空间任务人机协同作业内涵及关键技术问题

论述了空间任务人机协同作业的内涵,指出其与其它人机关系相比具有平等性、独立性和协同性的特点;分析了国内外相关研究情况,得出目前人机协同作业研究大多集中在人机交互领域,缺乏对顶层的研究;指出需要重点关注的人机任务分配、人机安全控制和人机信息交互三个关键问题,并提出了我国开展空间任务人机协同作业的发展建议,如与遥操作技术的发展和应用紧密结合、充分注重在轨演示、应当先采用人主机辅的模式等。     

地效飞行器重量估算方法

根据地效飞行器(WIG)的特点确定了3类地效飞行器的任务剖面,分析其与一般飞行器任务剖面和相关性能的异同点以及重量估算方法的适用度。通过现有地效飞行器数据和资料的整理,研究其起飞重量与空机重量以及其他各项参数的统计关系。比照一般飞行器重量估算的燃油系数法,确定地效飞行器各任务阶段的燃油系数及其相关计算过程中选择参数的修正。通过数据分析计算起飞重量和空机重量估算中的线性回归值,形成适用于各类地效飞行器的重量估算方法及其推荐经验系数。验算结果证明,A类和B类地效飞行器重量估算结果与实际产品基本相符,C类由于缺乏足够的统计数据,因此难以验算,但实际工程设计应用结果与经验类比法得到的重量估算结果基本一致,表明研究结果能够满足总体设计阶段重量估算的任务要求。     

基于FFMECA的任务可靠性综合评价方法

任务可靠性的评价是武器装备研制生产过程中的重要工作内容,任务阶段的FMECA评价多从定性的角度进行,未考虑故障模式影响程度的定量指标。基于模糊数学思想,结合FMECA分析中的故障模式影响概率,形成FFMECA分析方法;并在此基础上,将那些影响任务完成的故障模式以定量的形式进行区分,进行考虑故障模式影响概率的任务可靠性评价,并以可撒布地雷为例开展了任务阶段的定量与定性分析。结果表明:本文方法紧密结合可靠性前期工作,对武器装备可靠性评价流程进行了规划,对可靠性评价方法的工程应用具有一定的指导意义。      

考虑动态不确定因素的深空探测器任务规划

针对现有的任务规划方法在响应深空动态不确定因素的扰动情况时存在的不确定因素识别度低、响应策略单一等问题,文章提出了一种考虑动态不确定因素的深空探测器任务规划算法。首先,对不确定扰动按从轻到重四个等级进行划分,并采用模糊神经网络评估不确定扰动属于哪种扰动级别,根据评估结果选择对应的扰动响应策略;然后,采用基于分层任务网络规划（HierarchicalTaskNetwork,HTN）的局部任务修复方法,对受到扰动的子系统对应的复合任务重新进行任务分解,完成对初始规划方案的调整修复。仿真结果表明所提出的算法可以有效地对深空动态不确定因素进行评估和响应,从而提高了任务规划的可靠性和灵活性。     

The flyby anomaly: A case for strong gravitomagnetism?

In the last two decades an anomalous variation in the asymptotic velocity of spacecraft performing a flyby manoeuvre around Earth has been discovered through careful Doppler tracking and orbital analysis. No viable hypothesis for a conventional explanation of this effect has been proposed and its origin remains unexplained. In this paper we discuss a strong transversal component of the gravitomagnetic field as a possible source of the flyby anomaly. We show that the perturbations induced by such a field could fit the anomalies both in sign and order of magnitude. But, although the secular contributions to the Gravity Probe B experimental results and the Lense–Thirring effect in geodynamics satellites can be made null, the detailed orbital evolution is easily in conflict with such an enhanced gravitomagnetic effect.     

Improvement of the GRACE star camera data based on the revision of the combination method

The new release of the sensor and instrument data (Level-1B release 02) of the Gravity Recovery and Climate Experiment (GRACE) had a substantial impact on the improvement of the overall accuracy of the gravity field models. This has implied that improvements on the sensor data level can still significantly contribute to arriving closer to the GRACE baseline accuracy. The recent analysis of the GRACE star camera data (SCA1B RL02) revealed their unexpectedly higher noise. As the star camera (SCA) data are essential for the processing of the K-band ranging data and the accelerometer data, thorough investigation of the data set was needed. We fully reexamined the SCA data processing from Level-1A to Level-1B with focus on the combination method of the data delivered by the two SCA heads. In the first step, we produced and compared our own combined attitude solution by applying two different combination methods on the SCA Level-1A data. The first method introduces the information about the anisotropic accuracy of the star camera measurement in terms of a weighing matrix. This method was applied in the official processing as well. The alternative method merges only the well determined SCA boresight directions. This method was implemented on the GRACE SCA data for the first time. Both methods were expected to provide optimal solution characteristic by the full accuracy about all three axes, which was confirmed. In the second step, we analyzed the differences between the official SCA1B RL02 data generated by the Jet Propulsion Laboratory (JPL) and our solution. SCA1B RL02 contains systematically higher noise of about a factor 3–4. The data analysis revealed that the reason is the incorrect implementation of algorithms in the JPL processing routines. After correct implementation of the combination method, significant improvement within the whole spectrum was achieved. Based on these results, the official reprocessing of the SCA data is suggested, as the SCA attitude data are one of the key observations needed for the gravity field recovery.     

航天测控网资源均衡分配的调度方法

研究了航天测控网资源集中管理、统一分配的工作模式,以及满足多星测控任务的测控网资源调度方法。提出了测控网均衡调度的方法。首先面向任务,将卫星测控任务按优先级划分,按最优分配的原则进行分配,使测控网能够支持的任务数量大;在此基础上,考虑测控站负荷和备份再进行优化,使测控网内各测控站的负荷均衡。相比其他方法,考虑了任务执行的成功概率,各测控站任务分配更均匀,便于测控网的管理。     

无人火星取样返回任务关键环节分析

无人火星取样返回探测在科学成果获取和工程能力提升方面均具有重要意义,与国外已经多次实现的火星着陆巡视任务相比,其任务周期更长,技术风险更高。取样返回飞行方式决定了任务的系统顶层设计。通过对国外研究成果的对比论证,认为应当在火星轨道附近完成交会捕获与样品转移任务,因此需要采用2个不同功能探测器:一个完成火星捕获、样品转移收纳与火地返回;另一个完成火星大气进入、表面上升与样品投送。在此基础上对大气进入、起飞上升、火星轨道交会捕获、样品转移、地球再入等关键环节进行任务分析,论证主要技术难点和初步的可实现途径。     

微型空射诱饵任务载荷系统设计与工作状态分析

微型空射诱饵(MALD)是美军研发的一款以信号增强系统、有源雷达干扰机为载荷的由载机发射的诱饵弹。MALD经过20多年的发展,现已成为一款集侦察、欺骗、压制和打击于一体的射频综合诱饵,战场“踹门”作用十分强大。鉴于目前国内对该类型武器的研发尚处起步阶段,美对其载荷相关信息披露甚少,所以本文从MALD的功能出发,对MALD任务载荷系统组成进行分析,在给定的任务背景下,利用雷达对抗理论对其工作状态作初步分析,仿真结果可为MALD战场运用提供理论支撑。     

“嫦娥4号”中继星使命轨道段定轨计算与分析

"嫦娥4号"中继星是"嫦娥4号"探测器实现月球背面着陆与巡视的关键,目前正稳定运行在地-月L2点使命轨道上,该使命轨道为平均周期约14天的南族Halo轨道。因任务的需要,中继星本体系+Z轴需调整指向,处于正对太阳和非正对太阳两种状态。太阳光压在中继星+Z轴对日的情况下会加速卫星的角动量累积,增加卫星卸载喷气频次。基于中继星使命轨道段测控支持条件,采用重叠弧段法对两种状态下的中继星定轨精度进行分析与评估。结果表明,在中继星+Z轴非对日运行状态下,重叠弧段位置误差为1.6 km,速度误差为8 mm/s;在中继星+Z轴对日运行状态下,重叠弧段位置误差为0.6 km,速度误差为3 mm/s,这对中继星的长期运行具有重要参考价值。