Changes in the Earth’s ozonosphere due to ionization of high-latitude atmosphere by solar protons in October, 2003

Using the data of the Russian KORONAS-F satellite and American GOES spacecraft on solar cosmic ray fluxes associated with powerful events which occurred on the Sun at the end of October - the beginning of November, 2003, calculations of ionization of high-latitude (70° N) atmosphere were carried out. The calculations have shown that the maximum values of ionization for the chosen latitude lie in the range of 50–70 km. The largest ionization was caused by the flare on November 28, 2003. Based on a numerical photochemical simulation it is shown that, as a result of intensification of catalytic cycles with participation of ozone-destroying NO and OH, the concentration of ozone decreased by 30% at ionization maximum altitudes.Translated from Kosmicheskie Issledovaniya, Vol. 42, No. 6, 2004, pp. 653–662.Original Russian Text Copyright © 2004 by Krivolutsky, Kuminov, Vyushkova, Kuznetsov, Myagkova.     

Surface protection by shielding from a hot source under conditions of free convection

In this paper, one way of heat protection from hot elements of the ground-based power-driven high-temperature gas turbine plant case have been experimentally studied by using shields placed between the case and outer skin under free convection in air gaps. Using the experimental model setup, experiments aimed at studying the temperature state of all its elements, namely, hot and cold walls, shield, and air gaps under free convection have been conducted. In the course of these experiments, the temperature of hot wall and air gap thicknesses were varied. The plots obtained by thermometering all walls are presented. As a result, generalization of the data obtained makes it possible to augment the data base and use it in choosing an optimal version of heat protection.     

Spacecraft swarm dynamics and control about asteroids

This paper presents a novel methodology to control spacecraft swarms about single asteroids. This approach enables the use of small, autonomous swarm spacecraft in conjunction with a mothership, reducing the need for the Deep Space Network and improving performance in future asteroid missions. The methodology is informed by a semi-analytical model for the spacecraft relative motion that includes relevant gravitational effects without assuming J2-dominance as well as solar radiation pressure. The dynamics model is exploited in an Extended Kalman Filter (EKF) to produce an osculating-to-mean relative orbital element (ROE) conversion that relies on minimum knowledge of the asteroid gravity. The resulting real-time relative mean state estimate is utilized in a new formation-keeping control algorithm. The control problem is cast in mean relative orbital elements to leverage the geometric insight of secular and long-period effects in the definition of control windows for swarm maintenance. Analytical constraints that ensure collision avoidance and enforce swarm geometry are derived and enforced in ROE space. The proposed swarm-keeping algorithms are tested and validated in high-fidelity simulations for a reference asteroid mission.     

导弹滑模抗干扰自动驾驶仪设计

针对拦截弹的抗干扰控制问题，设计了一种基于扩张状态观测器和快速滑模控制的三通道自动驾驶仪。首先建立考虑有界未知不确定性和外界干扰的拦截弹系统模型，构建扩张状态观测器对有界未知不确定性和外界干扰进行估计；在此基础上，根据自动驾驶仪系统特性，设计了一种快速滑模控制算法使得系统在受到有界未知不确定性和外界干扰的情况下仍然能精准快速跟踪指令信号，并基于李雅普诺夫函数证明了其稳定性。仿真结果验证了所设计控制算法的有效性。