Attitude control of multi-spacecraft systems on SO(3) with stochastic links failure

In this paper, for Multi-Spacecraft System(MSS) with a directed communication topology link and a static virtual leader, a controller is proposed to realize attitude consensus and attitude stabilization with stochastic links failure and actuator saturation. First, an MSS attitude error model suitable for a directed topology link and with a static virtual leader based on SO(3) is derived, which considers that the attitude error on SO(3) cannot be defined based on algebraic subtraction. Then, we d...     

平流层上部负离子成分的直接测量和硫酸离子热化学分析

本文报道了在法国南部(44°N)上空进行的两次气球飞行实验的部分负离子成分探测结果.利用自然负离子谱计算了某些硫酸离子的热化学常数ΔG, ΔH和ΔS.讨论了上升段测量中气球表面放气造成的离子化学污染.      

磁层顶位置的卫星观测

本文用了自1963年到1979年卫星穿越磁层顶的1024个观测资料计算了向阳侧磁层顶椭球面的参数。企图从这些资料得出星际磁场和太阳风热压强对向阳侧磁层顶位置和形状的影响大小。但数值计算和理论分析都表明,目前所具有的观测资料的精度不足以获得星际磁场和太阳风热压强影响的数值。本文分析了各种因素所造成的在计算该椭球面参数时的不确定性。进而提出了对进一步工作的建议。该椭球面的平均大小、形状和方位的观测值与理论预计值是非常一致的。      

土星磁层顶的Kelvin-Helmholtz不稳定性和磁流体表面波

本文采用可压缩磁流体力学近似并选取Voyager-1的观测数据,讨论了土星磁层顶的Kelvin-Helmholtz不稳定性和磁流体表面波.计算表明,土星磁层随星体自转同磁鞘流之间的速度差,可以在地方时午前、中午和距中午不远的午后磁层顶激发不稳定性;午前和午后区有很强的非对称性.计算所得的波的特性与观测一致.      

一种微米级粒子的静电发射加速装置

为了研究空间微小碎片碰撞对航天器的影响,国内外研制了各种类型的微小碎片加速器。文章简要介绍了一种很有前景的静电式微小碎片加速器及其关键部件的工作原理、结构特点及适用范围等。     

赛斯纳162:轻型运动飞机的“制空者”

轻型运动类飞机(LSA)是填补超轻型飞机和高档两座单发活塞飞机之间空白的新型通用飞机,其兼顾了超轻型飞机和高档两座单发活塞飞机的优点,具有超轻型飞机的低价格、高性价比和高档两座单发活塞飞机的良好综合性能。不但克服了超轻型飞机过于简单,性能相对较低,安全性、可靠性和使用性差等缺点,同时也     

航天器非平稳振动环境TVAR时频分析(英文)

Predicting the time-varying auto-spectral density of a spacecraft in high-altitude orbits requires an accurate model for the non-stationary random vibration signals with densely spaced modal frequency. The traditional time-varying algorithm limits prediction accuracy, thus affecting a number of operational decisions. To solve this problem, a time-varying auto regressive （TVAR） model based on the process neural network （PNN） and the empirical mode decomposition （EMD） is proposed. The time-varying system is tracked on-line by establishing a time-varying parameter model, and then the relevant parameter spectrum is obtained. Firstly, the EMD method is utilized to decompose the signal into several intrinsic mode functions （IMFs）. Then for each IMF, the PNN is established and the time-varying auto-spectral density is obtained. Finally, the time-frequency distribution of the signals can be reconstructed by linear superposition. The simulation and the analytical results from an example demonstrate that this approach possesses simplicity, effectiveness, and feasibility, as well as higher frequency resolution.     

LES of film cooling for different jet fluids

The present paper investigates the impact of the velocity and density ratio on the turbulent mixing process in gas turbine blade film cooling.A cooling fluid is injected from an inclined pipe at α=30° into a turbulent boundary layer profile at a freestream Reynolds number of Re∞=400000.This jet-in-a-crossflow(JICF) problem is investigated using large-eddy simulations(LES).The governing equations comprise the Navier-Stokes equations plus additional transport equations for several species to simulate a non-reacting gas mixture.A variation of the density ratio is simulated by the heat-mass transfer analogy,i.e.,gases of different density are effused into an an air crossflow at a constant temperature.An efficient large-eddy simulation method for low subsonic flows based on an implicit dual time-stepping scheme combined with low Mach number preconditioning is applied.The numerical results and experimental velocity data measured using two-component particle-image velocimetry (PIV) are in excellent agreement.The results show the dynamics of the flow field in the vicinity of the jet hole,i.e.,the recirculation region and the inclination of the shear layers,to be mainly determined by the velocity ratio.However,evaluating the cooling efficiency downstream of the jet hole the mass flux ratio proves to be the dominant similarity parameter,i.e.,the density ratio between the fluids and the velocity ratio have to be considered.      

小长径比航天发动机的燃烧稳定性

根据线性稳定计算和发动机试验结果之间的差异(～100秒~(-1)),认为SSP(标准稳定预测)程序对不稳定的驱动的研究和阻尼的研究方法不适用于内孔长径比小、有周向槽和多头端的发动机。对SSP程序中的增益和损失机理的考察表明:(1)槽的流动拐弯损失处理得不合理,(2)气体档板的阻尼被忽略了,(3)在常规的R_(VC)=常数的范围内,T型燃烧器速度耦合的数据不能应用到小长径比的发动机里。因而从以上三方面对小长径比的航天发动机的计算进行了修正,从而改善了理论与试验的一致性。     

一种多级火箭飞行方案设计的工程方法

提出了一种进行单级和多级火箭飞行方案设计的一般方法。这是一种基于微积分变分原理的工程方法。其目的是根据给定导弹的攻角方案设计其俯仰角方案。最大攻角的优化根据给定的初始设计值采用正交法进行。该方法可以快速地进行多级火箭的飞行方案设计。