Gravitational wave detection on the Moon and the moons of Mars

The Moon and the moons of Mars should be extremely quiet seismically and could therefore become sensitive gravitational wave detectors, if instrumented properly. Highly sensitive displacement sensors could be deployed on these planetary bodies to monitor the motion induced by gravitational waves. A superconducting displacement sensor with a 10-kg test mass cooled to 2 K will have an intrinsic instrument noise of 10⁻¹⁶ m Hz^−1/2. These sensors could be tuned to the lowest two quadrupole modes of the body or operated as a wideband detector below its fundamental mode. An interesting frequency range is 0.1–1 Hz, which will be missed by both the ground detectors on the Earth and LISA and would be the best window for searching for stochastic background gravitational waves. Phobos and Deimos have their lowest quadrupole modes at 0.2–0.3 Hz and could offer a sensitivity h_min ? 10⁻²² Hz^−1/2 within their resonance peaks, which is within two orders of magnitude from the goal of the Big Bang Observer (BBO). The lunar and Martian moon detectors would detect many interesting foreground sources in a new frequency window and could serve as a valuable precursor for BBO.     

Mars Phobos and Deimos Survey (M-PADS) – A martian Moons orbiter and Phobos lander

We describe a Mars ‘Micro Mission’ for detailed study of the martian satellites Phobos and Deimos. The mission involves two ∼330 kg spacecraft equipped with solar electric propulsion to reach Mars orbit. The two spacecraft are stacked for launch: an orbiter for remote investigation of the moons and in situ studies of their environment in Mars orbit, and another carrying a lander for in situ measurements on the surface of Phobos (or alternatively Deimos). Phobos and Deimos remain only partially studied, and Deimos less well than Phobos. Mars has almost always been the primary mission objective, while the more dedicated Phobos project (1988–89) failed to realise its full potential. Many questions remain concerning the moons’ origins, evolution, physical nature and composition. Current missions, such as Mars Express, are extending our knowledge of Phobos in some areas but largely neglect Deimos. The objectives of M-PADS focus on: origins and evolution, interactions with Mars, volatiles and interiors, surface features, and differences. The consequent measurement requirements imply both landed and remote sensing payloads. M-PADS is expected to accommodate a 60 kg orbital payload and a 16 kg lander payload. M-PADS resulted from a BNSC-funded study carried out in 2003 to define candidate Mars Micro Mission concepts for ESA’s Aurora programme.     

Development of a gas chromatography compatible Sample Processing System (SPS) for the in-situ analysis of refractory organic matter in martian soil: preliminary results

In the frame of the 2009 Mars Science Laboratory (MSL) mission a new sample preparation system (SPS) compatible with gas chromatography–mass spectrometry (GC–MS) has been developed for the in situ analysis of complex organic molecules in the Martian soil. The goal is to detect, if they exist, some of the key compounds that play an important role in life on Earth including carboxylic acids, amino acids and nucleobases.     

基于可通过性的月面巡视探测器路径规划算法

应用于行星探测车的路径规划算法需要根据地形环境信息和车体的越障能力两方面进行考虑。结合月面巡视探测器移动子系统的通过特性以及地形信息将地图栅格进一步细分,使用了四个安全性指标描述车体静止或运动时的通过性,并将其引入到A~*与D~*两种规划算法的代价当中,给出了算法的流程,并通过仿真进行了验证。     

月面巡视探测器行为控制初探

阐述了月面巡视探测器几种行为控制结构的特点,详细阐述了巡视探测器的导航运动控制方式,研究了国外巡视探测器的导航运动控制特点;并以此提出了巡视探测器基于模糊逻辑的分层行为控制模式,举例说明了巡视探测器的行为描述方式。     

Comparative assessment of human–Mars-mission technologies and architectures

We compare a variety of mission scenarios to assess the strengths and weaknesses of options for Mars exploration. The mission design space is modeled along two dimensions: trajectory architectures and propulsion system technologies. We examine direct, semi-direct, stop-over, semi-cycler, and cycler architectures, and we include electric propulsion, nuclear thermal rockets, methane and oxygen production on Mars, Mars water excavation, aerocapture, and reusable propulsion systems in our technology assessment. The mission sensitivity to crew size, vehicle masses, and crew travel time is also examined. Many different combinations of technologies and architectures are applied to the same Mars mission to determine which combinations provide the greatest potential reduction in the injected mass to LEO. We approximate the technology readiness level of a mission to rank development risk, but omit development cost and time calculations in our assessment. It is found that Earth–Mars semi-cyclers and cyclers require the least injected mass to LEO of any architecture and that the discovery of accessible water on Mars has the most dramatic effect on the evolution of Mars exploration.     

崎岖地形中关节式月球车姿态估计数值求解方法

 以被动关节式地形自适应月球车为研究对象,融合关节机器人D-H坐标建模方法构建了月球车悬架运动学模型和以侧倾、俯仰和偏转角表示姿态的欧拉角方式建立了车轮到世界坐标系的悬架完整表达模型。利用悬架完整表达模型,用带有迭代因子的连续迭代和离散迭代数值求解方法,建立了光滑和离散崎岖地形姿态估计算法。最后以8轮扭杆双摇杆摇臂月球车原理样机为例来验证此模型求解方法。仿真结果验证了所建立的基于数值方法的崎岖地形被动关节式月球车姿态估计模型的正确性,其求解模型精度能够满足仿真要求。     

刚性车轮月面牵引通过性的模型试验

以重塑模拟月壤为介质,利用深空探测车车轮牵引特性实验台,研究了月面巡视探测器的刚性轮齿车轮与模拟月壤的交互作用,分析了车轮转速、轮上载荷等试验因素对车轮牵引通过性的影响.研究结果表明,当车轮转速较低时,挂钩牵引力随滑转率的增加而不断提高;当车轮转速较高时,存在着临界滑转率点.轮上载荷的增加有利于提高车轮的挂钩牵引力,但对挂钩牵引力系数的影响较小.     

美国新型载人火星探测技术方案

文章概括介绍了＂发现号＂宇宙飞船的布局结构。然后详细介绍了飞船用于火星探测的两种着陆舱的具体设计方案以及载人火星探测的任务剖面。最后分析了＂发现号＂宇宙飞船火星探测方案的关键可行技术和诸多设计优点。     

“凤凰号”火星探测器着陆过程

文章主要介绍了＂凤凰号＂火星着陆器的着陆过程、着陆点选择方法原则、巡航阶段工作任务,对进入（Entry）、下降（Descent）和着陆（Landing）即EDL阶段的蒙特卡罗分析结果和飞行器重建数值结果进行了总结比较。并对＂凤凰号＂相关的经验和教训进行了比较总结,这对中国未来的火星探测以及其他深空探测具有一定的借鉴作用。