串联驱动变弯度机翼设计与气动性能分析

针对飞行性能要求,采用NACA4412翼型设计了一种串联驱动变弯度机翼方案。将机翼沿弦向分为5个翼段,前缘部分为主承力结构固定段,后缘4段翼面由4个舵机实现串联驱动。偏转翼段内部采用空间五面体桁架结构,表面敷设复合材料弹性蒙皮。翼段间采用连杆止动以限制相对转角。建立了机翼的运动学分析模型,计算了变弯度机翼的作动速度。建立了机翼的气动分析模型,对4个典型飞行工况的气动性能进行了分析,并与传统舵面机翼性能进行对比。研究表明,在相同飞行工况下,弦向四级串联驱动变弯度机翼的作动时长仅为传统机翼的25%。起飞阶段升阻比增大71.94%,滚转机动时力矩增大12.46%,进近阶段升力增大11.19%,接地后减速阶段阻力增大104.83%。串联驱动变弯度机翼相对传统舵面机翼具有更优的操纵特性和气动性能。

A Design of Tandem Drive Variable Camber Wing and Analysis of Aerodynamic Performance

In order to meet the needs of flight performance, a tandem drive variable camber wing is designed with NACA4412 airfoil. Wing structure is divided into five sections along chordwise, and leading section is the main load-bearing structure. Four wing sections of the trailing edge are driven by four electrical servo motors in series. In the interior of deflecting wing section, pentahedron truss structure is adopted, and in the interior there is laid on the surface a composite elastic skin. Connecting rods with stop function is arranged to limit the relative rotation angle of the four trailing sections. A kinematics analysis model of the variable camber wing is established, and the drive speed is calculated. An aerodynamic analysis model of the wing is built, and the aerodynamic performance of four typical flight status is analyzed, and their performance is compared with that of the wing with conventional flight control surfaces. The results show that under the same flight status, the actuation time of the variable camber wing with fourstage tandem drive along chordwise is only 25% of that of the conventional wing. The lift-drag ratio increases by 71.94% for takeoff. The maneuver moment increases by 12.46% for roll. The lift increases by 11.19% for approach, and the drag increases by 104.83% for deceleration after touchdown. Tandem drive variable camber wing is superior relatively to the conventional control wing in handling characteristics and in aerodynamic performance.