eLoran系统ASF网格应用算法研究

ASF网格是提高增强型罗兰（Enhanced Long Range Navigation,eLoran）系统精度的重要方法。根据所在网格四个顶点的附加二次时延（Added Secondary Factor,ASF）值通过网格应用算法得到待测试点的ASF值,一定程度上比公式计算的ASF值更准确。在计算过程中,用户四个顶点ASF值的测量误差会传递给用户,同时内插算法本身也会引入误差,此时内插算法的选择尤为重要。本文通过仿真、分析比较几种常用的内插算法,得出结论：反距离插值算法引入的误差最大,双线应插值算法引入的误差最小,而且误差呈现一定层次感,网格从内到外误差逐渐减小。     

多航天器协同探测效能影响参数不确定性分析

为解决传统基于蒙特卡洛仿真的探测效能不确定性分析评价方法中时间效率低,参数关系映射单一的问题,提出一种基于神经网络的不确定性分析方法,利用人工神经网络在拟合回归分析上的非线性特性,设计了能够替代复杂系统的神经网络结构,能够通过少量仿真计算结果作为训练样本实现模型的收敛并能有效反映被替代系统的原有特性。选择以一个多航天器的天文观测任务作为典型用例,建立了仿真分析模型,并与蒙特卡洛仿真方法结果进行了对比,验证了此方法的准确性和计算效率。     

天基强银河背景下的空间碎片探测试验及分析

本文设计并完成了银河背景下碎片探测试验,数据分析表明,强的银河背景会降低探测器对暗弱碎片的探测能力,但对碎片的天文定位精度影响不大。本文验证了采用基于探测概率的极限探测星等方法表征探测器极限探测能力的合理性,以及基于仿真的方法增加数据完备度的可行性。本文的工作将为后续天基探测器的设计及探测试验的开展提供依据。     

基于数值模拟的翼身融合布局飞机上悬式发动机布置技术

发动机进排气对飞机气动特性具有重要影响。为了评估翼身融合布局（BWB）飞机上悬式发动机不同布置方式对全机气动特性的影响,首先开展了发动机短舱进排气与全机流场耦合的数值模拟技术研究,验证了计算方法的正确性。在此基础上,针对发动机安装于翼身升力面之上的BWB运输类飞机,开展飞机巡航飞行条件下,发动机不同支撑高度下沿流向及展向不同安装位置的进排气与全机流场耦合数值模拟,评估发动机不同布置方式对全机气动特性的影响,形成发动机不同布置方式影响的规律性结论。     

基于STM32F429的全向运动平台的运动控制

全向运动平台系统是可以实现人体在各个方位行走的2D运动平台。针对实现人体在全向运动平台稳定行走的运动控制,采用加入观测器的一阶控制算法对平台运动控制进行探究。先通过MATLAB软件进行算法的仿真,验证方法的可行性;再通过现场测试,验证控制算法的有效性。最终试验表明,加入观测器的一阶控制算法可对全向运动平台实现有效的运动控制。此运动控制策略的探究为全向运动平台的运动控制提供了一种可行的控制思路和方案。     

Dynamics and de-spin control of massive target by single tethered space tug

This paper investigates the dynamics and de-spin control of a massive target by a single tethered space tug in the post-capture phase. The dynamic model of the tethered system is derived and simplified to a dimensionless form. Further, a decoupled PD controller is proposed, and the local stability of the controller is analyzed by linearization technique. Parametric studies of the dynamics and de-spin control of a massive target are conducted to characterize the dynamic process of de-spin with the proposed control law. It is shown that the massive target can be de-span by a single and small space tug with limited thrust within finite time. The thrust tangent with the tether de-spins the target while the thrust normal to the tether prevents the tether from winding up the target. The tether length has a positive contribution to the de-spin of a target. The longer tether leads to a faster de-spin process.     

An evolutionary computational framework for capacity-safety trade-off in an air transportation network

Airspace safety and airport capacity are two key challenges to sustain the growth in Air Transportation. In this paper, we model the Air Transportation Network as two sub-networks of airspace and airports, such that the safety and capacity of the overall Air Transportation network emerge from the interaction between the two. We propose a safety-capacity trade-off approach,using a computational framework, where the two networks can inter-act and the trade-off between capacity and safety in an Air Transport Network can be established. The framework comprise of an evolutionary computation based air traffic scenario generation using a flow capacity estimation module(for capacity), Collision risk estimation module(for safety) and an air traffic simulation module(for evaluation). The proposed methodology to evolve air traffic scenarios such that it minimizes collision risk for given capacity estimation was tested on two different air transport network topologies(random and small-world) with the same number of airports. Experimental results indicate that though airspace collision risk increases almost linearly with the increasing flow(flow intensity) in the corresponding airport network, the critical flow depend on the underlying network configuration. It was also found that, in general, the capacity upper bound depends not only on the connectivity among airports and their individual performances but also the configuration of waypoints and mid-air interactions among conflicts. Results also show that airport network can accommodate more traffic in terms of capacity but the corresponding airspace network cannot accommodate the resulting traffic flow due to the bounds on collision risk.     

超燃冲压发动机燃烧模态转换直连式实验研究

为获得燃烧模态转换过程对超燃冲压发动机工作特性的影响,在直连式实验台上,通过液态煤油流量的线性变化,开展了飞行马赫数4.5条件下燃烧室不同工作模态的转换实验。通过对特征位置和参数的监测,实现了燃烧模态的实时判别,获得了燃烧模态转换过程对发动机性能的影响规律。实验结果表明,在燃烧模态转换过程中滞环现象明显,燃烧室压力和发动机推力性能存在突变。在燃油流量以相同的速率增加和减小过程中发生模态转换时刻的燃油当量比存在差异,分别为0.55和0.488,两个转换点燃烧室比推相差8.05%。在滞环区间内,对于同一当量比,会存在两个不同燃烧模态,对应不同的发动机推力性能。     

钛合金结构损伤容限设计可行性研究

对飞机结构常用金属材料损伤容限特性进行了对比分析,针对TC4和TA15损伤容限特性较差的缺点,研制出两种超低间隙（ELI）钛合金TC4ELI和TA15ELI,并对其进行结构损伤容限设计可行性论证。进行了两种超低间隙钛合金和普通钛合金裂纹扩展寿命、剩余强度和疲劳全寿命对比实验。实验结果表明：具有片层组织的超低间隙钛合金相对于普通成分钛合金断裂韧性和裂纹扩展特性有明显改善,剩余强度和疲劳全寿命相当;应力水平相当时,超低间隙钛合金工程可检裂纹扩展寿命比航空结构中常用铝合金稍长。因此,对于超低间隙钛合金TC4ELI和TA15ELI可以进行损伤容限设计。     

崎岖地形中关节式月球车姿态估计数值求解方法

 以被动关节式地形自适应月球车为研究对象,融合关节机器人D-H坐标建模方法构建了月球车悬架运动学模型和以侧倾、俯仰和偏转角表示姿态的欧拉角方式建立了车轮到世界坐标系的悬架完整表达模型。利用悬架完整表达模型,用带有迭代因子的连续迭代和离散迭代数值求解方法,建立了光滑和离散崎岖地形姿态估计算法。最后以8轮扭杆双摇杆摇臂月球车原理样机为例来验证此模型求解方法。仿真结果验证了所建立的基于数值方法的崎岖地形被动关节式月球车姿态估计模型的正确性,其求解模型精度能够满足仿真要求。