固冲发动机转级试验点火控制系统设计

摘要

For the requirement of transition test on integral solid propellant ducted rocket , an ignition control system is designed to simulate the control system on missile .According to the characteristics of solid propellant ducted rocket transition technology , the function and design requirements of the system are defined , and working principle , hardware structure and software design of the system are described in detail.The system has fully considered the different tranfer modes and the abnormal emergency response , and has the ability of ground transition test , which provides an effective test platform for the transition of rocket performance and reliability .%针对整体式固体火箭冲压发动机转级试验需求，设计了一套点火控制系统，用以模拟弹载控制系统功能。根据固冲发动机转级技术特点，明确了系统的功能和设计要求，对系统的工作原理、硬件结构和软件设计等内容做了详细描述。该系统充分考虑了不同转级方式和异常应急等情况，具备地面转级试验能力，为产品转级性能评定和可靠性验证提供了有效的试验平台。