摘要
MF-1是我国首次以高超声速空气动力学基础问题研究为目的的航天模型飞行试验,试验模型为锥-柱-裙体,主要研究0°迎角圆锥边界层转捩和压缩拐角激波/边界层干扰现象。针对飞行试验转捩区测量需求,引入和改进了风洞试验中常用薄壁测热技术,设计了一种新型变厚度薄壁测温结构,有效抑制了侧向导热损失,可基于一维热流辨识方法获取可靠的表面热流数据;与现有风洞试验薄壁测热技术相比,该方法可提高有效测量时间,降低时间延迟效应,适于长时间飞行试验测量。针对柱-裙压缩拐角激波/边界层干扰区压力测量需求,采用了风洞试验中常用的基于引压管和电子压力扫描阀的测量方案,通过改进装配工艺,提高了系统耐压能力,实现了模型飞行试验全弹道表面压力测量。模型飞行试验结果表明:MF-1模型飞行试验测量系统可靠,获得了可供边界层转捩和激波/边界层干扰研究分析及CFD验证的可信数据;在热流急剧下降时一维热流辨识存在较大误差,以及压力测量中的时间延迟和低压测量准确度存在不足,是需要进一步改进的问题。
For the fundamental studiesin hypersonic aerodynamics,the f irs t aerospace modeling fl ight named MF -1 was carried out in China. The tested model is a cone-cylinder-flare configuration in the payload modules of this flight, and the main objective of this test is the investigation of the boundary layer transitionon the cone surface and the shock wave/boundary layer interaction at the compression corner. According to the measurement requirements of the boundary layer transition study？the common thin-skin calorimeter design in wind tunnel tests was employed and modified. This modification led to a novel variable-thickness thin-skin temperature measurement structure. The variable-thickness thin-skin structure depresses effectively lateral heat conduction losses due to the temperature difference between thin-skin and surrounding shell during long-time fl ight, therefore an effective long time measurement was obtained. Heat f lu x data can be obtained using an one dimensional heat f lu x identification method based on variable-thickness thin-skin f l ight data. This method improves the response time in comparison w ith the thin-skin calorimetric method. A pressure measurement scheme based on pneumatic tubes and an electric pressure scanner was designed fo r the shock wave/boundary layer interaction study at the compression corner of the cylinder-flare modules. The fabrication process of the pneumatic tubes was modified to improve its pressure t ig h t capability. The parameter measurement system was proved reliable by the MF -1 f l ight test. The thin-skin temperature and surface pressure data ofthe whole trajectory were obtained, which can be used for relevant analysis in boundary layer transition and shock wave/boundary layer interaction study. However, we need to improve some deficiencies in the test including the significant errors in ID heat flux identification during steep drop of the heat f lux , the response delay, and accuracy in low-pressuremeasurement.
出处
《空气动力学学报》
CSCD
北大核心
2017年第5期732-741,共10页
Acta Aerodynamica Sinica
基金
国家重点研发计划"大科学装置前沿研究"重点专项(2016YFA0401200)
关键词
模型飞行试验
温度测量
压力测量
薄壁
modeling f l ight te s t
temperature measurement
pressure measurement
thin-skin
