摘要
在火箭发射地面设备设计中,火箭发动机尾焰对设备结构的影响不容忽视,精准测试尾焰燃气流场意义重大。当前虽有计算流体力学方法模拟燃气流场,但边界条件理想化且需试验验证,同时现有尾焰测试多在实验室安全环境下开展,难以适配实际火箭飞行试验中测试系统现场安装、调试及暴露于强燃气流的需求。分析火箭发射时尾焰燃气的温度、热流密度特点及对测试设备的影响,明确高热环境下接触式测量对传感器响应速度、耐高温能力、固定可靠性的要求。通过试验对比传感器选型,确定Φ0.255 mm铼3-钨铼25热电偶最适用于尾焰燃气流场温度测试;研究传感器安装方法,采用螺纹连接将传感器装于专用测试盒,并做好密封固定;规划测试系统总体布置,对不同区域设备分别采取热防护、减振降噪散热等措施。提出基于硅基材料的现场快速热防护技术,针对传感器端、结构连接处、非直面燃气流位置3种工况制定不同防护方案。该特种测量方法及热防护技术经过多次试验验证,结果表明,热防护层基本完好,传感器、电缆工作正常,防护方案成熟、可靠,可满足实际火箭发射尾焰燃气流场测试需求。
In the design of ground equipment for rocket launches,the impact of rocket engine exhaust plumes on the equipment structure cannot be ignored,and the accurate testing of exhaust gas flow fields is of great significance.Currently,although computational fluid dynamics(CFD)methods are used to simulate gas flow fields,the boundary conditions are idealized and require experimental verification.Meanwhile,most existing exhaust plume tests are conducted in safe laboratory environments,making it difficult to meet the requirements of on-site installation,commissioning of the testing system and exposure to intense gas flows in actual rocket flight tests.This study analyzes the temperature and heat flux characteristics of exhaust plumes during rocket launches,as well as their impact on testing equipment,and clarifies the requirements of contact measurement in high-temperature environments for sensor response speed,high-temperature resistance,and fixed reliability.Through experimental comparison of sensor selection,it is determined that theΦ0.255 mm Re3-WRe25 thermocouple is most suitable for temperature testing of exhaust gas flow fields.The sensor installation method is studied:the sensor is installed in a dedicated test box using threaded connections,with proper sealing and fixation.The overall layout of the testing system is planned,and measures such as thermal protection,vibration and noise reduction,and heat dissipation are adopted for equipment in different areas respectively.A on-site rapid thermal protection technology based on silicon-based materials is proposed,and different protection schemes are developed for three working conditions:the sensor end,structural joints,and positions not directly facing gas flows.This specialized measurement method and thermal protection technology have undergone extensive experimental verification.The results demonstrate that the thermal protective layer remained largely intact,with sensors and cables performing as expected,confirming that the protection scheme is mature and reliable.
作者
梁爽
吴奇峰
魏建波
弓韬
陈夺
刘子陈
LIANG Shuang;WU Qifeng;WEI Jianbo;GONG Tao;CHEN Duo;LIU Zichen(Beijing Institute of Aerospace Launch Technology,Beijing 100076,China)
出处
《电子测试》
2024年第6期65-71,共7页
Electronic Test
关键词
高热环境
火箭发动机尾焰
特种测量方法
传感器选型
硅基材料
热防护技术
high heat environment
rocket engine exhaust plume
special measurement
sensor selection
silicon-based material
thermal protection technologies
