Mathematical modeling of the solar sail spacecraft three- dimensional motionin heliocentric coordinate system

The paper outlines the mathematical motion model of the solar sail spacecraft. The work considers the mathematical three-dimensional motion model of the perfect-reflection solar sail and the operational orbit maintenance and correction algorithms in heliocentric coordinate system. On the basis of the formulated mathematical model the special software complex for interplanetary transfer simulation is developed. Especially, the mission of the transfer of the spacecraft from the Earth’s orbit to the potentially hazardous asteroid is simulated. The obtained results during simulation demonstrate correctness and feasibility of the considered mathematical motion model

Mathematical modeling of the space tug transfers between the Lagrange points of the Earth-Moon system

The paper outlines the mathematical modeling of the L1-L2 and L2-L1 missions using electric propulsion. The variation problem of the low thrust spacecraft transfer optimization, with total flight time as the optimization criterion is considered. The locally optimal control programs were obtained by using the Fedorenko method to estimate the derivatives, the gradient method to optimize the control laws and the Runge-Kutta method for the numerical integration of the differential equation system. As the result of optimization, optimal control programs and corresponding trajectories were determined for certain values of acceleration and jet stream velocity of the propulsion system

Modeling the process of optical characteristics variation for a solar sail surface during heliocentric flights

The changing of optical characteristics for the solar sail surface during the heliocentric flights is considered. The sail surface is a multilayer epitaxial structure, which is physically a polyamide film, covered with different metals from the front and back sides. Optical characteristics of the multilayer film are calculated by the transition matrix method adapted for quantum-sized layers taking into account the solar radiation spectrum. We model the influence of these characteristics on the acceleration of a spacecraft with a solar sail

Simulation of a system for protecting Earth from asteroid hazard by kinetic interceptor

В представленной работе рассмотрен метод отклонения астероидной опасности с помощью кинетического перехватчика - космического аппарата, который с помощью соударения отталкивает астероид с опасной орбиты. Выявлены параметры астероидов, сближающихся с Землёй. Разработана математические модели движения тел, программа управления и программный комплекс, предназначенный для визуализации и моделирования траекторий движения всех тел системы. The present work is devoted to one of the methods of protecting the Earth from asteroid’s danger, namely, the use of the kinetic interceptor. A software package the simulation and visualization of the trajectories is designed of all bodies. The obtained simulation results confirm the possibility of the deviation of the asteroid from a dangerous trajectory by the use of kinetic interceptor

Modeling of solar sail surface oscillations during interplanetary flight

Целью данной работы является изучения влияния колебаний поверхности солнечного паруса на движение космического аппарата, совершающего межпланетный перелет. Солнечный парус – это двигательная установка, создающая тягу за счет давления солнечного света на его поверхность. Данная статья состоит из трех частей: вывода уравнения колебаний поверхности солнечного паруса и определения создаваемой им тяги, решения задачи о колебаниях его поверхности и моделирования межпланетного перелета. В первой части приводятся основные допущения, необходимые для решения задачи и выводится уравнение колебаний поверхности солнечного паруса. Уравнение колебаний выводится как для различных случаев нагружения паруса, так и для различных видов его конструкции. Также выводится формула для определения силы тяги, создаваемой парусом. Во второй части производится моделирование колебаний поверхности паруса и определяется создаваемая им тяга. Сила тяги, создаваемая солнечным парусом, зависит как от его формы, так и от расстояния до Солнца. В третьей части моделируется межпланетный перелет космического аппарата с солнечным парусом с учетом этих факторов. The purpose of this work is to study the influence of the solar sail surface oscillations on the motion of spacecraft performing an interplanetary flight. The solar sail is a propulsion system, creating thrust due to the pressure of sunlight. The article consists of three parts: the derivation of the equation of oscillations of the solar sail surface and the definition of thrust created by it, the solution of the problem of solar sail oscillations and the modeling of the interplanetary flight. The first part deal with the use of the wave equation applied to this problem and gives the main assumptions. The equation of oscillations is derived both for various cases of sail loading, and for various types of its construction. Also the formula for thrust produced by solar sail was derived. In the second part, the problem of the oscillations of the sail structure is solved and its thrust was determined. Solar sail thrust depends both on the shape of the sail, and on the distance to the Sun. In the third part, the interplanetary flight was modeled taking into account these factors