How Galactic Cosmic Ray models affect the estimation of radiation exposure in space

The radiation environment in space is a major concern for human spaceflight because of the adverse effects of high levels of radiation on astronauts’ health. Therefore, it is essential to perform radiation risk assessments already during the concept studies of a manned mission. Galactic Cosmic Rays (GCR) have been identified to be one of the primary sources of radiation exposure in space.     

Location-aware channel estimation for capacity gains on multibeam satellite links

Bandwidth is an expensive and scarce resource, thus its efficient exploitation is of paramount importance. Recent communication satellites feature sophisticated spatial access strategies through spot beams providing this way a total throughput in the range of 100 Gbit/s. Next generations of communication satellites, as postulated in the Satellite Communications Network of Experts (SatNEx) III, a project funded by the European Space Agency (ESA) for advanced research in satellite communications, require technological developments to achieve the Tbit/s region. Multibeam architectures formed by a central gateway, a multibeam satellite, and an aggressive frequency reuse strategy can meet such ambitious design goals. Interference problems are tackled by appropriate countermeasures such as (joint) precoding and beamforming on the forward link as well as multi-user detection on the return link; these methods require accurate and timely knowledge of the channel state, which in turn necessitates suitable algorithms for channel estimation. This paper addresses performance issues related to channel state estimation on the symbol-synchronous forward link and the frame-synchronous return link. It highlights for both directions the potential performance gain by assuming a priori knowledge of the user position, in this context referred to as location-aware channel estimation.     

卫星天线反射面板热形变面形误差检测方法

为实现航天卫星天线面板热形变面形误差高精度检测,提出利用三坐标测量系统搭载高精度激光位移传感器,对检测对象进行扫描测量;并通过对其系统误差来源进行分析、公差合理分配及误差控制,提出对测量系统进行整体优化,以满足所提出检测精度要求。为验证所提出方法的可行性,搭建测量系统,对标准试件的测量数据进行面形拟合,获得测量偏差优于±4.22μm/m2;分别制作常规铝板及光滑铝板作为测试对象,在其背部黏贴加热板的加热方式,以模拟卫星面板在实际工作环境中发生热形变。采用提出的方法对其进行了热形变面形误差检测实验,检测结果验证了所提出方法的可行性。     

Influence of ionospheric perturbations in GPS time and frequency transfer

The stability of GPS time and frequency transfer is limited by the fact that GPS signals travel through the ionosphere. In high precision geodetic time transfer (i.e. based on precise modeling of code and carrier phase GPS data), the so-called ionosphere-free combination of the code and carrier phase measurements made on the two frequencies is used to remove the first-order ionospheric effect. In this paper, we investigate the impact of residual second- and third-order ionospheric effects on geodetic time transfer solutions i.e. remote atomic clock comparisons based on GPS measurements, using the ATOMIUM software developed at the Royal Observatory of Belgium (ROB). The impact of third-order ionospheric effects was shown to be negligible, while for second-order effects, the tests performed on different time links and at different epochs show a small impact of the order of some picoseconds, on a quiet day, and up to more than 10 picoseconds in case of high ionospheric activity. The geomagnetic storm of the 30th October 2003 is used to illustrate how space weather products are relevant to understand perturbations in geodetic time and frequency transfer.     

Semi-analytical theory of mean orbital motion for geosynchronous space debris under gravitational influence

This paper provides a hamiltonian formulation of the equations of motion of an artificial satellite or space debris orbiting the geostationary ring. This theory of order 1 has been formulated using canonical and non-singular elements for eccentricity and inclination. The analysis is based on an expansion in powers of the eccentricity and of the inclination. The theory accounts for the influence of the Earth gravity field expanded in spherical harmonics, paying a particular attention to the resonance occurring for geosynchronous objects. The luni-solar perturbations are also taken into account. We present the resonant motion and its main characteristics: equilibria, stability, fundamental frequencies and width of the resonant area by comparison with a basic analytical model. Finally, we show some results concerning the long term dynamics of a typical space debris under the influence of the gravitational field of the Earth and the luni-solar interactions.     

Spin-stabilized satellite magnetic attitude control scheme without initial detumbling

The angular motion of an axisymmetrical satellite equipped with an active magnetic attitude control system is considered. The dynamics of the satellite are analytically studied on the whole control loop. The control loop is as follows: preliminary reorientation along with nutation damping, spinning about the axis of symmetry, then precise reorientation of the axis of symmetry in inertial space. Reorientation starts right after separation from the launch vehicle. Active magnetic attitude control system time-response with respect to its parameters is analyzed. It is proven that low-inclined orbit forces low control system time-response. Comparison with the common control scheme shows the time-response gain. Numerical analysis of the disturbances effect is carried out and good pointing accuracy is proved.     

天线测试平台系统设计与安装

简要介绍了天线测试平台系统的基本工作原理、系统（机械系统、测量系统、控制系统）设计、材料选择、误差分析和系统的现场安装。     

歼击机平台发射弹道导弹攻击卫星技术

对歼击机平台发射弹道导弹攻击卫星作战模式与关键技术进行介绍、分析,强调在现阶段使用机载弹道导弹攻击卫星可行、合理.      

DBV-RCS中一种提高时延性能的时隙分配方法(英文)

在DVB-RCS卫星通信中,为某个业务分配的时隙在MF-TDMA帧中的位置分布将影响该业务的时延特性。本文分别针对固定速率和实时可变速率业务,对MF-TDMA的帧长度、终端分配的时隙数量及位置分布与业务时延性能之间的关系进行了建模分析。理论分析表明时隙位置是影响业务时延的一个重要因素,位置分布越均匀,越能提高业务的时延性能;时隙均匀分配相比传统的时隙连续分配可以有效降低业务平均时延,且时延不随帧长的变化而变化;在时隙均匀分配方式下,提高实时可变速率业务的带宽分配可以更有效的提高时延性能。在DVB-RCS标准基础上,提出了一种与标准完全兼容的时隙均匀分配方法(TUAM),通过计算机仿真验证了算法的有效性以及建模分析的正确性,该算法可有效地保证业务具有极低的平均时延和时延抖动,使得VoIP等实时业务不会由于端到端时延过大而丢包,提高了DVB-RCS系统对于实时业务QoS的保障能力。     

Contingency and recovery options for the European Student Moon Orbiter

This paper presents an overview of the analysis performed on the lunar orbit and some of the possible contingencies for the European Student Moon Orbiter (ESMO). Originally scheduled for launch in 2014 –2015 as a piggyback payload, it was the only ESA planned mission to the Moon. By way of a weak stability boundary transfer, ESMO is inserted into an orbit around the Moon. Propellant use is at a premium, so the operational orbit is selected to be highly eccentric. In addition, an optimization is presented to achieve an orbit that is stable for 6 months without requiring orbit maintenance. A parameter study is undertaken to study the sensitivity of the lunar orbit insertion. A database of transfer solutions across 2014 and 2015 is used to study the relation between the robustness of weak capture and the planetary geometry at lunar arrival. A number of example recovery scenarios, where the orbit insertion maneuver partially or completely fails, are also considered.