A comparison of radiation shielding effectiveness of materials for highly elliptical orbits

The Canadian Space Agency (CSA) has proposed a Polar Communications and Weather (PCW) satellite mission, in conjunction with other partners. The PCW will provide essential communications and meteorological services to the Canadian Arctic, as well as space weather observations of in situ ionizing radiation along the orbit. The CSA has identified three potential Highly Elliptical Orbits (HEOs) for a PCW satellite constellation, Molniya, Modified Tundra and Triple Apogee (TAP), each having specific merits, which would directly benefit the performance/longevity of a PCW spacecraft. Radiation shielding effectiveness of various materials was studied for the three PCW orbit options to determine the feasibility of employing materials other than conventional aluminium to achieve a specified spacecraft shielding level with weight savings over aluminium. It was found that, depending on the orbit-specific radiation environment characteristics, the benefits of using polyethylene based materials is significant enough (e.g., 22% in Molniya for PE at 50 krad TID) to merit further investigation.     

Fault detection and isolation in GPS receiver autonomous integrity monitoring based on chaos particle swarm optimization-particle filter algorithm

The receiver autonomous integrity monitoring (RAIM) is one of the most important parts in an avionic navigation system. Two problems need to be addressed to improve this system, namely, the degeneracy phenomenon and lack of samples for the standard particle filter (PF). However, the number of samples cannot adequately express the real distribution of the probability density function (i.e., sample impoverishment). This study presents a GPS receiver autonomous integrity monitoring (RAIM) method based on a chaos particle swarm optimization particle filter (CPSO-PF) algorithm with a log likelihood ratio. The chaos sequence generates a set of chaotic variables, which are mapped to the interval of optimization variables to improve particle quality. This chaos perturbation overcomes the potential for the search to become trapped in a local optimum in the particle swarm optimization (PSO) algorithm. Test statistics are configured based on a likelihood ratio, and satellite fault detection is then conducted by checking the consistency between the state estimate of the main PF and those of the auxiliary PFs. Based on GPS data, the experimental results demonstrate that the proposed algorithm can effectively detect and isolate satellite faults under conditions of non-Gaussian measurement noise. Moreover, the performance of the proposed novel method is better than that of RAIM based on the PF or PSO-PF algorithm.     

近圆轨道卫星编队捕获技术研究

基于近圆参考轨道的假设,研究处于同一入轨点多颗卫星的编队捕获方法.首先由高斯型拉格朗日轨道摄动运动方程得到轨道坐标系中控制冲量与轨道根数偏差的关系,基于近圆轨道的条件简化并带入相对运动方程,得到控制冲量与相对运动的关系表达式;通过深入分析各个方向(径向、沿迹向与轨道面法向)的控制冲量对相对运动的影响,给出了分别用径向与轨道面法向控制冲量组合和沿迹向与轨道面法向控制冲量组合实现编队捕获的两种控制策略;最后给出了一个空间圆编队捕获实例,并从燃料消耗、施加冲量次数及捕获时间等角度对比研究了两种控制策略的特点.仿真结果表明,这两种控制策略简单、实用,能够较好地解决近圆轨道卫星编队的捕获问题.     

应用改进果蝇优化算法的月面巡视器路径规划

文章针对果蝇优化算法易陷入局部最优的问题,对果蝇算法中的味道浓度判定值进行改进,并将其用于月球探测巡视器的动态路径规划。为验证算法的有效性,将改进果蝇优化算法与粒子群优化算法的路径规划寻优特性进行了仿真对比分析,结果表明改进果蝇优化算法具有良好的实时性,并有效解决了算法易陷入局部最优的问题。考虑到月球探测巡视器在沿规划路径进行月面巡视的过程中,有可能遇到未知障碍物的情况,提出了动态环境下月球巡视器遇到未知静态障碍物的避障策略。     

Epochwise prediction of GPS single differenced ionospheric delays of formation flying spacecraft

Both single and dual frequency GPS relative navigation filters may benefit from proper predictions of single differenced ionospheric delays. In this article, the single differenced ionospheric delays of GPS observations are predicted for the GRACE formation during the switch manoeuvre.Two prediction methods are considered. The first is based on a Taylor expansion to first order of a mapping function that maps slant total electron content measurements to vertical total electron content estimates. The second method fits a shape profile through undifferenced ionospheric data available. It then raytraces through this profile to estimate the difference in total electron content along the path of the GPS signals.Continuously changing ionospheric conditions hamper the assessment of the quality of the predictions. Comparison of both methods shows that the raytracing method performs better. The difference of predictions and measurements generally shows a smaller RMS than the measurements alone. However, both methods suffer from a number of systematically unpredicted observations, which arise from small unaccounted differential variations in electron densities along the path of the GPS signals. These prediction methods perform better when spacecraft separation is small. Baselines considered here range from tens of kilometres down to several hundred metres. When smallest spacecraft separation occurs (0.4 km), the single differenced ionospheric delays exhibit RMS values of 0.0089 m. The first method shows a difference between measurements and predictions with an RMS of 0.0081 m. For the second method the difference RMS is found to be 0.0067 m.     

基于粒子群算法的电帆轨迹优化设计

电帆是一种利用太阳风动量的新颖的无工质空间推进系统,文章研究了以电帆为对象的行星际转移轨迹优化问题。以地球轨道转移到火星、金星轨道为任务对象,采用连续推力模型,研究极坐标系下最小时间转移轨迹优化设计问题。提出了两种基于粒子群算法(PSO)的直接优化方法,避免对协态变量初值敏感的两点边值问题（TPBVP）求解。方法一是通过打靶法直接离散化控制量输入,将最优控制问题转化为非线性规划参数优化问题,采用PSO算法寻优,获得近似最优的转移轨迹。方法二是针对任何连续控制律曲线都能以一定精度的多项式函数进行曲线拟合的特性,设计逼近最优转移轨迹控制律的多项式函数,通过PSO算法优化多项式函数参数获得逼近最优解的转移轨迹。仿真结果表明采用上述两种方法进行转移轨迹优化设计,具有随机猜测初值、全局收敛、鲁棒性强的特点。     

Time suboptimal formation flying manoeuvres through improved magnetic charged system search

The development of fast and reliable optimization algorithms is required in order to obtain real-time optimal trajectory on-board spacecraft. In addition, the wide spread of small satellites, due to their low costs, is leading to a greater number of satellite formations in space. This paper presents an Improved version of the Magnetic Charged System Search (IMCSS) metaheuristic algorithm to compute time-suboptimal manoeuvres for satellite formation flying. The proposed algorithm exploits some strategies aimed at improving the convergence to the optimum, such as the chaotic local search and the boundary handling technique, and it is able to self-tune its internal parameters and coefficients. Moreover, the inverse dynamics technique and the differential flatness approach, through the B-splines curves, are used to approximate the trajectory. The optimization procedure is applied to the circular J2 relative model developed by Schweighart and Sedwick and to the elliptical relative motion model developed by Yamanaka and Ankersen. The results of this paper show that the convergence is better achieved by using the proposed tools, thus proving the efficiency and reliability of the algorithm in solving some space engineering problems.     

Charge-product control approach to electrostatic leader-follower formations in LEO plasma wakes

The feasibility of using electrostatic forces to stabilize a close-proximity leader-follower formation is investigated. The leader craft is equipped with a set of affixed spheres whose charge is modulated to hold the charged follower craft along a proscribed trajectory to its nominal leader-relative position. This charge structure and the follower craft are constrained to remain in the plasma wake generated behind all LEO craft because the more-dense ambient plasma outside the wake prevents object charging and electric field propagation. Once the formation is achieved, a controlled electric field is generated by the leader to counter relative accelerations from perturbations like differential drag and solar radiation pressure, holding the follow near its nominal position. Two controllers are derived for the system described, incorporating Coulomb accelerations and linearized gravity and drag accelerations. Simulations are run under unmodeled perturbations and sensor noise for different scenarios, demonstrating the challenges and benefits associated with electrostatic actuation.     

绳系微小卫星的旋转编队飞行

针对三星编队飞行问题,提出一种绳系控制方法,在自旋刚体卫星的平衡分析的基础上,建立了Thomson和Likins Pringle平衡构形的绳系三星编队模型,通过对编队系统的稳定性分析得到了两种构形下的稳定条件,并给出了三种控制策略用以解决Likins-Pringle构形不能满足平衡条件的问题。最后经过仿真验证了理论分析的正确性,并对三种控制策略进行了检验,结果表明Thomson构形无须辅助手段,在满足特定条件下可以稳定运行,Likins-Pringle构形采用弹簧系统和喷气辅助绳系控制时满足特定条件也可以稳定运行。     

Spacecraft fuel-optimal and balancing maneuvers for a class of formation reconfiguration problems

This paper presents fuel optimal and balancing methodologies for reconfiguring multiple spacecraft in formation subject to a Newtonian gravity field. For a kind of continuous-thrust propulsion system, a fuel-optimal control problem is formulated to minimize the integral squared control subject to the linearized Hill or Clohessy–Wiltshire dynamics of relative motion with respect to a circular reference orbit. Palmer’s analytical solution for general reconfiguration is adapted to maneuvers between projected circular orbits, resulting in the optimal fuel consumption index as a function of configuration parameters such as orbit radius, phase angle, and transfer time. Parametric analyses reveal unique characteristics of individual fuel optimality and gross fuel consumption: for an arbitrary selection of initial/terminal orbit radii, (i) there exist special transfer times such that individual fuel consumption is optimally uniform for all phase angles, and (ii) the total fuel expenditure for a group of three or more spacecraft is invariant for the relatively same configuration with respect to the departure phase. These results serve to effectively design fuel balancing strategies for formation reconfiguration of multiple spacecraft.     

一种小卫星绕飞编队的运动学设计新方法研究

在用运动学方法进行小卫星绕飞编队的相对运动分析和轨道设计时,一般假设环绕卫星和参考卫星的升交点赤经差、轨道倾角差和纬度幅角差均为小量,从而对相对运动方程进行近似和简化.但是当参考卫星的轨道倾角等于零或较小时,环绕卫星和参考卫星的升交点赤经差和纬度幅角差并不是小量,此时由于假设条件不成立而无法得到合理的轨道设计结果.针对这种情况,本文提出了一种小卫星绕飞编队的运动学设计新方法.首先对零轨道倾角卫星编队的卫星相对运动方程进行近似简化,得到了以轨道根数差为参数的相对运动方程和卫星编队设计方法,然后通过转移矩阵变换来进行任意轨道倾角的卫星绕飞编队设计,最后通过实例验证了方法的正确性.     

Spacecraft formation flying control around L2 sun-earth libration point using on–off SDRE approach

In this paper, on–off SDRE control approach is presented for spacecraft formation flying control around sun-earth L2 libration point. Orbits around libration points are significant targets for many space missions mainly because of efficient fuel consumption. Furthermore, less propellant usage can be achieved by considering optimal control approaches in spacecraft formation flying control design. Among various nonlinear and optimal control methods, SDRE has shown to be a popular controller in various missions due to the privileges including efficiency, accuracy and robustness. The spacecraft are assumed to have on–off thrusters as actuators. It requires them to be fed with a sequence of on–off pulses which is regarded as a challenge for spacecraft designers. Hence, the main contribution of this paper is designing an on–off SDRE approach for the formation flight around sun-earth L2 point with uncertainty with energy and accuracy considerations. Including on–off input as a constraint is not feasible for SDRE implementation because it makes the system non-affine. An alternative is utilizing an integral action technique and an auxiliary control to make the system affine which leads to on–off SDRE approach. It has also been shown that the proposed method is robust against parametric uncertainties of the states. Present study aims to design an energy-beneficial, simple and attractive controller for a complex nonlinear system with on–off inputs and uncertainty in CRTBP. Simulation results show that the on–off SDRE control could provide the formation flight around L2 point with high accuracy using less energy consumption.     

圆轨道航天器八面体编队构型轨道动力学分析

提出一个全新的八面体航天器编队构型,该构型体现出当前编队飞行多种轨道构型的特征,同时也适于作为空间演示试验的编队飞行模式。八面体编队构型的设计思路是基于C-W方程,轨道平面内沿航向编队构型可利用轨道动力学自然保持,正上方或正下方编队构型则需要依靠平面内控制来实现,垂直轨道平面的编队构型需要施加法向控制来实现。对基于C-W方程的悬停动力学模型进行了精度分析,最后以低轨道航天器的八面体编队构型为例进行了数学仿真验证。     

微小卫星编队飞行解析构型维持控制方法

编队构型维持是卫星编队飞行的基础.J2摄动和大气阻力是影响近地轨道卫星编队构型的主要摄动力,通常导致星间相对速度的长期变化,从而造成编队构型发生漂移.本文针对近地轨道卫星编队飞行,基于平均化的思想,采用平均相对速度表示编队构型漂移率,推导了平均相对速度与脉冲速度增量之间的解析表达式.通过引入平均相对加速度,将摄动力下的相对运动等效为匀变速直线运动.将其与单边极限环控制方法结合,提出一种基于星间测距信息的解析构型维持控制策略.仿真结果表明,该解析算法简单有效,易于工程实现,尤其适合微小卫星的星间自主控制.     

On the ability of sliding mode and LQR controllers optimized with PSO in attitude control of a flexible 4-DOF satellite with time-varying payload

Precise pointing of the satellite and its payload is essential in the accurate accomplishment of a space mission. In this study, the system of a satellite and its payload are considered as 4-DOF equations of motion. The time-varying payload can observe one direction of the Earth independently, and the satellite can point to the Earth station by its 3-DOF motions simultaneously. Sliding mode and LQR controllers are designed for damping disturbances, and consequently high pointing accuracy. Environmental disturbances and the associated time delay of Low Earth Orbit (LEO) are applied to the system. An algorithm based on Particle Swarm Optimization (PSO) is proposed to find the optimum values of variables and Normalized Integral Square Error (NISE) of the two aforementioned controllers. Numerical simulations indicate the optimized magnitudes of target detection errors and control efforts in four directions. The results revealed that PSO-SMC can finely track the time-varying payload and has better efficiency in comparison with PSO-LQR.     

Study of highly perturbed spacecraft formation dynamics via approximation

This paper explores methods for approximating and analyzing the dynamics of highly perturbed spacecraft formations with an emphasis on computationally efficient approaches. This facilitates on-board computation or rapid preliminary mission design analysis. Perturbed formation dynamics are often approximated as linear time-varying (LTV) systems, for which Floquet theory can be used to analyze the degree of system instability. Furthermore, the angular momentum of the relative orbital state can be computed with the approximate dynamics to provide additional insight. A general methodology is developed first and then applied to the problem of unstable formation dynamics in asteroid orbits. Here the dominant perturbative effects due to low-order gravitational harmonics and solar radiation pressure are modeled. Numerical simulations validate the approach and illustrate the approximation accuracy achieved.