论述了GPS(G loba l Pos ition ing System)卫星信号模拟器载波NCO(数控振荡器)和码NCO的系统结构及作用,根据多速率信号处理理论建立DDS(直接数字频率合成器)模型,分析其信号频谱;根据泰勒级数压缩算法分析了载波NCO s ine存储表压缩效...论述了GPS(G loba l Pos ition ing System)卫星信号模拟器载波NCO(数控振荡器)和码NCO的系统结构及作用,根据多速率信号处理理论建立DDS(直接数字频率合成器)模型,分析其信号频谱;根据泰勒级数压缩算法分析了载波NCO s ine存储表压缩效率,提出了模拟器码NCO参数更新实现方式.利用verilog在X ilinx'ISE 6.3中完成了载波NCO和码NCO的设计和仿真,并在FPGA中进行了实现.通过程序仿真与系统测试,证明本载波NCO和码NCO模块性能满足GPS卫星信号模拟器系统需求.展开更多
介绍如何利用CORDIC(Coordination Rotation Digital Computer)算法产生正余弦信号的实现过程基础上,研究并在FPGA中实现了基于流水线CORDIC算法的数控振荡器。仿真验证结果表明,该方法较之其它方法具有精度高、结构简单易于实现、节省...介绍如何利用CORDIC(Coordination Rotation Digital Computer)算法产生正余弦信号的实现过程基础上,研究并在FPGA中实现了基于流水线CORDIC算法的数控振荡器。仿真验证结果表明,该方法较之其它方法具有精度高、结构简单易于实现、节省资源且功耗低等特点,非常适合应用于高速高精度数字调制解调。展开更多
介绍一种利用矢量旋转的CORDIC(Coordination Rotation DIgital Computer)算法,相比较传统NCO采用的查找表算法,证明查找表算法运算速度已不适用于高速宽带数字接收机以及扩频通信的应用,为了实现高速正交数字混频器中的数控振荡器(NCO)...介绍一种利用矢量旋转的CORDIC(Coordination Rotation DIgital Computer)算法,相比较传统NCO采用的查找表算法,证明查找表算法运算速度已不适用于高速宽带数字接收机以及扩频通信的应用,为了实现高速正交数字混频器中的数控振荡器(NCO),采用CORDIC算法产生正余弦信号的实现过程,给出采用ALTERA的stratix系列FPGA中设计数控振荡器的顶层设计结构以及仿真结果,证明基于此算法采用FPGA的可行性设计。展开更多
Numerical simulation of unsteady flow control over an oscillating NACA0012 airfoil is investigated. Flow actuation of a turbulent flow over the airfoil is provided by low current DC surface glow discharge plasma actua...Numerical simulation of unsteady flow control over an oscillating NACA0012 airfoil is investigated. Flow actuation of a turbulent flow over the airfoil is provided by low current DC surface glow discharge plasma actuator which is analytically modeled as an ion pressure force produced in the cathode sheath region. The modeled plasma actuator has an induced pressure force of about 2 k Pa under a typical experiment condition and is placed on the airfoil surface at 0% chord length and/or at 10% chord length. The plasma actuator at deep-stall angles(from 5° to 25°) is able to slightly delay a dynamic stall and to weaken a pressure fluctuation in down-stroke motion. As a result, the wake region is reduced. The actuation effect varies with different plasma pulse frequencies, actuator locations and reduced frequencies. A lift coefficient can increase up to 70% by a selective operation of the plasma actuator with various plasma frequencies and locations as the angle of attack changes. Active flow control which is a key advantageous feature of the plasma actuator reveals that a dynamic stall phenomenon can be controlled by the surface plasma actuator with less power consumption if a careful control scheme of the plasma actuator is employed with the optimized plasma pulse frequency and actuator location corresponding to a dynamic change in reduced frequency.展开更多
文摘论述了GPS(G loba l Pos ition ing System)卫星信号模拟器载波NCO(数控振荡器)和码NCO的系统结构及作用,根据多速率信号处理理论建立DDS(直接数字频率合成器)模型,分析其信号频谱;根据泰勒级数压缩算法分析了载波NCO s ine存储表压缩效率,提出了模拟器码NCO参数更新实现方式.利用verilog在X ilinx'ISE 6.3中完成了载波NCO和码NCO的设计和仿真,并在FPGA中进行了实现.通过程序仿真与系统测试,证明本载波NCO和码NCO模块性能满足GPS卫星信号模拟器系统需求.
文摘介绍如何利用CORDIC(Coordination Rotation Digital Computer)算法产生正余弦信号的实现过程基础上,研究并在FPGA中实现了基于流水线CORDIC算法的数控振荡器。仿真验证结果表明,该方法较之其它方法具有精度高、结构简单易于实现、节省资源且功耗低等特点,非常适合应用于高速高精度数字调制解调。
文摘介绍一种利用矢量旋转的CORDIC(Coordination Rotation DIgital Computer)算法,相比较传统NCO采用的查找表算法,证明查找表算法运算速度已不适用于高速宽带数字接收机以及扩频通信的应用,为了实现高速正交数字混频器中的数控振荡器(NCO),采用CORDIC算法产生正余弦信号的实现过程,给出采用ALTERA的stratix系列FPGA中设计数控振荡器的顶层设计结构以及仿真结果,证明基于此算法采用FPGA的可行性设计。
基金supported by the Basic Science Research Program through the National Research Foundation of Korea (NRF) funded by the Ministry of Science, ICT & Future Planning (No. 2013R1A1A1012693)conducted at HighSpeed Vehicle Research Center of KAIST with the support of Defense Acquisition Program Administration (DAPA) and Agency for Defense Development (ADD)
文摘Numerical simulation of unsteady flow control over an oscillating NACA0012 airfoil is investigated. Flow actuation of a turbulent flow over the airfoil is provided by low current DC surface glow discharge plasma actuator which is analytically modeled as an ion pressure force produced in the cathode sheath region. The modeled plasma actuator has an induced pressure force of about 2 k Pa under a typical experiment condition and is placed on the airfoil surface at 0% chord length and/or at 10% chord length. The plasma actuator at deep-stall angles(from 5° to 25°) is able to slightly delay a dynamic stall and to weaken a pressure fluctuation in down-stroke motion. As a result, the wake region is reduced. The actuation effect varies with different plasma pulse frequencies, actuator locations and reduced frequencies. A lift coefficient can increase up to 70% by a selective operation of the plasma actuator with various plasma frequencies and locations as the angle of attack changes. Active flow control which is a key advantageous feature of the plasma actuator reveals that a dynamic stall phenomenon can be controlled by the surface plasma actuator with less power consumption if a careful control scheme of the plasma actuator is employed with the optimized plasma pulse frequency and actuator location corresponding to a dynamic change in reduced frequency.
