马尔科夫尼可夫规则机理的讨论

不对称烯烃与不对称试剂进行亲电加成反应时,遵守马尔科夫尼可夫规则,本文从生成碳正离子和环状高价正离子的两种反应途径对其反应机理加以讨论,并指出决定两种途径的主要因素.     

基于多项式近似的空间碎片群体轨道预报算法

快速准确地分析空间碎片群轨道演化行为对于其他在轨航天器碰撞规避至关重要。在各摄动力的作用下,空间碎片群演化运动呈现出复杂的非线性特征。空间碎片群体个体数量巨大,如果通过对空间碎片群中每个空间碎片进行轨道积分来分析群体预报的方法会导致计算量过大。针对该问题,提出一种基于多项式近似的轨道快速预报分析方法。该方法将空间碎片群分为少量的标称碎片和其他大量关联碎片。针对标称碎片的轨道预报采用数值积分求解保证预报精度;而针对其他大量的关联碎片轨道预报问题,采用多项式泰勒展开半解析方法求解,从而在保证预报精度的前提下有效减少空间碎片群轨道预报的计算量。为了验证方法的有效性,对不同空间碎片群进行了轨道预报仿真。仿真结果表明,当轨道预报精度设定在1m范围内时,多项式近似算法的计算量较蒙特卡洛方法计算效率提高了2.2~17.2倍,验证了所提出方法的有效性。     

Springback prediction of thick-walled high-strength titanium tube bending

Significant springback occurs after tube rotary-draw-bending （RDB）, especially for a high-strength Ti-3A1-2.5V tube （HSTT） due to its high ratio of yield strength to Young＇s modulus. The combination scheme of explicit and implicit is preferred to predict the springback. This simulation strategy includes several numerical parameters, such as element type, number of elements through thickness （NEL）, element size, etc. However, the influences of these parameters on spring- back prediction accuracy are not fully understood. Thus, taking the geometrical specification 9.525 mm × 0.508 mm ofa HSTT as the objective, the effects of numerical parameters on prediction accuracy and computation efficiency of springback simulation of HSTT RDB are investigated. The simulated springback results are compared with experimental ones. The main results are： （1） solid and continuum-shell elements predict the experimental results well; （2） for C3DSR elements, NEL of at least 3 is required to obtain reliable results and a relative error of 29% can occur as NEL is varied in the range of 1-3; （3） specifying damping factor typically works well in Abaqus/Emplicit simulation of springback and the springback results are sensitive to the magnitude of damping factor. In addition, the explanations of the effect rules are given and a guideline is added.     

铍仪表零件精加工后微细毛刺去除方法探析

航天产品对零件毛刺的去除要求极高.零件在精加工过程中会产生微细毛刺和材料堆积现象.这种现象对零件的尺寸检测、装配生产等都会产生不良影响.铍材作为惯性仪表零件的重要材料,其材料特性给去除毛刺带来了新的困难.我们经过大量的实验和摸索,找到了几种有效的铍仪表零件毛刺去除方法.同时在工艺文件中对具体零件的具体去毛刺方法及操作时...     

轨道误差对星敏感器对地指向精度的影响分析

针对使用星敏感器进行对地指向精度问题,分析了影响卫星对地指向精度的主要因素,根据卫星轨道误差,推导了轨道根数误差对经度方向和纬度方向上的指向误差方程.分析了轨道根数对指向精度的影响规律.最后对轨道根数误差的影响进行了仿真,仿真结果与分析结果一致.     

Walker星座摄动分析与保持控制策略

针对运行在中高轨道上的全球Walker星座的构形长期保持控制问题,通过分析星座卫星的轨道摄动及构形相对漂移,研究了星座构形长期保持的控制方法及控制策略.对于星座构形的保持,研究了星座构形摄动补偿法,提出了星座构形数值微分修正法.最后给出了全球星座构形长期保持控制策略并进行了仿真验证,仿真分析表明,星座构形数值微分修正法比构形摄动补偿法具有更高的控制计算精度.     

基于滤波算法的拟平均轨道根数自主实时确定方法

针对卫星长期自主运行的发展要求,首次提出了基于滤波算法的卫星自主计算拟平均轨道根数的在轨实时方法。首先以受地球非球形摄动影响的低轨卫星为研究对象,推导了拟平均轨道根数的变化率并考虑了J2平方项补偿;以拟平均轨道根数为状态变量并以卫星瞬时速度和位置作为观测量建立了滤波方程,然后分别应用平方根无迹卡尔曼滤波(SR UKF)和扩展卡尔曼滤波(EKF)对拟平均轨道根数进行估计。仿真结果表明,两种滤波方法均能有效地计算拟平均轨道根数,其中平方根UKF滤波具有更高的精度和稳定度,且都可以满足卫星在轨自主实时计算拟平均轨道根数的需求。     

轨道轰炸飞行器过渡段轨道设计与制导

针对轨道轰炸飞行器(OBV)的过渡段轨道设计与制导技术进行了讨论.在初始点位置、再入点位置和再入角固定的前提下,根据冲量假设和二体理论设计了固定时间转移轨道,其实质在于制动点位置和制动速度的确定.为了消除设计偏差,提出了一种基于虚拟再入点补偿的有限推力制导方案,并简要分析了关机点参数的选取原则.对于耗尽关机的动力系统,通过运用能量管理技术实现了多余燃料的耗散.仿真结果验证了上述方法的有效性.     

Direct Optimization of Low-thrust Many-revolution Earth-orbit Transfers

Low-thrust Earth-orbit transfers with 10^?5-order thrust-to-weight ratios involve a large number of orbital revolutions which poses a real challenge to trajectory optimization. This article develops a direct method to optimize minimum-time low-thrust many-revolution Earth-orbit transfers. A parameterized control law in each orbit, in the form of the true optimal control, is proposed, and the time history of the parameters governing the control law is interpolated through a finite number of nodal values. The orbital averaging method is used to significantly reduce the computational workload and the trajectory optimization is conducted based on the orbital averaging dynamics expressed by nonsingular equinoctial elements. Furthermore, Earth's shadowing and perturbation effects are taken into account. The optimal transfer problem is thus converted to the parameter optimization problem that can be solved by nonlinear programming. Taking advantage of the mapping between the parameterized control law and the Lyapunov control law, a technique is proposed to acquire good initial guesses for optimization variables, which results in enlarged convergence domain of the direct optimization method. Numerical examples of optimal Earth-orbit transfers are presented.