随着液体火箭发动机内部结构日益复杂,传统的控制遥测模式难以满足测控需求;针对液体火箭发动机的智能化需求,为实现高效的发动机状态管理和运行参数的实时监测,研制了一种基于现场可编程门阵列(FPGA)的控制监测系统;该系统拥有24路发...随着液体火箭发动机内部结构日益复杂,传统的控制遥测模式难以满足测控需求;针对液体火箭发动机的智能化需求,为实现高效的发动机状态管理和运行参数的实时监测,研制了一种基于现场可编程门阵列(FPGA)的控制监测系统;该系统拥有24路发动机驱动控制能力,具备32路信号同步采集、实时处理与存储能力,能够实现同步RS422总线通讯,并具有HDLC(High-Level Data Link Control)协议数据的编解码能力;实验结果表明,该系统能够对发动机阀门进行驱动控制及发动机状态参数的实时采集,实现基于HDLC协议的数据通讯;以硬件为核心的控制监测系统提高了发动机电器系统的集成性,提升了系统可靠性,为发动机健康管理、故障诊断算法的搭载奠定硬件基础。展开更多
Hydrogen and oxygen orbital maneuver thruster, based on gas-dynamic resonance ignition, is a new liquid rocket propulsion technology, and is especially applicable to space station. By means of theoretic thermodynamic ...Hydrogen and oxygen orbital maneuver thruster, based on gas-dynamic resonance ignition, is a new liquid rocket propulsion technology, and is especially applicable to space station. By means of theoretic thermodynamic calculation of the hydrogen and oxygen thruster, combined with the experimental exploration on the coaxial hydrogen and oxygen resonance ignition, a scheme of the thruster head configuration is designed as the combination of a coaxial hydrogen/oxygen resonance igniter and an oxygen augmentation injector. Through ignition tests on coaxial hydrogen/oxygen resonance igniter characterization, the thruster head ignition tests have been conducted successfully in sequence of resonance ignition and oxygen augmentation combustion. Finally, the thruster ground tests are successfully carried out in forms of single impulse, successive double impulses and 3.0 seconds continuous running, which verify the reliability and feasibility of the thruster. The response time of the thruster starting is restricted within 0.2 second.展开更多
文摘随着液体火箭发动机内部结构日益复杂,传统的控制遥测模式难以满足测控需求;针对液体火箭发动机的智能化需求,为实现高效的发动机状态管理和运行参数的实时监测,研制了一种基于现场可编程门阵列(FPGA)的控制监测系统;该系统拥有24路发动机驱动控制能力,具备32路信号同步采集、实时处理与存储能力,能够实现同步RS422总线通讯,并具有HDLC(High-Level Data Link Control)协议数据的编解码能力;实验结果表明,该系统能够对发动机阀门进行驱动控制及发动机状态参数的实时采集,实现基于HDLC协议的数据通讯;以硬件为核心的控制监测系统提高了发动机电器系统的集成性,提升了系统可靠性,为发动机健康管理、故障诊断算法的搭载奠定硬件基础。
文摘Hydrogen and oxygen orbital maneuver thruster, based on gas-dynamic resonance ignition, is a new liquid rocket propulsion technology, and is especially applicable to space station. By means of theoretic thermodynamic calculation of the hydrogen and oxygen thruster, combined with the experimental exploration on the coaxial hydrogen and oxygen resonance ignition, a scheme of the thruster head configuration is designed as the combination of a coaxial hydrogen/oxygen resonance igniter and an oxygen augmentation injector. Through ignition tests on coaxial hydrogen/oxygen resonance igniter characterization, the thruster head ignition tests have been conducted successfully in sequence of resonance ignition and oxygen augmentation combustion. Finally, the thruster ground tests are successfully carried out in forms of single impulse, successive double impulses and 3.0 seconds continuous running, which verify the reliability and feasibility of the thruster. The response time of the thruster starting is restricted within 0.2 second.
