用于质量特性参数测量的新型气浮扭摆台

常规扭摆台采用滚动轴承和扭杆振动结构,纵向尺寸大、测量精度低、抗倾覆力矩小,不能满足质量特性参数综合试验台的要求,必须对其进行结构的分析和优化。本文提出交叉弹簧板结构替换扭杆,减少了扭摆台纵向尺寸,分析和实验表明该结构具有和扭杆相同的振动效果。将滚动轴承替换为气浮轴承,提高了抗倾覆力矩,测量精度最高达0.1%;采用有限元法对柱坐标系下修正的雷诺方程进行仿真计算,研究气浮轴承结构参数对承载能力和抗倾覆力矩的影响规律,确定了给定轴承外径下的最优几何参数。实验表明,改进的试验台提高了测量精度和振动稳定性,对卫星等飞行体质量特性参数的测量有重要的意义。     

粘接剂对摆部件影响分析

石英摆部件装配中,通常使用粘接剂实现石英摆片与力矩线圈骨架的定位与粘接。不同粘接剂具有不同的粘接特性,不同的粘接特性对摆部件的影响也不相同。对4种常用粘接剂的粘接特性进行了测试,并对4种粘接剂对摆部件应力的影响进行了仿真分析,相关测试数据和仿真结果均表明,不同类型粘接剂的粘接特性有明显差异,对摆部件应力的影响也呈现出不同规律。综合来看,在0℃~80℃的加速度计工作温度范围内,6101型粘接剂的粘接特性最佳,对摆部件应力的影响也最小。     

Failure mechanisms of bolted flanges in aero-engine casings subjected to impact loading

In this paper, a failure evaluation criterion was proposed for the bolted casing-flange structure under impact loading. Subsequently, ballistic tests with eighteen bolted casing-flange structure specimens were conducted to validate the failure evaluation criterion. Parameter studies were then carried out using the validated FE models. Both the experimental and numerical results demonstrated the accuracy of the failure evaluation criterion. The failure evaluation criterion provided a quick and easy way to determine the failure mode of the casing connection area by using the materials and dimensions of the structure. Based on the failure evaluation criterion, designing the structural failure mode of the bolted casing-flange structure to be between flange failure and bolt failure can improve the impact resistance of the connection area of the aero-engine casings. This investigation revealed that the impact failure is not the unique criterion in evaluating the containment of the casing connection area, structural failure should also be involved in the evaluation criteria.     

Multiobjective genetic optimization of Earth–Moon trajectories in the restricted four-body problem

In this paper, optimal trajectories of a spacecraft traveling from Earth to Moon using impulsive maneuvers (ΔV maneuvers) are investigated. The total flight time and the summation of impulsive maneuvers ΔV are the objective functions to be minimized. The main celestial bodies influencing the motion of the spacecraft in this journey are Sun, Earth and Moon. Therefore, a three-dimensional restricted four-body problem (R4BP) model is utilized to represent the motion of the spacecraft in the gravitational field of these celestial bodies. The total ΔV of the maneuvers is minimized by eliminating the ΔV required for capturing the spacecraft by Moon. In this regard, only a mid-course impulsive maneuver is utilized for Moon ballistic capture. To achieve such trajectories, the optimization problem is parameterized with respect to the orbital elements of the ballistic capture orbits around Moon, the arrival date and a mid-course maneuver time. The equations of motion are solved backward in time with three impulsive maneuvers up to a specified low Earth parking orbit. The results show high potential and capability of this type of parameterization in finding several Pareto-optimal trajectories. Using the non-dominated sorting genetic algorithm with crowding distance sorting (NSGA-II) for the resulting multiobjective optimization problem, several trajectories are discovered. The resulting trajectories of the presented scheme permit alternative trade-off studies by designers incorporating higher level information and mission priorities.     

GBI反设计中的基本诸元快速装订技术研究

针对GB I反设计过程中的基本诸元快速装订问题,首先,应用牛顿迭代法进行惯性系中变发射点的单GB I基本诸元计算方法研究,在针对拦截窗口进行分析的基础上,讨论了牛顿迭代法的公式推导和使用过程中涉及到的诸元插值算法。其次,研究了多GB I的基本诸元优化策略问题。最后,研究了GB I基本诸元软件的实现技术,通过对GB I拦截窗口内插值表格生成流程、基本诸元快速计算流程、多对多诸元优化计算流程等进行详细的分析,给出了基本诸元快速装订软件的完整实现框架。     

基于隶属云发生器的智能控制

阐述一种利用隶属云发生器实现智能控制的方法。其控制策略是通过语言值构成规则,从而形成一种直观推理方法。它不要求给出被控对象精确的数学模型,仅仅依据人的经验、感觉和逻辑判断,将人用语言值定性表达的控制经验,通过语言原子和云模型转换到语言控制规则器中,就能解决非线性问题和不确定性问题。基于此理论控制倒立摆获得比较好的效果,结果表明,该方法对被控对象的状态和参数变化具有较强的鲁棒性。     

三维充液航天器的位置和姿态联合控制

考虑充液月球着陆器悬停避障阶段的控制问题,采用三维球摆作为液体晃动部分的等效模型.针对球摆与刚体耦合的三维动力学模型,给出动力学模型的矢量方程及各矢量在本体系的投影坐标,设计位置和姿态联合控制器.所设计的控制器可以稳定航天器刚体的位置和姿态,且只依赖刚体的位置和姿态,不依赖晃动角或者动力学方程,利于工程应用.利用LaSalle不变原理分析闭环系统的稳定性,给出期望姿态为竖直时系统渐近稳定的控制器参数选择依据.最后数值仿真验证控制方法的有效性.     

一种新的辊轴型摩擦摆隔振系统运动微分方程的推导

应用多体动力学理论研究了一种新的辊轴型摩擦摆隔振系统。基于该系统的运动学规律,将其简化为一个单自由度多体系统。应用非惯性系中微分形式的质点系相对动能定理,推导出该系统的非线性运动微分方程。通过讨论与小角位移无阻尼情形对应的线性无阻尼自由振动微分方程,得到了相应的固有频率,与实验结果一致。直接求解该运动方程可有效准确地研究摩擦摆隔振系统的动力学行为,并给包含该系统的半主动控制的仿真和实现带来便利。     

旋转倒立摆的神经网络控制

本文针对一种新型的倒立摆系统,设计了一个四输入单输出三层BP网络,并对一级旋转倒立摆控制器进行逼近.仿真结果表明,BP神经网络有很广阔的应用领域.     

Estimation of ballistic coefficients of space debris using the ratios between different objects

This paper proposes a new method to estimate the ballistic coefficient (BC) of low earth orbit space debris.The data sources are the historical two-line elements (TLEs).Since the secular variation of semi-major axes is mainly caused by the drag perturbation for space objects with perigee altitude below 600 km,the ballistic coefficients are estimated based on variation of the mean semi-major axes derived from the TLEs.However,the approximate parameters used in the calcu lation have error,especially when the upper atmosphere densities are difficult to obtain and always estimated by empirical model.The proportional errors of the approximate parameters are cancelled out in the form of ratios,greatly mitigating the effects of model error.This method has been also been validated for space objects with perigee altitude higher than 600 km.The relative errors of esti mated BC values from the new method are significantly smaller than those from the direct estimation methods used in numerical experiments.The estimated BC values are used for the prediction of the semi-major axes,and good performance is obtained.This process is also a feasible method for prediction over a long period of time without an orbital propagator model.