Multi-objective optimization of parachute triggering algorithm for Mars exploration

A multi-objective optimization procedure to design parachute triggering algorithm, based on Monte Carlo analysis of flight uncertainties, has been developed in this paper. Most of Mars explorations missions utilize parachute for a safe descent through the lowest of the atmosphere. The parachute triggering algorithm is designed to accommodate the range of off-nominal entry trajectories, and is aimed to parachute opening in certain range of Mach numbers, dynamic pressure and altitude. Our novel algorithm takes the fight uncertainty into the account through Monte Carlo analysis, selects maximization of altitude statistical mean and minimization of Mach number statistical mean as two objectives, then employs multi-objective evolutionary algorithm based on decomposition (MOEA/D), to search the Pareto-front framework. Such a methodology can be implemented on the future design of entry, descent, and landing (EDL) mission.     

Disturbance observer-based robust guidance for Mars atmospheric entry with input saturation

With low-lifting capability taken into account,a robust guidance law for Mars entry vehicles with low lift-to-drag ratios,such as Mars Science Laboratory(MSL),is presented.Consider the nonlinear term in the drag dynamic equation and bounded disturbances as a lumped disturbance,and design a linear disturbance observer(DOB)to estimate it.With the consideration of the control input saturation,an innovative sliding surface and a virtual system are introduced to design the guidance law.Analyses of disturbance observer performance and Lyapunov-based transient performance are also presented.It is shown that the drag tracking error can be adjustable by explicit choices of design parameters.Simulation results confirm the effectiveness of the proposed guidance law.     

Improved uncertainty propagation method of dynamic model for Mars entry spacecraft

In order to research the uncertainty propagation laws of Mars entry dynamic equations for the Mars entry phase,an improved method was presented for analyzing the effect of the initial state uncertainties and uncertainty factor on the system state in the state trajectories.When applying the method to the entry phase of one of the NASA Mars exploration missions,the simulation results agreed well with the Monte Carlo method,especially the flight path angle simulation at least reaching 92%.It is found that the improved method can not only predict the uncertainty propagation laws with high accuracy of at least 92%in flight path angle simulation and large application scope from-0.1degree to 0.1degree,compared with local linearization method,but also save several hours relative to Monte Carlo method.     

Planetary penetrators: Their origins,history and future

Penetrators, which emplace scientific instrumentation by high-speed impact into a planetary surface, have been advocated as an alternative to soft-landers for some four decades. However, such vehicles have yet to fly successfully. This paper reviews in detail, the origins of penetrators in the military arena, and the various planetary penetrator mission concepts that have been proposed, built and flown. From the very limited data available, penetrator developments alone (without delivery to the planet) have required ∼$30M: extensive analytical instrumentation may easily double this. Because the success of emplacement and operation depends inevitably on uncontrollable aspects of the target environment, unattractive failure probabilities for individual vehicles must be tolerated that are higher than the typical ‘3-sigma’ (99.5%) values typical for spacecraft. The two pathways to programmatic success, neither of which are likely in an austere financial environment, are a lucky flight as a ‘piggyback’ mission or technology demonstration, or with a substantial and unprecedented investment to launch a scientific (e.g. seismic) network mission with a large number of vehicles such that a number of terrain-induced failures can be tolerated.     

火星卫星的冻结轨道研究

冻结轨道是一种稳定的轨道,地球、火星、月球的卫星因引力场的南北不对称,都存在冻结轨道.由于主星体引力场的不同,它们卫星的冻结轨道也有不同的特性.地球卫星的冻结执道的偏心率非常小,对卫星遥感非常有利,国内外已有相当多的近地遥感卫星采用这种轨道.月球卫星的冻结轨道偏心率随轨道倾角的不同有很大的变化,对月球卫星冻结轨道的研究...     

21世纪的航天(续)

航天事业在20世纪已取得显著进展和辉煌成就。21世纪即将来临。在21世纪,世界航天如何发展、将取得哪些重大成就,是人们关注的话题。为此,笔者根据有关材料汇编了这份材料,以供参考。共4讲,第一、二讲已刊登在本刊1998年第4期,下面为第三、四讲。     

Investigation of the Influence of Magnetic Anomalies on Ion Distributions at Mars

Using data from the Mars Express Ion Mass Analyzer (IMA) we investigate the distribution of ion beams of planetary origin and search for an influence from Mars crustal magnetic anomalies. We have concentrated on ion beams observed inside the induced magnetosphere boundary (magnetic pile-up boundary). Some north-south asymmetry is seen in the data, but no longitudinal structure resembling that of the crustal anomalies. Comparing the occurrence rate of ion beams with magnetic field strength at 400 km altitude below the spacecraft (using statistical Mars Global Surveyor results) shows a decrease of the occurrence rate for modest (< 40 nT) magnetic fields. Higher magnetic field regions (above 40 nT at 400 km) are sampled so seldom that the statistics are poor but the data is consistent with some ion outflow events being closely associated with the stronger anomalies. This ion flow does not significantly affect the overall distribution of ion beams around Mars.     

IMF Direction Derived from Cycloid-Like Ion Distributions Observed by Mars Express

Although the Mars Express (MEX) does not carry a magnetometer, it is in principle possible to derive the interplanetary magnetic field (IMF) orientation from the three dimensional velocity distribution of pick-up ions measured by the Ion Mass Analyser (IMA) on board MEX because pick-up ions' orbits, in velocity phase space, are expected to gyrate around the IMF when the IMF is relatively uniform on a scale larger than the proton gyroradius. During bow shock outbound crossings, MEX often observed cycloid distributions (two dimensional partial ring distributions in velocity phase space) of protons in a narrow channel of the IMA detector (only one azimuth for many polar angles). We show two such examples. Three different methods are used to derive the IMF orientation from the observed cycloid distributions. One method is intuitive (intuitive method), while the others derive the minimum variance direction of the velocity vectors for the observed ring ions. These velocity vectors are selected either manually (manual method) or automatically using simple filters (automatic method). While the intuitive method and the manual method provide similar IMF orientations by which the observed cycloid distribution is well arranged into a partial circle (representing gyration) and constant parallel velocity, the automatic method failed to arrange the data to the degree of the manual method, yielding about a 30° offset in the estimated IMF direction. The uncertainty of the derived IMF orientation is strongly affected by the instrument resolution. The source population for these ring distributions is most likely newly ionized hydrogen atoms, which are picked up by the solar wind.     

甲烷-乙烷混合推进剂深度过冷技术的实验研究

针对甲烷采用液氮过冷可能发生甲烷冰堵风险,提出了在甲烷中添加乙烷,制备凝固温度更低的甲烷-乙烷混合推进剂的新方案,搭建实验系统测试了甲烷-乙烷凝固温度变化规律。研究发现,随着甲烷含量提高,混合推进剂凝固温度先降低后升高。当甲烷、乙烷比例为0.71∶0.29时,混合推进剂达到最低凝固温度,约73.0 K。当采用常压饱和液氮对混合推进剂过冷时,控制甲烷含量在0.52~0.81间可避免推进剂冻结。相较于常压饱和甲烷,防冻结区的混合推进剂密度提高了24.0%~38.4%,液相存在温区增大至35.7 K~40.5 K。此外,甲烷-乙烷混合推进剂具有理论比冲高、再生冷却性能佳、结焦与积碳小等优势。所提出的甲烷-乙烷混合推进剂在火星探测等任务中具有可观的应用前景。     

天问一号火星进入舱热控系统设计与验证

天问一号火星进入舱携带祝融号火星车实施进入、下降、着陆过程,其热控系统设计主要面临地火转移外热流大幅变化、进入火星舱壁气动烧蚀长时高温、着陆发动机点火局部超高温等技术挑战。为此,综合采用隔热设计、等温化设计、主动控温设计等热控手段,针对外热流大幅变化应用了新型SAL-2热控涂层,为解决局部超高温问题研制了新型气凝胶热防护装置,完整构建了进入舱的高效可靠热控系统。飞行遥测数据表明,全飞行过程设备温度和热控功耗均优于指标要求,进入、下降、着陆过程工作设备温度范围5.0~40.3℃,整舱平均控温功耗不超过43W,验证了进入舱热控系统设计的有效性。