“嫦娥二号”小行星探测试验定轨计算与分析

嫦娥二号于2012-04-15开展对图塔蒂斯小行星的探测试验,至2012-12-13与图塔蒂斯交会,共飞行243 d,这是我国对小行星的首次探测.因为未安装星载导航设备,CE-2 在小行星探测试验的全过程均基于地基USB（Unified S-Band）与甚长基线干涉测量技术（VLBI,Very Long Baseline Interferometry）测量实现导航.对小行星探测期间的定轨计算及精度分析进行了讨论,对我国新建深空站的测量数据进行了分析.针对交会前最后一次轨道机动后,仅有13 d控后数据的现状,提出了快速轨道重建策略.计算结果表明该策略不仅可以有效改进定轨计算精度,还可以实现轨控速度增量的标定.基于重叠弧段的轨道分析比较表明,单独使用USB长弧数据计算可以获得10 km的定轨精度,综合USB与VLBI数据联合定轨,定轨精度可以提高1倍.     

Oriented platform for the VEGA-probe to the Halley comet,position detection,working program

Two deep-space probes of the Venera type for the encounter with Halley's comet are being prepared in the Intercosmos program. 150 kg of scientific equipment will be onboard each sonde, including two TV cameras and two spectrometers. These instruments need precise orientation during the fly-by of the comet. For this purpose a stabilised platform is being developed in Czechoslovakia which will be installed onboard both probes and will be able to point to the target with precision 5 minutes of arc and maximum angular velocity 1°/second. A system of position detectors and the working program during the start and the fly-by are described.     

Excavation of artificial caverns inside asteroids by leveraging rotational self-energy

Future space ventures will likely require exploitation of near-Earth asteroid resources. Moreover, it can be envisaged that asteroids may host habitats in their interiors. In fact, a cavern inside an asteroid would be a natural radiation shield against cosmic radiation and may also serve as a confined environment for storage of mined material such as water ice or other processed volatiles such as propellants. To this end, this paper proposes to leverage the asteroid rotational self-energy to remove material from the asteroid interiors and create a spherical cavern, by means of the orbital siphon concept. The siphon is a chain of tether-connected payload masses (the asteroid material), which exploits the rotation of the asteroid for the delivery of mass from the asteroid to escape. Under certain conditions the siphon can be initiated to ensure self-sustained flow of mass from the asteroid to escape. A net orbital siphon effect is generated by connecting new payloads at the bottom of the chain while releasing the upper payloads. Key parameters are discussed, such as the required siphon dimension and the maximum size of the internal cavity that can be excavated, as a function of the asteroid rotational period. Moreover, assuming elastic material behaviour, a closed-form expression for the stress tensor is found and a failure criterion is used to identify regions in the asteroid interiors subjected to the larger stresses. It is shown that the conditions for failure are relaxed as the radius of the internal void increases.     

Encounter trajectories for deep space mission ASTER to the triple near Earth asteroid 2001-SN263. The laser altimeter (ALR) point of view

In cooperation with Russia, the Brazilian deep space mission ASTER plans to send a small spacecraft to investigate the triple asteroid 2001-SN263. The nearest launch opportunities for this project include June 2022 and June 2025. One main exploration campaign is being planned with focus on the largest asteroid (Alpha). Among the instruments under development, a laser altimeter (named ALR) was preliminarily designed and presented in 2010–2011. Many studies to define mission and instruments requirements were performed aiming at the characterization of important issues for the successful realization of the mission. Among them, the identification of a suitable trajectory that could be followed by the ASTER spacecraft in the encounter phase, when the main campaign will take place. This paper describes the effort undertaken with focus on the laser altimeter operation. Possible encounter trajectories were modelled and simulated to identify suitable approach parameters and conditions allowing the accomplishment of the intended investigation. The simulation also involves the instrument operation, considering approach geometry, attitude, relative motion, time/date, and the dynamics of the main asteroid. From the laser altimeter point of view, keeping in mind the desired coverage results (50% minimum surface coverage of asteroid Alpha, complying with horizontal and vertical resolution requirements), results point out crucial features for the encounter trajectory, like the need for a small inclination (10^-6 degrees; with respect to the asteroid's orbit), the most favourable spacecraft positioning (between the Sun and the asteroid) and pointing condition (back to the Sun), the minimum amount of achievable surface coverage (58%, focused on central areas), and the most proper time to conduct the main campaign (January 2025). Concerning the instrument, results offer refined values for divergence angle (500 to 650 μrad, half-cone), pulse repetition frequencies (from 1/20 to 1 Hz), and consequent data generation rates. A simulation tool that can use any 3D generated trajectories as input data was created for the analyses presented here. Although created for the ALR in this mission, this simple analysis tool can be adapted to other instruments in this or other missions.     

基于引力场不对称性的三体系统轨道自主导航

以月球背面的中继通信为背景,提出了基于三体系统引力场不对称特性的星–星测距自主定轨方案。该方案以环月极轨卫星和地–月L2点Halo轨道卫星组成中继通信网,以实现对月球两极和背面的覆盖。通过采集极轨卫星与Halo轨道卫星的测距信息,结合卡尔曼滤波在日–地–月动力学模型下获得两颗卫星的绝对轨道。数值仿真结果表明:本文方法能将导航的位置精度和速度精度分别提高到百米和厘米/秒量级。该自主导航方法还可以扩展到不规则引力场小天体附近星群运动的自主导航。     

非合作目标安全走廊设计及飞越逼近轨迹优化

为提高空间非合作目标近距离逼近轨迹的安全性,同时对接近时间及所消耗燃料进行优化,针对空间失效自旋非合作目标近距离接近问题,给出了失效卫星动态安全走廊,并以飞越逼近方式抵达走廊入口,进一步提出了飞越逼近轨迹优化方法。首先,在建立失效卫星自旋模型的基础上,规划了安全区与禁飞区,提出了2种安全走廊的选择依据。其次,采用飞越逼近作为近距离接近方式,以节约燃料和缩短逼近时间为目标对两脉冲机动模型进行优化,选择3种优化算法得到接近轨迹。仿真结果表明:安全走廊的选择与卫星失效自旋的形式、外形以及接口位置有关;在飞越逼近两脉冲机动模型的优化问题中,采用Fgoalattain算法进行优化处理更具优越性。      

The infrared imaging channel of the IKS instrument for detection of Comet Halley nucleus

The imaging Channel of the IKS Instrument placed on board the Vega fly-by probes will perform measurements of the infrared emission of the central region of Comet Halley at distances in the 10⁴ ? 10⁵ km range. An encoding wheel analyses one spatial frequency of the infrared image during the whole fly-by. Inversion of this measurement will give low resolution brightness profiles of the nucleus and its immediate surroundings, in two wave-length bandpasses and in two directions of analysis.     

利用绳系太阳帆减缓小行星自转的技术研究

提出一种利用太阳帆绳系系统逐渐减小小行星自转速率的方法。在系绳长度不变的情况下,利用太阳帆受到的太阳光压力使其始终保持与小行星同步,避免了由于小行星自转而引起的系绳缠绕问题。通过控制太阳帆使系绳始终拉紧,系绳中的拉力便可以持续提供一个与小行星自转方向相反的力矩,从而减小其自转速率。仿真结果表明,面积10⁶ m²的太阳帆,经过约86天可将小行星的自转消除,验证了该方法的有效性。     

The Pioneer anomaly and a rotating Gödel universe

Based upon a simple cosmological model with no expansion, we find that the rotational terms appearing in the Gödel universe are too small to explain the Pioneer anomaly. Following a brief summary of the anomaly, cosmological effects on the dynamics of local systems are addressed – including a derivation of the equations of motion for an accelerated Pioneer-type observer in a rotating universe. The rotation or vorticity present in such a cosmological model is then subjected to astrophysical limits set by observations of the cosmic microwave background radiation. Although it contributes, universal rotation is not the cause of the Pioneer effect. In view of the related fly-by anomalies, frame-dragging is also discussed. The virial theorem is used to demonstrate the non-conservation of energy during transfers from bound to hyperbolic trajectories.     

小行星远距离抵近轨道

讨论了小行星引力一阶项可被忽略情况下的小行星远距离轨道设计及动力学。此时,航天器的运动受太阳引力和太阳光压的影响。航天器和小行星的加速度之差在这两者之间形成的独特的相对动力学,为航天器在小行星附近停驻与观测提供特定轨道。完整解决了小行星处于圆形日心轨道这一较简单情况,也考虑和阐述了椭圆轨道情况,并取得了一些初步结果。     

Synergistic approach of asteroid exploitation and planetary protection

The asteroid and cometary impact hazard has long been recognised as an important issue requiring risk assessment and contingency planning. At the same time asteroids have also been acknowledged as possible sources of raw materials for future large-scale space engineering ventures. This paper explores possible synergies between these two apparently opposed views; planetary protection and space resource exploitation. In particular, the paper assumes a 5 tonne low-thrust spacecraft as a baseline for asteroid deflection and capture (or resource transport) missions. The system is assumed to land on the asteroid and provide a continuous thrust able to modify the orbit of the asteroid according to the mission objective. The paper analyses the capability of such a near-term system to provide both planetary protection and asteroid resources to Earth. Results show that a 5 tonne spacecraft could provide a high level of protection for modest impact hazards: airburst and local damage events (caused by 15–170 m diameter objects). At the same time, the same spacecraft could also be used to transport to bound Earth orbits significant quantities of material through judicious use of orbital dynamics and passively safe aero-capture manoeuvres or low energy ballistic capture. As will be shown, a 5 tonne low-thrust spacecraft could potentially transport between 12 and 350 times its own mass of asteroid resources by means of ballistic capture or aero-capture trajectories that pose very low dynamical pressures on the object.     

近地小行星防御策略分析

近年来,各国针对近地小行星的威胁及相应防御策略的研究越来越多。调研了国内外近地天体观测发展现状和多种近地小行星撞击地球的防御策略,通过比较分析防御策略的实现原理、关键技术和存在的问题,对各种策略的适用性、可行性和有效性进行了评估。通过对各种策略的分析和总结,结合我国近地小行星防御策略的研究现状,尝试性提出了采用多种策略组合的方式对有潜在威胁的小行星采取相关有效方案,为航天器的研制和防御策略的实施争取更多的时间。     

Dust environment models for comet P/Halley: Support for targeting of the GIOTTO S/C

In March 1985 ESA's GIOTTO spacecraft will fly by P/Halley's nucleus at a distance of a few hundred kilometres. The near nucleus dust environment the probe will traverse poses a hazard with respect to physical damage as well as to attitude disturbance with the possible loss of ground station contact. To predict S/C survivability and dust impact rates for the experiments, a model of the spatial distribution of the dust in the nucleus' vicinity is required. In the ‘dynamic’ model, the local spatial dust density is derived from exact expressions for the dust particle dynamic motion. The model has been implemented in a software system which allows for fast simulations of a cometary fly-by.     

双体小行星系统平衡态与稳定性研究

由于双体小行星独特的运动形式可为行星的演化提供重要线索,因而成为小行星探测中的热点目标。基于双椭球体模型研究了双小行星系统的相对运动、平衡态及稳定性。首先基于双椭球的全二体模型建立了双星系统相对运动的动力学方程;其次利用拉格朗日方程,通过求解系统角动量和能量,建立了双星系统平衡态对应的状态约束;最后给出了通过零速度状态曲面判断双星系统平衡态稳定性的一般性方法,在此基础上分析了小行星物理参数变化对系统平衡态稳定性的影响。研究可为未来双体小行星系统探测任务中的轨道设计与控制提供重要的理论参考。     

Finite-time asteroid hovering via multiple-overlapping-horizon multiple-model predictive control

This paper investigates the asteroid hovering problem using the Multiple-Overlapping-Horizon Multiple-Model Predictive Control method. The effectiveness of the predictive controllers in satisfying control constraints and minimizing the required control effort is making Model Predictive Control a desirable control method for asteroid exploration missions which consist of the asteroid hovering phase. However, the computational burden of Model Predictive Control is an obstacle to employing the asteroid’s complex gravitational field model. As an alternative option, the Multiple Horizon Multiple-Model Predictive Control method has been introduced previously, which could provide a solution with the less computational burden with respect to the nonlinear Model Predictive Control. It was shown that it is not necessary to deduce the exact dynamics model to predict the system’s behavior during a long period using this approach. However, the calculated control acceleration was not smooth enough because of the crisp borders of consecutive horizons, which may cause an image motion and degrades the geometric accuracy of high-resolution images in asteroid hovering missions. In this paper, the Multiple-Overlapping-Horizon Multiple-Model Predictive Control method is introduced instead to solve the problem of controlling acceleration fluctuations by overlapping consecutive horizons. Numerical simulation results are presented to validate the effectiveness of the proposed control method, and its advantage is demonstrated accordingly for the asteroid hovering problem in achieving the hovering position and velocity.     

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。     

Measurements of bidirectional reflectance of ordinary chondrite for muses-C in-situ detection

MUSES-C, a Japanese sample return mission, is targeting a small near Earth asteroid, 1998SF36, which is considered an S-type asteroid and is similar in spectroscopy to LL class ordinary chondrite meteorite ([Binzel et al., 2001]). Although this mission will bring us detailed photometric data, that is, disk-resolved bidirectional reflectance data of the asteroid, there were few bidirectional reflectance data of ordinary chondrite meteorites. For the purpose of comparison with the data obtained by the in-situ observation, we have performed measurements of bidirectional reflectance of ordinary chondrite samples.

Here we summarize the result of our laboratory measurements of the bidirectional reflectance and compare them with the scattering property of 1998SF36. Although the geometric albedo of 1998SF36 is higher than the typical value of S-type asteroids, however, the laboratory data of ordinary chondrite are similar to or brighter than the model disk-resolved reflectance of 1998SF36 derived from disk-integrated ground-based data. We found in our laboratory data that there is a positive correlation between the surface roughness and the strength of the opposition effect. A stronger opposition effect in the reflectance of 1998SF36 than the laboratory data may therefore indicate that the surface of the asteroid has rougher structure than our laboratory samples.     

Experimental study on drilling basalt with self-vibratory drilling head

Based on the goal of improving the rock breaking ability when drilling asteroid rock samples under limited energy conditions, this paper proposes a method of drilling rock using self-vibratory drilling head and develops a small self-vibratory drilling head for drilling rock. In order to analyze the dynamic characteristics of drilling rock with self-vibratory drilling head, a rock model hypothesis that the rock consists of a series of micro-segment uniform continuous media is put forward. Base on the hypothesis, the model of drilling rock is constructed, the stability lobes diagram of self-vibratory drilling head drilling basalt is plotted, and the energy mechanism of drilling rock system with self-vibratory drilling head is discussed. The comparison tests of drilling basalt by three kinds of self-vibratory drilling head with different spring stiffness and the conventional method are carried out. The rotational speed is a variable in the comparative tests. The test results show that under the specific rotational speed and spring stiffness, self-excited vibration is produced in self-vibratory drilling head drilling basalt. When self-excited vibration drilling is conducted, although the amplitude fluctuation range of the drilling thrust force is wider than that of conventional drilling, the average drilling thrust force is smaller than the conventional drilling. The amplitude of drilling thrust force increases with an increase in spring stiffness. The method of drilling rock by self-vibratory drilling head is proved to be a potential method for viable drilling of asteroid rock samples.     

Rapid impactor sample return (RISR) mission scenario

Due to the long lead time and great expense of traditional sample return mission plans to Mars or other astronomical bodies, there is a need for a new and innovative way to return materials, potentially at a lower cost. The Rapid Impactor Sample Return (RISR) mission is one such proposal. The general mission scenario involves a single pass of Mars, a Martian moon or an asteroid at high speeds (7 km/s), with the sample return vehicle skimming just 1 or 2 m above a high point (such as a top ridge on Olympus Mons on Mars) and releasing an impactor. The impactor strikes the ground, throwing up debris. The debris with roughly the same forward velocity will be captured by the sample return vehicle and returned to Earth. There is no delay or orbit in the vicinity of Mars or the asteroid: RISR is a one-pass mission. This paper discusses some of the details of the proposal. Calculations are presented that address the question of how much material can be recovered with this technique. There are concerns about the effect of Mars tenuous atmosphere. However, it will be noted that such issues do not occur for RISR style missions to Phobos, Deimos, or asteroids and Near Earth Objects (NEOs). Recent test results in the missile defense community (IFTs 6–8 in 2001, 2002) have scored direct hits at better than 1 m accuracy with closing velocities of 7.6 km/s, giving the belief that accuracy and sensing issues are developed to a point that the RISR mission scenario is feasible.