GPS接收机基带信号处理模块的FPGA实现

论述在GPS接收机三个功能模块中基带信号处理模块的具体作用。利用FPGA技术的先进性和软件无线电技术的灵活性开发出具有自主知识产权的功能模块。介绍其设计实现,着重于伪码生成器和NCO的实现,同时给出相关的仿真结果。     

线性不确定系统输出反馈滑模控制器设计

针对线性不确定系统出现的稳定不变零点和模型匹配不确定性 ,首先给出了满足Kimura Davison条件[3] 的滑动超平面和输出反馈滑模控制器[4 ,5] 的设计 ,然后 ,详细讨论了当系统不满足Kimura Davison条件时 ,需要引入补偿器 ,并且给出了补偿器、滑动超平面和控制器的设计方法。经过仿真 ,证明此方法能有效的抑制系统的模型匹配不确定性 ,并且能克服稳定不变零点给系统带来的不良影响     

大挠性多体卫星的自抗扰姿态控制系统设计

研究了最近提出的非线性自抗扰控制器 (ADRC)在大挠性多体卫星姿态控制中的应用问题。提出了一种双闭环自抗扰姿态控制器 (ADRAC) ,并从鲁棒性、干扰抑制、动静态性能指标和振动抑制等方面与使用于某挠性卫星的传统PID控制器进行了比较。在考虑了反作用轮和敏感器的实际非线性和敏感器噪声的影响情况下进行了仿真 ,结果表明 ,双闭环自抗扰姿态控制器各方面性能均优于传统的PID。本文提出的自抗扰姿态控制器 ,对实现挠性多体卫星的高精度高稳定度姿态控制 ,具有实际的应用价值     

一种基于权值存储的自适应旁瓣干扰对消系统

为了解决传统雷达旁瓣干扰对消系统在强近地杂波接收时对消器收敛环无法正常工作的问题,提出了一种基于收敛权值存储的自适应旁瓣干扰对消系统,并给出了详细的软硬件实现方法.整个系统以EP1K100为控制核心.实际设备装调的结果证明该系统能有效消除近地接收时强地杂波带来的影响.     

多路高速数据缓存器应用分析

文章将总线的概念引入数据处理器,提出一种星载高速数据传输总线。在一定的排队原则下,具体描述了总线控制器控制各个遥感数据分时复用总线的过程,从理论上分析了遥感数据进入总线前缓存的FIFO容量大小,并对FIFO容量进行了仿真,给出了总线与遥感器的接口信号及电路。     

深空接收机同步算法设计及实现

针对深空通信链路信号衰减大、传输时延长并存在大多普勒频移的特点,提出了一种基于CCSDS协议标准接收信号的同步算法,采用Costas反馈环进行载波同步,利用早迟门恢复定时时钟,通过相关性检测帧头解决相位模糊问题,最后对相位误差进行估计并补偿。在此基础上,设计并实现了适合于现场可编程门阵列(FPGA)定点运算特点的同步简化等效电路。基于Xilinx FPGA平台的实测结果表明,文章同步算法的硬件电路实现简单,在15dB信噪比的高斯白噪声情况下能较好地实现时间、频率的跟踪与锁定,可为未来深空接收机的优化设计提供有益参考。     

高超声速飞行器强鲁棒自适应控制器设计新方法

针对高超声速飞行器飞行过程系统参数大范围剧烈变化以及存在严重不确定性的特点,同时考虑外界环境干扰复杂,内部干扰严重的特殊问题,提出了一种新型强鲁棒自适应控制器构型。该新型强鲁棒自适应控制器将控制器分为标称控制器和补偿控制器。标称控制器可采用成熟的控制理论来设计,主要考虑闭环系统的性能;采用合适的手段估计系统参数大范围剧烈变化、系统的不确定性以及内、外部干扰等“系统扰动”作为补偿控制器的输入,通过设计强鲁棒补偿控制器对“系统扰动”进行补偿,使整个闭环控制系统对“系统扰动”具有强鲁棒性。将新型强鲁棒自适应控制器应用于高超声速飞行器的姿态控制系统的设计,大大提高了高超声速飞行器控制系统对内、外部干扰的抑制和对系统参数大范围剧烈变化以及严重不确定性的适应能力,可满足高超声速飞行器飞行控制的需求。     

Two-stage open-loop velocity compensating method applied to multi-mass elastic transmission system

In this paper, a novel vibration-suppression open-loop control method for multi-mass system is proposed, which uses two-stage velocity compensating algorithm and fuzzy I ＋ P control- ler. This compensating method is based on model-based control theory in order to provide a damp- ing effect on the system mechanical part. The mathematical model of multi-mass system is built and reduced to estimate the velocities of masses. The velocity difference between adjacent masses is cal- culated dynamically. A 3-mass system is regarded as the composition of two 2-mass systems in order to realize the two-stage compensating algorithm. Instead of using a typical PI controller in the velocity compensating loop, a fuzzy I ＋ P controller is designed and its input variables are decided according to their impact on the system, which is different from the conventional fuzzy PID controller designing rules. Simulations and experimental results show that the proposed veloc- ity compensating method is effective in suppressing vibration on a 3-mass system and it has a better performance when the designed fuzzy I ＋ P controller is utilized in the control system.     

Autonomous attitude coordinated control for spacecraft formation with input constraint,model uncertainties,and external disturbances

To synchronize the attitude of a spacecraft formation flying system, three novel autonomous control schemes are proposed to deal with the issue in this paper. The first one is an ideal autonomous attitude coordinated controller, which is applied to address the case with certain models and no disturbance. The second one is a robust adaptive attitude coordinated controller, which aims to tackle the case with external disturbances and model uncertainties. The last one is a filtered robust adaptive attitude coordinated controller, which is used to overcome the case with input con- straint, model uncertainties, and external disturbances. The above three controllers do not need any external tracking signal and only require angular velocity and relative orientation between a spacecraft and its neighbors. Besides, the relative information is represented in the body frame of each spacecraft. The controllers are proved to be able to result in asymptotical stability almost everywhere. Numerical simulation results show that the proposed three approaches are effective for attitude coordination in a spacecraft formation flying system.     

民用涡扇发动机多变量增广LQR控制器设计

针对民用涡扇发动机设计多变量控制器,提出将多变量增广LQR控制算法引入到民用涡扇发动机的方法。将发动机控制量作为增广的状态向量引入LQR算法设计,并根据控制系统回路的性能需求,设计期望动态响应曲线;期望动态响应与实际动态响应的差值范数作为优化目标用来调整、确定LQR控制算法的权阵取值;设计的控制器与民用涡扇发动机非线性模型仿真验证。结果表明,多变量增广LQR控制器满足民用涡扇发动机的控制需求。