航天任务计划工作模式的改进研究

阐述航天任务飞行控制、现有计划工作模式的基本概念,提出计划工作模式改进建议,即定义飞行状态向量、飞行控制规则,在现有非自动闭环控制的基础上设计引入状态反馈回路,增加冲突检测和自动修正功能,实现计划自动闭环输出,形成基于状态和规则运行、适应性强、自动化程度高的改进型计划工作模式。     

人工智能在航天飞行任务规划中的应用研究

 在航天飞行任务中，如何设计航天器的飞行过程，如何确定地面对航天器的控制操作，如何制定飞行控制计划等，是地面飞行控制中心面临的重大问题，也是航天飞行任务规划所要解决的基本问题。在充分认识和把握人工智能基本原理、方法和技术的基础上，提出了一个基于规则演绎和状态演化的生长式推理模型，并对模型的特性进行了详细讨论，然后导出了该模型在航天飞行任务规划问题中的具体形式，从而成功地解决了航天任务自动规划的难题。通过在实际航天任务中的应用和验证，不仅证明该模型和方法是正确的、可行的和高效的，而且证明人工智能在航天飞行任务规划中有着广阔的应用前景。     

2009年世界载人航天发展综合分析

2009年,世界载人航天领域取得重要进展。美国、俄罗斯、日本等国家围绕国际空间站建设执行多次航天飞行任务,并着手新型载人航天运输系统的研制。特别是美国出台载人航天飞行计划评审报告,审视未来发展。与此同时,主要国家间的航天合作更加密切,中美政府就国际航天合作前景展开对话,尤为引人关注。此外,美国、日本、印度的探月计划也取得预期成果。     

神舟七号载人航天飞行任务航天员选拔与训练

航天员选拔训练是载人航天工程中至关重要的环节,选拔训练合格的飞行乘组将直接影响到工程计划的顺利实施和飞行任务的成败。简要分析和阐述神舟七号载人航天飞行出舱活动任务对飞行乘组及航天员选拔训练的要求与挑战、选拔的策略和原则,概述选拔训练的项目、内容、方法、实施安排与结果,以及出舱活动训练简况。     

载人航天飞行试验任务中遥控计划正确性自动验证方法的研究

本文以我国栽人航天工程飞行试验任务为背景,讨论了在任务中遥控计划的验证内容、正确性判断准则和判断方法,并给出了遥控计划正确性验证的流程。通过在任务中实现遥控计划正确性自动验证。保证了北京中心遥控计划的正确性和可靠性,确保了飞控任务的顺利实施,大大提高了工作效率。     

无人机任务段轨迹控制模式对姿态平稳性的影响分析

姿态平稳性是机载任务设备工作的重要影响因素,是无人机飞控和飞行品质的重要考核内容。飞控系统的姿态内回路参与飞行轨迹的精确控制,因此,在任务阶段采用不同的控制模式,对姿态平稳度有显著影响。通过分析纵向和水平方向不同轨迹控制模式的原理,对比无人机飞行姿态角数据的差异,得出轨迹控制模式对姿态平稳度和轨迹控制精度的影响。     

航天任务控制中心容灾模式研究

航天任务是一项高投入、高风险的活动,作为管理所有在轨飞行航天器及资源的航天任务控制中心,要求具备很高的可靠性与较强的容灾能力。国际航天大国对地面系统,特别是任务中心级的备份均非常重视,也开展了相关建设和系统运行。在对我国航天任务控制中心容灾模式进行探讨的基础上,提出容灾中心的技术要素、需求分析以及运行机制。     

电传飞控不同纵向指令形式系统响应特性分析

现代战斗机大都采用带有多模态的电传飞行控制系统,通常在不同的任务模态下,控制系统采用的指令形式不同,飞机对驾驶员的操纵响应也有所不同。文中以电传飞行控制系统中,纵向控制律构型常见的几种指令形式为例,通过理论分析和数字仿真试验方法,分析了不同指令形式下,电传飞行控制系统对飞行员操纵的响应特性,并总结了不同响应特性的指令形式所适合的飞行任务场景。文中分析总结的结果,可为电传飞行控制律设计工作中不同任务模态下,指令形式选择与飞行员飞行任务训练工作提供参考。     

新成就 新跨越 新高度——中国载人航天工程负责人谈神舟七号载人航天飞行任务

在神舟七号载人航天飞行任务获得圆满成功之际,中国载人航天工程负责人接受了本报记者的专访。神舟七号载人航天飞行任务获得圆满成功,巩固了我国载人航天事业业已取得的丰硕成果,实现了我国载人航天发展新的历史跨越,确保了我国载人航天事业持续稳步发展的良好态势。     

战斗机动态逆控制律对比研究

分别采用常规动态逆和模型参考动态逆设计了战斗机飞行控制律,并通过开环时域仿真以及基于任务的闭环飞行品质评估方法,对比分析了两类控制律的特点及差异.研究表明,模型参考动态逆对高频小幅指令跟踪效果较好,在需要驾驶员频繁补偿的飞行任务中表现出的飞行品质更佳.研究结果对战斗机飞行控制律的选择与设计、控制律与飞行任务种类的匹配有一定的参考意义.     

船载多目标模拟器的构建与应用

船载统一S频段（USB）测控系统是我国航天测控网的重要组成部分,承担着一箭单星或一箭多星的海上测控任务。从航天测量船执行多目标测控任务的特点出发,分析了测量船船载飞行目标模拟器的现状以及对多目标模拟器的需求。提出了在船载USB联试应答机的基础上,通过改造应答机的部分模块,构成多目标模拟器的方法,并成功地在某次实战任务中得到了应用。     

Tracking and data acquisition for space exploration

The tracking and data acquisition systems provide the key link between the remote spacecraft and the scientific experimenter on the ground. The operation of the space experiment takes place through the links of command, telemetry and tracking. The evolution from the early very simple spacecraft missions toward more complex and sophisticated missions has been paralleled by a similar evolution in the tracking and data acquisition systems. The early Minitrack interferometer tracking system still carries the major tracking workload for space missions; however greater tracking accuracy requirements for more recent missions, such as the Orbiting Geophysical Observatory and the Apollo mission, have brought about the development of unified tracking and data acquisition systems which utilize hybrid pseudo-random code/sidetone ranging techniques. The data acquisition has evolved from analog telemetry systems to the present day heavy use of PCM digital telemetry. Likewise the command systems have evolved from early simple on/off command systems into PCM digital command data systems. The trend is toward greater real time control of more complex functions on board the spacecraft. Newer spacecraft are incorporating computer-type systems in the spacecraft which require programming and memory load through the ground command link. The most attractive concept for the next generation network for tracking and data acquisition is a network consisting of synchronous-orbit Tracking and Data Relay Satellites for covering launches and low-orbit earth satellites plus a few selected ground stations for supporting spacecraft in high earth orbit and lunar orbit.     

Logistics Transportation for Space Station Support

Logistics support of a long duration space station will dictate a high degree of space flight activity to rotate personnel and transport supplies and equipment. Systems characteristics and mission requirements for space station logistics have been analyzed within the context of a broad spectrum of space missions. Preliminary concepts for a space shuttle system (space transportation) have been developed. This system can support not only a space station program, but a wide variety of space missions for both NASA and the DOD.     

无人直升机地面指挥控制站任务规划系统研究

任务规划系统是无人直升机地面指挥控制站的核心组成部分,是地面指挥控制站规划、感知和管理无人直升机任务的集合。研究和发展任务规划系统是提高无人直升机执行任务效率和降低任务风险的必然趋势。以无人直升机为对象进行了任务规划系统研究,分析了其功能模块组成,并归纳了任务规划系统实现关键技术。     

我国空间站运行的测控通信工作模式初探

在分析我国载人空间站在轨运行的任务特点和对测控通信提出的新要求的基础上,对测控通信工作模式进行了探讨。针对任务中心,采用分布式模式进行任务的组织和实施,建立常态化工作体系;针对测控通信资源的使用,对资源进行简化、优化,发挥天、地基各自优势,并实现天地基资源统一调度;针对在轨故障诊断和应急处置,提出了“天地联合,以地为主”的载人航天故障诊断模式和实现途径;针对空间站遥操作需求,提出了一套工作模式和实施流程;针对测控通信长期执行任务的可靠性,提出了任务中心容灾备份工作模式和通信路由的备份模式。以期为后续任务工作模式设计提供参考。     

The canberra high altitude mission platform

This presents the capabilities of two English Electric Aviation Canberra aircraft owned by High Altitude Mapping Missions, Inc. These aircraft are available for high altitude commercial, government, and scientific missions. The basic specifications of the Canberra are provided and compared to other high-performance jet aircraft falling into the same category. This describes the high altitude flight characteristics and mission capabilities of the Canberras. The aircraft are configured to conduct up to eight-hour flight operations with up to six hours at 50,000 feet altitude. Shorter missions can be conducted at higher altitudes. Potential missions include: IFSAR, magnetic field mapping, gravity field mapping, imaging (SAR, IR, & hyper-spectral), LIDAR, communications relay, dropsonde deployment, hybrid rocket launching, severe storm monitoring, and disaster monitoring. Canberra high altitude operations have minimal weather impact on missions, are free from flight constraints imposed by air traffic control, can do large area coverage, and long mission times.     

高超声速飞行器表面测热技术综述

高超声速飞行中飞行器表面气动加热量是飞行器热防护系统最为关键的设计输入,在理论计算与地面模拟的有限近似条件下,通过飞行试验实时获取真实环境下飞行器表面的气动加热量,并在此基础上完成对计算模型与地面试验的验证与改进具有重要意义。详细列举了20世纪50年代以来,国外具有代表性的飞行试验与测热方案。以“内置式”与“嵌入式”作为测热技术的分类特征,介绍了各类测试设备及相应的飞行试验结果。着重分析了“热匹配性”与“结构匹配性”作为关键因素对飞行测热技术的影响,通过飞行试验实例介绍了该问题的解决方法及工程经验。归纳了飞行测热技术发展的共性、特点与未来趋势,并结合当前我国发展现状,对该领域未来研究提出建议。     

Mission segment division of the whole aeroengine loading spectrum based on flight actions

This paper studies on a division method of the whole aeroengine loading spectrum flight mission segment and rotor speed mission segment, which is based on the actual flight actions and related to the flight operations of aeroengine and is suitable for the variable-speed aeroengines such as turbojet and turbofan. Through the research, the aeroengine loading spectrum operation-related mission segments can be divided, which can provide important data basis for the life research on the structures wh...     

Flight trajectory optimization of sun-tracking solar aircraft under the constraint of mission region

The optimal yawing angle of sun-tracking solar aircraft is tightly related to the solar azimuth angle, which results in a large arc flight path to dynamically track the sun position. However, the limited detection range of payload usually requires solar aircraft to loiter over areas of interest for persistent surveillance missions. The large arc sun-tracking flight may cause the target area on the ground to be outside the maximum coverage area of payload. The present study therefore develops an optimal flight control approach for planning the flight path of sun-tracking solar aircraft within a mission region. The proposed method enables sun-tracking solar aircraft to maintain the optimal yawing angle most of the time during daylight flight, except when the aircraft reverses its direction by turning flight. For a circular region with a mission radius of 50 km, the optimal flight trajectory and controls of an example Λ-shaped sun-tracking solar aircraft are investigated theoretically. Results demonstrate the effectiveness of the proposed approach to optimize the flight path of the sun-tracking aircraft under the given circular region while maximizing the battery input power. Furthermore, the effects of varying the mission radius on energy performance are explored numerically. It has been proved that both net energy and energy balance remain nearly constant as the radius constraint varies, which enables the solar aircraft to achieve perpetual flight at almost the same latitude as the large arc flight. The method and results presented in this paper can provide reference for the persistent operation of sun-tracking solar aircraft within specific mission areas.