Multi-Sphere Method for modeling spacecraft electrostatic forces and torques

The use of electrostatic (Coulomb) actuation for formation flying is attractive because non-renewable fuel reserves are not depleted and plume impingement issues are avoided. Prior analytical electrostatic force models used for Coulomb formations assume spherical spacecraft shapes, which include mutual capacitance and induced effects. However, this framework does not capture any orientation-dependent forces or torques on generic spacecraft geometries encountered during very close operations and docking scenarios. The Multi-Sphere Method (MSM) uses a collection of finite spheres to represent a complex shape and analytically approximate the Coulomb interaction with other charged bodies. Finite element analysis software is used as a truth model to determine the optimal sphere locations and radii. The model is robust to varying system parameters such as prescribed voltages and external shape size. Using the MSM, faster-than-realtime electrostatic simulation of six degree of freedom relative spacecraft motion is feasible, which is crucial for the development of robust relative position and orientation control algorithms in local space situational awareness applications. To demonstrate this ability, the rotation of a cylindrical craft in deep space is simulated, while charge control from a neighboring spacecraft is used to de-spin the object. Using a 1 m diameter craft separated by 10 m from a 3 by 1 m cylindrical craft in deep space, a 2 °/s initial rotation rate can be removed from the cylinder within 3 days, using electric potentials up to 30 kV.     

Electrostatic Structure of the Electron Phase-space Holes Generated by the Electron Two-stream Instability with a Finite Width

Space satellite observations in an electron phase-space hole (electron hole) have shown that bipolar structures are discovered at the parallel cut of parallel electric field, while unipolar structures spring from the parallel cut of perpendicular electric field. Particle-in-cell (PIC) simulations have demonstrated that the electron bi-stream instability induces several electron holes during its nonlinear evolution. However, how the unipolar structure of the parallel cut of the perpendicular electric field formed in these electron holes is still an unsolved problem, especially in a strongly magnetized plasma (Ω_e > ω_pe, where Ω_e is defined as electron gyrofrequency and ω_pe is defined as plasma frequency, respectively). In this paper, with two-dimensional (2D) electrostatic PIC simulations, the evolution of the electron two-stream instability with a finite width in strongly magnetized plasma is investigated. Initially, those conditions lead to monochromatic electrostatic waves, and these waves coalesce with each other during their nonlinear evolution. At last, a solitary electrostatic structure is formed. In such an electron hole, a bipolar structure is formed in the parallel cut of parallel electric field, while a unipolar structure presents in the parallel cut of perpendicular electric field.      

基于N-S方程的尾迹面法翼型气动阻力计算

研究了计算翼型阻力改进的方法——尾迹面法及尾迹面积分的位置和相应的积分技术.在亚跨声速时分别采用了表面积分和尾迹积分求得给定翼型RAE2822的阻力.结果显示,2种方法具有相同的结果,表明尾迹面积分方法是有效的,与实验值吻合较好.尾迹面法中,尾迹面位置应处于离后缘相对弦长距离0.6~1.0之间.尾迹面积分方法中积分结果不依赖于物体的详细几何外形,可以预计对曲率变化大的三维复杂外形,该方法有更大的优势.      

多导弹协同攻击编队非线性最优控制器设计

针对多导弹协同攻击编队控制问题,采用仿射非线性系统最优控制理论设计了基于领弹-从弹法的多导弹编队控制器.首先采用基于微分几何理论的非线性系统精确线性化方法,将导弹非线性运动模型线性化;然后根据从弹、领弹间的相对运动关系,给出了包含领弹运动信息和队形信息的从弹期望轨迹,建立了基于从弹跟踪误差向量的系统状态方程;最后采用基于稳态解的黎卡提矩阵微分方程求解方法解决最优控制问题,设计了从弹的三维非线性编队控制器;仿真结果表明所设计的控制器能够在领弹机动地情况下快速、稳定地实现编队队形的形成和保持.      

分离式飞机应急数据记录跟踪系统设计与试验

分离式飞机应急数据记录跟踪系统具备智能弹射与分离、拖曳式跟踪拍摄、缓降与应急漂浮和数据传输等功能,针对弹射和缓降等过程进行了系统设计和无人机试验验证。同时,针对伞-囊组合体的特点,分析了气囊尾流区中伞衣阻力系数的变化规律。结果表明:气囊半径和伞衣名义直径是影响伞衣阻力系数的主要因素;伞衣阻力系数随气囊半径增大而下降,随伞衣名义直径增大而上升;在气动力分析和数值模拟的基础上,确定了伞衣阻力系数的计算公式。无人机试验完成各项设计功能,系统整体方案合理可行,为后续工程应用提供了重要参考。      

气动力计算的积分技术讨论

讨论了"尾迹面积分法"的气动力计算方法及其改进技术.基于欧拉方程求解流场,通过对飞行器以外的一个控制体采用动量定理而得,是传统远场积分法的改进.在飞行器所在流场的下游一垂直于来流速度的截面上进行积分计算,得到升力、诱导阻力、激波阻力和总阻力.这种方法的优点是有利于外形复杂物体的气动力积分计算,并可将总阻力按产生的物理机理进行分解,以使设计师对飞行器的气动特点有更为明确的了解.详细讨论了影响这种方法计算精度和效率的多种因素及解决途径.各种数值模拟结果证明了该方法和改进技术的正确性和实用性.      

基于路径跟随的改进领航-跟随无人机协同编队方法

针对集群无人机完成高精度协同编队的需要,提出了一种基于路径跟随的改进领航-跟随无人机协同编队方法。首先,在传统A*算法的基础上,引入了障碍威胁系数改进A*算法,为领航无人机规划从起点到目标的全局安全路径;其次,采用Hermite多项式在离散化后对领航无人机的全局安全路径进行参数化表示。当遇到新的障碍信息时,利用改进A*算法重新规划路径;随后,领航无人机将跟随无人机的空间编队信息与编队路径参数信息在集群中完成同步;最后,基于一致性原理设计了编队队形协同控制器,并基于改进人工势场法设计了动态避障控制器。仿真结果表明,与传统的领航-跟随方法相比,该方法可以降低编队误差,提高了复杂曲线路径下无人机的编队精度与稳定性,具有一定的工程应用价值。     

Field emission characteristics of gold dust grains

The space plasma environment usually contains charged dust grains. The grain charge is an important parameter determining its migration through the space, coagulation, formation of dust clouds and so on. The knowledge of its charge is thus one of the basic information we want to know. There are several emission processes leading to both positive and negative charges, among others photoemission, all kinds of secondary emissions, field emissions, etc. The present study is focused on a laboratory simulation of emissions caused by impacts by energetic ions. Our experiment is based on the Paul trap which gives us an opportunity to catch a single dust grain for several days inside the vacuum vessel and exposed it by electron/ion beams. This experimental approach allows us to separate an individual charging process. We have chosen spherically shaped gold grains and discussed the processes leading to the limitation of the grain charge. We suggested that the implantation of charging ions leads to deformations of the grain surface. The deformations enhance the local electric field strength that becomes sufficient for the field ionization.     

Particle-in-cell simulation of the plasma environment of a spacecraft in the solar wind

The main interactions between the plasma and the spacecraft are the wake effects, the emission of a dense photoelectron cloud and the electric charging of the surface of the spacecraft. An electrostatic particle-in-cell computer simulation model is presented, that allows the simultaneous calculation of these related effects. For different plasma properties, two-dimensional simulations yielded the steady state self-consistent potential distributions around the probe. These potentials, especially the potential barriers produced by the photoelectron cloud, have great influence on the measurements of the low energy solar wind electrons. The essential features can be verified by a comparison with selected electron distributions measured onboard the HELIOS spacecraft.     

Formation of Saturn's spokes

The scattering properties of the spokes in Saturn's rings suggest that they consist of micron-sized dust particles. We suggest that these grains are elevated above the ring plane by electrostatic charging. We show that electrostatic levitation requires a sufficiently large plasma density near the rings. If the plasma density near the rings exceeds a few 10² cm^?3 levitation may occur at significant rates in the strong electric fields which exist in the wall-sheaths at the ring. Once the dust particles are elevated they drift relative to the plasma (except at synchronous orbit). This relative motion constitutes a current which causes a polarization electric field if the plasma is azimuthally inhomogeneous. The dense plasma will drift radially in response to this electric field and cause levitation of more dust particles as it moves along. It leaves a radially aligned trail of elevated dust particles—the spokes. One way of producing dense plasma is by meteor impact on the rings. We discuss the mechanisms of ring charging, electrostatic levitation and the currents in the plasma-dust mixture. We show that for reasonable conditions spokes of more than 10,000 km radial length can be formed in less than five minutes. We also show that under the same conditions the electrostatic levitation model predicts a dust grain population which peaks at a size of 0.6 microns and can reach optical depths of 0.1.     

ESF的Transition区谱分布特性

本文提出了研究Transition区谱分布的静电模型,并按等离子体弱耦强湍理论对其重正化得到了谱方程.对谱方程作适当近似后,证明了该近似谱方程存在扰动密度谱为k~(-5),扰动电场谱为k~(-3)分布的解,从而定量解释了Transition区的实验谱分布结果.     

Effective Coulomb force modeling for spacecraft in Earth orbit plasmas

Coulomb formation flight is a concept that utilizes electrostatic forces to control the separations of close proximity spacecraft. The Coulomb force between charged bodies is a product of their size, separation, potential and interaction with the local plasma environment. A fast and accurate analytic method of capturing the interaction of a charged body in a plasma is shown. The Debye–Hückel analytic model of the electrostatic field about a charged sphere in a plasma is expanded to analytically compute the forces. This model is fitted to numerical simulations with representative geosynchronous and low Earth orbit (GEO and LEO) plasma environments using an effective Debye length. This effective Debye length, which more accurately captures the charge partial shielding, can be up to 7 times larger at GEO, and as great as 100 times larger at LEO. The force between a sphere and point charge is accurately captured with the effective Debye length, as opposed to the electron Debye length solutions that have errors exceeding 50%. One notable finding is that the effective Debye lengths in LEO plasmas about a charged body are increased from centimeters to meters. This is a promising outcome, as the reduced shielding at increased potentials provides sufficient force levels for operating the electrostatically inflated membrane structures concept at these dense plasma altitudes.     

折背式轿车尾流结构研究

轿车的气动阻力对轿车的燃油经济性有着重要影响.对于折背式轿车,由尾部产生的气动阻力可占整个外形气动阻力的50%.因此,弄清折背式轿车的尾流结构对开发具有良好气动特性的新型轿车有重要意义.利用风洞试验和CFD(Computational Fluid Dynamics)技术相结合,分析了折背式轿车的尾流结构及尾部形状对尾流结构的影响,为设计具有良好气动特性的折背式轿车提供了依据.     

Active space debris charging for contactless electrostatic disposal maneuvers

The remote charging of a passive object using an electron beam enables touchless re-orbiting of large space debris from geosynchronous orbit (GEO) using electrostatic forces. The advantage of this method is that it can operate with a separation distance of multiple craft radii, thus reducing the risk of collision. The charging of the tug–debris system to high potentials is achieved by active charge transfer using a directed electron beam. Optimal potential distributions using isolated- and coupled-sphere models are discussed. A simple charging model takes into account the primary electron beam current, ultra-violet radiation induced photoelectron emission, collection of plasma particles, secondary electron emission and the recapture of emitted particles. The results show that through active charging in a GEO space environment high potentials can be both achieved and maintained with about a 75% transfer efficiency. Further, the maximum electrostatic tractor force is shown to be insensitive to beam current levels. This latter later result is important when considering debris with unknown properties.     

Effects of electrostatic forces on the vertical structure of planetary rings

We have calculated the vertical structure of planetary dust rings as it results from a balance between an electrostatic force on the dust grains and the vertical component of the gravitational force from the central planet. The electrostatic force results from the charging of the dust grains by the ambient plasma and a large scale electric field due to a shielding electric field and the resulting vertical dust distribution are strongly dependent on dust size, dust and plasma density, plasma temperature and plasma ion type. The dust density distribution has a different dependence on these parameters in tenuous and in dense dust rings. We solve the relevant equations numerically and also by linearization in the limiting cases of tenuous or dense rings. Our results indicate that the effects treated in this paper may be important in both Jupiter's and Saturn's rings.     

底凹结构减阻效应数值分析

为研究弹丸底凹结构的减阻机理,使用三维定常CFD方法对M910弹丸的流场特性进行了数值模拟。给出了零升阻力系数随马赫数的变化规律,所得结果与实验数据符合很好。在此基础上,为M910弹丸引入底凹结构并进行数值模拟。对比了不同弹底结构的底部流场特性,对底凹结构减阻效应的产生机理进行了分析。结果表明:亚声速下,底凹结构在底凹腔体内引入了高压“死水区”,并以“屈从”的流体边界代替了原固体底面,从而改变了尾部涡街的形成位置、形状和强度,最终增大底部压力,减小弹丸阻力;跨声速下,由于尾部涡街远离弹丸底面,固体底面与流体边界面的作用相同,使得底凹不再具有减阻效果;超声速下,底凹结构的减阻机理与底排弹丸减阻机理类似,即底凹结构中的流体为弹丸底部回流区添加质量从而达到减阻作用。      

Rarefied gas effects on the aerodynamics of high area-to-mass ratio spacecraft in orbit

The aerodynamic situation of a satellite-on-a-chip operating in low Earth orbit bears some resemblance to a classical Crookes radiometer. The large area-to-mass ratio characteristic of a SpaceChip means that very small surface-dependent forces produce non-negligible accelerations that can significantly alter its orbit. When the temperature of a SpaceChip changes, the drag force can be changed: if the temperature increases, the drag increases (and vice versa). Analytical expressions available in the literature that describe the change in drag coefficient with orbit altitude and SpaceChip temperature compare well with our direct simulation Monte Carlo results presented here. It is demonstrated that modifying the temperature of a SpaceChip could be used for relative orbit control of individual SpaceChips in a swarm, with a maximum change in position per orbit of 50 m being achievable at 600 km altitude.     

Active stimulation of the ionospheric plasma

Laboratory experiments in which high power, pulsed electromagnetic waves interact with an inhomogeneous plasma indicate that the generated nonlinear plasma phenomena depend on peak incident power and not on pulse length. The electromagnetic waves can penetrate beyond the cutoff and produce large, enhanced electrostatic fields at the critical layer within 100 electron plasma periods. The enhanced electric field pressure can be comparable to the thermal pressure and can accelerate ions and electrons to velocities much greater than their thermal speed. Large density cavities (with δn/n ? 10%) can be created in a time shorter than the usual ion response time because of the accelerated ion dynamics. These laboratory results have been extended to create a new and generalized concept to actively stimulate space plasmas with high power pulses of short duration. A field experiment will be used for the stimulation of auroral ionospheric plasma. The ground-based system is modular, each module consisting of a 2 MW pulsed HF transmitter designed at UCLA and a crossed-dipole antenna element. Incoherent scatter radar and optical diagnostic methods are discussed.     

静电场仪校准系统的设计及仿真研究

静电场仪的精确校准对提高卫星在轨电场探测精度、保障卫星安全发射升空、精确预测雷电等具有重要意义。针对电场仪校准的需要,设计了平行极板电容式静态电场仪校准装置。利用三维电磁场仿真软件CST对标准静电场发生装置进行数值仿真,研究了校准箱内部及边缘处的静电场分布特点,分析标准极板直径和间距对边缘效应的影响,结合极板平行度对电场均匀性的影响分析,确定了校准过程中电场仪探头的最佳位置,实现静电场仪校准装置的最优化设计。     

静电场仪校准系统的设计及仿真研究

静电场仪的精确校准对提高卫星在轨电场探测精度、保障卫星安全发射升空、精确预测雷电等具有重要意义。针对电场仪校准的需要,设计了平行极板电容式静态电场仪校准装置。利用三维电磁场仿真软件CST对标准静电场发生装置进行数值仿真,研究了校准箱内部及边缘处的静电场分布特点,分析标准极板直径和间距对边缘效应的影响,结合极板平行度对电场均匀性的影响分析,确定了校准过程中电场仪探头的最佳位置,实现静电场仪校准装置的最优化设计。