Vol 50, No 7 (2016)

This paper contains a description of methods and software tools for creation of the informationanalytical system for monitoring hazardous space objects. The paper presents the structure of the system and a description of its functional components that enable rapid assessment of the NEO hazard and forecast of the effects of dangerous celestial bodies colliding with the Earth. The results of the system’s operation regarding the modeling the motion of space objects are also included in this work.

The paper proposes a concept of a microrocket system meant for the injection of nano-, pico-, and femtoscale satellites into near-Earth orbit. Requirements for the appearance and basic design parameters of the micro-rocket system are substantiated. Characteristics of possible prototypes and analogues of this system are analyzed.

This article presents some types of planetary descent vehicles, the shape of which varies in different flight phases. The advantages of such vehicles over those with unchangeable form (from launch to landing) are discussed. It is shown that the use of transformable descent vehicles widens the scope of possible tasks to solve.

The procedure and algorithms are proposed for an experimental and computational estimate of attenuation of radial shock waves occurring in shells of detonating extended charges during glancing detonation of their ammunition (explosives). Based on results of experimental, the semiempirical dependence characterizing the attenuation law for such waves is obtained.

Analytical models of weight and energy balances, aerodynamic models, and solar irradiance models to perform pseudo-satellite preliminary design are presented. Feasibility criteria are determined in accordance with the aim of preliminary design dependent on mission scenario and type of payload.

A brief description of the design concept, structure and performance of the onboard control system (AOCS) of the “Navigator” satellite platform, on the basis of which the spacecraft “Electro-L’ and “Spektr-R” are designed, is presented. The test-flight results of the AOCS attitude accuracy are given. Approaches to the further development of the onboard control equipment for advanced spacecraft are determined and presented.

The problem of optimizing the interplanetary trajectories of a spacecraft (SC) with a solar electric propulsion system (SEPS) is examined. The problem of investigating the permissible power minimum of the solar electric propulsion power plant required for a successful flight is studied. Permissible ranges of thrust and exhaust velocity are analyzed for the given range of flight time and final mass of the spacecraft. The optimization is performed according to Portnyagin’s maximum principle, and the continuation method is used for reducing the boundary problem of maximal principle to the Cauchy problem and to study the solution/ parameters dependence. Such a combination results in the robust algorithm that reduces the problem of trajectory optimization to the numerical integration of differential equations by the continuation method.

The orbital positioning options and orbital structure control methods are considered for the Arktika-M highly elliptical hydrometeorological space system, which is designed for continuous 24-hour imaging of the Earth’s Arctic region. The purpose of the control is to ensure on-going performance during the entire operational life of the space system given a major spatial and temporal deformation of its orbital structure due to the nonuniform evolution of the orbital parameters. The highly elliptical Molniya orbits are considered. The proposed control procedure is based on the minimization of the spatial and temporal deformation of the orbital structure by means of the differential choice of the initial orbital parameters during the deployment and follow-up of the space system.

The paper is devoted to the design features of the prospective Russian INTERHELIO-PROBE spacecraft using, depending on the configuration version, an electric or chemical propulsion system as a sustainer. The scientific goal of the mission is the study of near-solar space from close distances (60–70 solar radii). The paper presents the description of several versions of the spacecraft options depending on the installed propulsion system, as well as the main characteristics of the flight profile depending on the engine type.

The article describes a model of the two-way measurements of radial velocity based on the Doppler effect. The relations are presented for the instantaneous value of the increment range at the time of measurement and the radial velocity of the mid-dimensional interval. The compensation of methodological errors of interpretation of the two-way Doppler measurements is considered.

The article reviews application features of the method of bilevel coordinated optimization of spacecraft modification parameters during integrated replacement of subsystems. The algorithm for problem solution is presented in the article. It is shown that in the case of implementation of a balanced bilevel schematic of optimization search, the agreement of project solutions for spacecraft modification is provided by integrated replacement of subsystems. Project models are shown for the problem solution of optimization parameters for spacecraft modification with the integrated replacement of subsystems of the payload equipment module and a unified space platform.