基于抱爪式对接机构捕获缓冲系统动力学仿真研究

现有在轨服务的对接机构由于其尺寸大、结构复杂、对接目标单一等局限性因素,无法很好地为后续我国探月工程任务提供有力支撑,且受限于运载能力,对接机构的轻量化也是必不可少的一项环节.为研究可服务于未来月球空间站以及载人登月等高轨道任务的对接机构,设计了一种新型抱爪式对接机构,其采用异体同构周边式构型,可以实现主/被动飞行器之间的互换.利用 V 型槽与爪钩等结构部件实现飞行器对接过程中的捕获以 及能量消耗功能,从而实现两飞行器之间的稳固联接.该对接机构具备尺寸小、重量轻、结构简单、功能易实现等优势. 对其捕获缓冲系统进行了动力学分析,计算了缓冲元器件的参数对其捕获性能的影响,在 ADAMS 完成了数字虚拟样机的建立,结合实际两种典型的对接初始条件工况进行了仿真研究.研究结果表明,两种工况下的对接过程能量消耗满足设计要求,能够以较小的 V 型槽的碰撞力完成捕获,结果证明了捕获缓冲系统的可行性以及该构型对接机构具备较好实现任务的能力.      

基于有限时间收敛的双臂空间机器人捕获卫星主动对接力/位姿阻抗控制

针对双臂空间机器人捕获卫星主动对接力/位姿阻抗控制进行了研究.为防止捕获过程中机械臂末端执行器与卫星接触、碰撞时产生的冲击载荷对机器人关节造成冲击破坏,在各关节电机与机械臂之间加入了一种弹簧阻尼缓冲机构.该机构可通过弹簧实现冲击力矩的卸载,阻尼器则用于因弹簧引起的柔性振动的抑制.为解决捕获过程中的非完整动力学约束及捕获后混合体系统的协调控制问题,结合牛顿第三定律、捕获点的速度约束及闭链几何约束,获得捕获后混合体系统的动力学方程,且通过动量守恒关系计算碰撞冲击效应与碰撞冲击力.通过分析对接装置在载体坐标系下的运动学关系,建立对接装置相对载体的运动雅可比矩阵,并基于此建立基于力的二阶线性阻抗模型,实现对接装置输出力的精确控制.考虑到主动对接操作过程要求控制器具有收敛速度快,控制精度高的特点,通过结合终端滑模与超扭滑模的特点,提出一种非奇异快速终端滑模阻抗控制策略.该策略即能实现主动对接操作中位姿与输出力的快速响应,又能有效地抑制滑模的抖振以保证控制精度.通过Lyapunov定理证明系统的稳定性;利用数值模拟验证缓冲装置的抗冲击性能及所提阻抗控制策略的有效性.     

Design and mobility evaluation of tracked lunar vehicle

Past lunar vehicles have had difficulty traveling through soft sand areas due to the thick, soft and dry regolith. This paper describes the design and evaluation results of a tracked lunar vehicle which aims at achieving greater mobility, particularly improved climbing ability on pure sand slopes, by reducing contact pressure with a crawler link. The tracked vehicle uses mesh crawler links to reduce complexity, weight and parts count. Single-crawler tests on simulated lunar soil revealed that the crawler’s slip ratio was lower than that of a rigid wheel at any slope angle, and that its power consumption was lower than that of a wheel on slopes of 10° or more. Furthermore, the crawler’s slip ratio was stable or decreasing along the traveling distance on steep slopes, contrary to the wheel. Our tracked lunar vehicle, the “Light Crawler”, is equipped with four such mesh-crawlers, each of which is independently driven and steered. It is intended to realize high climbing ability, a small turning circle, and an obstacle-crossing capability using a unique suspension system. The vehicle’s climbing and obstacle-crossing capabilities were tested on both simulated lunar soil and a rock-scattered field, and its mobility performance was successfully confirmed.     

Design and characterization of GRC-1: A soil for lunar terramechanics testing in Earth-ambient conditions

Earth experiments must be carried out on terrain that deforms similarly to the lunar terrain to assess the tractive performances of lunar vehicles. Most notably, terrain compaction and shear response underneath the lunar vehicle wheels must represent that of the Moon. This paper discusses the development of a new lunar soil simulant, Glenn Research Center lunar soil simulant #1 (GRC-1), which meets this need. A semi-empirical design approach was followed in which the soil was created by mixing readily available manufactured sands to a particle size distribution similar to the coarse fraction of lunar soil. By varying terrain density, a broad range of in situ cone penetration measurements collected by the Apollo mission astronauts can be replicated. An extensive set of characterization data is provided in this article to facilitate the use of this material. For reference, the index and geotechnical properties of GRC-1 are compared to the lunar soil and existing lunar soil simulants.     

基于摇臂——转向架结构月球车的越障能力判断准则

对轮式移动系统进行越障分析时,常以垂直越障作为评价标准.但是,月球车在凹凸不平的月面上行驶时,垂直越障模型不具有一般性.为此,本文对基于摇臂-转向架结构月球车在任意路面的越障进行了研究.一般情况下,由于任意路面越障模型相对复杂,可以建立的独立平衡方程数目少于未知变量数,因此无法得到越障能力与路面参数的函数关系式.针对上述问题,文中将最大有效牵引力假设引入越障模型中,得到了一种任意路面越障能力的判断准则.通过算例分析,表明了所提方法的有效性.     

基于柔性机构捕捉卫星的空间机器人动态缓冲从顺控制

研究了空间机器人在轨捕获非合作卫星过程避免关节受碰撞冲击破坏的缓冲从顺控制问题, 为此在机械臂与关节电机之间配置了一种柔性机构, 其作用在于: (1)在接触、碰撞阶段可通过其内置弹簧的变形来吸收被捕获卫星对空间机器人关节产生的冲击力矩; (2)在镇定运动阶段, 结合与之配合的缓冲从顺控制策略来适时开、关关节电机, 以保证关节受到的冲击力矩受限在安全范围. 首先, 利用多刚体系统理论获得配置柔性机构空间机器人及目标卫星分体系统动力学方程; 之后, 结合整个系统动量守恒关系, 捕获操作后系统运动几何关系及力的传递规律, 建立了两者形成联合体系统的动力学方程, 并计算了碰撞过程的冲击效应与冲击力. 为了实现失稳联合体系统的镇定控制, 提出了一种基于动态面的缓冲从顺控制方案. 上述控制方案可在实现吸收捕获操作产生的冲击力矩的同时, 还能在冲击力矩过大时适时开启、关闭关节电机, 以避免关节电机发生破坏; 此外, 动态面的引入避免了反演法存在的计算膨胀问题, 有效减少了计算量. 基于Lyapunov函数法证明了系统的稳定性, 并通过系统数值仿真结果验证了上述缓冲从顺控制策略的正确性.      

BUFFER AND COMPLIANT DYNAMIC SURFACE CONTROL OF SPACE ROBOT CAPTURING SATELLITE BASED ON COMPLIANT MECHANISM$^{\bf 1)}$

研究了空间机器人在轨捕获非合作卫星过程避免关节受碰撞冲击破坏的缓冲从顺控制问题, 为此在机械臂与关节电机之间配置了一种柔性机构, 其作用在于: (1)在接触、碰撞阶段可通过其内置弹簧的变形来吸收被捕获卫星对空间机器人关节产生的冲击力矩; (2)在镇定运动阶段, 结合与之配合的缓冲从顺控制策略来适时开、关关节电机, 以保证关节受到的冲击力矩受限在安全范围. 首先, 利用多刚体系统理论获得配置柔性机构空间机器人及目标卫星分体系统动力学方程; 之后, 结合整个系统动量守恒关系, 捕获操作后系统运动几何关系及力的传递规律, 建立了两者形成联合体系统的动力学方程, 并计算了碰撞过程的冲击效应与冲击力. 为了实现失稳联合体系统的镇定控制, 提出了一种基于动态面的缓冲从顺控制方案. 上述控制方案可在实现吸收捕获操作产生的冲击力矩的同时, 还能在冲击力矩过大时适时开启、关闭关节电机, 以避免关节电机发生破坏; 此外, 动态面的引入避免了反演法存在的计算膨胀问题, 有效减少了计算量. 基于Lyapunov函数法证明了系统的稳定性, 并通过系统数值仿真结果验证了上述缓冲从顺控制策略的正确性.     

Shape effects of wheel grousers on traction performance on sandy terrain

This paper presents the effects of different wheel grouser shapes on the traction performance of a grouser wheel traveling on sandy terrain. Grouser wheels are locomotion gears that allow small and lightweight exploration rovers to traverse on the loose sand on extraterrestrial surfaces. Although various grouser shapes have been analyzed by some research groups, a more synthetic and direct comparison of possible grousers is required for practical applications. In this study, we developed a single wheel testbed and experimentally investigated the effects of four grouser shapes (parallel, slanted, V-shaped, and offset V-shaped) on the traction performance of linear movement on flat sand. The wheel slip, sinkage, traction and side force acting on the wheel axle, the wheel driving torque, and the efficiency of each wheel were examined. Thereafter, the effects on the lateral slope traversability of a small and lightweight four-wheeled rover with different grouser shapes were also examined. The traversability experiment demonstrated the vehicle mobility performance in order to contribute to the design optimization of rover systems. These experimental results and their comparisons suggested that, of the shapes studies herein, the slanted shape was the optimal grouser design for use in wheeled rovers on lunar and planetary soil.     

月球着陆器着陆过程的DEM-FEM耦合分析

实现月球着陆器的安全软着陆是宇航员、搭载设备、仪器安全以及着陆器后续正常工作的重要保证。本文采用离散元-有限元方法建立月壤与着陆器相互作用的耦合模型,其中月壤采用具有粘接作用的球体离散元单元,着陆器采用壳单元和梁单元组合的有限元模型,与缓冲垫连接的支撑腿采用可压缩弹簧模型,以实现着陆器自身的缓冲功能;为分析着陆于不同月表的过程,建立平坦、斜坡月球表面;针对不同坡度的斜坡月表,研究不同着陆模式下着陆器与月壤的相互作用,分析冲击力峰值的大小与作用时间的关系,并从能量方面讨论和解释大坡度下冲击力峰值小的原因。以上研究为月球着陆器的安全着陆分析提供有益的参考。     

Drivability analysis of through-the-road-parallel hybrid vehicles

In the last decade, Hybrid Electric Vehicles (HEVs) have spread worldwide due to their capability to reduce fuel consumption. Several studies focused on the optimisation of the energy management system of hybrid vehicles are available in literature, whilst there are few articles dealing with the drivability and the dynamics of these new powertrain systems. In this paper a ‘Through-the-Road-Parallel HEV’ is analysed. This architecture is composed of an internal combustion engine mounted on the front axle and an electric motor powering the rear one. These two powertrains are not directly connected to each other, as the parallel configuration is implemented through the road-tyre force interaction. The main purpose of this paper is the drivability analysis of this layout of HEVs, using linearised mathematical models in both time (i.e. vehicle response during tip-in tests) and frequency domain (i.e. frequency response functions), considering the effect of the engaged gear ratio. The differences from a traditional Front-Wheel-Drive (FWD) configuration are subsequently highlighted. Furthermore, the authors compare different linearised dynamic models, with an increasing number of degrees of freedom, in order to assess which model represents the best compromise between complexity and quality of the results. Finally, a sensitivity analysis of the influence of the torque distribution between the front (thermal) and rear (electric) axles on vehicle drivability is carried out and presented in detail.     

Design of manned lunar rover wheels and improvement in soil mechanics formulas for elastic wheels in consideration of deformation

Most of the current lunar rover vehicle wheels are inconvenient for changing broken wheels and have poor shock absorbing in driving, so they cannot be used to carry people on the moon. To meet the demands for manned lunar transportation, a new wheel possessing a woven metal wire mesh tire and using hub-rim combination slide mechanism is designed in this article. The characteristics of the new wheel is analyzed by comparing with the same-size conventional rover wheels after demonstrating the validity of FEM simulation. The new wheel possesses lighter structure and superior shock absorbing. It also provides stronger traction because the deformation of the designed wheel increases the contact area between the tire and lunar terrain. In order to establish an on-line soil parameter estimation algorithm for low cohesion soil, the stress distribution along a driven deformable wheel on off-road terrain is simplified. The basic mechanics equations of the interaction between the wheel and the lunar soil can be used for analytical analysis. Simulation results show that the soil estimation algorithm can accurately and efficiently identify key soil parameters for loose sand.     

航行体梯度密度式头帽结构设计及降载性能分析

针对航行体在以大于100 m/s的速度高速入水过程中承受巨大的冲击载荷可能导致的结构损坏、弹道失控等现象, 而现有的缓冲措施降载能力有限的难题, 本文设计了一种航行体高速入水梯度密度式缓冲头帽, 确保航行体能够高速安全入水, 并给出了详细的设计过程. 同时基于ALE (arbitrary Lagrangian-Eulerian)算法建立了航行体带缓冲头帽高速入水数值计算模型, 且数值计算的结果与试验测试数据具有较好的一致性. 然后在此基础上, 开展了航行体带梯度密度式缓冲头帽高速入水降载特性的数值研究, 探究了双层缓冲件不同分层厚度、正负密度梯度排列以及层间密度差等重要参数对缓冲头帽能量吸收以及缓冲降载效果的影响规律, 并进行了大尺度模型高速入水冲击测试试验, 根据航行体模型干模态分析时的二阶弯曲模态固有频率对试验数据进行滤波处理. 研究结果表明, 在本文所研究的范围内, 分层的缓冲件相比较于不分层的缓冲件表现出更强的冲击能量吸收效果, 且缓冲件吸收的冲击能量随着分层数的增加而增加; 负密度梯度排列的缓冲件其缓冲能力强于正密度梯度的缓冲件; 当层间密度差越大时, 冲击能量的损耗也将越大, 缓冲头帽的降载效果越好.      

水下发射水动力的多尺度预测网络研究

空泡的演化和水动力特征的预测在航行体发射的设计中有非常重要的意义.人工智能技术已经成为了参数预测的重要手段.为了能够快速预测航行体水下发射过程的尾部压力的复杂变化,提出了一种多尺度深度学习网络.该网络模型以一维卷积网络(1DCNN)为基础,构建了一种编码--解码型网络结构,通过不同的采样频率将原始数据分解为光滑部分和脉...     

A Novel Cutting Strategy for Measuring Two Components of Residual Stresses Using Slitting Method

An exact knowledge of residual stresses that exist within the engineering components is essential to maintain the structural integrity. All mechanical strain relief (MSR) techniques to measure residual stresses rely on removing a section of material that contains residual stresses. Therefore, these techniques are destructive as the integrity of the components is compromised. In slitting method, as a MSR technique, a slot with an increasing depth is introduced to the part incrementally that results in deformations. By measuring these deformations the residual stress component normal to the cut can be determined. Two orthogonal components of residual stresses were measured using the slitting method both experimentally and numerically. Different levels of residual stresses were induced into beam shaped specimens using quenching process at different temperatures. The experimental results were then compared with those numerically predicted. It was shown that while the first component of residual stress was being measured, its effect on the second direction that was normal to the first cut was inevitable. Finally, a new cutting configuration was proposed in which two components of residual stresses were measured simultaneously. The results of the proposed method indicated a good agreement with the conventional slitting.     

基于表面分析技术和铁谱技术的某重载履带车辆主离合器摩擦副失效机理研究

利用扫描电子显微镜、能量色散谱仪及铁谱仪分析了某重载履带车辆主离合器分离机构中的活动盘弹子槽的磨损失效机理.结果表明:磨损表面存在明显的犁沟痕迹和点蚀坑,而粘着磨损迹象不明显;铁谱分析结果表明润滑脂中的磨粒主要包括典型的粘着磨粒、接触疲劳磨粒和腐蚀磨粒;磨损表面的主要失效机制为磨料磨损、粘着磨损、接触疲劳磨损和腐蚀磨损的综合作用;采用联合表面分析技术和铁谱技术研究材料表面磨损失效机理具有一定的优越性.     

配置柔顺机构空间机器人双臂捕获卫星操作力学模拟及基于神经网络的全阶滑模避撞柔顺控制

讨论了空间机器人双臂捕获卫星操作过程避免关节冲击破坏的避撞柔顺控制问题. 为此在关节电机与机械臂之间设计了一种旋转 型串联弹性执行器(rotatory series elastic actuator, RSEA)--柔顺机构,其作用在于:(1) 通过其内置弹簧的拉伸或压缩变形来吸收捕获操作过程中被捕获卫星对空间机器人关节产生的冲击能量;(2) 可以利用合理设计的与之配合的避撞柔顺控制策略来保证关节冲击力矩受限在安全范围. 首先,利用第二类Lagrange方程分别建 立了捕获操作前含柔顺机构双臂空间机器人的开环分系统动力学模型与目标卫星的分系统动力学模型;之后,基于系统动量 守恒关系、闭链系统位置与速度几何约束关系,获得了捕获操作后空间机器人与被捕获卫星闭链混合体系统综合动力学方程; 最后,基于RBF神经网络提出了一种捕获操作后两者混合体系统镇定运动的全阶终端滑模避撞柔顺控制方案. 所提方案结合柔 顺机构在有效吸收、缓冲被捕获卫星冲击能量的同时,还在冲击能量过大时适时开、关空间机器人关节驱动器,以避免关节驱 动器过载、破坏;此外,还通过最小权值范数法分配了机械臂各关节力矩,以保证双臂协调操作. Lyapunov稳定性理论证明了 系统的全局稳定性,系统计算机数值仿真也验证了上述避撞柔顺控制策略的有效性.      

真实气体效应试飞器气动布局研究

针对真实气体效应飞行试验的要求对试飞器气动布局开展了设计研究,采用平衡气体模型对真实气体效应进行数值模拟,通过与理想气体状态方程数值模拟结果的比较,分析了真实气体效应对不同试飞器外形气动特性的影响规律,总结出真实气体效应试飞器外形的基本设计要素,给出了适用于真实气体效应飞行试验的试飞器气动布局．     

高g值冲击下存储测试电路模块缓冲保护研究

为了采用弹载存储测试技术记录弹体高速侵彻硬目标过程中的加速度—时间曲线,必须对存储测试电路模块进行缓冲保护。本文利用非线性缓冲理论、技术,选择较理想的缓冲材料,设计出缓冲器件-泡沫铝试件,进行了静态压缩,得到应力-应变曲线,采用LS-DYNA模拟了空气炮冲击实验中泡沫铝试件的缓冲效果,并对应用于某型号弹侵彻混凝土靶的存储测试电路模块进行了缓冲保护,提高了数据的捕获率和电路模块的重复使用次数。通过试验证明了所设计缓冲器件对电路模块具有保护效果。     

Lunar landing trajectory design based on invariant manifold

The low-energy lunar landing trajectory design using the invariant manifolds of restricted three-body problem is studied.Considering angle between the ecliptic plane and lunar orbit plate the four-body problem of sun-earth-moon-spacecraft is divided into two three-body problems,the sun-earth-spacecraft in the ecliptic plane and the earth- moon-spacecraft in the lunar orbit plane.Using the orbit maneuver at the place where the two planes and the invariant manifolds intersect,a general method to design low energy lunar landing trajectory is given.It is found that this method can save the energy about 20% compared to the traditional Hohmann transfer trajectory,The mechanism that the method can save energy is investigated in the point of view of energy and the expression of the amount of energy saved is given.In addition,some rules of selecting parameters with respect to orbit design are provided.The method of energy analysis in the paper can be extended to energy analysis in deep space orbit design.     

Investigation of a model of the Soyuz spacecraft washed by the control jets of the Apollo spacecraft

During mission design for the joint flight of the Soyuz and Apollo spacecraft in the ÉPAS program, a preliminary analysis was made of the thermal and force interactions of the motor jets of the Apollo control system on the Soyuz spacecraft. It was shown that the flow over the service, command, and docking modules of Apollo formed shock waves which intersected the communication antennas, the solar cells, and other structural elements of Soyuz during the docking. The flight program provided for possible simultaneous operation of four motors of the control system. In that case the jets interact, forming a complex three-dimensional flow. In the regions where shock waves interact with the Soyuz structural elements, the local convective heat fluxes, which are significant in magnitude, increase, since the temperatures and pressures in the Apollo engine combustion chambers are 3000 °K and 7·10⁵ Pa, respectively. The need for reliable operation of all devices of Soyuz located in the jet interaction zone required experimental investigations to be performed to determine the heat flux to the structure and the surface pressures on the spacecraft, with particular attention being paid to modeling of the phenomena. It should be noted that the results of analogous investigations carried out earlier by the USA with reference to the manned lunar flight program could not be used because of the difference of the Soyuz geometry and the newly developed docking module in the ÉPAS mission from the Apollo lunar module geometry.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 3, pp. 124–133, May–June, 1977.