飞翼无人机静气弹参数分析及操纵效率计算  

Flying Wing UAV Static Aeroelastic Parameter Analysis and Control Efficiency Calculation

作　　者：许军[1,2] 马晓平[3] Xu Jun Ma Xiaoping(College of Aeronautics, Northwestern Polytechnical University, Xi＇an 710072, China Department of Aerostat Platform, No. 38 Research Institute of CETC, Hefei 230088, China UAV Research Institute, Northwestern Polytechnical University, Xi＇an 710065, China)

机构地区：[1]西北工业大学航空学院,陕西西安710072 [2]中国电子科技集团公司第三十八研究所浮空平台部,安徽合肥230088 [3]西北工业大学无人机所,陕西西安710065

出　　处：《西北工业大学学报》2016年第5期747-753,共7页Journal of Northwestern Polytechnical University

基　　金：陕西省自然科学基金(2013JM015)资助

摘　　要：耦合流体控制方程与结构动力学方程求解飞翼式无人机的静气动弹性参数响应及不同舵面的操纵效率。首先通过气动结构松耦合技术研究了飞翼无人机静气动弹性响应,对比分析刚性与弹性气动特,分析高度、马赫数、迎角及侧滑角对静气动弹性的影响;其次研究单一舵面偏转与组合舵面偏转的静气弹性,并分析结构几何非线性对静气动弹性的影响;然后分析阻力方向舵开裂角对静气弹的影响;最后计算不同马赫数不同舵面的操纵效率。研究表明迎角增大位移幅值也增大,不同高度位移响应频率形式是一样的,侧滑角对无人机半模静气动弹性响应并没有影响;开裂角增大位移幅值减小,且振荡收敛时间越短;方向舵操纵效率与组合舵面操纵效率相比差异较小,组合舵面操纵效率与单一舵面相比较高,不同组合舵面操纵效率比较接近。The flying wing UAV static aeroelastic parameters responses and different rudders control efficiency,based on the fluid control equation and structural dynamics equation coupling model,were solved. Firstly the flying wing UAV static aeroelastic responses based on the aerodynamic structural loosely coupling method were studied,the rigid and elastic aeordynamic characteristic were analysis,the effect of height,Mach numbers,attack angle,sideslip angle on the static responses were also analysis. Secondly the single rudder and combination rudders deflection static aeroelastic were given,and the linear and nonlinear on the static aeroelastic responses were also studied.And then effect of rudder crack initiation angles on the static aeroelastic were given; Finally different rudders control efficiency at different Mach numbers were calculated. The research results showed that：（ 1） the displacement amplitude increased as the attack angle increased,the displacement response frequency was the same at different heights,and the sideslip angle had no effect on the UAV semi model static aeroelastic responses;（ 2） the displacement amplitude decreased as the cracking angle increased,and the oscillation convergence time was shorter;（ 3）the rudder control efficiency were closed to the combination rudders control efficiency,which had higher control efficiency compared with the single rudder,and the different rudders control efficiency were almost the same.

关 键 词：飞翼无人机 静气动弹性 CFD/CSD 操纵效率 阻力方向舵 开裂角 弹性变形 

分 类 号：V211.5[航空宇航科学与技术—航空宇航推进理论与工程]