基于TLE的弹道系数计算方法及应用分析

针对仅使用两行要素（Two Line Element，TLE）作为数据源的应用需求，研究了基于TLE轨道衰减的弹道系数计算方法。介绍了一种常用的基于两组TLE的直接计算法，分析TLE选取间隔对结果精度的影响；提出了一种基于多组TLE的迭代计算方法，以降低异常TLE对计算结果的影响；从弹道系数计算效果、在再入预报中的应用等方面对这两种方法进行比较分析。结果表明，两种方法各有优劣，基于多组TLE的迭代计算法稳定性更高、受TLE精度的影响更小；由于数据区间更短，基于两组TLE的计算结果对短期轨道衰减特性反应得更准确，用于临近再入时的预报效果更好。     

Robust model predictive control for satellite formation keeping with eccentricity/inclination vector separation

This study presents model predictive formation control based on an eccentricity/inclination vector separation strategy. Alternative collision avoidance can be accomplished by using eccentricity/inclination vectors and adding a simple goal function term for optimization process. Real-time control is also achievable with model predictive controller based on convex formulation. Constraint-tightening approach is address as well improve robustness of the controller, and simulation results are presented to verify performance enhancement for the proposed approach.     

Spacecraft formation flying control around L2 sun-earth libration point using on–off SDRE approach

In this paper, on–off SDRE control approach is presented for spacecraft formation flying control around sun-earth L2 libration point. Orbits around libration points are significant targets for many space missions mainly because of efficient fuel consumption. Furthermore, less propellant usage can be achieved by considering optimal control approaches in spacecraft formation flying control design. Among various nonlinear and optimal control methods, SDRE has shown to be a popular controller in various missions due to the privileges including efficiency, accuracy and robustness. The spacecraft are assumed to have on–off thrusters as actuators. It requires them to be fed with a sequence of on–off pulses which is regarded as a challenge for spacecraft designers. Hence, the main contribution of this paper is designing an on–off SDRE approach for the formation flight around sun-earth L2 point with uncertainty with energy and accuracy considerations. Including on–off input as a constraint is not feasible for SDRE implementation because it makes the system non-affine. An alternative is utilizing an integral action technique and an auxiliary control to make the system affine which leads to on–off SDRE approach. It has also been shown that the proposed method is robust against parametric uncertainties of the states. Present study aims to design an energy-beneficial, simple and attractive controller for a complex nonlinear system with on–off inputs and uncertainty in CRTBP. Simulation results show that the on–off SDRE control could provide the formation flight around L2 point with high accuracy using less energy consumption.     

Formation flying reconfiguration manoeuvres via environmental forces in highly elliptical orbits

A study on reconfiguration manoevres applied to a tetrahedral formation in highly elliptical orbits is proposed, by using a propellantless solution. The manoeuvring strategy consists in exploiting certain environmental forces, specifically those provided by solar radiation pressure and atmospheric drag, by actively controlling the satellites’ attitudes. Through inverse dynamics particle swarm optimization the optimal attitudes required for the manoeuvres are evaluated, whereas the configuration’s evolution is simulated by a high-fidelity orbital simulator. The goal of the reconfiguration problem is to find an optimal control in order for the four spacecraft to reach a desired configuration in a specified portion of orbit, where the desired configuration is evaluated by a shape and size geometric parameter. By increasing the manoeuvring time and the satellites’ area to mass ratio, all the case studies considered are successfully verified.     

InfraRed Astronomy Satellite Swarm Interferometry (IRASSI): Overview and study results

The far-infrared (FIR) regime is one of the few wavelength ranges where no astronomical data with sub-arcsecond spatial resolution exist yet. Neither of the medium-term satellite projects like SPICA, Millimetron or OST will resolve this malady. For many research areas, however, information at high spatial and spectral resolution in the FIR, taken from atomic fine-structure lines, from highly excited carbon monoxide (CO) and especially from water lines would open the door for transformative science. These demands call for interferometric concepts. We present here first results of our feasibility study IRASSI (Infrared Astronomy Satellite Swarm Interferometry) for an FIR space interferometer. Extending on the principal concept of the previous study ESPRIT, it features heterodyne interferometry within a swarm of five satellite elements. The satellites can drift in and out within a range of several hundred meters, thereby achieving spatial resolutions of <0.1 arcsec over the whole wavelength range of 1–6 THz. Precise knowledge on the baselines will be ensured by metrology methods employing laser-based optical frequency combs, for which preliminary ground-based tests have been designed by members of our study team. We first give a motivation on how the science requirements translate into operational and design parameters for IRASSI. Our consortium has put much emphasis on the navigational aspects of such a free-flying swarm of satellites operating in relatively close vicinity. We hence present work on the formation geometry, the relative dynamics of the swarm, and aspects of our investigation towards attitude estimation. Furthermore, we discuss issues regarding the real-time capability of the autonomous relative positioning system, which is an important aspect for IRASSI where, due to the large raw data rates expected, the interferometric correlation has to be done onboard, in quasi-real-time. We also address questions regarding the spacecraft architecture and how a first thermomechanical model is used to study the effect of thermal perturbations on the spacecraft. This will have implications for the necessary internal calibration of the local tie between the laser metrology and the phase centres of the science signals and will ultimately affect the accuracy of the baseline estimations.     

大展弦比飞翼布局飞机新型操纵面设计

大展弦比飞翼布局飞机取消常规布局的安定面和操纵面,本体的 动态特性出现许多不足.介绍了在该新布局飞机上采用的升降副翼和开裂式方向舵等 新型操纵面的气动特点,并在计算空气动力学的基础上分析了其三轴控制效率.引进舵容量 的概念提出了操纵面的参数化设计方法,基于飞机的可控性对各新型操纵面的操纵效率需求 进行了评估,最终对某型飞机的操纵面初步设计进行了修正.研究结果为飞翼布局飞机的操 纵面设计提供了一套实用的方法.      

冷轧无间隙原子钢中的微带生成机理

分析了冷轧体心立方金属中微带的形成原因.基于塑性变形理论,运用Taylor模型和Bishop＆Hill最大功原理,计算了变形体心立方晶体中滑移系上的切应变分布.计算结果表明,冷轧时当晶粒的轧向平行于晶粒的某些特定取向时,大量的局部切应变将集中产生在一个滑移面上并在此形成微带.这一高度局域性的切应变是形成剪切带的原因.此时,剪切带与轧制方向之间夹角为30°.另外,微带呈片状是双交滑移的结果,透射电子显微镜观察到的剪切带所在晶粒的取向和所在滑移面证实了这一微带的形成机制.     

LEO原子氧剥蚀太阳电池阵Ag互连材料的试验研究

暴露在低地球轨道(LEO)上的太阳电池阵,会与大量具有极强氧化性的原子氧发生碰撞,导致太阳电池阵中对氧原子敏感的Ag互连材料受到剥蚀。文章依据原子氧剥蚀Ag材料的机理,选取了约400 km高度轨道上1年时间内原子氧的累积通量作为最高剂量,进行了原子氧剥蚀不同厚度Ag互连材料的地面模拟环境试验。试验表明:Ag在原子氧作用下在宏观上会经历"氧化—剥落"的循环剥蚀过程。根据反应方程简化推导了Ag互连片的剥蚀厚度公式,同时结合试验结果计算出了不同厚度Ag互连材料的厚度损失率。该研究成果可为LEO太阳电池阵原子氧防护设计提供技术支持。     

基于自由权矩阵的时变时延线性群系统编队控制

研究了基于自由权矩阵方法的时变时延线性群系统编队控制问题。首先,基于一致性理论,设计了具有时变时延的线性群系统编队控制协议。其次,通过变量代换,将时延条件下的线性群系统编队控制问题转化为时延系统的镇定问题。构造Lyapunov-Krasovskii函数,并利用自由权矩阵方法对时延系统的镇定问题进行分析,得到了保守性较小的线性矩阵不等式（LMI）判据,并求解出时延上界和编队控制器增益。最后,通过仿真实验,验证了方法的有效性。     

近地卫星严格回归轨道保持控制

研究了近地卫星基于严格回归参考轨道的轨道保持控制方法：将卫星编队理论引入单星绝对轨道保持控制,提出了"虚拟卫星编队"的概念,分析了卫星轨道相对于参考空间轨迹在轨道摄动情况下的偏离状态及变化趋势,然后根据卫星编队相对运动学,推导出了偏离状态与虚拟卫星编队构形参数之间的对应关系,并设计了以轨道参数超调、偏置及阈值触发为特征的管道保持控制策略。数值仿真结果表明,使用该控制策略能够将卫星轨道保持在以空间参考轨迹为中心的轨道管道内,并且有效减少了因周期性轨道摄动波动造成的管道保持控制量和控制频次。研究成果对于有空间轨迹回归要求的卫星轨道保持控制具有指导意义。