火星进入减速器技术综述与展望

随着火星着陆探测任务的不断推进,火星采样返回、载人登陆火星和火星基地等任务要求能将更大、更重的探测器着陆到火星表面,这就需要在火星大气进入阶段进行高效减速。基于以往成功的火星着陆探测任务,首先系统地回顾了火星进入段气动减速技术的发展历史;然后,结合火星进入过程的特点阐述了火星进入段减速设计的必要性及其面临的挑战;接着,系统地总结了充气式气动减速器、可展开式气动减速器和超声速反推减速器的系统构成和研究进展;最后,对这3种减速器技术的未来发展方向和亟待解决的关键问题进行了比较全面的分析和展望。     

Soft landing stability analysis of a Mars lander under uncertain terrain

Safe soft landing of the lander is vital to the Mars surface exploration mission. Analysis and verification of the landing stability under uncertain terrain play an important role in lander design. However, the effect of uncertain terrain is ignored in most existing studies, making the analysis incomprehensive and increasing the risk of landing failure in practice. In this paper, a Mars lander with 10 attitude control thrusters is introduced and its dynamics model is then established considering...     

火星无人机实验台发展综述及构想

火星地表崎岖、环境复杂,火星无人机由于其具有高机动性和灵活性,为火星探测提供了一种新的工作模式,是未来深空探测的重要范式。本文对比了火星与地球相关地表环境参数的差异,分析了火星无人机需要克服的困难和主要用途,阐明了火星无人机实验台的重要性;详细介绍了国内外研究机构研发火星无人机实验台的技术特点与功能优劣,总结了实验台需要具备的模拟火星环境和测量相关参数。在此基础上,提出了构建火星无人机实验台设想,给出了总体设计思想和思路,并对火星无人机气动力学实验平台的应用前景进行了展望。     

火星全球导航卫星系统

讨论了建立类地行星全球导航定位系统的意义,并对火星全球导航卫星系统星座的布构型进行了初步分析设计.对不同导航星座的覆盖特性与导航定位性能进行了评估,给出了最佳星座设计,它可以作为将来建立火星导航卫星系统的星座设计参考.     

火星着陆器抛背罩分离体气动特性

为便于火星着陆器抛背罩安全性仿真,针对火星着陆器简化外形开展了背罩分离的定常数值计算,分析了着陆平台与背罩之间的气动效应,获得了着陆平台与背罩的轴向力系数随分离间距的变化规律。结果表明：初始分离瞬间,由于着陆平台嵌入背罩内部,它们之间的压力接近驻点压力,随着分离间距的增加,背罩与着陆平台之间的压力逐渐由接近驻点压力慢慢过渡到接近底部绕流压力,至分离间距为0.1倍大底直径后,背罩一直处于着陆平台的底部绕流区。分离间距为0~0.06倍大底直径时,背罩的轴向力系数大于着陆平台,容易分离;分离间距为0.06~6倍大底直径时,着陆平台的轴向力系数大于背罩,存在分离后重新结合并发生碰撞的危险,且在分离间距为1倍大底直径时,着陆平台与背罩之间由于回流作用而产生的吸力达到峰值,此时发生碰撞的危险系数最大;分离间距超过6倍大底直径后,背罩的轴向力系数再次超越着陆平台,可以确保抛背罩安全分离。     

固推约束下的火星表面起飞上升制导律设计

针对受固推约束的火星上升器(MAV)起飞上升问题,设计了上升段、无动力滑行段、入轨段三段式火星表面起飞上升全过程制导策略。首先,根据实际任务需求进行了上升器标称轨迹优化。其次,在上升段引入了阿波罗制导方法,通过类攻角和类侧滑角的控制实现对标称轨迹的跟踪。为减少上升段末端偏差对无动力滑行段与标称轨迹间误差的影响,提出了一种通过调整倾侧角改变上升器所受气动力进而控制飞行轨迹的技术路线,并设计了相应的滑模制导律。另外,兼顾固推发动机的能量管理需求,针对入轨段设计了Lambert制导策略,并参考标称控制量对其进行修正,使得上升器能够在控制能力有限的情况下完成较高精度的入轨。最后,通过典型场景火星表面起飞上升全过程数值仿真验证了所设计策略的有效性和鲁棒性。     

Phobos regolith simulants PGI-1 and PCA-1

The Martian moon Phobos is the target of the upcoming JAXA Martian Moons eXploration (MMX) mission. There are currently no known samples of Phobos, so spacecraft hardware testing and scientific studies require Phobos regolith simulants. Here, we present two new Phobos regolith simulants: Phobos Captured Asteroid-1 (PCA-1) and Phobos Giant Impact (PGI-1). These two simulants reflect the two hypotheses for Phobos’s formation, and thus the two broad possibilities for composition. This work follows previous efforts to document the development of mineralogically accurate simulants, in an effort to overcome past pitfalls with inappropriate uses of simulants. We report physical and geotechnical properties of PCA-1 and PGI-1, including their reflectance spectra, grain size distributions, abrasivity, cohesion, strength, and hardness. Our intent is for PCA-1 and PGI-1 to be open standards for Phobos simulants, and we present the simulant recipes and production methodology for use and modification by the community.     

DSMC量子动理学模型在火星再入流动中的应用

为解决化学反应模型高温数据缺乏的难题，探索DSMC方法量子动理学（QK）模型在实际中的应用，本文将该模型进一步应用于火星探测器稀薄气动特性的数值预测。通过计算探路者号在85 km、95 km和110 km高度的稀薄绕流，评估了QK模型的性能和稀薄气体效应的影响规律。结果表明，QK模型不依赖宏观的化学反应速率系数，适用于火星再入流动计算。化学反应及其模型对气动力的影响很小，但对气动热特性的影响不容忽略，考虑化学反应后的驻点热流可以下降约12%~14%。     

Schumann resonance frequency and conductivity in the nighttime ionosphere of Mars: A source for lightning

We have solved the Maxwellian equations of electromagnetic waves which oscillate within the cavity formed in the lower ionosphere of Mars between 0 and 70?km. The electrical conductivity and Schumann Resonance (SR) frequencies are calculated in the lower ionosphere of Mars, in the presence of a major dust storm that occurred in Martian Year (MY) 25 at low latitude region (25°–35°S). It is found that the atmospheric conductivity reduced by one to two orders of magnitude in the presence of a dust storm. It represents a small dust layer at about 25–30?km altitudes where lightning can occur. We also found that the SR frequencies peak at?～18?km with values 19.9, 34.5 and 48.8?Hz for the modes l?=?1, 2 and 3, respectively, in the non-homogeneous medium. Our results indicate that practical or measurable values of SR are dependent on the altitudes.     

Neutral atmosphere and crustal magnetization as factors determining differences in plasma convection and magnetic fields distribution in the ionospheres of Mars and Venus

The pattern of the magnetic field/plasma convection can be, to some extent, recovered from the magnetic field measurements by employing either theoretical or numerical models. We use the MAG/ER day-time measurements of the magnetic field at the altitudes from 90 to 180 km during the elliptical orbits of MGS. Analysis of the altitude variation of the characteristics of the large-scale magnetic fields, which were measured some distance away from strong crustal magnetic anomalies, is summarized. The low density of the Martian atmosphere together with the crustal magnetization result in critical differences in plasma convection which are followed by remarkable differences of the magnetic field features within the ionosphere of Venus and Mars (even in its northern hemisphere where the crustal magnetization is, on the average, low) and distribution of currents.