Природные катастрофы, процессы их зарождения, крупномасштабные техногенные катастрофы сопровождаются аномальными физическими явлениями в околоземном космическом пространстве. Для обнаружения таких явлений, их регистрации и исследований необходим комплексный мониторинг ОКП с помощью специализированного состава научной аппаратуры, размещенного на борту низкоорбитального космического аппарата. В работе представлены результаты летных испытаний малого космического аппарата “Вулкан-Компас-2” с комплексом научной аппаратуры, созданным специально для орбитального мониторинга ионосферы и поиска аномальных явлений, обусловленных крупномасштабными катастрофами различной природы.

Natural disasters, the processes of their origin and large-scale technogenic catastrophes are accompanied by anomalous physical phenomena in near-Earth space (NES). In order to reveal such phenomena, record and investigate them, complex NES monitoring is required with the use of specially designed research equipment onboard a low-orbiting spacecraft. This work presents the results of flight tests of the small Vulkan-Compass-2 satellite with research equipment specially designed for orbital monitoring of the ionosphere and search for abnormal phenomena caused by large-scale catastrophes of different nature.

The possibility to create the new concept for usage of small satellites constellation arises today in connection with development of the circuit technology for manufacturing of real small space vehicles. Their low price allows the formation of a multi-purpose satellite constellation. Such a constellation is created in frames of the Russian Federal space program up to 2006. It is designed for monitoring of natural (typhoons, hurricanes, eruptions of volcanoes etc.) and man-made (radioactive contamination etc.) catastrophes. The space segment will be designed and manufactured by the Research Institute for Electromechanics of the Federal State Unitary Enterprise. The Institute of Terrestrial Magnetism, Ionosphere and Radiowave Propagation (IZMIRAN) will design the set of scientific devices and programs.

A highly pure Al2O3 sample, degassed at 500°, does not chemisorb hydrogen. The absorption of microamounts of hydrogen was observed after degassing at 800–900°.

Herein a research spacecraft design is theoretically and experimentally estimated. The suggested spacecraft ensures guidance of a massive penetrating probe impacted on an asteroid and carrying out telemetry analysis in synchronism with the spectroscope examination of the procedures accompanying the impact to determine physic-chemical and mechanical properties of the asteroid in-depth substance. Both the spacecraft and the penetrating probe being its component have propulsion and control systems providing direct probe penetration into the asteroid and the specified distance between position of the spacecraft equipped with telemetry instrumentation and the asteroid during the impact. The spacecraft is launched into the asteroid impact trajectory by the launch vehicles MOLNIYA, PROTON, TITAN-4, ARIANE-5, N-2, ANGARA. The spacecraft configuration will permit it to conduct effective investigations of asteroids approaching the Earth at a distance of up to one million kilometres.

Theoretical and experimental estimations are given on the structure of a universal space interceptor designed on the modular principle. The interceptor comprising one command-impact module and a variable number of separable impact modules, each with propulsion and guidance systems, can be injected into a trajectory towards an Earth approaching space object by launch vehicles MOLNIYA, PROTON, TITAN-4, ARIANE-5, N-2, and ANGARA. The universal space interceptor is capable to attack Earth approaching asteroids and comets of up to 300 m in diameter and destroy them into a number of safe fragments. In this case objects with a diameter of up to 100-150 m are destroyed by non-nuclear kinetic module and to attack larger objects it is required to use a nuclear explosive device.