空间站中长时间的微重力环境可以解耦浮力对火焰不稳定性的影响，有利于研究边缘火焰在涡流及声场扰动下的动力学响应和不稳定性，相关成果对能源动力系统中火焰失稳的防控、航天器微重力环境下的灭火机制具有重要指导意义。该文介绍了中国空间站中用于产生不稳定边缘火焰的实验装置设计与初步测试结果。实验装置由燃烧器、声学模块和光学模块组成，安装在中国空间站燃烧科学实验系统中的气体实验插件上; 使用独特的燃烧器搭配光学方法形成了振荡的边缘火焰并进行在轨拍摄; 通过光学模块和燃烧科学实验系统现有相机进行二维火焰的温度反演，研究边缘火焰的固有不稳定性现象以及剪切产生涡流和声学扰动对火焰振荡的影响。在此基础上，进行一系列地面测试以验证边缘火焰对不同声频和由剪切层产生的涡旋扰动的响应。在低剪切率扰动下，边缘火焰表现出低频上下振荡模式; 而在高剪切率扰动下，火焰表现出高频左右振荡模式，甚至出现吹熄。通过地面实验确定的推举稳定边缘火焰的稳定工况，可为后续在微重力条件下获取火焰扰动后的结构变化、响应频率、响应模态和温度场分布等重要参数提供参考。

Objective: Microgravity environment on the space station decouples buoyancy from other limit effects on flame instability. The decoupling facilitates the study dynamical response and associated theories of edge flame under vortical and acoustic excitation. Such research can contribute significantly to the theory development for flame instability control and prevention in energy and power systems and fire suppression mechanisms under microgravity conditions within spacecraft. Methods: The paper introduces the design and initial testing of an experimental apparatus aboard the China Space Station (CSS) for generating and studying acoustic or vortices disturbed edge flames. The apparatus comprises an acoustic slot burner and an optical module, installed on the gaseous combustion experiment insert within the Combustion Science Rack (CSR) aboard the CSS. Compared to traditional co-flow structures, the slot design assures a better control of shear effects and flow field uniformity, allowing more precise control of flame characteristics. Diagnostic methods are introduced to create and capture oscillating edge flames in orbit. The optical module and high-speed CCDs in the CSR are used for two-dimensional temperature inversion of flames. Structural optimization and unique optical beam-splitting design improve diagnostic accuracy and flame visibility. This setup provides a controlled environment to study the effects of vortical structures and acoustic disturbances on flame oscillations. Results: A set of ground testing experiments were conducted to verify the response of edge flames to acoustic disturbances across different acoustic frequencies and vortical disturbances generated by shear layers. At low vortex intensities, the edge flames exhibit low-frequency vertical oscillation patterns, while at high vortex intensities, the flames display high-frequency horizontal oscillation patterns. Under extreme stretching conditions, edge flames can even extinguish. Based on this analysis, future experiments are planned to refine the stability and extinction diagram boundaries of edge flame oscillation. Additional ground experiments and microgravity data will be collected to provide a comprehensive understanding of edge flame behavior under different shear layer strengths and acoustic frequencies. These experiments aim to develop a robust theoretical framework for predicting and controlling flame oscillations and instabilities, contributing to safer and more efficient energy and power systems. Conclusions: The design of the experimental apparatus for the CSS represents a significant advancement in the study of edge flame dynamics under microgravity. The initial results from ground tests demonstrate the complex interaction between flame behavior and external disturbances, which has direct implications for flame stability control in various applications. The stable operating conditions identified through ground experiments will serve as a reference for future experiments conducted in microgravity, where key parameters such as flame structure, response frequency, oscillation modes, and temperature field distribution will be further analyzed. Continued research in this field promises to enhance our understanding of combustion processes in both terrestrial and space environments, ultimately contributing to safer and more efficient energy systems.