Study of UV Ne II line shapes in the cathode sheath of an abnormal glow discharge

We report results of an experimental and theoretical study of complex UV line shapes of Ne II 369.421 nm, Ne II 370.962 nm, Ne II 371.308 nm, and.Ne II 372.711 nm lines in the cathode sheath (CS) region of an abnormal DC glow discharge in pure neon. Two sets of experimental profiles and electric field distributions, one for discharge with tungsten and the other with titanium cathode, were obtained by means of the optical emission spectroscopy (OES) and theoretically studied by the iterative CS kinetic model. It is shown that our theoretical model enables the determination of the most important CS parameters (e.g. the thickness of the CS region, and the theoretical distributions of electric field and gas temperature) and thereupon based accurate theoretical predictions of the experimentally observed profiles of the studied lines.     

Close relative motion on distant retrograde orbits

Distant Retrograde Orbits (DROs) in the Earth-Moon system have great potential to support varieties of missions due to the favorable stability and orbital positions. Thus, the close relative motion on DROs should be analyzed to design formations to assist or extend the DRO missions. However, as the reference DROs are obtained through numerical methods, the close relative motions on DROs are non-analytical, which severely limits the design of relative trajectories. In this paper, a novel approach is proposed to construct the analytical solution of bounded close relative motion on DROs. The linear dynamics of relative motion on DRO is established at first. The preliminary forms of the general solutions are obtained based on the Floquet theory. And the general solutions are classified as different modes depending on their periodic components. A new parameterization is applied to each mode, which allows us to explore the geometries of quasi-periodic modes in detail. In each mode, the solutions are integrated as a uniform expression and their periodic components are expanded as truncated Fourier series. In this way, the analytical bounded relative motion on DRO is obtained. Based on the analytical expression, the characteristics of different modes are comprehensively analyzed. The natural periodic mode is always located on the single side of the target spacecraft on DRO and is appropriate to be the parking orbits of the rendezvous and docking. On the basis of quasi-periodic modes, quasi-elliptical fly-around relative trajectories are designed with the assistance of only two impulses per period. The fly-around formation can support observations to targets on DRO from multiple viewing angles. And the fly-around formation is validated in a more practical ephemeris model.     

涡轮弯扭叶片气动设计工程方法研究

采用弯扭叶片设计是提高燃气涡轮效率的主要手段之一,而构建弯扭叶片积叠线的参数化模式是设计涡轮弯扭叶片的重要基础。为了满足各种涡轮叶片弯扭设计的工程需要,提出了采用圆弧型、抛物线型、分段样条曲线积叠线规律的涡轮弯扭叶片设计方法,编制了积叠线生成代码,并推荐了各方法的应用条件和方式;提出的回归正交设计方法可以对分段样条曲线积叠线的涡轮弯扭叶片进行寻优设计。所提出的弯扭叶片工程设计方法已经在多个涡轮气动设计中得到应用。     

Aerial-ground collaborative routing with time constraints

The advancement of autonomous technology makes electric-powered drones an excellent choice for flexible logistics services at the last mile delivery stage. To reach a balance between green transportation and competitive edge, the collaborative routing of drones in the air and trucks on the ground is increasingly invested in the next generation of delivery, where it is particularly reasonable to consider customer time windows and time-dependent travel times as two typical time-related factors in daily services. In this paper, we propose the Vehicle Routing Problem with Drones under Time constraints (VRPD-T) and focus on the time constraints involved in realistic scenarios during the delivery. A mixed-integer linear programming model has been developed to minimize the total delivery completion time. Furthermore, to overcome the limitations of standard solvers in handling large-scale complex issues, a space-time hybrid heuristic-based algorithm has been developed to effectively identify a high-quality solution. The numerical results produced from randomly generated instances demonstrate the effectiveness of the proposed algorithm.     

基于PSK调制的数字通信信号仿真分析技术

基于PSK调制的数字通信系统在无线通信工程实践中有着广泛的应用，由于受到各种条件的限制，从实际工程系统接收到的PSK数字通信信号在教学科研中不易获得，而PSK调制仿真数据则可以自己产生。在掌握通信原理和仿真技术的基础上利用Matlab实现对BPSK、DPSK、QPSK、DQPSK、8PSK、π/4-DQPSK、OQPSK等数字通信信号源的模拟仿真，可对调制体制、工作频率、传输码率、采样频率、信道特征等参数进行灵活设置，并按要求生成规定格式的DAT数据文件，可作为调制方式识别软件的训练和测试样本。结合模方谱、平方谱、四次方谱、八次方谱等谱线参数特征，同时结合星座图和眼图进行基于PSK调制的数字通信信号的调制体制判别和验证。     

中弧线角度分布对跨音叶栅特性影响研究

中弧线角度分布形式对压气机叶片表面等熵马赫数分布具有重要的影响。为了对比不同压气机叶型的流动特征，采用数值模拟和平面叶栅试验相结合，对两种中弧线角度分布形式的跨音叶型在不同来流工况下的气动特性展开了详细研究。结果表明：在设计点，前加载配合均匀加载的中弧线角度分布叶型能够消除叶片吸力面的局部超音区，与前加载的中弧线角度分布叶型相比，叶片表面等熵马赫数分布更加饱满。其次，前加载配合均匀加载叶型能够推迟叶片吸力面的涡层失稳，减弱了吸力面分离涡与端壁分离涡的耦合作用，进而改善了端区的流动状况，截面平均总压损失系数降低了8.2%。最后，对非设计工况下两种中弧线角度分布的气动特性进行了分析，随着来流马赫数的降低，两种中弧线角度分布叶型的损失差异逐渐减小，均具有较优的气动性能。来流速度对叶片表面等熵马赫数、损失分布和分离面形状特征影响较小，仅影响叶片表面等熵马赫数和损失数值大小。     

Parameterized design of abort trajectories with a lunar flyby for a crewed mission

This article proposes an analytical preliminary design method for abort trajectory with a lunar flyby and the trajectory ergodic representation based on parameterization, as well as their application in studying the abort trajectories’ characteristics. First, by introducing two parameters, the perilune altitude and the perilune transfer time, the preliminary solution is developed parametrically using pseudostate theory to connect two special Lambert processes. The fast convergence of the improved differential correction under the high-fidelity gravity field verifies the accuracy of the proposed preliminary design method. Next, the two parameters are regarded as a set of variables to define an abort trajectory. Based on this, an ergodic representation of the abort trajectory with a certain abort time is yielded using the proposed design method, which offers a global view of the feasible abort trajectories. In addition, the influences of some factors on the performance of these abort trajectories are investigated based on the proposed design method and ergodic representation. The simulation results show that the abort time and the transfer time of the nominal trajectory significantly affect the ergodic representation and characteristics of the abort trajectory.     

Calculating the simultaneous effect of ion dynamics and oscillating electric fields on Stark profiles

We calculate hydrogen line shapes resulting from the simultaneous Stark effect of the plasma microfield and an oscillating electric field. Like laboratory plasmas, many kinds of space plasmas are affected by oscillating electric fields with a magnitude similar to that of the microfield. Here we focus on conditions where we expect that the effect of ion dynamics and oscillating electric are both significant. The combined effect of their dynamics on the quantum emitter is retained by a computer simulation coupled to a numerical integration of the Schrödinger equation. Our calculations are applied for conditions and transitions where significant changes in the line shape allow for a diagnostic of the plasma and oscillating field.     

Four-body cislunar quasi-periodic orbits and their application to ballistic lunar transfer design

Examining the properties of quasi-periodic orbits provides insight into the Sun-perturbed environment in cislunar space. In this investigation, quasi-periodic trajectories and their properties are explored in the Sun-Earth-Moon four-body problem. Computation and the stability characteristics of families of invariant tori are detailed. Furthermore, this investigation offers a framework for construction of ballistic lunar transfer trajectories in the four-body problem. The framework leverages manifold trajectories to supply a set of initial conditions for construction of periapsis Poincaré maps. Periapsis maps reduce the dimensionality of the space and illuminate solutions of interest as a basis to produce feasible families of transfers. Through a continuation process, families of ballistic transfers and families of transfers that include powered lunar flybys are constructed. Ultimately, these solutions supply an initial guess for transition to the Sun-Earth-Moon ephemeris model.     

一阶微分方程终值问题拟解的存在性

利用拟上下解方法,研究了一阶微分方程终值问题u′(t)=f()t,u(t),u(T)=xT拟解的存在性,并通过构造单调迭代序列得到该终值问题的最大最小拟解。