INVESTIGATION OF TIGHTLY COUPLED SINS/GPS INTEGRATION MIDCOURSE GUIDANCE FOR AIR-TO-AIR MISSILES

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No deal in space: A bargaining model analysis of U.S. resistance to space arms control

Space systems are essential to the global economy and security. The possibility of disruptions arising from competition between the United States and China through the testing and deployment of weapons in space has led to concerns over an incipient space arms race that would threaten satellites, leading to international calls for a space arms control treaty. The paper presents a rationalist theory analysis on the lack of progress in establishing such a treaty, identifying the United States' position of primacy in the global order and its preeminence in space as a primary cause.     

SETI implications of gravitational assist via chaotic trajectories of binary objects

Extrapolating from the technique of gravitational assist via chaotic trajectories of binary objects, this paper considers how such techniques might be used in other systems. We examine which types of systems are the best candidates for harvesting gravitational energy for payload ejection. We also consider what signatures might be present in either the asteroid orbits or radiation of the central body if extraterrestrial intelligences were to use such techniques about these candidate systems.The simulation studies show that current technology cannot approach the sensitivity needed to detect either of these signals. Instead, we provide these results as guidance to studies in coming decades on patterns that may indicate the use of an asteroid ejection system.     

基于博弈模型的航空型号异地协同知识共享激励研究

在航空型号异地协同研发的过程中需要参研单位进行知识共享,针对知识共享过程中产生的问题,构建知识共享博弈模型并对其进行分析,提出了对采取共享策略的参研单位给予奖励,在博弈模型中引入激励因素,并分析了激励对参研单位知识共享行为的影响。     

预制语块理论在外语低起点学习者口语教学中的应用研究

通过设置实验组和对照组,对某高职院校2012级会计班的英语预制语块教学改革展开研究。结果表明,尽管低起点学习者的语言水平、课堂学习积极性以及对新方法的配合程度对口语教学质量构成一定影响,但整体来说,这一理论的运用对低起点英语学习者口语表达能力的提高有帮助。对教学改革的启示是,教师能够通过一系列有趣的、行之有效的教学新理论和监督指导策略帮助部分低起点学习者找到好的学习方法,重拾学习兴趣,树立学好英语的信心。     

舰尾流环境中载机纵向QFT/TECS控制系统设计

为了消除舰尾流对载机着舰过程产生的影响,同时完成低动压状态下飞行速度与高度的解耦工作,基于定量反馈理论/总能量控制理论(QFT/TECS)设计了纵向着舰控制系统。针对着舰过程中数学模型所具有的不确定因素及舰尾流对下滑航迹的影响,以载机高度变化率为控制对象,使用定量反馈理论结合推力补偿系统进行了内回路鲁棒控制律设计。外回路控制律设计是以总能量控制理论为基础,通过粒子群优化算法对待调控制参数进行寻优,进而实现了对高度、速度等参数的精确控制,完成了载机纵向着舰轨迹与速度的解耦工作。仿真结果表明,该控制律在拥有较强的鲁棒性的基础上具有良好的解耦控制能力,实现了载机着舰段的高度与速度的解耦控制,明显提高了载机对着舰轨迹的跟踪能力,可满足不确定条件下载机的着舰要求。     

共信道干扰环境下星基ADS-B系统监视性能

星基广播式自动相关监视系统（星基ADS-B）是实现广域范围内航空器监视的主要技术手段。为揭示星基ADS-B系统共信道干扰对系统监视性能的影响，提出了星基ADS-B系统监视容量的计算方法。首先给出了星基ADS-B系统模型，随后理论分析给出消息正确接收概率、位置消息更新间隔及位置报告更新间隔的计算公式，以此为基础给出了星基ADS-B系统监视容量的计算公式，最后基于SNS软件构建了星基ADS-B仿真系统，仿真验证了理论结果的正确性。研究表明：星基ADS-B系统的监视容量由ADS-B应用子系统所要求的航空器位置报告更新间隔、航空器-卫星链路的误码率、星-地面站链路的误码率及卫星数目联合确定。     

某型干扰机干扰效果提升研究

通过研究某型干扰机对多普勒雷达速度跟踪系统的干扰方式，分析假多普勒频率产生的干扰工作机理，研究对抗科目训练中该模式干扰效果不佳的具体原因，提出了采用数字移向技术替代行波管移相，增大对雷达回波原载频的抑制度，增强干扰效果。通过对样机的测试验证，给出了两种移相电路的假多普勒干扰比较。     

Tractable Fragments of Fuzzy Qualitative Algebra

Abstract

In this paper we study the computational complexity of Fuzzy Qualitative Temporal Algebra (QA ^fuz ), a framework that combines qualitative temporal constraints between points and intervals, and allows modelling vagueness and uncertainty. Its tractable fragments can be identified by generalizing the results obtained for crisp Constraint Satisfaction Problems (CSPs) to fuzzy CSPs (FCSPs); to do this, we apply a general methodology based on the notion of α-cut. In particular, the results concerning the tractability of Qualitative Algebra QA, obtained in a recent study by different authors, can be extended to identify the tractable algebras of the fuzzy Qualitative Algebra QA ^fuz in such a way that the obtained set is maximal, namely any maximal tractable fuzzy algebra belongs to this set.     

Spacecraft Design-for-Demise implementation strategy & decision-making methodology for low earth orbit missions

Space missions designed to completely ablate upon an uncontrolled Earth atmosphere reentry are likely to be simpler and cheaper than those designed to execute controlled reentry. This is because mission risk (unavailability) stemming from controlled reentry subsystem failure(s) is essentially eliminated. NASA has not customarily implemented Design-for-Demise meticulously. NASA has rather approached Design-for-Demise in an ad hoc manner that fails to entrench Design-for-Demise as a mission design driver. Thus, enormous demisability challenges at later formulation stages of missions aspired to be demisable are evident due to these perpetuated oversights in entrenching Design-for-Demise practices. The investigators hence propose a strategy for a consistent integration of Design-for-Demise practices in all phases of a space mission lifecycle. Secondly, an all-inclusive risk-informed, decision-making methodology referred to as Analytic Deliberative Process is proposed. This criterion facilitates in making a choice between an uncontrolled reentry demisable or controlled reentry. The authors finally conceive and synthesize Objectives Hierarchy, Attributes, and Quantitative Performance Measures of the Analytical Deliberative Process for a Design-for-Demise risk-informed decision-making process.