火星大气进入段侧向预测校正制导律设计

火星大气进入段预测校正制导方法通常采用误差走廊来约束侧向运动,该方法只能满足侧向运动的末端约束,而无法实现对侧向运动过程约束的满足。将预测制导的方法引入侧向制导律设计中,该方法无需离线规划误差走廊,而是根据侧向运动中的相关约束,在线计算倾侧角反转时刻,从而同时满足侧向运动的末端约束与过程约束,并能够克服采用误差走廊可能导致的飞行器因频繁反转机动而使燃料过快消耗的问题。仿真结果表明:该侧向预测制导律不仅能满足开伞位置精度,同时也能实现对进入轨迹侧向运动的灵活规划。     

复杂约束下航天器姿态机动球面几何规划方法

针对航天器进行大角度姿态机动过程中约束多且复杂的问题，提出一种基于球面几何的姿态规划方法。该方法将复杂指向约束描述为多个禁入锥，设计了区分有效约束和无效约束的路径约束检测方法，能有效减少当前路径处理的约束数量；然后将三维空间避障问题映射到二维平面上，通过球面几何距离公式推导了中间姿态指令解析解。仿真结果表明，该方法规划的姿态机动路径不仅能够满足复杂指向约束，而且具有节省机动时间、计算效率高的优点。     

RLV末端能量管理段三维鲁棒制导方法

针对传统可重复使用运载器(RLV)末端能量管理段(TAEM)制导方法在精度和实时性方面的不足,提出了一种三维鲁棒制导方法,提高扰动情形下的返回精度。首先,转换RLV时域制导模型为以高度为自变量的等效模型,设计基于滑模控制理论的制导算法,根据运载器当前状态生成满足动力学、末端和动压约束的状态轨线及制导指令;输入指令至RLV时域制导模型,一个制导周期后根据当前飞行状态更新制导指令,抵抗气动、大气及质量偏差等扰动。标称和扰动两种情形下的仿真验证了制导方法的性能。     

航天器自主任务规划修复技术研究进展

结合航天器自主能力发展的迫切需求，阐述了航天器自主任务规划修复的必要性和难点。给出了航天器自主任务规划修复技术、航天器任务规划稳定性和规划修复问题的定义。根据规划执行失败时采用的修复策略，将自主任务规划修复技术分为规则匹配型、局部调整型、删除/求精型、状态转移型和构造新问题型五类。重点归纳了各类自主任务规划修复技术的研究进展和特点，分析了规划稳定性的定量评价方法。并在对目前任务规划修复方法总结分析的基础上，给出了未来航天器自主任务规划修复技术的研究方向建议。     

火星大气进入段纵向可达区生成的解析同伦法

针对火星大气进入段飞行器的飞行能力分析问题，提出一种基于解析同伦法的纵向可达区(开伞点高度-航程剖面)计算方法。该方法首先分别为最大航程问题/最小航程问题和最大/小开伞高度问题构造最优解已知的初始辅助优化问题，并以此为出发点最终求取原最优问题的解。在求解4个子优化问题的基础上，通过构造合适的同伦参数延拓出纵向可达区。〖JP2〗仿真结果表明，该方法有效避免了最优问题协态初值猜测困难的问题，通过设计合适的同伦参数，可以快速求取任意初始路径角下的开伞点最大/最小航程、最大开伞高度以及纵向可达区。     

Behavioral and biological effects of autonomous versus scheduled mission management in simulated space-dwelling groups

Logistical constraints during long-duration space expeditions will limit the ability of Earth-based mission control personnel to manage their astronaut crews and will thus increase the prevalence of autonomous operations. Despite this inevitability, little research exists regarding crew performance and psychosocial adaptation under such autonomous conditions. To this end, a newly-initiated study on crew management systems was conducted to assess crew performance effectiveness under rigid schedule-based management of crew activities by Mission Control versus more flexible, autonomous management of activities by the crews themselves. Nine volunteers formed three long-term crews and were extensively trained in a simulated planetary geological exploration task over the course of several months. Each crew then embarked on two separate 3–4 h missions in a counterbalanced sequence: Scheduled, in which the crews were directed by Mission Control according to a strict topographic and temporal region-searching sequence, and Autonomous, in which the well-trained crews received equivalent baseline support from Mission Control but were free to explore the planetary surface as they saw fit. Under the autonomous missions, performance in all three crews improved (more high-valued geologic samples were retrieved), subjective self-reports of negative emotional states decreased, unstructured debriefing logs contained fewer references to negative emotions and greater use of socially-referent language, and salivary cortisol output across the missions was attenuated. The present study provides evidence that crew autonomy may improve performance and help sustain if not enhance psychosocial adaptation and biobehavioral health. These controlled experimental data contribute to an emerging empirical database on crew autonomy which the international astronautics community may build upon for future research and ultimately draw upon when designing and managing missions.     

Mechanical behavior of the metal parts welded with extraterrestrial regolith simulant by the solar concentrator in ISRU & ISRF application

The use of in-situ resources plays an important role on future extraterrestrial human activities for the facility repair and habitat construction, especially in sustainable space exploration of Moon and Mars. A method of the metal welded with extraterrestrial regolith simulant using solar processing under ambient conditions is presented. Metal parts are made of Q235B ferroalloy and TA2 titanium alloy into standard tensile members according to the ASTM code. They are disconnected from the middle in advance, and then welded together with lunar and Martian regolith simulant under ambient conditions, respectively. The entire welding process and precautions are detailed. Additionally, the mechanical behavior of weldments is characterized regarding their tensile strength. Furthermore, the fusion zone of weldments is studied by Scanning electron microscopy (SEM), energy dispersive X-ray spectroscopy (EDS) and X-ray diffraction (XRD) measurements. The results show that it is possible to weld metal parts together with extraterrestrial regolith simulant by the solar concentrator. The average ultimate tensile strength of ferroalloy specimens welded with lunar and Martian regolith simulant is 2.94 MPa and 1.66 MPa; The average ultimate tensile strength of titanium alloy specimens welded with lunar and Martian regolith simulant is 4.95 MPa and 2.59 MPa. Moreover, the failure mode of all weldments was brittle failure. The welding joints strength derives from the phases that the regolith as the solder fusing into ferroalloys in a homogeneous way and titanium alloys in an inhomogeneous way. The presented method may provide a new thought for astronaut assistance associating with repairing and fabricating in subsequent Moon and Mars missions.     

Taiwan's second remote sensing satellite

FORMOSAT-2 is Taiwan's first remote sensing satellite (RSS). It was launched on 20 May 2004 with five-year mission life and a very unique mission orbit at 891 km altitude. This orbit gives FORMOSAT-2 the daily revisit feature and the capability of imaging the Arctic and Antarctic regions due to the high enough altitude. For more than three years, FORMOSAT-2 has performed outstanding jobs and its global effectiveness is evidenced in many fields such as public education in Taiwan, Earth science and ecological niche research, preservation of the world heritages, contribution to the International Charter: space and major disasters, observation of suspected North Korea and Iranian nuclear facilities, and scientific observation of the atmospheric transient luminous events (TLEs). In order to continue the provision of earth observation images from space, the National Space Organization (NSPO) of Taiwan started to work on the second RSS from 2005. This second RSS will also be Taiwan's first indigenous satellite. Both the bus platform and remote sensing instrument (RSI) shall be designed and manufactured by NSPO and the Instrument Technology Research Center (ITRC) under the supervision of the National Applied Research Laboratories (NARL). Its onboard computer (OBC) shall use Taiwan's indigenous LEON-3 central processing unit (CPU). In order to achieve cost effective design, the commercial off the shelf (COTS) components shall be widely used. NSPO shall impose the up-screening/qualification and validation/verification processes to ensure their normal functions for proper operations in the severe space environments.     

Aerospace launch vehicle control: an intelligent adaptive approach

A theoretical analysis of on-line autonomous intelligent adaptive tracking controller based on emotional learning model in mammalians brain (BELBIC) for aerospace launch vehicle is presented. The control algorithm is provided with some sensory inputs and reward signal, subsequently it autonomously seeks the proper control signal to be executed by actuators, thus eliminating tracking error without pre-knowledge of the plant dynamics. The algorithm is very robust and fast in adaptation with dynamical change in the plant, due to its on-line learning ability. Development and application of this algorithm for an aerospace launch vehicle during atmospheric flight in an experimental setting is presented to illustrate the performance of the control algorithm.