无人机自主控制等级及其系统结构研究

正确制定无人机(UAV)自主控制等级,有利于了解中国无人机所处的自主控制水平,也有利于为中国无人机自主控制技术的发展提供正确的指导方向.鉴于无人机自主控制等级应该是由无人机代替有人驾驶飞机所能完成的驾驶员的智能行为等级这一认识,从人类智能活动的机理分析,给出了人类的智能控制行为等级.然后,在深入分析美国无人机自主控制等...     

三体系统中引力拖车的偏置非开普勒轨道研究

为了研究太阳-小行星-引力拖车三体系统中引力拖车的轨道运动问题,采用柱坐标系下的Hill方程描述了三体系统中引力拖车的运动情况,应用平均化方法消除周期项的影响,得到平均偏置非开普勒轨道的表达式,并研究了轨道稳定性与引力拖车最大有效拉力等问题.研究表明:三体系统中,在小行星飞行方向（或反方向）上存在偏置非开普勒轨道;与二...     

A sample collector for robotic sample return missions II: Radiation tests

Sample return from small solar system objects is playing an increasingly important part in solar system exploration. Critical to such missions is a robust, simple, and economic sample collector. We have developed a collector such as this for near-Earth asteroid sample return missions that we have termed the Touch-and-Go Impregnable Pad (TGIP). The collector utilizes a silicone substrate that is pushed into the dust and gravel surface layer of the asteroid. As part of a systematic evaluation of the TGIP, we have investigated the resilience of this substrate to ionizing radiations. Several miniature versions of the collector, containing typically ∼3 g of the collection substrate, were exposed to 0.564 MeV beta particles from a ⁹⁰Sr source and a 6 MeV electron beam in a linear accelerator to simulate the wide range of energies of solar and galactic ionizing radiation. Various radiation levels up to eight times greater than expected on a six-year asteroid mission (in the case of beta radiation) and 50 times greater than expected (in the case of the 6 MeV electron radiation) were administered to the substrate. After irradiation, the efficiency of the substrate in collecting samples of mock regolith was compared with that of collectors that had not been irradiated. No difference beyond experimental uncertainty was observed and we suggest that the operational TGIP will not be affected adversely by radiation doses expected during a typical six-year inner solar system mission.     

A methodology to support strategic decisions in future human space exploration: From scenario definition to building blocks assessment

The human exploration of multiple deep space destinations (e.g. Cis-Lunar, NEAs), in view of the final challenge of sending astronauts to Mars, represents a current and consistent study domain especially in terms of its possible scenarios and mission architectures assessments, as proved by the numerous on-going activities about this topic and moreover by the global exploration roadmap. After exploring and analysing different possible solutions to identify the most flexible path, a detailed characterisation of several Design Reference Missions (DRMs) represents a necessity in order to evaluate the feasibility and affordability of deep space exploration missions, specifically in terms of enabling technological capabilities.The study presented in this paper was aimed at defining an evolutionary scenario for deep space exploration in the next 30 years with the final goal of sending astronauts on the surface of Mars by the end of 2030 decade. Different destinations were considered as targets to build the human exploration scenario, with particular attention to Earth–Moon Lagrangian points, NEA and Moon. For all the destinations selected as part of the exploration scenario, the assessment and characterisation of the relative Design Reference Missions were performed. Specifically they were defined in terms of strategies, architectures and mission elements. All the analyses were based on a pure technical approach with the objective of evaluating the feasibility of a long term strategy for capabilities achievement and technological development to enable future space exploration.This paper describes the process that was followed within the study, focusing on the adopted methodology, and reports the major obtained results, in terms of scenario and mission analysis.     

RPC-IES: The Ion and Electron Sensor of the Rosetta Plasma Consortium

The ion and electron sensor (IES) is part of the Rosetta Plasma Consortium (RPC). The IES consists of two electrostatic plasma analyzers, one each for ions and electrons, which share a common entrance aperture. Each analyzer covers an energy/charge range from 1 eV/e to 22 keV/e with a resolution of 4%. Electrostatic deflection is used at the entrance aperture to achieve a field of view of 90°× 360° (2.8π sr). Angular resolution is 5°× 22.5° for electrons and 5°× 45° for ions with the sector containing the solar wind being further segmented to 5°× 5°. The three-dimensional plasma distributions obtained by IES will be used to investigate the interaction of the solar wind with asteroids Steins and Lutetia and the coma and nucleus of comet 67P/Churyumov–Gerasimenko (CG). In addition, photoelectron spectra obtained at these bodies will help determine their composition.     

基于微分进化算法的深空小推力轨道优化设计

针对多目标多任务的深空探测轨道优化设计问题,基于以太阳为主引力体的二体模型,采用电推进小推力系统,提出了将目标行星的探测方式、探测顺序、发射窗口同时进行全局优化的解决方案.依此建立小推力轨道优化设计算法模型,利用微分进化算法进行全局一体化优化设计,得出多目标多任务的一体化深空探测轨道.通过与相同条件下其他设计方法的结果比对分析得出：基于小推力推进方式并采用微分进化算法进行优化的轨道优化设计方案,在多目标多任务深空轨道一体化设计问题上具有可行性及应用价值.     

基于XGBoost的航空器动态滑行时间预测方法研究

对航空器进港和离港滑行时间进行精确的动态预测,可以有效提升机场的运行效率。首次提出基于XGBoost 的航空器动态滑行时间预测方法,该方法首先通过分析影响机场滑行时间的各类因素,构建可变滑行时间预测的关键特征指标;然后选取XGBoost 算法建立可变滑行时间预测模型,对模型的关键输入参数进行测试调整;最后将XGBoos...     

用飞行员模型进行飞行品质自动评估技术研究

介绍了飞机的飞行品质评估典型任务,初步建立了飞行员行为特性数学模型以及飞行品质自动评定专家知识库,开发了基于试飞员模型的飞行品质评定软件的设计与实现;在六自由度动基座飞行模拟器上,针对某高教机电传飞控系统进行了飞行模拟器部分典型任务的飞行品质自动评估,其评估结果与飞行员评估结果基本吻合.该技术应用于飞控系统控制律设计、优化中,能提高设计效率,节约主观评定的时间,是客观飞行品质评定的有力补充.     

Two-dimensional launch window method to search for launch opportunities of interplanetary missions

Accurate and highly efficient approaches to obtain mission opportunities are still the goals of mission planners of interplanetary explorations. The search for launch opportunities not only determines the specified launch window of the mission but also presents the performance requirements for the interplanetary probe and its launch vehicle. An effective method, namely the two-dimensional launch window method, is developed from a completely new perspective to determine all the launch opportunities of the mission in this research. For a fixed launch time, the method to determine all the time windows in the dimension of Time-of-Flight (TOF) is firstly proposed and these time windows represent all the launch opportunities for the given launch time. And then, the two-dimensional launch window method is proposed, which computes the time windows in both the launch time and TOF dimensions to achieve all launch opportunities of the mission. Numerical examples are provided to demonstrate the accuracy and high efficiency of the method. Compared with the widely-used pock-chop plot method, the proposed method reduces the computational time by two orders of magnitude for the same search precision, and thus is especially suitable for the cases involving rapid, high-precision, and/or large-scale searches for mission opportunities.     

服务通告全面成本评估

从工作实际出发，提出了服务通告的全面成本评估方案，详细给出成本项分类和量化方法，应用投资收益率方法综合决策各成本项，帮助工程管理人员科学量化服务通告，得到更准确合理的评估结论。