B737飞机变速恒频电源分析

分析Ｂ７３７飞机变速恒频电源的基本组成、工作原理，介绍按谐波抑制原理的正弦脉宽调制技术，给出试用结果和存在的主要问题，指出ＶＳＣＦ飞机电源的应用前景。     

分布式计算机技术在飞机非标测控设备中的应用和实现

在研究、分析和总结分布式计算机技术与系统实现的基础上，以苏-27战斗机火控雷达天线部件性能测控系统研制过程为例，详细论述了分布式计算机测控系统的实现模式，介绍了一种先进合理的非标测控设备设计解决方案和快捷、低成本的系统实用集成方案。     

长配管、高落差空调系统的计算机仿真与试验研究

空调系统在长配管、高落差情况下其运行性能和可靠性会受到影响。建立数学模型预测长配管、高落差空调系统的性能，可以提供给用户准确的性能资料，指导用户合理安装空调器，提高产品的可靠性。     

太阳能飞行器能源昼夜闭环仿真分析

以能量为核心，建立太阳能飞行器的获能模型；通过对太阳能飞行器飞行剖面特点的分析，设计飞行过程中各个阶段的飞行方案，并建立相应的耗能模型；考虑目前储能电池技术水平，根据产能和耗能模型，建立储能模型，完成了能源闭环模型的设计；参照Zephyr 7太阳能无人机的结构参数对论文建立的模型进行了仿真分析，获取了飞行过程中能量变化规律，同时对飞行姿态进行优化。结果表明：通过对太阳能飞行器昼夜飞行高度的不同设置以及飞行姿态角的优化，太阳能飞行器可以实现跨昼夜持久飞行。     

飞机穿越烟气流场的响应计算与分析

本文把烟气流作为一种人为的风切变场,分析和计算了烟气流的抬升夹卷模式,讨论了飞机对称穿越烟气流场时的响应。可为电厂和机场的相关设计提供参考依据。     

折叠式变体飞行器轨迹优化及控制分析

针对临近空间高超声速飞行器存在的问题，设计了一种折叠翼飞行器，可以通过折叠机翼来适应各种飞行状态，保持最优的气动特性。并针对临近空间滑翔式高超声速的特点，采用高斯伪谱法对固定翼飞行器和折叠翼飞行器的轨迹优化，通过将折叠翼飞行器与传统固定翼飞行器在射程能力、规避热流能力方面进行对比，提出了一种综合目标的轨迹优化思想。设计的折叠翼飞行器相比传统固定翼飞行器性能更加优越，更适合临近空间环境，提高了17.67%的航程，减少了热流率峰值的35.72%，并通过控制系统的设计和仿真加以验证，仿真结果表明变体飞行器机动能力相比固定翼飞行器有了显著的提高。     

A comparative study of ionospheric IRIEup and ISP assimilative models during some intense and severe geomagnetic storms

Three-dimensional (3-D) electron density matrices, computed in the Mediterranean area by the IRI climatological model and IRIEup and ISP nowcasting models, during some intense and severe geomagnetic-ionospheric storms, were ingested by the ray tracing software tool IONORT, to synthesize quasi-vertical ionograms. IRIEup model was run in different operational modes: (1) assimilating validated autoscaled electron density profiles only from a limited area which, in our case, is the Mediterranean sector (IRIEup_re(V) mode); (2) assimilating electron density profiles from a larger region including several stations spread across Europe: (a) without taking care of validating the autoscaled data in the assimilation process (IRIEup(NV)); (b) validating carefully the autoscaled electron density profiles before their assimilation (IRIEup(V)).The comparative analysis was carried out comparing IRI, IRIEup_re(V), ISP, IRIEup(NV), and IRIEup(V) foF2 synthesized values, with corresponding foF2 measurements autoscaled by ARTIST, and then validated, at the truth sites of Roquetes (40.80°N, 0.50°E, Spain), San Vito (40.60°N, 17.80°E, Italy), Athens (38.00°N, 23.50°E, Greece), and Nicosia, (35.03°N, 33.16°E, Cyprus). The outcomes demonstrate that: (1) IRIEup_re(V), performs better than ISP in the western Mediterranean (around Roquetes); (2) ISP performs slightly better than IRIEup_re(V) in the central part of Mediterranean (around Athens and San Vito); (3) ISP performance is better than the IRIEup_re(V) one in the eastern Mediterranean (around Nicosia); (4) IRIEup(NV) performance is worse than the IRIEup(V) one; (5) in the central Mediterranean area, IRIEup(V) performance is better than the IRIEup_re(V) one, and it is practically the same for the western and eastern sectors.Concerning the overall performance, nowcasting models proved to be considerably more reliable than the climatological IRI model to represent the ionosphere behaviour during geomagnetic-ionospheric storm conditions; ISP and IRIEup(V) provided the best performance, but neither of them has clearly prevailed over the other one.     

大型客机低速构型高雷诺数风洞腹撑支架干扰数值模拟

风洞到飞行相关性修正是获取现代大型客机低速气动特性的重要手段，通常采用增压提高风洞试验雷诺数，而支架干扰修正是该修正体系的一个关键环节。采用数值模拟研究了增压风洞腹撑的支架干扰，并分析了腹撑对飞机各部件的干扰及其对风洞流场的影响。通过数值模拟与风洞试验对比，表明升力系数相差0.006，阻力系数最大相差0.001 2，俯仰力矩系数最大相差0.01，验证了CFD数值模拟方法的可靠性。CFD计算结果表明：腹撑使得全机升力增加、阻力减小，俯仰力矩增加；腹撑对升力影响的主要部件是机翼，腹撑使得风洞中心以上动压增加，提升上翼面流速，从而增加了机翼的升力；与传统认识不同的是腹撑对阻力影响为负，且主要影响部件为缝翼，原因为缝翼下偏使得法矢分量向前从而减小了阻力；腹撑对俯仰力矩影响的主要部件是机身及平尾。研究结果揭示了腹撑对飞机气动特性影响的量级、主要影响部件及其流场变化，可为支架干扰数据修正及支架优化设计提供参考。所得结论可更好用于支架干扰试验的开展及风洞到飞行数据的修正，具有一定的工程实用性。     

Sliding mode control design for oblique wing aircraft in wing skewing process

When the wing of Oblique Wing Aircraft (OWA) is skewed, the center of gravity, inertia and aerodynamic characteristics of the aircraft all significantly change, causing an undesirable flight dynamic response, affecting the flying qualities, and even endangering the flight safety. In this study, the dynamic response of an OWA in the wing skewing process is simulated, showing that the three-axis movements of the OWA are highly coupled and present nonlinear characteristics during the wing skewing. As the roll control efficiency of the aileron decreases due to the shortened control arm in an oblique configuration, the all-moving horizontal tail is used for additional roll and the control allocation is performed based on minimum control energy. Given the properties of pitch-roll-yaw coupling and control input and state coupling, and the difficulty of establishing an accurate aerodynamic model in the wing skewing process due to unsteady aerodynamic force, a multi-loop sliding mode controller is formulated by the time-scale separation method. The closed-loop simulation results show that the asymmetric aerodynamics can be balanced and that the velocity and altitude of the aircraft maintain stable, which means that a smooth transition is obtained during the OWA’s wing skewing.     

提升民用飞机水废水系统运营经济性技术研究

基于现代民机绿色环保设计理念和对经济性的追求,减重是飞机设计中重点考虑因素,关于降低民用飞机水废水系统运营载重、提高运营经济性研究,国内外尚未发布公开文献。本文基于对航线用水统计数据研究,形成航线运营所需水量计算技术;基于我国航线飞行时长分布特点,提出基于航线实际运营时间和载客人数为需求、为系统设定分档加水设计技术。结果表明：与同类机型数据对比,本文的水量计算技术是有效的;分档加水设计技术能够有效地降低系统在航线运营过程中的运营重量,可以提升民用飞机水废水系统的运营经济性。