Shock tunnels are important ground test facilities that can generate high-enthalpy flow. Flight velocity at a high Mach number can be simulated for aerodynamic testing of chemically reacting flows. However, the application of these tunnels is limited due to the only milliseconds-long test duration, especially for aerodynamic force measurement using traditional strain gauge balances. This study presents an impulse force-measurement system, which was used for a large-scale test model to measure its drag in a high-enthalpy shock tunnel with an approximately 3–7-ms test time. Force tests were conducted for a cone in the JF-10 high-enthalpy shock tunnel in the Institute of Mechanics, Chinese Academy of Sciences. An integrated design of the impulse force-measurement system was proposed for load measurement over a short duration, for which a recommended design criterion is that the measurement period be a minimum of twice the period corresponding to the lowest natural frequency of the measurement system. The current measurement technique breaks the limitations of the application of the conventional strain gauge balance. As an integrated measuring system, the impulse force-measurement system expands the structural design concept of strain gauge balances. The impulse force-measurement system performed well in the present tests. The test results show differences from the numerical simulations and some data obtained in a conventional wind tunnel. A preliminary analysis was performed on the real gas effects on the aerodynamic force.

中文翻译：

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冲击力测量系统

冲击隧道是重要的地面试验设施，可以产生高焓流。可以模拟高马赫数下的飞行速度，用于化学反应流的空气动力学测试。然而，这些隧道的应用受到限制，因为测试持续时间只有几毫秒，特别是对于使用传统应变计天平的空气动力测量。本研究提出了一种冲击力测量系统，该系统用于大型测试模型，以大约 3-7 毫秒的测试时间测量其在高焓冲击隧道中的阻力。在中科院力学所JF-10高焓激波隧道中对锥体进行了受力试验。提出了一种冲击力测量系统的集成设计，用于短持续时间的载荷测量，推荐的设计标准是测量周期至少是对应于测量系统最低固有频率的周期的两倍。目前的测量技术打破了传统应变计天平应用的局限性。作为一个集成的测量系统，冲击力测量系统扩展了应变计天平的结构设计理念。冲击力测量系统在目前的测试中表现良好。测试结果显示了与数值模拟和在常规风洞中获得的一些数据的差异。对真实气体对气动力的影响进行了初步分析。