus intelligent node for the core controller, and the integrated integrated control unit control command can be used to implement the interface function through the CAN bus.
  • the command control board 6 implements various OC (Open Collector) commands. Including ON/OFF command, camera control OC command, pyrotechnic control OC command and star arrow separation stroke switch OC signal acquisition.
  • the instructions executed by the OC output driver interface are sent by the integrated integrated control unit through the CAN bus, and the instructions are executed after being decoded by the core controller.
  • the OC receiving interface is latched by the latch to the OC input state, processed by the controller, and sent from the CAN bus to the integrated integrated control unit.
  • the active temperature control board 7 described in this embodiment is composed of a temperature acquisition module and a temperature control module. Temperature acquisition module obtains temperature through thermistor, analog switch, signal amplification and A/D conversion For the digital information, the core controller performs the whole-loop closed-loop temperature control according to the predetermined thermal control strategy and sends the active temperature-controlled telemetry parameters to the integrated integrated control unit through the CAN bus.
  • the predetermined thermal control strategy can be adjusted according to specific needs.
  • the mechanism control board 8 of the embodiment is responsible for completing the position control of the focusing and the biasing mechanism of the new optical camera, and the driving control required for the stepping motor is generated after the core controller completes the encoder signal acquisition and acquires the absolute position information of the mechanism. signal.
  • the focus parameter and the position parameter of the biasing mechanism are given by the integrated integrated control unit through the CAN bus.
  • the increase of the mechanism control board can be adapted to the driving requirements of multiple optical cameras integrated satellites for multiple sets of focusing mechanisms and multiple sets of biasing mechanisms. .
  • the present embodiment is a hardware structure of an integrated management system for a platform load integrated satellite according to the first embodiment, and the present embodiment comprehensively considers integrated control.
  • the composition and design features of the unit and the standardized function expansion unit strictly follow the top-down design concept of the top-down, and adopt the design concept of integration of the integrated and modular dual structure.
  • the drawbacks of the traditional aerospace computer chassis structure design can not meet the needs of different types of satellite function improvement and structural expansion.
  • An integrated computer structure form exploded view, combined with Figure 5.
  • the integrated integrated control unit in the embodiment adopts a plug-in type chassis, and the front and rear panels, the left and right side panels, and the upper and lower panels of the chassis are assembled.
  • Printed board rail slots are formed on the left and right side panels of the chassis, and the printed boards forming the integrated integrated control unit are pressed into the rail slots by the wedge locking mechanism, and electrically interconnected through the bottom plate.
  • the standardized function expansion unit in the embodiment adopts a frame type chassis, and each frame is connected as a whole machine by a through-rod screw, and the CAN bus is interconnected through the connectors, and each board realizes each external function through the upper electrical connector. interface.
  • the plug-in type chassis and the frame type chassis in this embodiment are both designed with a lug structure. Therefore, the integrated management system can be integrated with the single-unit installation or modular decentralization according to the configuration of each functional module and the layout characteristics of the entire star structure in combination with Figure 6, (a) and (b). Multi-machine, namely: single machine 1, single machine 2) installation form, which is convenient for platform load integrated satellite structure layout.

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Abstract

A comprehensive management system for a platform and payload integrated satellite, which relates to the technical field of aerospace, solves the problems of low resource utility rates and non-expandability in existing satellite electronics systems using distributed on-board computer design method, and comprises an integrated comprehensive control unit and a standardized function extension unit, the standardized comprehensive extension unit using an external CAN bus for interconnection with the integrated comprehensive control unit; the integrated comprehensive control unit is composed of a comprehensive management module, a communication interface module, a secondary power source and an arbitration logic control module, and the standardized function extension unit comprises an instruction control board, an active temperature control board and a mechanism control board. The management system in the present invention realizes: resource integration, i.e. reducing the number of standalone computers and components; instruction integration, i.e. reducing instruction types and forwarding links; telemetering integration, i.e. reducing redundant telemetering so as to improve bandwidth; function integration, i.e. reducing test links and test procedures; and performance integration, i.e. reducing the volume, weight and power consumption of a device.

Description

用于平台载荷一体化卫星的综合管理系统Integrated management system for platform load integrated satellites 技术领域Technical field
本发明涉及航天航空技术领域，具体涉及用于平台载荷一体化卫星的综合管理系统，可实现高性能小卫星平台与载荷电子系统的一体化高度集成，同时兼顾不同型号小卫星模块化和标准化功能扩展任务需求。The invention relates to the field of aerospace technology, in particular to an integrated management system for a platform load integrated satellite, which can realize integrated and high integration of a high performance small satellite platform and a load electronic system, and at the same time take into account the modularization and standardization functions of different types of small satellites. Expand task requirements.
背景技术Background technique
随着航天电子技术和计算机技术的不断进步，现代小卫星电子系统的集成度越来越高，这就要求卫星电子系统需具备更高的处理速度和更多的功能。而传统卫星电子系统均采用以功能为中心的分布式设计方法，即将各种功能分配给组成卫星电子系统的星务管理计算机、姿态控制计算机、有效载荷计算机等各个分系统的星载计算机去完成。这种设计方法无法将载荷和平台的电子系统做统筹规划与功能整合，资源利用率低，在实际工程中往往造成星载计算机数量庞大并数倍增加了电子系统的体积、重量与功耗；同时各星载计算机为按需定制，不具备可扩展性，难以满足不同型号任务需求，可重用率低、研制周期长、研发成本高。本发明针对此提出了一种用于平台载荷一体化卫星的综合计算机以满足未来高性能、高集成度的小卫星应用要求。With the continuous advancement of aerospace electronic technology and computer technology, the integration of modern small satellite electronic systems is getting higher and higher, which requires satellite electronic systems to have higher processing speed and more functions. The traditional satellite electronic system adopts a function-centered distributed design method, which assigns various functions to the on-board computer of the satellite management computer, attitude control computer, payload computer and other sub-systems that make up the satellite electronic system. . This design method cannot integrate the electronic system of the load and the platform into overall planning and function, and the resource utilization rate is low. In actual engineering, the number of on-board computers is often huge and the volume, weight and power consumption of the electronic system are increased several times; At the same time, each onboard computer is customized on demand, does not have scalability, and is difficult to meet the needs of different types of tasks. It has low reusability, long development cycle and high R&D cost. The present invention is directed to an integrated computer for a platform load integrated satellite to meet future high performance, high integration small satellite application requirements.
发明内容Summary of the invention
本发明为了解决现有卫星电子学系统采用分布式星载计算机设计方法存在的资源利用率低和不具备可扩展性等问题，提供一种用于平台载荷一体化卫星的综合管理系统，The invention provides an integrated management system for platform load integrated satellites, in order to solve the problems of low resource utilization and non-scalability of the existing satellite electronic system using the distributed on-board computer design method.
用于平台载荷一体化卫星的综合管理系统，包括集成化综合控制单元和标准化功能扩展单元，标准化综合扩展单元采用外部CAN总线与集成化综合控制单元实现互联；An integrated management system for integrated platform load satellites, including an integrated integrated control unit and a standardized function expansion unit. The standardized integrated expansion unit uses an external CAN bus to interconnect with an integrated integrated control unit;
所述集成化综合控制单元由综合管理模块、通信接口模块、二次电源及仲裁逻辑控制模块组成，The integrated integrated control unit is composed of an integrated management module, a communication interface module, a secondary power supply, and an arbitration logic control module.
综合管理模块负责整星计算任务及调度任务，并向通信接口模块发磅控制指令，同时接收通过通信接口模块传送的外部信息数据；The integrated management module is responsible for the whole star computing task and the scheduling task, and sends a pound control instruction to the communication interface module, and receives external information data transmitted through the communication interface module;
通信接口模块根据综合管理模块发送的控制指令与外部接口进行信息交 互，以及向综合管理模块传送外部信息数据；The communication interface module performs information exchange with the external interface according to the control command sent by the integrated management module. Mutual and transfer of external information data to the integrated management module;
二次电源及仲裁逻辑控制模块用于为集成化综合控制单元提供二次电源并负责为综合管理模块提供仲裁控制；The secondary power supply and arbitration logic control module is used to provide secondary power to the integrated integrated control unit and is responsible for providing arbitration control for the integrated management module;
标准化功能扩展单元包括指令控制板、主动控温板和机构控制板；The standardized function expansion unit includes an instruction control board, an active temperature control board, and a mechanism control board;
指令控制板实现各种OC指令；包括ON/OFF指令、相机控制OC指令、火工品控制OC指令和星箭分离行程开关OC信号采集；The instruction control board implements various OC commands; including ON/OFF command, camera control OC command, pyrotechnic control OC command, and star arrow separation stroke switch OC signal acquisition;
主动控温板由温度采集模块和温度控制模块组成，温度采集模块通过热敏电阻、模拟开关、信号放大和A/D转换后获得温度值数字量信息，温度控制模块根据所述的温度值数字量信息依照预定热控策略进行整星闭环控温；The active temperature control board is composed of a temperature acquisition module and a temperature control module. The temperature acquisition module obtains temperature value digital information through the thermistor, the analog switch, the signal amplification and the A/D conversion, and the temperature control module according to the temperature value. The quantity information is subjected to a full-scale closed-loop temperature control according to a predetermined thermal control strategy;
机构控制板根据采集的编码器信息驱动步进电机实现相机调焦及调偏流机构的位置控制；The mechanism control board drives the stepping motor according to the collected encoder information to realize the position control of the camera focusing and the biasing mechanism;
本发明的有益效果：本发明针对平台载荷一体化卫星电子系统在拓扑结构设计上改变了传统的设计方法，不是以功能为中心，将各种功能分配给各个分系统的星载计算机去完成，而是超越各分系统间界限，采用资源共享思想，将平台载荷一体化卫星电子系统作为一个整体进行考虑，设计出一种用于平台载荷一体化卫星的综合管理系统，利用高度集成式综合计算机实现平台载荷一体化卫星的电子学管理。Advantageous Effects of the Invention: The present invention changes the traditional design method for the topology design of the platform load integrated satellite electronic system, and does not focus on functions, and assigns various functions to the onboard computer of each subsystem to complete. Rather, it transcends the boundaries between the sub-systems, adopts the idea of resource sharing, considers the platform load integrated satellite electronic system as a whole, and designs an integrated management system for platform-load integrated satellites, using a highly integrated integrated computer. Realize the electronic management of platform load integrated satellites.
具体优点体现为：一、采用高性能处理器实现平台与载荷的综合控制管理；二、基于内外两种总线实现设备的一体化集成及模块化扩展；三、利用双机热备份处理器实现在轨数据并行计算与处理。本发明所述的管理系统实现资源整合，减少单机以及元器件数量，指令整合，减少指令类型及转发环节，遥测整合，减少冗余遥测以提高带宽，功能整合，减少测试环节和测试流程，性能整合，降低设备体积重量及功耗。The specific advantages are as follows: 1. The high-performance processor is used to realize the integrated control and management of the platform and the load; 2. The integrated integration and modular expansion of the device based on the internal and external buses; 3. The dual-machine hot backup processor is implemented in Parallel data parallel computing and processing. The management system of the invention realizes resource integration, reduces the number of single machines and components, integrates instructions, reduces instruction types and forwarding links, integrates telemetry, reduces redundant telemetry to increase bandwidth, integrates functions, reduces testing links and testing processes, and performs performance. Integration reduces device volume and power consumption.
附图说明DRAWINGS
图1为本发明所述的用于平台载荷一体化卫星的综合管理系统中集成化综合控制单元架构框图；1 is a block diagram of an integrated integrated control unit architecture in an integrated management system for a platform load integrated satellite according to the present invention;
图2为本发明所述的用于平台载荷一体化卫星的综合管理系统中的双CPU并行联合计算硬件框图；2 is a hardware block diagram of a parallel computing of dual CPUs in an integrated management system for a platform load integrated satellite according to the present invention;
图3为本发明所述的用于平台载荷一体化卫星的综合管理系统中标准化功 能扩展单元架构框图；3 is a standardization work in an integrated management system for a platform load integrated satellite according to the present invention; Can expand the block diagram of the unit structure;
图4为本发明所述的用于平台载荷一体化卫星的综合管理系统中扩展单元板卡标准化设计框图；4 is a block diagram of a standardized design of an extension unit board in an integrated management system for a platform load integrated satellite according to the present invention;
图5为本发明所述的用于平台载荷一体化卫星的综合管理系统的硬件结构形式分解图；5 is an exploded view showing the hardware structure of an integrated management system for a platform load integrated satellite according to the present invention;
图6中(a)和(b)为本发明所述的用于平台载荷一体化卫星的综合管理系统中综合计算机集成式和分散式布局示意图。Fig. 6 (a) and (b) are schematic diagrams showing an integrated computer integrated and distributed layout in an integrated management system for a platform load integrated satellite according to the present invention.
具体实施方式detailed description
具体实施方式一、结合图1至图4说明本实施方式，用于平台载荷一体化卫星的综合管理系统，由集成化综合控制单元和标准化功能扩展单元组成。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS First, the present embodiment is described with reference to FIG. 1 to FIG. 4, and an integrated management system for a platform load integrated satellite is composed of an integrated integrated control unit and a standardized function expansion unit.
将星上必备最小功能进行一体化设计融合形成集成化综合控制单元；负责整星自主任务管理和信息集中管理，同时完成控制及成像相关算法的解算。所述集成化综合控制单元由综合管理模块、通信接口模块、二次电源及仲裁逻辑控制模块组成，用于构成卫星综合管理的核心计算及处理单元；The integrated minimum function of the star is integrated into an integrated integrated control unit; it is responsible for the autonomous task management and centralized information management of the whole star, and completes the calculation of the control and imaging related algorithms. The integrated integrated control unit is composed of an integrated management module, a communication interface module, a secondary power supply and an arbitration logic control module, and is used for forming a core calculation and processing unit of the integrated satellite management;
综合管理模块负责整星计算任务及调度任务，并向通信接口模块发磅控制指令，同时接收通过通信接口模块传送的外部信息数据；The integrated management module is responsible for the whole star computing task and the scheduling task, and sends a pound control instruction to the communication interface module, and receives external information data transmitted through the communication interface module;
通信接口模块根据综合管理模块发送的控制指令与外部接口进行信息交互，以及向综合管理模块传送外部信息数据；The communication interface module performs information interaction with the external interface according to the control instruction sent by the integrated management module, and transmits the external information data to the integrated management module;
二次电源及仲裁逻辑控制模块用于为集成化综合控制单元提供二次电源并负责为综合管理模块提供仲裁控制；The secondary power supply and arbitration logic control module is used to provide secondary power to the integrated integrated control unit and is responsible for providing arbitration control for the integrated management module;
结合图1和图2说明本实施方式，所述的综合管理模块采用高性能双处理器热备份设计，由CPUA板1、CPUB板2、通信A板3、通信B板4、电源及仲裁板5以及底板构成。综合考虑计算性能及可靠性，互为备份的CPUA和CPUB板采用高性能国产或进口SPARC V8体系结构的32位RISC嵌入式处理器，辅以时钟电路、存储器及与应用相关的外围电路构成完整的计算机系统。双CPU之间通过高速串行总线及FIFO进行信息、数据的传递，实现点对点双机并行计算，避免采用共享全局存储器及并行总线扩展设计所带来的冗余环节，提高可靠性。The embodiment is described with reference to FIG. 1 and FIG. 2, and the integrated management module adopts a high-performance dual-processor hot backup design, which is composed of a CPUA board 1, a CPUB board 2, a communication board A, a communication board B, a power supply, and an arbitration board. 5 and the bottom plate. Considering the computational performance and reliability, the CPUA and CPUB boards that are backed up each other use a high-performance domestic or imported SPARC V8 architecture 32-bit RISC embedded processor, complemented by clock circuits, memory and application-related peripheral circuits. Computer system. The dual CPUs transmit information and data through the high-speed serial bus and FIFO to realize point-to-point parallel computing, avoiding the redundant links brought by the shared global memory and parallel bus expansion design, and improving reliability.
本发明综合考虑平台载荷一体化卫星电子系统通信总线类型及与测控应答 机间通信方式，互为备份的两个通信板功能包括CAN总线通信、1553B总线通信、RS422总线通信以及遥控遥测同步通信。该通信板采用具有高可靠性的反熔丝型(或FLASH型)FPGA进行集成化设计，可有效缩小了硬件系统的电路规模并充分涵盖小卫星综合计算机对外通信需求。具体资源包括：The invention comprehensively considers the communication bus type of the platform load integrated satellite electronic system and the measurement and control response Inter-machine communication mode, two communication board functions for mutual backup include CAN bus communication, 1553B bus communication, RS422 bus communication, and remote telemetry synchronous communication. The communication board adopts an anti-fuse type (or FLASH type) FPGA with high reliability for integrated design, which can effectively reduce the circuit scale of the hardware system and fully cover the external communication requirements of the small satellite integrated computer. Specific resources include:
一、六路CAN总线通信：两路综合CAN与星上其它单元互联、两路控制CAN与姿控部件互联、两路扩展CAN与扩展单元互联；One-six-way CAN bus communication: two-way integrated CAN and other units on the star, two-way control CAN and attitude control components interconnection, two-way expansion CAN and expansion unit interconnection;
二、四路遥测遥控同步通信：采用门控、数据和时钟组成的三线制设计方式，两路遥控上行，两路遥测下行，码型分别为NRZ-L和NRZ-M；Second, four-way telemetry remote control synchronous communication: three-wire system design consisting of gate control, data and clock, two-way remote control uplink, two-way remote measurement downlink, the code types are NRZ-L and NRZ-M respectively;
三、两路RS422总线：采用标准异步串口设计，根据UART协议实现串行数据通信，发送及接收缓冲区大小可调。Third, two-way RS422 bus: adopts standard asynchronous serial port design, realizes serial data communication according to UART protocol, and the size of sending and receiving buffer is adjustable.
本实施方式所述的标准化功能扩展单元用于各型号卫星外围功能需求扩展。采用标准化设计方式，可依照各型号任务的具体要求灵活增减模块数量配置，实现综合计算机的快速集成，一体化设计的同时兼顾模块化设计，以满足高性能小卫星电子学模块更换、系统升级、功能扩展等需求，降低研发成本和缩短研制周期。标准化功能扩展单元与集成化综合控制单元通过扩展CAN总线进行互联。The standardized function expansion unit described in this embodiment is used for extending the peripheral function requirements of each model satellite. Standardized design method can be used to flexibly increase or decrease the number of modules according to the specific requirements of each type of task, to achieve rapid integration of integrated computers, integrated design and modular design to meet high-performance small satellite electronics module replacement and system upgrade. , functional expansion and other requirements, reduce research and development costs and shorten the development cycle. The standardized function expansion unit and the integrated integrated control unit are interconnected by extending the CAN bus.
本实施方式所述的标准化功能扩展单元由指令输出模块6、主动热控模块7、机构控制模块8和扩展电源模块9等组成，结合图3和图4，各功能扩展板卡均采用单片机(当PCB布局尺寸受限，需提高单板功能密度时，可采用FPGA)为核心控制器构建CAN总线智能节点，通过CAN总线接收集成化综合控制单元控制指令实现接口功能。The standardized function expansion unit described in this embodiment is composed of an instruction output module 6, an active thermal control module 7, a mechanism control module 8, and an extended power supply module 9, etc., in combination with FIG. 3 and FIG. 4, each function expansion board adopts a single chip microcomputer ( When the PCB layout size is limited and the function density of the board needs to be increased, the CAN bus can be used to construct the CAN bus intelligent node for the core controller, and the integrated integrated control unit control command can be used to implement the interface function through the CAN bus.
本实施方式所述的指令控制板6实现各种OC(Open Collector，集电极开路)指令。包括ON/OFF指令、相机控制OC指令、火工品控制OC指令和星箭分离行程开关OC信号采集。OC输出驱动接口执行的指令由集成化综合控制单元通过CAN总线发送而来，指令经核心控制器译码处理后执行。OC接收接口由锁存器将OC输入状态锁存后经控制器处理后自CAN总线发送给集成化综合控制单元。The command control board 6 according to the present embodiment implements various OC (Open Collector) commands. Including ON/OFF command, camera control OC command, pyrotechnic control OC command and star arrow separation stroke switch OC signal acquisition. The instructions executed by the OC output driver interface are sent by the integrated integrated control unit through the CAN bus, and the instructions are executed after being decoded by the core controller. The OC receiving interface is latched by the latch to the OC input state, processed by the controller, and sent from the CAN bus to the integrated integrated control unit.
本实施方式所述的主动控温板7由温度采集模块和温度控制模块两部分组成。温度采集模块通过热敏电阻、模拟开关、信号放大和A/D转换后得到温度 值数字量信息，再由核心控制器依照预定热控策略进行整星闭环控温并通过CAN总线向集成化综合控制单元发送主动控温遥测参数。所述的预定热控策略可以根据具体需要调整。The active temperature control board 7 described in this embodiment is composed of a temperature acquisition module and a temperature control module. Temperature acquisition module obtains temperature through thermistor, analog switch, signal amplification and A/D conversion For the digital information, the core controller performs the whole-loop closed-loop temperature control according to the predetermined thermal control strategy and sends the active temperature-controlled telemetry parameters to the integrated integrated control unit through the CAN bus. The predetermined thermal control strategy can be adjusted according to specific needs.
本实施方式所述的机构控制板8负责完成新型光学相机调焦及调偏流机构的位置控制，由核心控制器完成编码器信号采集并获取机构绝对位置信息后产生步进电机所需的驱动控制信号。调焦参量及偏流机构位置参量由集成化综合控制单元通过CAN总线给出，此外可通过机构控制板的增加适应多种光学相机集成式卫星对多套调焦机构以及多套偏流机构的驱动需求。The mechanism control board 8 of the embodiment is responsible for completing the position control of the focusing and the biasing mechanism of the new optical camera, and the driving control required for the stepping motor is generated after the core controller completes the encoder signal acquisition and acquires the absolute position information of the mechanism. signal. The focus parameter and the position parameter of the biasing mechanism are given by the integrated integrated control unit through the CAN bus. In addition, the increase of the mechanism control board can be adapted to the driving requirements of multiple optical cameras integrated satellites for multiple sets of focusing mechanisms and multiple sets of biasing mechanisms. .
具体实施方式二、结合图5和图6说明本实施方式，本实施方式为具体实施方式一所述的用于平台载荷一体化卫星的综合管理系统的硬件结构，本实施方式综合考虑集成化控制单元和标准化功能扩展单元的组成及设计特点，严格遵循自上而下的顶层设计思路，采用一体化和模块化双结构形式融合的设计理念。完全避免了传统航天计算机机箱结构设计无法满足不同型号卫星功能改进与结构扩充需求的弊端。综合计算机结构形式分解图，结合图5。2, the present embodiment is described with reference to FIG. 5 and FIG. 6. The present embodiment is a hardware structure of an integrated management system for a platform load integrated satellite according to the first embodiment, and the present embodiment comprehensively considers integrated control. The composition and design features of the unit and the standardized function expansion unit strictly follow the top-down design concept of the top-down, and adopt the design concept of integration of the integrated and modular dual structure. The drawbacks of the traditional aerospace computer chassis structure design can not meet the needs of different types of satellite function improvement and structural expansion. An integrated computer structure form exploded view, combined with Figure 5.
本实施方式中的集成化综合控制单元采用插板式机箱，机箱前后面板、左右侧板及上下盖板拼装组成。机箱左右侧板上加工有印制板导轨槽，组成集成化综合控制单元的各印制板通过楔形锁紧机构压紧在导轨槽内，并通过底板实现电气互联。The integrated integrated control unit in the embodiment adopts a plug-in type chassis, and the front and rear panels, the left and right side panels, and the upper and lower panels of the chassis are assembled. Printed board rail slots are formed on the left and right side panels of the chassis, and the printed boards forming the integrated integrated control unit are pressed into the rail slots by the wedge locking mechanism, and electrically interconnected through the bottom plate.
本实施方式中的标准化功能扩展单元采用框架式机箱，各框架通过穿杆螺钉相连为一个整机，板间通过接插件实现CAN总线互联，各板并通过其上部的电连接器实现各外部功能接口。The standardized function expansion unit in the embodiment adopts a frame type chassis, and each frame is connected as a whole machine by a through-rod screw, and the CAN bus is interconnected through the connectors, and each board realizes each external function through the upper electrical connector. interface.
本实施方式中的插板式机箱和框架式机箱均设计有凸耳结构。因此，综合管理系统装星时可依照各功能模块配置情况和整星结构布局特点，结合图6，(a)和(b)，采取一体化集成式(单机)安装形式或模块化分散式(多机，即：单机1、单机2)安装形式，便于平台载荷一体化卫星结构布局。 The plug-in type chassis and the frame type chassis in this embodiment are both designed with a lug structure. Therefore, the integrated management system can be integrated with the single-unit installation or modular decentralization according to the configuration of each functional module and the layout characteristics of the entire star structure in combination with Figure 6, (a) and (b). Multi-machine, namely: single machine 1, single machine 2) installation form, which is convenient for platform load integrated satellite structure layout.

Claims (10)

  1. 用于平台载荷一体化卫星的综合管理系统，其特征是，包括集成化综合控制单元和标准化功能扩展单元，标准化综合扩展单元采用外部CAN总线与集成化综合控制单元实现互联；The integrated management system for platform load integrated satellites is characterized in that it comprises an integrated integrated control unit and a standardized function expansion unit, and the standardized integrated expansion unit is interconnected by an external CAN bus and an integrated integrated control unit;
    所述集成化综合控制单元由综合管理模块、通信接口模块、二次电源及仲裁逻辑控制模块组成，The integrated integrated control unit is composed of an integrated management module, a communication interface module, a secondary power supply, and an arbitration logic control module.
    综合管理模块负责整星计算任务及调度任务，并向通信接口模块发磅控制指令，同时接收通过通信接口模块传送的外部信息数据；The integrated management module is responsible for the whole star computing task and the scheduling task, and sends a pound control instruction to the communication interface module, and receives external information data transmitted through the communication interface module;
    通信接口模块根据综合管理模块发送的控制指令与外部接口进行信息交互，以及向综合管理模块传送外部信息数据；The communication interface module performs information interaction with the external interface according to the control instruction sent by the integrated management module, and transmits the external information data to the integrated management module;
    二次电源及仲裁逻辑控制模块用于为集成化综合控制单元提供二次电源并负责为综合管理模块提供仲裁控制；The secondary power supply and arbitration logic control module is used to provide secondary power to the integrated integrated control unit and is responsible for providing arbitration control for the integrated management module;
    标准化功能扩展单元包括指令控制板(6)、主动控温板(7)和机构控制板(8)；The standardized function expansion unit comprises an instruction control board (6), an active temperature control board (7) and a mechanism control board (8);
    指令控制板(6)实现各种OC指令；包括ON/OFF指令、相机控制OC指令、火工品控制OC指令和星箭分离行程开关OC信号采集；The instruction control board (6) implements various OC commands; including ON/OFF command, camera control OC command, pyrotechnic control OC command, and star arrow separation stroke switch OC signal acquisition;
    主动控温板(7)由温度采集模块和温度控制模块组成，温度采集模块通过热敏电阻、模拟开关、信号放大和A/D转换后获得温度值数字量信息，温度控制模块根据所述的温度值数字量信息依照预定热控策略进行整星闭环控温；The active temperature control board (7) is composed of a temperature acquisition module and a temperature control module. The temperature acquisition module obtains temperature value digital information through the thermistor, the analog switch, the signal amplification and the A/D conversion, and the temperature control module according to the The temperature value digital quantity information is subjected to a full-scale closed-loop temperature control according to a predetermined thermal control strategy;
    机构控制板(8)根据采集的编码器信息驱动步进电机实现相机调焦及调偏流机构的位置控制。The mechanism control board (8) drives the stepping motor according to the collected encoder information to realize the position control of the camera focusing and the biasing mechanism.
  2. 根据权利要求1所述的用于平台载荷一体化卫星的综合管理系统，其特征在于，所述综合管理模块由互为备份的CPUA板(1)和CPUB板(2)组成，通信接口模块由互为备份的通信A板(3)和通信B板(4)组成，二次电源及仲裁逻辑控制模块(5)由电源及仲裁板组成。The integrated management system for a platform load integrated satellite according to claim 1, wherein the integrated management module is composed of a CPUA board (1) and a CPUB board (2) that are mutually backed up, and the communication interface module is composed of The communication A board (3) and the communication B board (4) which are mutually backups are composed, and the secondary power supply and arbitration logic control module (5) is composed of a power supply and an arbitration board.
  3. 根据权利要求2所述的用于平台载荷一体化卫星的综合管理系统，其特征在于，互为备份的CPUA板(1)和CPUB板(2)之间通过高速串行总线FIFO进行信息传递，实现点对点双机并行计算。The integrated management system for platform load integrated satellite according to claim 2, characterized in that information is transmitted between the CPUA board (1) and the CPUB board (2) which are mutually backups through a high-speed serial bus FIFO. Achieve peer-to-peer parallel computing.
  4. 根据权利要求2所述的用于平台载荷一体化卫星的综合管理系统，其特征在于，所述互为备份的通信A板(3)和通信B板(4)之间通过CAN总线 通信、1553B总线通信、RS422总线通信以及遥控遥测同步通信。The integrated management system for platform load integrated satellite according to claim 2, wherein the communication A board (3) and the communication B board (4) which are mutually backups pass through the CAN bus. Communication, 1553B bus communication, RS422 bus communication, and remote telemetry synchronous communication.
  5. 根据权利要求2或4所述的用于平台载荷一体化卫星的综合管理系统，其特征在于，所述的通信A板(3)和通信B板(4)采用高可靠性的反熔丝型FPGA进行集成化设计。The integrated management system for platform load integrated satellite according to claim 2 or 4, characterized in that said communication A board (3) and communication board B (4) are of high reliability anti-fuse type. The FPGA is integrated.
  6. 根据权利要求1所述的用于平台载荷一体化卫星的综合管理系统，其特征在于，所述标准化功能扩展单元的指令控制板(6)、主动控温板(7)和机构控制板(8)均采用单片机为核心控制器构建CAN总线智能节点，通过CAN总线接收集成化综合控制单元控制指令，实现接口功能。The integrated management system for platform load integrated satellite according to claim 1, wherein the instruction control board (6), the active temperature control board (7) and the mechanism control board of the standardized function expansion unit (8) The single-chip microcomputer is used as the core controller to construct the CAN bus intelligent node, and the integrated control unit control command is received through the CAN bus to realize the interface function.
  7. 根据权利要求1所述的用于平台载荷一体化卫星的综合管理系统，其特征在于，所述集成化综合控制单元采用插板式机箱，标准化功能扩展单元采用框架式机箱。The integrated management system for a platform load integrated satellite according to claim 1, wherein the integrated integrated control unit adopts a plug-in chassis, and the standardized function expansion unit adopts a frame type chassis.
  8. 根据权利要求7所述的用于平台载荷一体化卫星的综合管理系统，其特征在于，所述插板式机箱和框架式机箱均设计有凸耳结构。The integrated management system for a platform load integrated satellite according to claim 7, wherein the plug-in chassis and the frame chassis are both designed with a lug structure.
  9. 根据权利要求8所述的用于平台载荷一体化卫星的综合管理系统，其特征在于，所述插板式机箱由前后面板、左右侧板及上下盖板拼装组成，所述左右侧板上加工印制板导轨槽，各印制板通过楔形锁紧机构压紧在导轨槽内，并通过底板实现电气互联。The integrated management system for a platform load integrated satellite according to claim 8, wherein the plug-in type chassis is composed of front and rear panels, left and right side panels, and upper and lower panels, and the left and right side panels are processed and printed. The plate guide groove, each printed board is pressed into the guide groove by a wedge locking mechanism, and is electrically connected through the bottom plate.
  10. 根据权利要求8所述的用于平台载荷一体化卫星的综合管理系统，其特征在于，所述框架式机箱由多个框架组成，每个框架通过穿杆螺钉连接为一个整机，机箱板间通过接插件实现CAN总线互联。 The integrated management system for a platform load integrated satellite according to claim 8, wherein the frame type chassis is composed of a plurality of frames, and each frame is connected to a whole machine by a through-bolt screw, and the chassis plate is arranged. CAN bus interconnection is realized by connectors.
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