摘要
为了实现0.6 m跨超声速风洞试验过程中模型可连续变滚转角,提升0.6 m量级风洞的试验效率和试验范围,研制了一种滚转机构。介绍了该滚转机构、中空内置力矩电机以及控制系统软硬件的设计,对涉及到的关键技术问题进行了分析和总结,给出了结论并进行了风洞试验验证。试验结果表明:分别采用滚转机构与常规测力中部支架作为模型的支撑机构时,试验数据重复性好;滚转机构控制精度高(滚转角≤±3');载荷、工程性、可靠性均满足风洞试验要求。
A rolling device is developed for the continuous change of model's rolling angle, the improve- ment of test efficiency and test range in the 0.6 m × 0.6 m transonic and supersonic wind tunnel. The de- signs of rolling device, hollow built-in torque servomotor and the software and hardware of control system are introduced. The key technical problems are analyzed and summarized, and the conclusions are finally validated by a wind tunnel test. The test data shows that the roiling device and the central support of the normal force test, as model's supporting mechanisms, can be used to acquire better repeatable data. Meanwhile, the system has a high level control precision (rolling angle ≤ ± 3') , and the engineering re- liability of the loads meets the wind tunnel test requirements.
出处
《兵工学报》
EI
CAS
CSCD
北大核心
2017年第8期1658-1664,共7页
Acta Armamentarii
基金
国家"973"计划项目(613240)
国家自然科学基金项目(11402286)
关键词
飞行器试验技术
风洞
滚转机构
力矩电机
控制系统
工程应用
experimental technology of aerocraft
wind tunnel
rolling device
torque servomotor
con- trolling system
engineering application