装备管理是现代测控装备发挥有限潜能的重要基础,传统的设备管理模式存在着诸多不适应测控装备运行与使用的问题,需要改进设备管理模式以适应日益紧张的测控活动需要.TPM和LM作为一种先进的设备管理维修模式,在现代设备管理中发挥着重要的作用.从测控装备管理存在的问题入手,分析TPM和LM的内涵与优势,并在此基础上提出了TPM和LM在测控装备管理中的具体应用,对测控装备进行TPM和LM实施提供了相应的解决方案.

阐述深空基带数传接收机环路设计原理,环路动态性能测试,分析环路解调性能,探讨数传接收机环路的自适应设计,从而实现不同信噪比及动态条件下,目标捕获和跟踪解调.

为了解决测控基带备机双向捕获过程中错锁的问题,对接收机载波锁定原理、频率捕获单元工作流程进行分析,查找产生错锁原因.搭建模拟测试环境开展试验验证,并对软硬件进行适应性修改,改进了防错锁方法,为测控活动提供有力保障.

深空测控活动具有信号空间衰减大、传输时延长、传播环境复杂等特点,电磁干扰对活动影响较大.对某型深空站电磁干扰现状开展分析,区分各类干扰源,对常用的抗电磁干扰对策方法进行研究.以电磁环境监测与管理信息系统为依据来研究电磁环境实时监测在深空站的实现,探索适宜深空站使用的电磁干扰监测方法和抗电磁干扰的对策,并从体制机制上对深空站实施有效保护.

The exploration of the far-side of the Moon has significant scientific meaning but no suc-cessful experience till now. By establishing the 3-body dynamic model in Earth centered inertial co-ordinate system, and using the differential correction method, the candidate free-return orbit for fu-ture manned lunar mission was designed. Through establishing the CR3BP model in rotating coordi-nate, and employing the proposed "Halo-like Section" method, the low-energy transfer orbit from free-return orbit to L2 Halo orbit was designed and optimized. The simulation and computation re-sults showed that the hybrid orbit could not only meet the safety requirements, but also could lay the relay satellite providing communication relay service for the mission. The design method and results could serve as references for the safe orbit and relay satellite constellation designing for the future manned lunar exploration mission.

天线的指向精度是系统的关键指标，影响任务执行的质量。指向改正和标校是提高精度的基本途径。佳木斯66米深空探测系统现有的指向标校工作需要人为制定计划，手动完成大量宇宙天体目标的跟踪扫描，工作期间要不断重复设置目标、操作天线。设计并完成了一套完整的指向标校自动化软件，能够完成标校计划的自动规划和标校观测计划的自动执行，提高了扫描效率，极大地降低了人工操作和干预程度，解放了人力。该系统使标校目标的观测方位和俯仰更加均匀，使结果用于指向改正模型解算时能更好地提高指向精度。

China deep space controlling network (CDSCN)constructed and applied in lunar missions can do range and range-rate as well as VLBI together with remote control and telemetry at radio band for deep space tracking like Mars missions and other deep space exploration missions.Remote deep space exploration missions shift the direction of up-link and down-link signals because of increasing time duration of microwave transmission between aiming planets and ground.This is a challenge for remote exploration telecommunication because it is not possible to do up-link and down-link radio communications simultaneously.For a typical Mars exploration,the disadvantages of deep-space measurements with single radio antenna controlling system are analyzed.Several suggestions for updating and upgrading controlling equipments are made which are necessary for remote communication on deep space exploration missions.The up and down-links could be time-divided on a solo antenna at a given deep space tracking station.Or the up and down-links are set up in multiple stations with solo antenna each with 3-way open loop method.The DSN/JPL/NASA method are used to set up multiple antennas at each deep space tracking station,with antennas share the same time-frequency standard,and the antennas at same station realizing close-loop up and down link real-time TT & C continuously.

Pointing accuracy is one of the most important characteristics for a large radio telescope;it is very fundamental for telescope running. To ensure good performance for measuring the flux density of a radio source, pointing accuracy must be kept within 10% of telescope beam size. In this paper we present results of large measurements of telescope points for Jiamusi 66m radio telescope, and show the basic-parameter model and the fitting residuals of pointing data. We find that even after the correction of a new best-fitting basic-parameter model, the pointing uncertainty data still have a systematic variations of concentration along with the azimuth and elevation, which we believe is caused by the high order variations of the angle between the azimuth axis and elevation axis as well as the gravity deformation. We improve the basic-parameter model for the pointing corrections, and we get much improved pointing accuracy for Jiamusi 66m radio telescope from 45″to less than 20″.