辐射变色薄膜剂量计性能测试及加速器应用

本课题的目的是建立用于辐射加工高剂量水平吸收剂量测量的辐射变色薄膜剂量计。通过系统研究,批量制备了以尼龙为基材,副品红氰化物为染料的辐射变色薄膜剂量计。为了验证批制辐射变色薄膜剂量测量的可靠性,选择了国际上应用较广的FWT-60膜及丙氨酸薄膜剂量计与本实验室批制的辐射变色薄膜开展实验室内剂量比对,比对结果均在±4%内符合,归一化偏差En绝对值均小于1。通过在加速器上进一步应用实验表明批制辐射变色薄膜可用于电子束辐照参数测量。     

Trajectory optimization of multiple asteroids exploration with asteroid 2010TK7 as main target

In this study, the Earth’s Trojan asteroid 2010 TK₇ is selected as the rendezvous target. The multiple flyby sequence of asteroid exploration was proposed by optimizing the probe’s orbit. Impulsive maneuvers and low-thrust propulsion were used respectively to design the trajectories of the multiple asteroids exploration mission. Under impulsive maneuvers, gravity assist technique was adopted to reduce fuel consumption. First a reference orbit with only 2010 TK₇ as the rendezvous target was designed. Then five asteroids near the reference orbit were selected as candidates. Finally, we obtained a multiple asteroids exploration sequence of three asteroids based on gravity assist technique and genetic algorithm, and an additional velocity impulse of 0.4?km/s was required. In the subsequent section, a sixth-degree inverse polynomial shape-based method is applied to the low-thrust trajectory design of 2010 TK₇, and the exploration sequence under the action of low-thrust propulsion was provided.     

近地小行星采矿与防御计划发展现状

近地小行星交会、绕飞、着陆与采样返回技术经过数10年的发展日趋成熟。美国的OSIRIS-Rex对C类小行星进行特征分析与采样,日本宇宙航空研究开发机构的“隼鸟-2号”任务目的是小行星深层采样。美国国家航空航天局（NASA）和欧洲空间局（ESA）的小行星探测任务开始转向行星防御领域。NASA的ARM（Asteroid Redirect Mission）计划是开展小行星抓捕与轨道重定向,ESA联合NASA提出了小行星撞击与偏转评估计划,拟对双星系统开展撞击实验,为行星防御提供技术积累。此外,行星资源公司和深空工业公司分别规划了小行星商业采矿的蓝图,并已开展相关的在轨技术验证。对近地小行星的探测历程进行了回顾,重点介绍了OSIRIS-Rex、“隼鸟-2号”、NASA和ESA的行星防御计划及小行星采矿公司的商业采矿战略规划,总结了未来开展行星防御与采矿的关键技术。     

激光吸收法辐射测温技术研究

对辐射测温技术的发展进行了回顾,总结了辐射测温中遇到的主要问题,分析了激光吸收法辐射测温技术的发展现状,对激光吸收法辐射测温技术的理论模型进行了公式推导,对本单位建立的实验装置及其测温结果进行了介绍。     

The INTEGRAL view of Gamma-Ray Bursts

After more than six and half years in orbit, the ESA space observatory INTEGRAL has provided new, exciting results in the soft gamma-ray energy range (from a few keV to a few MeV). With the discovery of about 700 hard X-Ray sources, it has changed our previous view of a sky composed of peculiar and “monster” sources. The new high energy sky is in fact full of a large variety of normal, very energetic emitters, characterized by new accretion and acceleration processes (see also IBIS cat4 (Bird et al., 2010). At the same time, about one GRB/month is detected and imaged by the two main gamma-ray instruments on board: IBIS and SPI. In this paper, we review the major achievements of the INTEGRAL observatory in the field of Gamma-Ray Bursts. We summarize the global properties of Gamma-Ray Bursts detected by INTEGRAL, with respect to their duration, spectral index, and peak flux distributions. We recall INTEGRAL results on the spectral lag analysis, showing how long-lag GRBs appear to form a separate population at low peak fluxes. We review the outcome of polarisation studies performed by using INTEGRAL data. Finally, concerning single GRB studies, we highlight the properties of particularly interesting Gamma-Ray Bursts in the INTEGRAL sample.     

基于地球椭球特性的红外地球敏感器测量值的修正算法

基于地球的椭球特性，讨论了对扫描式红外地球敏感器的测量值进行修正的问题。利用地球椭球的小扁率特性，给出了相应的一阶修正算法。与现有文献中的方法相比，给出的算法计算简单，具有较高的精度，仿真结果表明，对于中、低轨道而言该算法的精度优于0．01°     

遥感小卫星地面站的系统技术设计

针对遥感小卫星工作方式的特殊性，根据系统的总体指标，对通信线路进行分析与设计，确定了优化的地面站主要技术参数，并对信息传输的实时性和可靠性作出分析     

北斗系统地固系自主定轨算法

为避免传统惯性系自主定轨算法中的多次坐标转换,针对地固系分布式自主定轨算法原理及其中的关键技术开展研究。给出在地固系中进行自主星历生成的总体框图,推导了地固系自主定轨算法的基本方程,提出一种新的以地固系位置速度为状态量的状态转移矩阵解析计算方法并分析其计算量,证明了地固系自主定轨算法可以进一步降低定轨算法复杂度,且无需上注地球定向参数进行坐标转换。使用仿真数据和真实在轨测量数据的测试结果表明,提出的地固系分布式自主定轨算法与传统算法定轨精度相当,说明了所提算法的可行性,验证了星载自主定轨原型软件的有效性。     

Interplanetary CubeSats system for space weather evaluations and technology demonstration

The paper deals with the mission analysis and conceptual design of an interplanetary 6U CubeSats system to be implemented in the L₁ Earth–Sun Lagrangian Point mission for solar observation and in-situ space weather measurements.     

Fast solar sail rendezvous mission to near Earth asteroids

The concept of fast solar sail rendezvous missions to near Earth asteroids is presented by considering the hyperbolic launch excess velocity as a design parameter. After introducing an initial constraint on the hyperbolic excess velocity, a time optimal control framework is derived and solved by using an indirect method. The coplanar circular orbit rendezvous scenario is investigated first to evaluate the variational trend of the transfer time with respect to different hyperbolic excess velocities and solar sail characteristic accelerations. The influence of the asteroid orbital inclination and eccentricity on the transfer time is studied in a parametric way. The optimal direction and magnitude of the hyperbolic excess velocity are identified via numerical simulations. The found results for coplanar circular scenarios are compared in terms of fuel consumption to the corresponding bi-impulsive transfer of the same flight time, but without using a solar sail. The fuel consumption tradeoff between the required hyperbolic excess velocity and the achievable flight time is discussed. The required total launch mass for a particular solar sail is derived in analytical form. A practical mission application is proposed to rendezvous with the asteroid 99942 Apophis by using a solar sail in combination with the provided hyperbolic excess velocity.