摘要
针对全尺寸的吸气式高超声速飞行器的低阶弹性弯曲模态极易被控制和扰动输入激发的特点,提出了一种基于准定常激波膨胀波理论进行前体处于振动条件下的气流参数计算方法,然后用该方法分析了一个具有二维可调进气道的全尺寸吸气式高超声速飞行器机体弹性弯曲振动对前体压缩性能的影响。分析表明:对于实际飞行中可能发生的小振幅的低频弯曲振动,其最主要的影响是引起头部激波的改变;机体弯曲振动幅值或频率增大都会对超燃冲压发动机进气道调节范围和前体压缩性能产生不利影响。
The control input and disturbance are prone to excite the lower order bending mode of a full-scale airbreathing hypersonic flight vehicle（AHFV）.A method based on the quasi-steady shock-expansion wave theory for calculating the unsteady aerodynamics of airframe under bending vibration was proposed for a full-scale AHFV.The effect of airframe bending on the fore-body compression performance is analyzed with this method.It shows that for the possible low frequency and small amplitude vibration of airframe bending,the change of nose shock wave is identified as the main effect;and if the vibration amplitude or frequency of airframe bending is increased,the scramjet may encounter difficulties in adjusting cowl position and compression performance.
出处
《飞行力学》
CSCD
北大核心
2011年第5期57-61,共5页
Flight Dynamics
