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| 1 | 飞行器概念设计中的多学科优化模型(英文)显示文摘多学科优化技术的发展有效地提高了飞机的设计水平,同时提高了设计人员对非常规布局飞机的设计能力。以一种双后掠飞翼布局飞机为研究对象,建立新的优化模型对其进行气动、结构优化。优化过程分为系统级优化和学科级优化。在系统级优化中,航程定义为飞机全局性能指标。在学科级优化模型中,把升阻比和展向气动载荷分布的综合气动性能作气动学科优化目标,结构重量作为结构优化目标。优化结果表明,优化模型可以高效地运行,优化方案更接近最优解。 | 潘亚林 黄俊 李锋 | 2017 | 科学技术与工程2017，17，22： | 3 |
| 2 | Research on parafoil stability using a rapid estimate model显示文摘With the consideration of rotation between canopy and payload of parafoil system, a four-degree-of-freedom(4-DOF) longitudinal static model was used to solve parafoil state variables in straight steady flight. The aerodynamic solution of parafoil system was a combination of vortex lattice method(VLM) and engineering estimation method. Based on small disturbance assumption,a 6-DOF linear model that considers canopy additional mass was established with benchmark state calculated by 4-DOF static model. Modal analysis of a dynamic model was used to calculate the stability parameters. This method, which is based on a small disturbance linear model and modal analysis, is high-efficiency to the study of parafoil stability. It is well suited for rapid stability analysis in the preliminary stage of parafoil design. Using this method, this paper shows that longitudinal and lateral stability will both decrease when a steady climbing angle increases. This explains the wavy track of the parafoil observed during climbing. | Hua YANG Lei SONG Weifang CHEN | 2017 | Chinese Journal of Aeronautics2017，30，5： | 3 |
| 3 | Three-axis coupled flight control law design forflying wing aircraft using eigenstructure assignment method显示文摘Due to elimination of horizontal and vertical tails,flying wing aircraft has poor longitudinal and directional dynamic characteristics.In addition,flying wing aircraft uses drag rudders for yaw control,which tends to generate strong three-axis control coupling.To overcome these problems,a flight control law design method that couples the longitudinal axis with the lateraldirectional axes is proposed.First,the three-axis coupled control augmentation structure is specified.In the structure,a‘‘soft/hard'cross-connection method is developed for three-axis dynamic decoupling and longitudinal control response decoupling from the drag rudders;maneuvering turn angular rate estimation and subtraction are used in the yaw axis to improve the directional damping.Besides,feedforward control is adopted to improve the maneuverability and control decoupling performance.Then,detailed design methods for feedback and feedforward control parameters are established using eigenstructure assignment and model following technique.Finally,the proposed design method is evaluated and compared with conventional method by numeric simulations.The influences of control derivatives variation of drag rudders on the method are also analyzed.It is demonstrated that the method can effectively improve the dynamic characteristics of flying wing aircraft,especially the directional damping characteristics,and decouple the longitudinal responses from the drag rudders. | Lixin WANG Ning ZHANG Ting YUE Hailiang LIU Jianghui ZHU Xiaopeng JIA | 2020 | Chinese Journal of Aeronautics2020，33，10： | 1 |
| 4 | 翼反角对高压捕获翼构型亚声速气动特性影响分析研究显示文摘高压捕获翼新型气动布局在高超声速设计状态下具有较好的气动性能,新升力面的引入使其在亚声速条件下也具有较大的升力,但在亚声速下的稳定特性还有待研究.基于高压捕获翼气动布局基本原理,在机身-三角翼组合体上添加单支撑和捕获翼,设计了一种参数化高压捕获翼概念构型.以捕获翼和机体三角翼上/下反角为设计变量,采用均匀试验设计、计算流体力学数值计算方法及Kriging代理模型方法,研究了0°~10°攻角状态下不同翼反角对高压捕获翼构型亚声速气动特性的影响,重点分析了升阻特性、纵向和横航向稳定性的变化规律以及流场涡结构等.结果表明,小攻角状态下翼反角对升阻比的影响比大攻角更加显著,捕获翼上反时,升阻比略微增大,下反则升阻比减小;三角翼上反时,升阻比减小,下反则升阻比先略微增大后缓慢减小;翼反角对纵向稳定性的总体影响较小,捕获翼上反会稍微提高纵向稳定性,而三角翼上反则会降低纵向稳定性;捕获翼或三角翼上反都会增强横向稳定性,下反则减弱横向稳定性,但大攻角状态时,三角翼上反角过大对提升横向稳定性作用有限;捕获翼上反航向稳定性增强,下反航向稳定性则减弱,而三角翼下反对提升航向稳定性的整体效果比上反更加显著. | 常思源 肖尧 李广利 田中伟 崔凯 | 2022 | 力学学报2022，54，10： | 1 |
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