| Oleg Alifanov | - Dean of Cosmonautics |
| Veniamin Malyshev | - Department Chairman, vehicle control and navigation |
| Guy Severin | - Department Chairman, life support systems |
| Nikolav Tolyarenko | - Department Chairman, space systems engineering |
| Vladimir Malozyomov | - Deputy Department Chairman, life support systems |
| Vladimir Bobronnikov | - Department of flight vehicle control and navigationi |
| Sergei Rumyanstev | - College Of Applied Mathematics, MAI |
| Sergei Loginov | - Department of life support systems |
| Yuri Zacharov | - Department of space systems engineering |
General principles of design and testing of thermal protection systems. Diagnostics and identification of heat transfer processes for the purpose of thermal design and testing. General methodology of identification based on the solution of Inverse Heat Transfer Problems (IHTP). Formulation of IHTP of different types, arising in the problems of experimental data processing of various types of heat shields and thermal regimes of spacecraft and technology processes. Inverse problems of design of a multi-layer heat shield. Historical survey of methods for the solution of IHTP.
Survey and methods for the solution of IHTP. Iterative solutions based on gradient minimization methods (steepest ascent and conjugate gradient methods): conditions of stability, utilization of apriori information on an unknown solution, modifications for multifactor problems. Application to boundary and coefficient IHTP (diagnostics and identification), computation of gradient of residual. Smoothing and differentiation of experimental data by means of iterative regularization methods. Algorithms and programs for the solution of IHTP: results of simulation.
Prospective analysis of Soviet manned and automatic launch vehicles is given with trends of design processes in the years 1960-1990. General principles in design and architecture of launch vehicles are discussed on the basis of choosing the best design solution.
Possible types of launch vehicles are selected on the basis of analysis of rocket techniques development. Among them: automatic expendable vehicles for average and heavy payloads, partical and fully reusable vehicles, small space planes, maneuvering orbital vehicles, etc.
Additional structural problems of mixed transport systems are tested in mono-criteria and multi-criteria statements with some restrictions. Special features and structure of software are examined (models of mass, power, volume, dynamics, criteria, etc.). Cost efficiency concepts of the transport and space program in the whole are introduced.
The influence of vehicle carrying power, available payload volume, reliability of vehicles, relative cost of launch vehicles and payloads, and limit delay time on the efficiency of systems are determined on the basis of mathematical modelling. Some ways space transportation costs are diagnosed. The most reasonable from them are service systems specification, successive modifications in the life cycle, etc.
A brief review of the possible uses of manned spacecraft is made: short duration space missions with reentry and landing, long duration missions in near Earth and interplanetary space, spacecraft for descent to and ascent from planetary surfaces, emergency rescue and service vehicles. A retrospective analysis of Soviet manned space programs (Vostok, Soyuz, Mir, etc.) is given.
Concepts for the main designing parameters are introduced and their rational mixture for each type of manned spacecraft. Basic dependences between design parameters, mass and energy of spacecraft, trajectory forms, and designing criteria are analyzed.
Possible design concepts in the structure of space stations are discussed. Among them: mono-body, and multi-body designs with distributed structures. Some prospective variants of multi-module space stations are analyzed. Problems of interconnection between the payloads and service systems and their characteristics are raised. The influence of reliability, inflight service, onboard spares, and some variants of repair are evaluated from the point of view of the space station program's efficiency.
Performance comparisons of chemical, nuclear and combined rocket engines for a manned mission to Mars are made on the basis of design analysis. Some mission scenarios with wide international cooperation are discussed. Interrelationships of manned factors of long duration space flights and possible methods of artificial gravity onboard a Martian facility are investigated.
Problems are considered for space suit technology and EVA activities, as well as crew emergency rescue. A brief history of these problems are presented. Basic concepts of space suit and portable life support system development ensuring crew safety are given. Some results illustrating adaptation of cosmonauts to repeat scheduled EVA activities are reviewed. The role of emergency escape systems in designing the acceptable level of mission safety are considered. Statistical data of emergencies and fatal accidents encountered in both Soviet and American manned programs are analyzed. A list of emergencies is formulated. A conceptual approach to the function of an emergency escape means ensuring both spaceplane mission safety and orbital station safety is proposed. Different types of emergencies is taken into account. Data on the Energia - Buran emergency escape means are presented. Selection of the multiprogram ejection seat with a solid thrust rocket motor and an EVA suit as an alternative to the ejection capsule is justified. Considerations of the unification of portable life support, space suit, airlock and other parameters is given. The role of such unification for spacecraft, whatever nation they belong to, is stressed, and its significance for future international rescue missions is emphasized.
Overview: The course will cover some new spacecraft and space systems navigation and control developed in the USSR (including MAI) and will consider how navigation and control problems were solved or are being solved in the Soviet space program.
Introduction: Classification of spacecraft flight control problems, navigation, and guidance and control of spacecraft motion. Deterministic, stochastic and garanteeing approaches to the statement of spacecraft motion control problems. Synthesis and control of space systems.
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