一种GEO/LEO双层卫星网络路由算法及仿真研究

时间虚拟化策略的时间片过短将影响路由性能,提出一种基于GEO/LEO双层卫星网络的时间虚拟化和分层管理的路由算法（VLRA）,对时间虚拟化策略进行合理改进,通过新的分层管理思想,在每个时间片开始进行路由计算和更新。分析和仿真验证表明,改进的时间虚拟化策略得到的时间片更合理,利于网络的路由和通信。GEO/LEO双层卫星网络下VLRA算法时延稳定,并具有较好的丢包率和吞吐量性能。     

European initiative & strategy for prioritising and harmonising space technology R&D

This document outlines the objectives, strategy guidelines, and the approach for the harmonisation of European space technology activities, in line with and in support of the resolution “Shaping of the Future of Europe in Space”, adopted at the ESA Ministerial Council in May 1999.Under an overall ESA co-ordination, the European space sector is elaborating a technology strategy based on top-level priorities (Dossier 0), on the mapping of European development and competences and on a co-ordinated Space Technology Master Plan (ESTMP). This plan shall take into account the various European developments, industry capacities and budgets and shall enhance the complementary role of the various partners towards common objectives.The proposed strategy includes selection of priority activities as pilot projects for harmonisation. For these pre-selected pilot projects, agreements are required on responsibilities, leaderships, partnerships and budget commitments.     

A Franco–German view of Europe's ambition in space for the 21st century

Europe has at last started to integrate the assets of its broad set of actors into a comprehensive European Space Strategy. But will this first approach be ambitious enough to strengthen Europe as a global actor? In this contribution, the individuals responsible for strategy in the French and German space agencies seek an answer to this question. They do so by reviewing the historical background to European space efforts, and its role in shaping present-day activities; setting forth a vision of how Europe should proceed in space, and measuring current progress in drafting a European space strategy against this vision.     

The DISC Quotient

D.I.S.C: Decipherment Impact of a Signal's Content.The authors present a numerical method to characterise the significance of the receipt of a complex and potentially decipherable signal from extraterrestrial intelligence (ETI). The purpose of the scale is to facilitate the public communication of work on any such claimed signal, as such work proceeds, and to assist in its discussion and interpretation.Building on a “position” paper rationale, this paper looks at the DISC quotient proposed and develops the algorithmic steps and comprising measures that form this post detection strategy for information dissemination, based on prior work on message detection, decipherment. As argued, we require a robust and incremental strategy, to disseminate timely, accurate and meaningful information, to the scientific community and the general public, in the event we receive an “alien” signal that displays decipherable information. This post-detection strategy is to serve as a stepwise algorithm for a logical approach to information extraction and a vehicle for sequential information dissemination, to manage societal impact.The “DISC Quotient”, which is based on signal analysis processing stages, includes factors based on the signal's data quantity, structure, affinity to known human languages, and likely decipherment times. Comparisons with human and other phenomena are included as a guide to assessing likely societal impact. It is submitted that the development, refinement and implementation of DISC as an integral strategy, during the complex processes involved in post detection and decipherment, is essential if we wish to minimize disruption and optimize dissemination.     

使用解析目标分流策略的海洋卫星多学科优化

在海洋卫星总体设计阶段,为了提高卫星整体设计性能和效率,采用多学科设计优化（MDO）技术对其总体参数进行设计优化。考虑轨道、有效载荷、结构和电源四个学科的设计变量和约束条件,以卫星总质量最小为优化目标建立海洋卫星MDO模型;针对各学科优化问题属性设计高效的优化方案并采用解析目标分流（ATC）这一多级MDO策略来协调整个优化过程。优化后海洋卫星总质量相对海洋一号（HY-1）卫星下降17.6%,整个优化过程花费的时间也比采用单级All at once(AAO)策略减少85.7%。一方面表明所建立的海洋卫星MDO模型的合理有效性,另一方面表明ATC策略结合学科定制优化方案的求解技术的有效性。     

基于输入成型法的空间站变构型过程挠性振动抑制策略

针对空间站组合体变构型引起的挠性附件振动问题,将航天器大角度机动中用于抑制挠性振动的输入成型思想引入到变构型过程中,提出一种新的变构型策略。首先根据拟坐标拉格朗日方程建立组合体变构型动力学模型,然后采用零振动和零微分法(ZVD)和级联法求出变构型系统的输入成型模型,最后根据初始变构型策略的特点和期望构型的约束确定新的变构型策略。将基于输入成型的变构型策略应用于组合体变构型时,仿真结果表明,由变构型引起的挠性振动得到显著抑制,各阶振动的最大振幅可以抑制到原来的10%～20%,对低阶振动抑制效果尤为明显。     

ESA strategic planning for space exploration

The European Space Agency (ESA) is pursuing an independent strategic planning process for consolidating a destination driven (LEO, Moon, Mars) space exploration strategy. ESA's space exploration strategy is driven by the goals to maximise knowledge gain and to contribute to economic growth. International cooperation is a key pillar of ESA's strategy as it is considered both, an enabler for achieving common goals and a benefit, opening new perspective for addressing future challenges. The achievement of ESA's space exploration strategy is enabled through international partnerships. The interagency coordination process conducted within the framework of the International Space Exploration Coordination Group (ISECG) plays an important role in laying the foundations for future partnerships. It has achieved so far the development of a common vision for space exploration, a common plan for implementing the vision in the form of the Global Exploration Roadmap, as well as a common approach for articulating the value of global space exploration. ESA has been a strong promoter and supporter of the interagency coordination process conducted within ISECG and thanks to its unique expertise in international cooperation the Agency has contributed to its success.     

Space in the UK: something to celebrate?

This article discusses current UK space activities that were debated during the ‘policy’ day of a 3-day ‘Festival of Space’ held at Surrey University in July 2003. While the emphasis is on using space to fulfil the needs of society, it is apparent that crafting a coherent strategy that would provide the political support needed to do this—in Europe as well as in the UK—remains difficult.     

导弹直接侧向力机动突防方案设计

针对敌方不同来袭方位的拦截弹,提出了一种可用于导弹末段侧向力机动的突防方案。在建立拦截弹和导弹的相对运动模型基础上给出了脱靶量与视线转率、相对距离和机动加速度的解析表达式。以拦截弹在视线系Z向上的脱靶量达到最大值作为性能指标,对机动发动机开启时刻进行优化确定。同时通过分析机动发动机与Y向舵偏的不同组合方式对导弹的速度增量及交会角的影响,确定机动发动机的推力方向应与气动力方向一致,并使交会角明显减小。仿真结果表明,此方案能使导弹最终落入拦截弹杀伤半径10 m之外,成功实现突防。     

Design of meo constellations for galileo: towards a “design to cost” approach

GALILEO aims at involving Europe in a new generation of satellite navigation services. In the context of the phase A of this programme, many system options are still widely open: detailed requirements, constraints and hypotheses are not yet fully stabilised.In order to design a satellite constellation satisfying civil aviation and other users needs in this early stage of the system definition, it is necessary not only to take into account classical performance aspects, such as accuracy and availability of accuracy, but also cost constraints. The paper describes the design and dimensioning method which has led ALCATEL to propose a set of MEO constellations in the frame of the GALILEO project for ESA. It especially places emphasis upon the sensitivity of the system design to numerous parameters as well as its sensitivity to performance requirements.Potential candidate constellations obviously need to meet given performance specifications which are determined by operational aspects such as: satellite reliability, maintenance strategy (spare in orbit, launch on schedule, launch on need), deployment strategy (launcher choice, etc.). The estimated cost of a potential solution is mainly derived from the number of satellites and the deployment/maintenance strategy, but it is representative of the whole life-cycle of the constellation. Furthermore, the exhibited solution shall be “as robust as” possible to requirement or assumption changes. So, it should be a baseline solution that could be easily updated in order to take into account small upgrades.This has led to the performance of some trend analyses to understand the actual influence of some constraints or requirements on the system design, and to see how initial requirements can be efficiently relaxed in order to obtain the maximum system cost diminution for a minimum constraint relaxation. This will be very useful, if cost reduction is necessary, to quickly propose alternative or sub-solutions to the baseline one.     

The CPR approach to space sustainability: Commentaries on Weeden and Chow

Space sustainability is emerging as a core element of national policy and international initiatives. At this time, however, a coherent strategy and supporting policies have not been developed. To initiate a conversation to develop such a strategy, the authors have applied the principles developed by Elinor Ostrom for terrestrial common-pool resource (CPR) governance to near-Earth orbit in space. A concern arises as to whether Ostrom's eight principles are a good “fit” for application to space CPR because of the unique physical characteristics of space and the legal underpinnings of our presence there. This commentary will address selected issues raised by Weeden and Chow, and suggest alternative ways to approach near-Earth orbit sustainability.     

Deployment of a lander on the binary asteroid (175706) 1996 FG3, potential target of the european MarcoPolo-R sample return mission

The idea of deploying a lander on the secondary body of the binary primitive asteroid (175706) 1996 FG3 is investigated. 1996 FG3 is the backup target of the European sample return space mission MarcoPolo-R under assessment study at the European Space Agency in the framework of the M3 Medium-Class mission competition. The launch will take place in 2022–2024, depending on its selection at the end of 2013. A lander is indicated as an optional payload, depending on mass availability on the spacecraft. Obviously, the possible complexity of a lander deployment is also an important parameter to take into account. Here we demonstrate that, considering worst case scenarios and low requirements on the spacecraft GNC and deployment mechanism, the operations are easy to implement and safe for the main spacecraft. The concept of operations is to deploy a light lander from the L₂ Lagrange point of the binary system, on a ballistic trajectory that will impact the secondary asteroid. The fundamental principles of this strategy are briefly presented and a detailed model of 1996 FG3 is considered, to which the strategy is applied. We show that the deployment is successful in 99.94% of cases.     

On-orbit determination and adjustment of electrostatic accelerometer lever arm

In order to ensure the proof mass center of electrostatic accelerometer (EA) is fixed at the center of gravity of satellite as precisely as possible, an on-orbit determination and adjustment strategy of EA lever arm is presented in this paper. The EA lever arm is determined using the observations of EA, gyro and magnetometer first. Then it is adjusted by screw slider mechanism. The simulation results demonstrate that the proposed strategy can be carried out several times to yield better accuracy. Meanwhile, the optimal geographic location for EA lever arm determination along each axis is found.     

Effects of long-duration space flight on target acquisition

The purpose of the study was to explore the effects of long-duration space flight on the acquisition of specific visual targets in the horizontal plane. Seven cosmonauts (4 high performance pilots and 3 non-pilots) who had flown between 186–198 days on Mir served as subjects. Baseline testing was performed 4 times prior to launch and 4 times following landing at different intervals totrack recovery. During testing the subjects were required to acquire targets that were randomly presented with both a head and eye movement using a time optimal strategy. Prior to flight two unique head movement strategies, related primarily to piloting experience, were used for target acquisition. Non-pilots employed a Type-I strategy consisting of high velocity head movements with large peak amplitudes, while high performance pilots used primarily low velocity, small amplitude head movements (Type-II) to acquire the targets (p<0.02). For both strategies peak head velocities increased as the angular distance to the target increased (p<0.01) resulting in greater discrimination between strategies for the 60° targets. While preflight eye velocity between strategies did not reach statistical significance, postflight testing revealed a decrease in eye velocity for Type-I compared with their preflight performance (p<0.02) for the 60° targets. Postflight, the Type-I group showed a decrease in head velocity (p<0.20) while the Type-II group compensated by increasing head velocity (p<0.02). Variability for both of the head and eye parameters tended to increase postflight for both types of strategies.     

Orbit determination and control for the European Student Moon Orbiter

This paper presents the preliminary navigation and orbit determination analyses for the European Student Moon Orbiter. The severe constraint on the total mission Δv and the all-day piggy-back launch requirement imposed by the limited available budget, led to the choice of using a low-energy transfer, more specifically a Weak Stability Boundary one, with a capture into an elliptic orbit around the Moon. A particular navigation strategy was devised to ensure capture and fulfil the requirement for the uncontrolled orbit stability at the Moon. This paper presents a simulation of the orbit determination process, based on an extended Kalman filter, and the navigation strategy applied to the baseline transfer of the 2011–2012 window. The navigation strategy optimally allocates multiple Trajectory Correction Manoeuvres to target a so-called capture corridor. The capture corridor is defined, at each point along the transfer, by back-propagating the set of perturbed states at the Moon that provides an acceptable lifetime of the lunar orbit.     

Some comments on the ESA/EU space strategy

Not only have the European Space Agency (ESA) and the European Union Commission succeeded in producing a joint space strategy within the time set for it, they have created a substantial and worthwhile document which recognises the importance of space for Europe and acknowledges that ESA—not national agencies—is the right body for the conduct of Europe's space efforts. Nevertheless, the strategy's lack of any government financial commitment is a worry— Public–Private Partnerships will never be enough—as is its failure to include any thought for the long term, and in particular manned flight. This critique of the strategy argues for more government spending on space and for greater long-term vision.     

Influence of estimation errors on wayfinding-decisions in unknown street networks – analyzing the least-angle strategy

The least-angle strategy is a common wayfinding method that can be applied in unknown environments if the target direction is known. The strategy is based on the navigator's heuristic to select the street segment at an intersection which is most in line with the target direction. To use this strategy, the navigator needs to know the angles between the target direction and the street segments leading out from the intersection. If the direct view to the target is blocked and the target vector cannot be perceived, the target direction that is needed for the decision process is based on the agent's believed position and orientation (estimated through path integration). The agent's believed position and target direction are distorted by human errors in estimation of distances and directions, mainly affecting the path integration process. In this paper we examine how human estimation errors of distance and rotation influence the decision behavior in the wayfinding process in an unknown street environment. To demonstrate the geometrical consequences for a specific test case, we use a simulated software agent which navigates in a simulated street environment.     

Leading change at NASA: The case of Dan Goldin

Daniel Goldin set the record for longevity as administrator of NASA, serving from 1992 to 2001. Active and controversial, he was unusually visible as a self-proclaimed ‘agent of change’. Coping with a turbulent political environment, Goldin directed NASA from the end of the Cold War to the early 21st century. He effected change in the multitude of programs under his aegis, especially the Space Station and robotic Mars program. He was hailed at one point as a miracle worker and poster boy of government reinvention for his ‘faster, better, cheaper’ strategy of ‘doing more with less’. But Goldin left the agency under fire for cost overruns and reforms that reached too far. Using a policy innovation process approach, this paper traces Goldin's eventful years at NASA, his policy ends and administrative and technological means. It analyzes the record of success and failure of one of the most, influential administrators in NASA history. That record provides useful lessons for how an administrator gains, uses, and loses power in the US space policy system.     

微重力环境模拟作业训练机器人碰撞力反馈控制

针对航天员在地球表面进行微重力环境中操作训练时微重力环境模拟作业训练机器人存在的碰撞力反馈控制问题,建立碰撞力反馈模型、提出单个柔索驱动单元控制策略和机器人系统碰撞力反馈控制策略。利用Matlab/Simulink软件对碰撞力反馈模型和控制策略进行仿真验证,该模型和控制策略可以实现机器人碰撞力反馈,且具有计算量小、实时性好、不需要额外增加传感器等优势;结合提出的柔索驱动单元复合控制策略和机器人系统碰撞力反馈控制策略进行机器人碰撞力反馈控制实验,提高机器人控制的准确性和实时性。结果表明,基于干扰观测器的柔索驱动单元复合控制策略将柔索驱动单元主动控制精度提升11%,被动控制多余力消除率达到81.82%;机器人碰撞力反馈控制策略可以有效提升航天员作业训练时碰撞力临场感体验。     

一种基于组合策略的低轨星座网络流规划方法

低轨星座网络流规划方法是提升大型星座网络性能的关键技术。针对现有低轨星座网络流规划方法手段单一，难以兼顾全局性能优化与卫星自主灵活性等问题，研究提出了一种基于组合策略的低轨星座网络流规划方法，首先根据业务特点对网络流进行分类映射，针对6类映射业务的QoS差异，分别采用集中式、分布式和源端路由等路由控制策略；在此基础上将星座网络流规划问题抽象为求解带宽约束下的多源单汇网络最大流和多源多汇网络最大流问题，分别采用负载均衡路由和多约束QoS路由算法；对基于组合策略和单一策略的星座网络流规划方法进行了仿真分析，结果表明组合策略比集中式的传输时延低约20ms，丢包率低约9%，比分布式的带宽利用率高约42%，可有效提升星座网络性能，能够更好满足不同场景及需求。