摘要
针对不同飞行器模型在不同情况下进行结冰风洞试验时,需提供流量、压力、温度连续可调的热气源,设计并实现了一种大流量、高精度热气源系统。通过多支路结构设计和控制参数优化,解决了大流量下高精度控制问题,在1.5kg/s流量下,达到1.6g/s控制精度;通过控制算法参数优化,解决了大流量下流量突变对配气系统的冲击问题;通过对系统控制流程分解,实现了3变量到2变量的转换,降低了控制系统维数,解决了气体流量、压力、温度联合控制问题。调试结果表明:系统各项指标达到了预期效果,可以满足不同型号飞行器模型在不同情况下的试验需求。
While different types of acrobat model conducting icing tunnel tests under different circumstances, a flow, pressure and temperature continuous adjustable hot air supply is needed. In this paper, a large flow and high precision hot air supply system was proposed＇ and implemented, to solve the problem under large flow by multi-branch design and control parameter optimization, the control precision is 1.6 g/s under the flow of 1.5 kg/s. The multi-variables control problem was solved by separating the system control procedure. The test results show that the system works well, and achieves the design goals.
出处
《机械工程与自动化》
2015年第3期170-172,175,共4页
Mechanical Engineering & Automation
