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A method has been developed for the combined de-orbiting of large-size objects of space debris from low-Earth orbits using an electro-rocket propulsion system as an active de-orbiting means. A principal de-orbiting technique has been devised, which takes into consideration the patterns of using an electric rocket propulsion system in comparison with the sustainer rocket propulsion system. A procedure for determining the parameters of the de-orbiting scheme has been worked out, such as the minimum total speed and the time of the start of the de-orbiting process, which ensures its achievement. The proposed procedure takes into consideration the impact exerted on the process of the de-orbiting by the ballistic factor of the object, the height of the initial orbit, and the phase of solar activity at the time of the de-orbiting onset. The actual time constraints on battery discharge have been accounted for, as well as on battery charge duration, and active operation of the control system. The process of de-orbiting a large-size object of space debris has been simulated by using the combined method involving an electro-rocket propulsion system. The impact of the initial orbital altitude, ballistic coefficient, and the phase of solar activity on the energy costs of the de-orbiting process have been investigated. The dependences have been determined of the optimal values of a solar activity phase, in terms of energy costs, at the moment of the de-orbiting onset, and the total velocity, required to ensure the de-orbiting, on the altitude of the initial orbit and ballistic factor. These dependences are of practical interest in the tasks of designing the means of the combined de-orbiting involving an electric rocket propulsion system. The dependences of particular derivatives from the increment of a velocity pulse to the gain in the ballistic factor on the altitude of the initial orbit have been established. The use of these derivatives is also of practical interest to assess the effect of unfolding an aerodynamic sailing unit

Работа посвящена проблеме космического мусора, который представляет серьезную угрозу деятельности человека в околоземном космическом пространстве. Выполнен краткий обзор известных технических средств и технологий для удаления космического мусора с низких околоземных орбит. На сегодняшний день основными путями борьбы с техногенным засорением околоземного пространства является использование активных и пассивных методов увода космического мусора. Активные методы позволяют обеспечить увод объектов мусора в гарантированные сроки, однако требуют значительных энергетических затрат. Пассивные методы являются более экономичными, но процесс более продолжителен и может не удовлетворять требованиям международной конвенции по уменьшению космического мусора. В работе рассмотрен новый комбинированный подход к уводу крупногабаритного космического мусора в плотные слои атмосферы Земли, где он прекратит своё существование. Данный метод предполагает совместное использование активного средства-реактивной двигательной установки-и пассивного средства-аэродинамического парусного устройства. Представлена концепция использования комбинированного метода для очистки околоземного пространства, определена область эффективного его использования. Данная область составляет высоты от 700 до 2500 км в зависимости от баллистического коэффициента. В качестве критерия эффективности предложено рассматривать относительное отклонение массы компонентов топлива, необходимых для обеспечения увода. Показана целесообразность и перспективность применения комбинированного метода увода. Результаты работы представляют практический интерес для технико-экономического обоснования и разработки мероприятий по использованию комбинированного метода очистки низких околоземных орбит от элементов крупногабаритного космического мусора. Ключевые слова: загрязнение околоземного пространства, космический мусор, комбинированный метод очистки.

A methodology for assessing the relative effectiveness of alternative options for building space object diversion systems has been improved. An algorithm for assessing the effectiveness of the system of removal of space objects from near-Earth orbit based on the method of integral assessment is given. It makes it possible to simplify the process of optimal choice of the method to divert space objects and determine efficiency in the early phases of the life cycle of rocket and space technology objects. The use of the appropriate toolset makes it possible to build a system for assessing the effectiveness of projects for the removal of space objects from low Earth orbits using various diversion methods (active, passive, combined). The analysis of defining world indicators of evaluation of objects of rocket and space technology based on regulations by international space agencies has been carried out. An indicator of the total integrated relative efficiency of projects of space object diversion systems from low Earth orbits has been proposed, which makes it possible to build the removal of passive, active, and combined methods for leveling the risks of space activities. It is argued that the selected combined system using an autophagic launch vehicle could reduce environmental losses and, as a result, reduce compensation payments to owners of space objects. The possibilities of building combined systems with reusable engines have been considered in order to reduce such indicators as the period of diversion and reduction of operating costs due to fuel economy.

This article is devoted ascent depreciation in an earth orbit of space crafts for different functions that allow to solve many problems connected with space activity, in particular, maintenance of wider use of space resources and more effective clearing of a near space from space debris. The last is particularly true for bulky space objects of a technogenic origin which can be deorbit from earth orbits by using the special means for deorbiting injection into the target orbit by launch vehicles. As the ascent of such means for deorbiting by orbital launch vehicle demands significant financial expenses, for their decreased application of easy autophagy launch vehicles with burned fuel tanks is offered. The basic making unit of such launch vehicles is an autophagy engine. The design of autophage engine design and the principle of its operation of the version with compulsory fuel supply to the combustion chamber are presented and the expediency of use of such an engine for small spaceships in case of the impossibility of application of rather heavy usual systems of storage and fuel supply is shown. However, now the weight of the accepted systems of compulsory fuel supply autophagy engines for spaceships remains significant for launch vehicles. As one of the alternative ways of a feed the engine of autophagy launch vehicle, the capability of submission by using the inertia of the most fuel charge is considered. The unit of the autophagy engine contains an evaporator and works in a pulse mode, supplying fuel supply between momentums at the moment of low pressure in the engine. The effect of retardation (easings), representing pressure decrease and engine thrusts in flight time is established. This effect is called by the forces of inertia acting on the sliding engine, and has экспоненциальную an easing picture. Considering the effect of retardation, a system of the equations for calculating kinematic and design data of the launch vehicle with the autophagy engine is offered. The received results of the research have scientific and practical value and can find wide applications in the design of schemes and deorbiting means.

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The conducted researches are directed on the solution of one of the most important problems of the space use – a problem connected with existence and inadmissibility of growth the quantity of a technogenic origin space debris on low near-earth and geostationary orbits because its further increase will overlap to mankind an exit in space and will terminate space activity. In the basis of a technique of researches the analysis of an existing ecological condition of the surrounding space environment on which base determined the major factors of pollution of the space and considered ways of struggle against space debris on near-earth orbits is put. It is established that the major factors of pollution of the near-earth space are spent stages of launch vehicles and accelerating units, the space crafts which have terminated its existence, fragments of destroyed artificial space objects, operational elements etc. Space debris basically is concentrated on low orbits and around a geostationary orbit which on the basis of the analysis of statistical data on space crafts starts are in most common use. Here groupings of space crafts of the various particular mission, including space crafts of communication, relay, TV, the early prevention of a rocket attack are concentrated. It is shown that the main ways of struggle against space debris are prevention of occurrence new and removal of the already existing debris. Notable decrease in level of the pollution can achieve at cumulative use of such measures, as an exception of explosions of the space objects, limitation of quantity of the started space crafts, reduction of number of the accompanying fragments injected into orbits at starts. Methods and means of withdrawal from working orbits of space crafts upon termination of term of their active existence and known ways and systems of active removal of already existing fragments of the space debris, such as: application of an ionic bunch, the space ship-towing vehicle, the polyurethane foam, the pulsing laser, harpoon system, electrodynamic cord system are considered. Scientific novelty of the presented results consists in the description of conceptual actions for reduction of pollution of the space. The activities executed in the given direction, have huge practical value as the outer space exploration gives huge advantage and significant progress to mankind, but the further operation at near-earth space by existing methods without acceptance of the measures indicated in the article, its further safe development already will not allow in the near future.

The history of creation and the present one of scientific directions of chair of designing and designs and research laboratory of rocket-technical engineering of scientific research institute of power, introduction of results in practice are considered. The powerful contribution to development of this direction of professor Dronja Nikolay Mihajlovicha is noted.