一种巡视器惯性/视觉组合导航新方法

在以运动参数误差为状态量、视觉导航与惯导导航相对运动参数差为观测量 的传统惯性/视觉组合导航方法中, 为解决相对运动参数同时与前后两个时 刻状态相关的问题, 采用将前一时刻位置和姿态误差增广到状态量中的方法, 并且假设增广的状态量为常值, 导致状态模型中引入了较大的误差. 基于 真实位置、姿态建立观测量误差模型, 导致观测量同时与前后两个时刻的状 态相关. 本文以惯导误差方程为状态模型, 采用四元数差形式的相对运动 参数差作为观测量, 基于上一时刻组合导航位置、姿态估计值建立观测量误 差模型, 实现了状态的增广, 并使得量测信息仅与当前时刻的位置误差和平 台失准角相关, 克服了状态模型误差较大的问题. 月面仿真和地面模拟实验 均表明, 该方法能够达到较高的位置和姿态估计精度.     

欧拉—庞卡莱方程在“和平号”太空站姿态恢复分析中的应用

1997年因"进步号"飞船与空间站对接时发生意外碰撞而使得姿态失去控制,从而导致太阳翼无法朝向太阳而获得能量。使用欧拉方法和四元数方法建立运动学方程,通过欧拉—庞卡莱方程建立动力学方程来分析其姿态恢复的运动过程,研究得出太阳翼能够重新得到光照的可行性方案。     

Consequences of the application of the streamer fluid model to the study of the sprite inception mechanism

We present the results of a streamer-fluid model used to investigate the electrodynamical coupling between the troposphere and upper atmosphere due to the penetration of lightning electric fields into the mesosphere and the lower ionosphere, generating sprites. The model solves the continuity equation for electrons and ions coupled to Poisson equation. The dominant physical response of the atmosphere is the formation of a screening-ionization wave. The wave shields the atmosphere above it from the action of the lightning field and, together with the conductivity reduction below it due to attachment, the wave amplifies the total field below it, allowing for the penetration of intense electric fields in the mesosphere as it propagates downwards into regions of higher density that compress the wave. This is the key physical mechanism for sprite inception. We evaluated the effects of the thundercloud charge geometry, lightning current waveshape, atmospheric conductivity, via different electron density profiles, and the effect of ionization, attachment and electron mobility coefficients in the electrical breakdown process, related to halo production, and sprite streamer initiation. The results showed that electrons with higher mobility are more efficient in shielding the lightning electric field before breakdown, causing delay, and they contribute to the formation of the streamer seed after breakdown, anticipating the sprite streamer inception. Similarly, a higher effective ionization rate, produced by modifications in the attachment and ionization coefficients, anticipates sprite inception. The simulations with 6 different electron density profiles, and therefore conductivities, spanning 4 orders of magnitude, showed that the altitude of breakdown and sprite initiation, as well as their time delays from the lightning discharge are directly related to atmospheric conductivity: higher conductivities produce halo and sprite inception at lower altitudes with longer delays and may hinder sprite formation. We document that variations of 30 times in the lightning current leads to sprite initiation altitudes in the range 66.0–73.5 km, with delays between 1.550 and 34.500 ms, while variations of 4 orders of magnitude in the conductivity profile lead to initiation altitudes 61.0–70.6 km, with delays in the range 3.825–9.825 ms. Consequently, we suggest that lightning characteristics dominate over atmospheric parameters in determining sprites’ initiation altitude and delay. The simulation of a −CG, with a constant current of 30 kA, did not produce a sprite seed, confirming an asymmetry in the response of the atmosphere to positive and negative lightning. This is due to the free electron drift direction that is away from the screening ionization wave, preventing the formation of the streamer seed for the great majority of −CGs. The same does not apply to halos, which depend on the occurrence of breakdown and can be produced by discharges of both polarities.     

Interaction of single-pulse laser energy with bow shock in hypersonic flow

Pressure sensing and schlieren imaging with high resolution and sensitivity are applied to the study of the interaction of single-pulse laser energy with bow shock at Mach 5. An Nd:YAG laser operated at 1.06 lm, 100 mJ pulse energy is used to break down the hypersonic flow in a shock tunnel. Three-dimensional Navier–Stokes equations are solved with an upwind scheme to simulate the interaction. The pressure at the stagnation point on the blunt body is measured and calculated to examine the pressure variation during the interaction. Schlieren imaging is used in conjunction with the calculated density gradients to examine the process of the interaction. The results show that the experimental pressure at the stagnation point on the blunt body and schlieren imaging fit well with the simulation. The pressure at the stagnation point on the blunt body will increase when the transmission shock approaches the blunt body and decrease with the formation of the rarefied wave. Bow shock is deformed during the interaction. Quasi-stationary waves are formed by high rate laser energy deposition to control the bow shock. The pressure and temperature at the stagnation point on the blunt body and the wave drag are reduced to 50%, 75% and 81% respectively according to the simulation. Schlieren imaging has provided important information for the investigation of the mechanism of the interaction.     

基于目标压力分布的旋翼先进气动外形反设计分析方法

基于雷诺平均Navier-Stokes（RANS）方程、运动嵌套网格、目标压力分布及余量修正方法,构建了一套直升机旋翼桨叶先进气动外形反设计方法。为避免由桨叶气动外形变化导致的网格畸变,发展了一套基于Poisson方程求解的旋翼桨叶结构化贴体正交网格的快速、自动化生成方法,为提高运动嵌套网格的生成质量和通用性,采用剖面间网格插值与桨尖翻折相结合的方法,同时建立了基于“Top Map”和“Inverse Map”相结合的洞边界划定和贡献单元搜寻的新方法。基于Navier-Stokes方程和双时间法建立了旋翼非定常流场模拟方法,通量求解采用Roe-MUSCL格式,并使用低速预处理法来克服前飞旋翼流场收敛中遇到的刚性问题。在计算流体力学（CFD）方法基础上,基于旋翼翼型压力系数余量联立各方位角处的反设计MGM（Modified Garabedia-McFadden）超定方程组,并依据激波分离、失速等约束设置了各方位角处的反设计权重系数,创建了基于MGM超定方程组最小二乘解的旋翼气动外形（翼型）设计方法。应用所建立的方法,分别针对多目标、多状态和前飞时的旋翼（翼型）气动外形进行反设计分析,验证了本文方法的有效性。最后,将该方法拓展应用到旋翼桨尖气动外形设计中,设计得到与UH-60A直升机旋翼气动特性相似的矩形桨叶外形。     

中心对称平面三连杆的同步运动

研究中心对称平面三连杆的运动.该模型是常见的力学系统,可以近似描述外层空间中弱引力条件下带有太阳能板的卫星的运动状况.然而,由于该系统是不可积系统,一般的运动状况比较复杂.在本文中对该模型建立Lagrange运动方程,主要研究其同步运动,求出同步运动的精确解,并分析其运动规律,证明了在一定条件下存在周期解.本文的结果为进一步研究该系统的在同步运动附近的复杂性打下了基础.      

实闭域计算的一个实用有效方法

在计算实践中,处理大型多项式时,由于复杂性原因,实闭域一阶理论判定方法实际上无效.因此寻找求解多项式方程与不等式组的有效方法(未必是判定方法)是符号计算中的重要问题.为解决这一问题,将Budan-Fourier 定理与Ritt-Wu 方法结合提出确定多项式方程实根和证明不等式的简单有效方法.尽管该方法不完备,但是在计算实践中发现这一方法对许多例子在计算上很有效.      

一种基于CW方程的交会远程导引终端误差分析新方法

直接采用轨道坐标系的相对位置和速度描述交会远程导引误差会产生误差放大的不合理现象,对远程导引误差的精确分析需寻求新的误差描述与分析方法。本文在算例分析的基础上提出了一种基于CW方程的远距离导引终端误差分析新方法,并利用该方法建立误差模型分析远程导引的误差分布与传播。分析结果表明基于CW方程的远程导引误差模型能较为准确地描述远程导引终端的误差状态和后续传播情况,适合在实际工程中用于描述远程导引终端精度指标。     

绕翼型低速湍流的数值模拟

采用求解低速流动的SIMPLE算法,用标准K-ε两方程模型、非线性K-ε两方程模型和一种改进的K-ε两方程模型来对绕两种翼型（A翼型和GAW-1翼型）在接近失速攻角情况下的低速湍流流动进行了数值模拟。计算结果表明,非线性K-ε两方程模型和改进的K-ε两方程模型较好地模拟出了翼型表面上的分离流动特性,较准确地预测出了分离点位置以及翼型的气动力系数,对翼型与机翼的工程设计具有一定的参考价值。     

Randomization method of deterministic equation for probability fracture mechanics

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