在轨物体接近算法研究

根据NORAD公布的在轨物体(空间碎片或航天器) 的轨道数据,给出了计算在轨物体两两间发生接近事件的方法。该方法结合了计算在轨物体 接近的运动学筛选法和相对距离函数法,以提高计算效率。以该方法为基础,提出了特定航 天器与全体在轨物体间的接近事件算法。算法采用了改进后的几何筛选法。该方法并不求解 两轨道的最近点,而是求解包含最近点的时间窗口,从而解决了原方法漏报接近事件的问题 。该方法在理论上可以检测到所有的接近事件,数值仿真验证支持了该结论。在计算效率 上新方法相对于原算法也有约10倍的提高。     

基于数学形态学的空间飞行器特征提取算法

在基于机器视觉的空间飞行器相对定姿研究中,特征提取算法是相对定姿的基础。提出了基于数学形态学的空间飞行器特征提取算法,该算法有机地融入了空间飞行器的姿轨信息,实现了特征提取中结构元素的动态重构。仿真结果表明,该算法是解决空间飞行器特征提取的一种有效方法,尤其是结构元素的动态选取思路在相关研究领域也具有一定的参考价值。     

Compliance of disposal orbits with the French Space Operations Act: The Good Practices and the STELA tool

Space debris mitigation is one objective of the French Space Operations Act (FSOA), in line with Inter-Agency Space Debris Coordination Committee (IADC) recommendations, through the removal of non-operational objects from populated regions. At the end of their mission, space objects are to be placed on orbits that will minimize future hazards to space objects orbiting in the same region. The FSOA, which came into force in 2010, ensures that technical risks associated with space activities are properly mitigated. The Act confers CNES a central support role in providing technical expertise to government on regulations dealing with space operations. In order to address the compliance of disposal orbits with the law technical requirements, CNES draws up Good Practices as well as a dedicated tool, Semi-analytic Tool for End of Life Analysis (STELA).     

平均轨道根数与密切轨道根数的互换

基于双行轨道根数和简化普适摄动算法,提出平均轨道根数与密切轨道根数的互换算法。以在轨Tan-DEM-X编队的双星为例进行仿真。与传统的只考虑J2项摄动短周期影响的转换算法相比,本文提出的互换算法精度更高：由平均轨道根数转换的密切轨道根数与STK 8软件给出的结果一致;由密切轨道根数转换的平均轨道根数与北美防空司令部公布的双行轨道根数一致。仿真结果表明该互换方法具有科学性和工程应用价值。     

轨道要素奇异问题的改进四元数方法

运用四元数方法可以在一定范围内解决描绘飞行器轨道运动时轨道要素的奇异问题。但四元数固有的双值性使得在对运动方程进行积分时,其正负选取很困难。为了解决这一问题,采用了改进约束方程的四元数方法,并用该方法描述了拉格朗日行星摄动方程,然后研究了地球扁率摄动对地球同步卫星轨道的影响。仿真结果表明：当偏心率小于1时,四元数可以很好地解决轨道要素奇异性问题。与改进的春分点轨道要素相比,四元数的方法有着更加明确的物理意义和几何意义,用四元数表示的运动变量方程的计算更为简单,积分计算效率更高,而且其计算误差也能达到精度要求。     

一组新的四元数轨道要素建模方法

针对传统以欧拉角为参数的轨道要素的奇异性、不确定性以及计算效率低等问题,提出了一种新的四元数轨道要素。建立了新轨道要素与经典轨道要素,以及新轨道要素与惯性系下位置、速度的相互转换关系,推导了基于新轨道要素的高斯摄动方程。以J₂项摄动下的轨道推演为例进行仿真验证,结果表明新轨道要素不仅在圆轨道与赤道平面轨道处不存在奇异性和不确定性,而且由于新轨道要素不涉及三角函数运算,新高斯摄动方程积分效率和计算精度明显提高。     

Cleaning space debris with a space-based laser system

High-energy pulsed laser radiation may be the most feasible means to mitigate the threat of collision of a space station or other valuable space assets with orbital debris in the size range of 1–10 cm. Under laser irradiation, part of the debris material is ablated and provides an impulse to the debris particle. Proper direction of the impulse vector either deflects the object trajectory or forces the debris on a trajectory through the upper atmosphere, where it burns up. Most research concentrates on ground-based laser systems but pays little attention to space-based laser systems.There are drawbacks of a ground-based laser system in cleaning space debris. Therefore the placement of a laser system in space is proposed and investigated. Under assumed conditions,the elimination process of space debris is analyzed. Several factors such as laser repetition frequency, relative movement between the laser and debris, and inclination of debris particles which may exercise influence to the elimination effects are discussed. A project of a space-based laser system is proposed according to the numerical results of a computer study. The proposed laser system can eliminate debris of 1–10 cm and succeed in protecting a space station.     

Orbit determination of BeiDou navigation satellite system maneuvered satellites based on instantaneous velocity pulses parameters

The BeiDou navigation satellite system (BDS) comprises geostationary earth orbit (GEO) satellites as well as inclined geosynchronous orbit (IGSO) and medium earth orbit (MEO) satellites. Owing to their special orbital characteristics, GEO satellites require frequent orbital maneuvers to ensure that they operate in a specific orbital window. The availability of the entire system is affected during the maneuver period because service cannot be provided before the ephemeris is restored. In this study, based on the conventional dynamic orbit determination method for navigation satellites, multiple sets of instantaneous velocity pulses parameters which belong to one of pseudo-stochastic parameters were used to simulate the orbital maneuver process in the orbital maneuver arc and establish the observed and predicted orbits of the maneuvered and non-maneuvered satellites of BeiDou regional navigation satellite system (BDS-2) and BeiDou global navigation satellite system (BDS-3). Finally, the single point positioning (SPP) technology was used to verify the accuracy of the observed and predicted orbits. The orbit determination accuracy of maneuvered satellites can be greatly improved by using the orbit determination method proposed in this paper. The overlapping orbit determination accuracy of maneuvered GEO satellites of BDS-2 and BDS-3 can improve 2–3 orders of magnitude. Among them, the radial orbit determination accuracy of each maneuvered satellite is basically better than 1 m. simultaneously, the combined orbit determination of the maneuvered and non-maneuvered satellites does not have a great impact on the orbit determination accuracy of the non-maneuvered satellites. Compared with the multi GNSS products (indicated by GBM) from the German Research Centre for Geosciences (GFZ), the impact of adding the maneuvered satellites on the orbit determination accuracy of BDS-2 satellites is less than 9 %. Furthermore, the orbital recovery time and the service availability period are significantly improved. When the node of the predicted orbit is traversed approximately 3 h after the maneuver, the accuracy of the predicted orbit of the maneuvered satellite can reach that of the observed orbit. The SPP results for the BDS reached a normal level when the node of the predicted orbit was 2 h after the maneuver.     

Fast calculation method for mission opportunities in orbital interception and rendezvous problems

This paper proposes a fast calculation method to solve all mission opportunities for orbital interception and orbital rendezvous under the impulse-magnitude constraint. Different from the existing search methods, the proposed method does not need to solve Lambert’s problem in the whole process. Three cases are considered for either departure time or transfer time being free, or both being free. For fixed departure time, the feasible windows of transfer time are obtained by solving a single-variable nonlinear equation only of terminal true anomaly. Similarly, for fixed interception (or rendezvous) time, the feasible windows of departure time are obtained. For free departure time and free transfer time, all mission opportunities are obtained by using a one-dimensional search strategy. The hyperbolic-transfer and the multiple-revolution cases are also analyzed. Numerical results show that the proposed method is superior to the typical pork-chop plot method and the two-dimensional launch window method in computational time.     

A novel visual servo method for space manipulators by planning jerk

A novel trajectory planning method for space manipulators is proposed in this article, which can generate trajectory in Cartesian space with continuous joint jerk. The key idea is that, given the desired position for an individual joint, the corresponding joint trajectory is generated in a way like a controller. The generated jerk acts as the controller’s output driving an ideal third-order system to arrive at the desired position, with no need for discrete points in advance. In real applications, the visual servo task is accomplished hierarchically. Since the desired pose in Cartesian space measured by cameras concerns multi degrees of freedom (DOF), desired positions for individual joints are obtained by inverse-kinematics model. Then, joint trajectories are generated as above. To improve the trajectory’s smoothness, a bridging matrix is implemented to ensure that the desired pose varies continuously. Simulation and experimental results show that the proposed method is effective to track targets with different kinds of motion, i.e. can track the input-bounded signal asymptotically.