陈乃兴先生的主要学术成就和对科技发展的重要贡献:隆重纪念陈乃兴先生逝世一周年

2019年8月6日是中国著名工程热物理学家陈乃兴先生逝世一周年的纪念日。从6个方面详细阐述了陈乃兴先生的主要学术成就和对科技发展的重要贡献。他一生献身祖国、献身科学研究的拼搏精神，将鼓舞大家砥砺奋进。     

Low-energy near Earth asteroid capture using Earth flybys and aerobraking

Since the Sun-Earth libration points L₁ and L₂ are regarded as ideal locations for space science missions and candidate gateways for future crewed interplanetary missions, capturing near-Earth asteroids (NEAs) around the Sun-Earth L₁/L₂ points has generated significant interest. Therefore, this paper proposes the concept of coupling together a flyby of the Earth and then capturing small NEAs onto Sun–Earth L₁/L₂ periodic orbits. In this capture strategy, the Sun-Earth circular restricted three-body problem (CRTBP) is used to calculate target Lypaunov orbits and their invariant manifolds. A periapsis map is then employed to determine the required perigee of the Earth flyby. Moreover, depending on the perigee distance of the flyby, Earth flybys with and without aerobraking are investigated to design a transfer trajectory capturing a small NEA from its initial orbit to the stable manifolds associated with Sun-Earth L₁/L₂ periodic orbits. Finally, a global optimization is carried out, based on a detailed design procedure for NEA capture using an Earth flyby. Results show that the NEA capture strategies using an Earth flyby with and without aerobraking both have the potential to be of lower cost in terms of energy requirements than a direct NEA capture strategy without the Earth flyby. Moreover, NEA capture with an Earth flyby also has the potential for a shorter flight time compared to the NEA capture strategy without the Earth flyby.     

基于CW方程的航天器追逃问题半直接求解方法

针对时间固定的两航天器追逃问题,提出一种以半直接配点法研究追逃双方最优控制策略的求解方法。航天器追逃问题是基于微分对策的追逃问题,该问题是含有追逐者和逃逸者控制变量的两点边值问题。若采用必要条件求解,则对迭代初值要求高,收敛困难。在两航天器均为连续小推力的假设条件下,以终端距离为支付函数,给出半直接配点法的求解过程。在此数值方法中,根据半直接转换将微分对策问题转化为最优控制问题,采用Gauss-Lobbato配点法将此最优问题最终转化为非线性规划问题,继而通过序列二次规划算法求解。这种半直接配点法避免了对微分对策问题最优策略的必要条件(两点边值问题)求解。采用该方法求解对迭代初值不敏感,且数值稳定性好。数值仿真实例验证了这种求解方法的可行性。该方法提高了求解两点边值问题的收敛性,为求解含有双方控制变量的微分对策问题提供了一种思路。     

敏捷成像卫星调度的改进量子遗传算法

针对敏捷成像卫星调度问题中解空间大,选择任务的搜索空间和确定任务观测时间的搜索空间分别是离散域和连续域的难题。建立了多种决策变量混合的敏捷成像卫星调度模型,提出一种改进的量子遗传算法对其求解,改进的量子遗传算法采用二进制与实数杂合的编码方式,降低染色体的基因位编码数目,提高了搜索效率,有效适应了敏捷成像卫星调度问题中离散与连续混合的解空间;以杂合编码为基础,设计对应的观测函数将敏捷成像卫星调度问题的解映射到相位空间,从而将量子优化机制引入敏捷成像卫星调度问题中,利用量子遗传算法在相位空间搜索的特性解决敏捷成像卫星解空间大、解空间离散与连续并存的问题。最后,通过不同规模的仿真校验对算法的调度效果进行测试和分析。结果表明,所提改进的量子遗传算法在收敛速度和方案收益方面都有较好的表现,能够满足敏捷成像卫星调度的需要。     

航天器交会两点边界值问题

从绝对运动和相对运动两方面讨论近地空间航天器交会中的两点边界值问题。其中，绝对运动涉及多圈Lambert问题，以Lagrange时间方程为研究工具，而相对运动Lambert问题应用C—W线性解。对圆轨道之间的双冲量转移，给定转移角与转移时间，研究最小变轨速度增量所对应的转移圈数与轨道参数的求解方法，提出满足最小变轨速度增量要求的多圈转移的工程图解法，并从工程应用出发，在飞行时间约束下，按最小速度增量要求，阐述航天器交会两点之间飞行轨道（轨迹）设计方法。这种方法将飞行轨迹划分为初始漂移段、轨道转移段与终端停泊段三部分，应用两点边界值问题的解，选择两次冲量机动时刻，使速度增量之和最小。模拟算例表明，这种方法对航天器交会设计是适用的、有效的。     

大学生道德状况与应对之策

本文在调查研究、综合分析的基础上对大学生的道德现状做出了明确判断:道德价值取向多元化,道德认知、道德情感主流健康向上;道德认知与道德行为脱节,价值判断模糊化,价值取向现实化、功利化,文化追求流行化、感性化、个性化,物质生活追求享乐化,科学精神淡泊化,性道德观念随意化。文章系统分析了大学生道德问题的成因,提出了应对之策。     

计算外壁热响应的非线性瞬态导热反问题方法

研究组合结构外壁热响应特性,采用Beck’s序列函数法,优化算法各个环节,建立应用多个温度测点、多个未来时间步的计算模型。文章通过假设热流变化呈三角波形,计算结构内部温度场,并取其中数点温度信息作为反问题输入条件迭代反演得到外壁热流响应,得到热流误差不超过0.5%、温度误差不超过0.01%的理想结果,并得到测点数量、位置等因素对计算误差的影响。该计算方法可应用于包装结构在模拟火灾等特殊环境中的外壁热响应研究。     

Effect of Variable Selection on Multidisciplinary Design Optimization： a Flight Vehicle Example

Different multidisciplinary design optimization (MDO) problems are formulated and compared. Two MDO formulations are applied to a sounding rocket in order to optimize the performance of the rocket. In the MDO of the referred vehicle, three disciplines have been considered,which are trajectory, propulsion and aerodynamics. A special design structure matrix is developed to assist data exchange between disciplines. This design process uses response surface method (RSM) for multidisciplinary optimization of the rocket. The RSM is applied to the design in two categories: the propulsion model and the system level. In the propulsion model, RSM deter-mines an approximate mathematical model of the engine output parameters as a function of design variables. In the system level, RSM fits a surface of objective function versus design variables. In the first MDO problem formulation, two design variables are selected to form propulsion discipline. In the second one, three new design variables from geometry are added and finally, an optimization method is applied to the response surface in the system level in order to find the best result. Application of the first developed multidisciplinary design optimization procedure increased accessible altitude (performance index) of the referred sounding rocket by twenty five percents and the second one twenty nine.     

Optimization Design System for Composite Structures Based on Grid Technology

To solve the topology optimization of complicated multi-objective continuous/discrete design variables in aircmit structure design, a Parallel Pareto Genetic Algorithm （PPGA） is presented based on grid platform in this paper. In the algorithm, the commercial finite element analysis （FEA） software is integrated as the calculating tool for analyzing the objective functions and the filter of Pareto solution set based on weight information is introduced to deal with the relationships among all objectives. Grid technology is utilized in PPGA to realize the distributed computations and the user interface is developed to realize the job submission and job management locally/remotely. Taking the aero-elastic tailoring of a composite wing for optimization as an example, a set of Pareto solutions are obtained for the decision-maker. The numerical results show that the aileron reversal problem can be solved by adding the limited skin weight in this system. The algorithm can be used to solve complicated topology optimization for composite structures in engineering and the computation efficiency can be improved greatly by using the grid platform that aggregates numerous idle resources.     

瞬态热应力问题的组合杂交有限元方法

求解瞬态热应力问题的杂交元方法面临Ladyshenskaya-Babuska-Brezzi(LBB)条件的检查,其稳定性难以保证,从而提出瞬态热应力问题的组合杂交有限元方法。建立瞬态热应力问题的基于区域分解的组合杂交变分原理及其有限元离散;通过数值算例验证求解瞬态热应力问题的组合杂交元的数值性能。结果表明:在大宽厚比网格下,八节点六面体组合杂交元(CHH(0-1))可以获得与二十节点六面体元(B20)精度相当的位移计算结果和更好的应力计算结果。