01356658 Дар Академперіодика

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ABBREVIATIONS.....9
PREFACE....11
ANALYSIS OF SPACECRAFT OBJECT REMOVAL
SYSTEMS FROM LOW-EARTH ORBITS
1.1. The problem of near-Earth space pollution.... 13
1.2. The current state of development of active systems for the space debris objects removal from working orbits....15
1.3. Analytical review of passive space debris deorbiting systems ....18
1.3.1. Aerodynamic deorbit systems....18
1.3.2. Electrodynamic tether systems, electromagnetic devices and solar sails.....35
1.4. Prerequisites for the creation of hybrid means of space debris objects deorbiting from working orbits... 38
1.5. State of the art of the hybrid space debris deorbiting means development.....39
MATHEMATICAL MODEL FOR
STUDYING THE ORBITAL AND ATTITUDE
MOTION OF THE SPACECRAFT
WITH AERODYNAMIC DEORBIT SYSTEM
2.1. Reference frames and corresponding quaternion relations for analysis of spacecraft position.... 42
2.2. Mathematical model of spacecraft orbital motion ...49
2.3. Disturbance model in the analysis of the translational motion of the spacecraft...51
2.3.1. Gravitational perturbations associated with the Earth’s nonsphericity ... 51
2.3.2. Aerodynamic perturbative accelerations....52
2.3.3. Solar pressure perturbations... 53
2.3.4. Sun and Lunar gravitational perturbative accelerations.... 54
2.4. Mathematical model of spacecraft attitude motion.... 56
2.4.1. Perturbative torques.....57
MODELS TO CHOOSE DESIGN PARAMETERS OF AERODYNAMIC DEORBITING SYSTEMS
3.1. Classification of aerodynamic deorbit systems.... 59
3.2. Determination of the aerodynamic deorbiting system parameters functioning......62
3.3. Aerodynamic element parameters...63
3.3.1. Monoblock systems parameters......67
3.3.2. Frame-inflatable systems parameters....68
3.3.3. Parameters of deployable systems 75
3.3.4. Parameters of the aerodynamic element of the transformed aerodynamic deorbit systems....76
3.4. Deployment system parameters.....77
3.5. Inflation system parameters ....77
3.6. Storage system parameters...83
DESIGN SCHEMES OF AERODYNAMIC SYSTEMS FOR DEORBITING SPACE OBJECTS
4.1. Schematic of the aerodynamic deorbiting systems of space objects of the «nano» class.... 86
4.2. Scheme of the aerodynamic deorbiting system of space objects of the «micro» class... 87
4.3. Diagrams of the aerodynamic systems of deorbiting space objects of the «large» class....91
METHODS TO ANALYZE
THE INFLUENCE OF THE PARAMETERS OF THE AERODYNAMIC SYSTEM FOR DEORBITING SPACE OBJECTS ON ITS EFFICIENCY
5.1. The method to determine the parameters of the aerodynamic system....96
5.2. Calculation of aerodynamic element parameters...98
5.2.1. Selection of parameters of the aerodynamic element of monoblock systems.......104
5.2.2. Selection of parameters of the aerodynamic element of frame-inflatable systems...104
5.2.3. Selection of the parameters of the aerodynamic element of deployable aerodynamic deorbiting systems ....108
5.3. Selection of the inflation system parameters ...110
5.4. Assessment of the limits of the effective applicability of aerodynamic deorbiting systems.... 114
5.5. Determination of the limit of effective application of the unified aerodynamic deorbiting system....118
5.5.1. Computer modeling of the orbital motion of the upper stage of a launch vehicle with a unified aerodynamic deorbiting system... 118
5.5.2. Justification of the choice of structural type and design parameters of the modernized aerodynamic-de-orbiting system... 122
5.5.3. General mass and dimensional characteristics of the modernized aerodynamic deorbiting system of the upper stage of the launch vehicle....123
5.5.4. Determining the limit of effective application of the modernized aerodynamic deorbiting system of the upper stage of
the launch vehicle in close to circular low Earth orbits.... 123
5.5.5. Determining the limit of effective application of the modernized aerodynamic deorbiting system of the upper stage of
the launch vehicle in low Earth elliptical orbits....127
5.5.6. Calculation of the parameters of the modernized aerodynamic deorbiting system.... 127
5.5.7. Conclusions to subsection 5.5.....129
5.6. Determining the limits of application of the deorbiting system based on the transformation of a space object into an aerodynamic system...129
5.7. Selection of parameters of the aerodynamic deorbiting system of modular large space objects ...131
SPECIALIZED INFLATABLE гмдртрр AERODYNAMIC SYSTEMS \_rir\r I EK
6.1. Inflatable modules of the space industrial platform.....135
6.1.2. State of the at of inflatable space systems development...142
6.1.3. Aspects of a conceptual design of inflatable systems of space industrial platform.....146
6.2. Aerodynamic systems for creating orbital solar radiation screens....149
6.2.1. An overview of the most popular concepts of Earth’s global climate control....150
6.2.2. Peculiarities of aerodynamic shading system creation...153
6.2.3. Determination of further research tasks using the developed SBSLS ballistic and navigational mathematical model structure.....158
REFERENCES ....160

The monography considers the features of the design of space aerodynamic systems for passive control of spacecraft. One of the purposes of using this technology is the deorbiting of space debris fragments from working orbits. The classification of the aerodynamic deorbiting system has been proposed. Classes of aerodynamic systems are divided according to various criteria such as: the degree of stiffness of the aerodynamic element, according to the method of forming the aerodynamic deorbit system, according to the modularity of the design of the aerodynamic element, into groups using the transformation of the design elements of the object, depending on the type of material, etc.
For scientific and engineering workers working in the field of rocket and space technology, as well as for graduate students and students of relevant specialties.