某型双座电动飞机设计与试验

沈阳航空航天大学一直致力于新能源电动飞机的研制，某型双座轻型电动飞机于2012年6月立项研制，该型电动飞机采用一台40 kW稀土永磁同步直流电机作为动力装置，全复合材料机体和板簧起落架结构。巡航升阻比24.1，起飞总重500 kg，最大飞行速度160 km/h，巡航速度110 km/h。该型电动飞机具有零排放、低噪声、运行成本低、使用维护方便等特点。参照中国民航CCAR-21部和美国ASTM标准，完成了电动飞机型号设计批准书TDA和生产许可PC取证。     

运输机机翼平面参数快速优化方法

提出了一套机翼平面参数快速优化方法。新方法通过改变优化思路,简化计算模型,合理选择计算方法,有效地提高了优化效率。简要介绍参数优化思想与流程控制,重点阐述优化程序的气动、重量与性能计算模块的算法。以某运输机为算例,优化结果与资料数据吻合,验证了新方法的正确性。     

空客公司成功的机翼设计I——A300及A310机翼设计

空客公司的成功离不开其先进的机翼设计，其机翼由英国宇航公司负责设计和生产。空客飞机机翼先进的空气动力设计，包括尖峰后加载翼型、超临界翼型、先进跨声速机翼设计——超临界机翼设计、机翼与机身的干扰、翼梢小翼设计、增升装置设计，机翼低重量设计、机翼构型与载荷，详细设计，结构设计和低成本设计等。作为系列论文之一，综述A300及A310的机翼设计特点。     

有翼再入飞行器气动外形集成设计优化

气动外形设计是有翼再入飞行器（RV-W）的关键技术之一。分析了气动参数对再入飞行性能的影响,探讨了有翼再入飞行器气动外形设计的规律和准则。基于上述设计准则,以类X-37B飞行器为研究对象,集成几何参数化建模、气动力、气动热、热防护等学科快速分析方法,采用多学科设计优化方法,以最优气动特性为目标对飞行器气动外形进行了优化;得到优化气动外形后,对飞行器热防护系统（TPS）进行了轻量化设计优化。结果表明,优化外形的气动特性相比初始外形得到了较大的提升,设计优化得到的热防护系统重量占比（8.7%）优于同类飞行器的热防护系统重量占比统计数据,说明了本文有翼再入飞行器气动外形集成设计优化方法的有效性,可为同类飞行器提供参考。     

S型进气道隐身与气动综合特性数值分析

针对S型进气道弯度对其隐身气动特性影响程度的问题,利用CAD软件对进气道进行参数化建模,通过改变进、出口的中心偏移量实现对进气道弯度的改变。采用数值仿真方法分别研究了进气道前向电磁散射特性和进气道流场及气动特性。仿真结果表明,进气道弯度增加对隐身特性和气动特性的影响是完全相反的,并进一步分析出这一现象的产生机理,对进气道的隐身气动一体化设计具有指导性意义。     

HB-2 high-velocity correlation model at high angles of attack in supersonic wind tunnel tests

Responding to a need for experimental data on a standard wind tunnel model at high angles of attack in the supersonic speed range, and in the absence of suitable reference data, a series of tests of two HB-2 standard models of different sizes was performed in the T-38 trisonic wind tunnel of Vojnotehnickˇi Institut(VTI), in the Mach number range 1.5–4.0, at angles of attack up to+30°. Tests were performed at relatively high Reynolds numbers of 2.2 millions to 4.5 millions(based on model forebody diameter). Results were compared with available low angle of attack data from other facilities, and, as a good agreement was found, it was assumed that, by implication, the obtained high angle of attack results were valid as well. Therefore, the results can be used as a reference database for the HB-2 model at high angles of attack in the supersonic speed range, which was not available before. The results are presented in comparison with available reference data, but also contain data for some Mach numbers not given in other publications.     

Review on bio-inspired flight systems and bionic aerodynamics

Humans' initial desire for flight stems from the imitation of flying creatures in nature. The excellent flight performance of flying animals will inevitably become a source of inspiration for researchers. Bio-inspired flight systems have become one of the most exciting disruptive aviation technologies. This review is focused on the recent progresses in bio-inspired flight systems and bionic aerodynamics. First, the development path of Biomimetic Air Vehicles (BAVs) for bio-inspired flight systems and the latest mimetic progress are summarized. The advances of the flight principles of several natural creatures are then introduced, from the perspective of bionic aerodynamics. Finally, several new challenges of bionic aerodynamics are proposed for the autonomy and intelligent development trend of the bio-inspired smart aircraft. This review will provide an important insight in designing new biomimetic air vehicles.     

Control-oriented Modeling for Air-breathing Hypersonic Vehicle Using Parameterized Configuration Approach

This article presents a parameterized configuration modeling approach to develop a 6 degrees of freedom (DOF) rigid-body model for air-breathing hypersonic vehicle (AHV). The modeling process involves the parameterized configuration design, inviscous hypersonic aerodynamic force calculation and scramjet engine modeling. The parameters are designed for airframe-propulsion integration configuration, the aerodynamic force calculation is based on engineering experimental methods, and the engine model is acquired from gas dynamics and quasi-one dimensional combustor calculations. Multivariate fitting is used to obtain analytical equations for aerodynamic force and thrust. Furthermore, the fitting accuracy is evaluated by relative error (RE). Trim results show that the model can be applied to the investigation of control method for AHV during the cruise phase. The modeling process integrates several disciplines such as configuration design, aerodynamic calculation, scramjet modeling and control method. Therefore the modeling method makes it possible to conduct AHV aerodynamics/propulsion/control integration design.     

临近空间螺旋桨气动性能分析

基于叶素理论和儒可夫斯基涡流理论,通过求解螺旋桨合成速度、速度环量及诱导速度的非线性方程组,分析了高度为20 km的临近空间中桨叶数目、桨径长度、旋转速度及前进速度对螺旋桨气动性能的影响。结果显示:诱导速度、拉力、扭矩沿桨径的分布规律都是先增大后减小;螺旋桨拉力随桨径长度、旋转速度的增大而增大,随前进速度的增大先增大后减小且峰值在0.45 Ma左右;螺旋桨效率随桨叶数、桨径长度和旋转速度的增大而减小,随前进速度的增大先增大后减小且峰值在0.1 Ma左右。     

基于风洞试验的非定常空气动力模型识别

在某飞机模型大振幅风洞试验的基础上,分析讨论了单自由度叠加模型、动导数模型、混合模型和非定常模型的适用性.结果表明,单自由度叠加模型、动导数模型和混合模型在小攻角时均是可用的,在大攻角时都不能正确反映飞机的非定常迟滞特性;但与前两种模型相比,混合模型在中等攻角时仍然适用.对于非定常模型,无论在小攻角还是大攻角时,均能较好地反映耦合运动的非定常气动特性.