第三届深空轨道设计竞赛冠军团队方法与结果

介绍了2011年第3届全国深空轨道设计竞赛冠军团队中科院空间应用工程与技术中心（筹）的设计方法与结果.设计方法包括总体设计思路、小推力转移轨道优化方法、小推力轨道简化模型、行星引力辅助序列设计、小行星搜索方法等.给出了具体设计步骤以及初步和最终的设计结果.最后,总结了从此次设计过程中获得的若干经验与启示.     

一般形式的共振轨道研究

为了利用较小的推力使航天器的轨道产生较大的变化,可以利用共振原理来研究航天器的运动,称这样一类非开普勒轨道为共振轨道.将圆频率作为变量,通过合理地选择轨道描述参数、时间尺度和推力描述方式建立了一般形式的共振轨道模型,并基于仿真分析研究了共振轨道圆频率对共振轨道的影响.通过对地球-火星共振转移轨道的算例进行仿真分析,初步研究了共振轨道在星际探测轨道设计中应用的效果.研究结果表明:圆频率改变将对推力峰值产生影响;共振轨道在星际探测中的应用是可行的,并且在能量消耗方面优于Lambert轨道.     

一种改进的轨道动力学模型

航天器的矢径可以分解为矢径模和单位矢量的乘积,利用该性质将传统轨道动力学方程分解为矢径模和矢径方向的动力学方程组,实现了航天器位置信息的分离;针对两个方程分别采用常数变易法和四元数描述方法,将轨道动力学模型转化为线性无奇异的方程组,同时得到了7 个新轨道变量,且建立了新轨道变量与惯性系下航天器位置速度信息以及轨道六要素之间的相互转换关系. 该轨道模型适用于任意形式的推力和摄动,避免了奇异性,且在虚拟时间的意义下,航天器的旋转角速度只取决于法向力;在常值推力和变推力的情况下,对该模型进行了数值验证,验证了新模型的可适用性、数值稳定性以及计算精度高的优势.      

XNAV/UVNAV/SINS组合导航在航天器轨道机动中的应用

针对X射线脉冲星导航在航天器轨道机动过程中精度不高甚至发散的问题,提出一种将X射线脉冲星导航结合惯性导航和紫外敏感器的组合导航方法。以航天器在惯性系中的位置、速度、姿态四元数和惯性导航设备误差作为系统状态变量,用X射线探测器测量X射线脉冲到达时间,用紫外敏感器测量中心天体质心相对于航天器的方向矢量和距离以及航天器在惯性系中的姿态四元数,用扩展卡尔曼滤波器估计组合导航系统状态。仿真结果验证了该组合导航方法的可行性,能够解决轨道机动中X射线脉冲星单独导航的误差过大(位置误差达107m)问题,且该组合导航具有较高的导航精度,在轨道机动前、机动中和机动后导航位置误差均在100 m以内。     

卫星编队构型设计与轨道机动算法优化

卫星编队与轨道机动是完成在轨监视与捕获等空间任务的关键技术。针对追踪航天器在相对目标航天器的绕飞过程中特殊构型的编队飞行问题,提出了三种特殊的编队构型机动方案;针对近距离轨道逼近问题,分析了同平面轨道变轨策略和轨道转移能耗最优化问题,在此基础上给出了三脉冲升降轨机动方法,并可以根据需要将其扩展为N脉冲机动。以目标星运行轨道高度780 km为例进行仿真分析,结果表明平行四边形编队中追踪星在各交点处完成变轨所需的速度脉冲向量分别为0.1172m/s、0.1843 m/s,而花形编队和菱形编队中追踪星在各交点处完成变轨所需的速度脉冲向量均为0.1978m/s,从而验证了所提出方法的有效性。     

气动力辅助变轨的数值模拟

采用了航天器在行星上层大气中进行高超声速飞行时的轨道动力学方程,针对航天器从地球静止轨道转移到一个共面圆形低地轨道的变轨过程,进行了气动力辅助变轨过程的模拟.在变轨过程中,航天器从地球静止轨道开始,经过8次大气路径,耗时43.7小时,到达圆形低地轨道,与霍曼转移进行对比,其所消耗的推进剂质量仅为霍曼转移的41%.研究结果表明:气动力辅助变轨技术能够在降低推进剂消耗的情况下实现航天器的轨道转移.     

木卫停泊轨道间低耗能小推力转移轨道设计方法研究

对木卫停泊轨道间的低耗能小推力转移轨道设计方法进行了研究,提出基于"类halo轨道截面"法的低耗能转移轨道参数化方法和基于配点法的多体Lambert问题求解算法,并利用全局优化算法得出了燃耗最少的初步优化结果;利用多体同伦法和固定近心点高度的多圈转移控制律得到了各段小推力转移轨道的有效设计结果.所提方法同样适用于其他天体间的转移轨道设计,为多体环境下低耗能小推力转移轨道提出了新的设计思路和方法.     

不规则小行星引力场内的飞行动力学

小行星探测是当前深空探测的主要方向之一,具有重要的科学意义.绝大多数小行星引力场极不规则,探测器在小行星附近运动形态复杂多样.由于同时受到中心引力、快速自旋的不规则形状摄动力、以及光压摄动等作用,探测器容易与小行星发生碰撞或逃逸.概述小行星研究现状和不规则引力场建模方法.重点介绍不规则引力场内动力学特性,包括引力平衡点、局部流形、自然周期轨道和悬停探测轨道等,尝试提出新的研究方向.     

AN ALGORITHM FOR SOLVING SPACECRAFT REACHABLE DOMAIN WITH SINGLE-IMPULSE MANEUVERING 1)

航天器轨道机动可达域是表征其在未来时间可能到达空间位置集合的有效方式,对维护航天器在轨安全、改善空间态势感知能力具有重要意义.现有关于可达域计算的方法仍然存在模型复杂、初值敏感性高导致计算效果较差等缺点,因此有必要发展更加简洁有效的可达域包络求解算法.本文基于近心点坐标系建立了基于未来可达位置矢量极值求解的可达域求解模型,首先定义任意指向的矢量描述方法并给出未来该指向位置是否可达的判据;其次,设置转移轨道面内机动方位角,将可达域求解问题转化为当前可达位置矢量方向的单变量极值求解问题,利用极值点处可达域包络面函数梯度需为零的条件确定转移轨道面机动方位角的取值,从而确定航天器的轨道机动可达域;此外根据二体轨道动力学特性,利用包络的对称性减少可达域求解计算量;最后通过蒙特卡洛打靶仿真对提出的可达域求解方法进行仿真验证.结果表明,本文方法对航天器单脉冲轨道机动可达域的计算结果与蒙特卡洛打靶仿真吻合良好,模型更加简洁且计算精度优于现有方法.     

地球-火星引力辅助下的地-火无动力循环轨道

针对火星探测任务,提出一种地?火无动力循环轨道设计方法.该方法有望实现火星探测的自由返回,井能够多次无动力地火往返.本文首先求解地火之间转移的Lambert问题,考虑地球和火星引力辅助效应,井分别给出以地球和火星为中心的半圈转移轨道.其次,以该轨道作为辅助轨道,设计搜索能够实现无动力循环的发射窗口和转移轨道.最后,本文...     

Numerical study of rowing hydrofoil performance at low Reynolds numbers

In this paper, the hydrodynamic performance of a 2-D flat-plate hydrofoil in rowing motion is numerically studied by a Cartesian grid method with the cut-cell approach. Adaptive mesh refinement is used to save on the number of mesh cells without harming spatial resolution in critical regions. The rowing kinematics of the hydrofoil is the same for all simulations in this work. The design parameters studied are the reduced frequency of the rowing motion, the heave amplitude, and the time lags of the feathered-to-broadside rotation and the broadside-to-feathered rotation. Results show that larger thrust and efficiency can be attained if the feathered-to-broadside rotation is started right after the beginning of the power stroke and the broadside-to-feathered rotation is finished right before the end of the power stroke. Finally, both the thrust and the efficiency increase with Reynolds number.     

Planning and control of 3-D nano-manipulation

The use of atomic force microscope (AFM) as a nanomanipulator has been evolving for various kinds of nano-manipulation tasks. Due to the bow effect of the piezo scanner of the AFM, the AFM space is different from the Cartesian space. Traditional nanomanipulation based on AFM is only a 2-D operation and does not consider the bow effect of the piezotube. In this paper, different 3-D nanomanipulation tasks using AFM such as nanolithography, pushing and cutting have been discussed. 3-D path planning is performed directly in the AFM space and the 3-D paths are generated based on the 3-D topography information of the surface represented in the AFM space. This approach can avoid the mappings between the AFM space and Cartesian space in planning. By following the generated motion paths, the tip can either follow the topography of the surface or move across the surface by avoiding collision with bumps. Nanomanipulation using this method can be considered as the “true“ 3-D operations since the cantilever tip can be controlled to follow any desired 3-D trajectory within the range of AFM space. The experimental study shows the effectiveness of the planning and control scheme.     

基于径向基函数配点法的梁板弯曲问题分析

采用径向基函数配点法分析考虑剪切效应的梁板弯曲问题,该方法利用径向基函数作为近似函数,基于配点法离散方程,通过最小二乘法求解。径向基函数配点法在离散和计算过程中不需要任何形式的网格划分,是一种真正的无网格法;径向基函数可以用一元函数来描述多元函数,存在明显的储存和运算简单的特点;而基于配点法求解不需要积分,提高了计算效率。分析考虑剪切效应的薄梁板问题时,传统的有限元法或无网格法求解均会存在剪切锁闭问题,而径向基函数在全域内存在无限连续性,能够准确地满足Kirchhoff约束条件,因此径向基函数配点法能够消除剪切锁闭现象,而且不会出现应力波动。该方法的优势在于,其不仅易于离散、精度高,而且具有指数收敛率,计算效率高。数值算例验证了上述结论和该方法的稳定性。     

On optimization of many-revolution low-thrust orbit transfers: Part 1

The paper proposes a numerical approach to the problem of optimal control of low-thrust spacecraft in a strong central gravity field. The approach employs the solution of the averaged equations of optimal motion. For an optimal variable-thrust maneuver, it is shown that quasioptimal trajectories are close to the averaged ones. It is established that in the case of constant thrust, the averaged solutions can be used as a satisfactory first approximation for finding a quasioptimal solution by minimizing the discrepancy at the right end of the trajectory __________ Translated from Prikladnaya Mekhanika, Vol. 44, No. 7, pp. 110–119, July 2008.     

THREE-DIMENSIONAL MODELING FOR THIN PLATE-LIKE STRUCTURES INCLUDING SURFACE EFFECTS BY USING STATE SPACE METHOD

<正>A three-dimensional(3-D)approach based on the state space method is proposed to study size-dependent mechanical properties of ultra-thin plate-like elastic structures considering surface effects.The structure is modeled as a laminate composed of a bulk bounded with upper and bottom surface layers,which are allowed to have different material properties from the bulk layer.State equations,including the surface properties of the structure,can be established on the basis of 3-D fundamental elasticity to analyze the size-dependent static characteristics of the thin plate-like structure.Compared with two-dimensional plate theories based size-dependent models for thin film structures in literature,the present 3-D approach is exact,which can provide benchmark results to assess the accuracy of 2-D plate theories and various numerical approaches. To show the feasibility of the proposed approach,a 3-D analytical solution for a simply supported plate-like thin structure including surface layers is derived.An algorithm is proposed for the calculation of the state equations obtained to ensure that the numerical results can reveal the surface effects clearly even for extremely thin surface layers.Numerical examples are carried out to exhibit the surface effects and some discussions are provided based on the results obtained.     

PRECISE INTEGRAL ALGORITHM BASED SOLUTION FOR TRANSIENT INVERSE HEAT CONDUCTION PROBLEMS WITH MULTI-VARIABLES

IntroductionIHCPs (InverseHeatConductionProblems)arecloselyassociatedwithmanyengineeringaspects,andwelldocumentedintheliteratures,coveringtheidentificationsofthermalparameters[1,2 ],boundaryshapes[3],boundaryconditions[4 ]andsource_relatedterms[5 ,6 ]etc .Howeveritseemsthatonlylittleworkisdirectlyconcernedwithmulti_variablesidentificationsbyauthors’knowledge.Tsengetal.presentedanapproachtodeterminingtwokindsofvariables[7],butonlygavefewnumericalexamplestodeterminethemsimultaneously .Thesol…     

吸气式激光推进推力产生机理的数值模

采用二阶精度的Roe格式，分别采用完全气体模型和高温平衡气体模型，对激光引致的激波在流场中的传播以及轴对称激光推力器的推力产生过程进行了数值模拟，揭示了大气吸气模式激光推进的推力产生机理。结果表明，采用高温平衡气体模型可以更精确地模拟等离子体流场的演化过程，计算所得的冲量耦合系数与已有实验结果吻合较好。     

Theoretical analysis of non-probabilistic reliability based on interval model

The aim of this paper is to propose a theoretical approach for performing the nonprobabilistic reliability analysis of structure.Due to a great deal of uncertainties and limited measured data in engineering practice,the structural uncertain parameters were described as interval variables.The theoretical analysis model was developed by starting from the 2-D plane and 3-D space.In order to avoid the loss of probable failure points,the 2-D plane and 3-D space were respectively divided into two parts and three parts for further analysis.The study pointed out that the probable failure points only existed among extreme points and root points of the limit state function.Furthermore,the low-dimensional analytical scheme was extended to the high-dimensional case.Using the proposed approach,it is easy to find the most probable failure point and to acquire the reliability index through simple comparison directly.A number of equations used for calculating the extreme points and root points were also evaluated.This result was useful to avoid the loss of probable failure points and meaningful for optimizing searches in the research field.Finally,two kinds of examples were presented and compared with the existing computation.The good agreements show that the proposed theoretical analysis approach in the paper is correct.The efforts were conducted to improve the optimization method,to indicate the search direction and path,and to avoid only searching the local optimal solution which would result in missed probable failure points.     

两串列扑翼的相位差对平均推力影响机理的实验研究

在一个低雷诺数的循环水洞中,实验研究了前后翅翼之间的相位差对两串列扑翼平均推力的影响.利用一个三分量的Kistler 压力传感器来测量扑翼的瞬时力;利用一个数字粒子测速仪系统(TSI DPIV) 来测量扑翼的前缘涡以及其周围的流场. 当相位差从0° 增加到360°,前翅的平均推力随着相位差正弦变化;前翅平均推力的增加是由于后翅的前缘涡和滞止区域增加了前翅的有效攻角. 后翅平均推力曲线有一个明显的V 字形低谷.低谷处较小的平均推力是由于前翅的脱落涡抑制了后翅前缘涡的形成并且减小了其有效攻角.当间距为0.5倍弦长相位差约为290°时,前后翅翼平均推力系数的合值能达到最大值0.667,明显大于两倍的单翼平均推力系数(2×0.255).      

区间模型非概率可靠性全局最优解

考虑到实际工程中大量存在不确定性因素,将结构中不确定参数描述为凸集变量的一种特殊情况－区间变量,根据区间模型可靠性指标的定义,采用解析方法进行非概率可靠性全局分析。为避免可能失效点遗漏,解析分析从二、三维开始,对平面和空间进行区域划分,根据极限状态函数的形式,指出了可能失效点依赖于极限状态函数的极值点和根植点。通过简单的量值比较,即可确定最可能失效点,进一步可求得可靠性指标。将低维分析方法推广到n维情况,给出了n维空间中用于计算极值点和根植点方程的数量,能够有效避免发生可能失效点遗漏现象,对优化搜索具有指导意义。针对两类算例进行求解,并与已有结果比较,验证了本文解析方法的正确性。