摘要
建立了一种考虑刚体小翼-弹性桨叶耦合的后缘小翼智能旋翼动力学分析模型,分析小翼受控后的旋翼气动弹性响应及动载荷变化。通过与SA349/2直升机的飞行实测数据比较,证实模型的计算结果可靠,精度与CAMRAD II软件相当。悬停状态基准旋翼的后缘小翼受控后,桨尖的挥舞/摆振/扭转响应都明显增加,且响应幅值基本随小翼的偏转角线性增加。对0.197前进比的前飞状态,以针对桨毂载荷的优化控制规律操纵后缘小翼偏转,挥舞与摆振响应变化不明显,震荡扭转响应的幅值明显增大。对于两个计算状态,挥舞响应与扭转响应收敛速度均比摆振响应快。
A dynamic analysis model for smart rotor was built to investigate the aeroelastic response and dynam-ic loads with controlled trailing edge flaps. The predicted results were compared to the flight test data of the SA349/2 helicopter to verify the reliability of the aeroelastic model, and the model was verified to have the similar precision as the CAMRAD II. For the baseline rotor in hover, controlled trailing edge flaps can obviously increase the respon-ses at blade tip in flap, lag and torsion directions. The amplitudes of responses linearly increase with the controlled deflection angle. In forward flight condition of 0. 197 advance ratio, control the flaps with an optimized control law for hub load reduction. The variation of flap and lag responses are not obvious, while the vibratory torsional re-sponse is significantly increased. For the discussed two conditions, the convergence rates of flap and torsion direc-tions are faster than the lag direction.
出处
《科学技术与工程》
北大核心
2016年第14期56-60,共5页
Science Technology and Engineering
关键词
直升机
旋翼
载荷
后缘小翼
瞬态响应
helicopter rotor
load trailing
edge flap
transient response
