制导飞行器控制系统硬件设计
发布时间：2018-08-26 07:52
【摘要】：制导飞行控制系统是飞行器系统的核心和关键部分,其性能在很大程度上决定着飞行器的飞行性能和飞行品质,特别是制导精度。本文主要研究了新型全数字靶弹电动舵机伺服控制系统的硬件设计问题,该系统采用了高性能数字信号处理器(DSP)和脉宽调制技术控制四台无刷直流电机(BLDCM)工作。论文首先在分析了靶弹控制系统工作原理的基础上,对姿态控制系统的功能和构架进行详细的分析和探讨,同时按照系统的性能需求对系统所需的元器件进行选型,重点研究了靶弹控制系统的控制技术和PID控制策略,最后给出了DSP控制四个相互独立工作的舵机位置伺服控制系统的总体设计方案。论文的主要任务为制导控制系统设计一套与软件配套的硬件电路。详细设计了基于DSP的最小系统和外部辅助电路、供电电源电路、舵机伺服驱动电路、舵面实时偏转位置检测及AD采样调理电路、电池电压检测电路、舵面零点位置检测电路等。最后根据系统的性能需求和实际调试结果对电路进行一些抗干扰处理。后两章主要对制导控制做一些仿真和分析实验,主要是硬件模块的测试和软硬件联调。接着通过三个地面半实物综合仿真实验对系统进行软硬件的联调,其中包括三轴转角平台实验、偏航距离测试实验和舵机程控实验。最后针对仿真过程中发现的问题和错误及时进行优化和处理。通过对仿真测试过程中获取的实际数据进行分析和验证,证明了本系统的硬件设计能配合软件稳定可靠的工作,同时满足了预期的各项性能指标。
[Abstract]:The guidance flight control system is the core and key part of the aircraft system. Its performance largely determines the flight performance and flight quality of the aircraft, especially the guidance accuracy. In this paper, the hardware design of the servo control system for a new type of all-digital target projectile electric steering gear is studied. The system adopts the high performance digital signal processor (DSP) and the pulse width modulation (PWM) technology to control the operation of four brushless DC motors (BLDCM). Firstly, on the basis of analyzing the working principle of the target missile control system, the function and framework of the attitude control system are analyzed and discussed in detail. At the same time, according to the performance requirements of the system, the components required for the system are selected. The control technology and PID control strategy of the target missile control system are studied emphatically. Finally, the overall design scheme of four independent servo control systems of steering gear controlled by DSP is presented. The main task of this paper is to design a set of hardware circuit matching with software for the guidance control system. The minimum system and external auxiliary circuit based on DSP, power supply circuit, servo drive circuit of steering gear, real-time deflection position detection of rudder surface and AD sampling and conditioning circuit, battery voltage detection circuit, rudder zero position detection circuit and so on are designed in detail. Finally, according to the performance of the system and the actual debugging results of the circuit for some anti-interference treatment. The last two chapters mainly do some simulation and analysis experiments on guidance control, mainly the test of hardware module and the combination of hardware and software. Then through three ground hardware-in-the-loop integrated simulation experiments, the software and hardware of the system are adjusted, including triaxial angle platform experiment, yaw distance test experiment and steering gear program control experiment. Finally, the problems and errors found in the simulation process are optimized and handled in time. Through the analysis and verification of the actual data obtained in the course of simulation test, it is proved that the hardware design of the system can cooperate with the stable and reliable work of the software, and at the same time meet the expected performance indexes.
【学位授予单位】：西安工业大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V249
本文编号：2204211
[Abstract]:The guidance flight control system is the core and key part of the aircraft system. Its performance largely determines the flight performance and flight quality of the aircraft, especially the guidance accuracy. In this paper, the hardware design of the servo control system for a new type of all-digital target projectile electric steering gear is studied. The system adopts the high performance digital signal processor (DSP) and the pulse width modulation (PWM) technology to control the operation of four brushless DC motors (BLDCM). Firstly, on the basis of analyzing the working principle of the target missile control system, the function and framework of the attitude control system are analyzed and discussed in detail. At the same time, according to the performance requirements of the system, the components required for the system are selected. The control technology and PID control strategy of the target missile control system are studied emphatically. Finally, the overall design scheme of four independent servo control systems of steering gear controlled by DSP is presented. The main task of this paper is to design a set of hardware circuit matching with software for the guidance control system. The minimum system and external auxiliary circuit based on DSP, power supply circuit, servo drive circuit of steering gear, real-time deflection position detection of rudder surface and AD sampling and conditioning circuit, battery voltage detection circuit, rudder zero position detection circuit and so on are designed in detail. Finally, according to the performance of the system and the actual debugging results of the circuit for some anti-interference treatment. The last two chapters mainly do some simulation and analysis experiments on guidance control, mainly the test of hardware module and the combination of hardware and software. Then through three ground hardware-in-the-loop integrated simulation experiments, the software and hardware of the system are adjusted, including triaxial angle platform experiment, yaw distance test experiment and steering gear program control experiment. Finally, the problems and errors found in the simulation process are optimized and handled in time. Through the analysis and verification of the actual data obtained in the course of simulation test, it is proved that the hardware design of the system can cooperate with the stable and reliable work of the software, and at the same time meet the expected performance indexes.
【学位授予单位】：西安工业大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V249
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，本文编号：2204211
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