Using an astronomical model of insolation of the polar day and polar night zones of the Earth, the influence of cosmic factors on the ice conditions in them is estimated. It is shown that the temperature increase in the Northern Hemisphere began about 20 000 years ago due to volcanic events that occurred at that time, as well as in connection with the presence of a surplus of solar energy in this area of the planet, caused by the parameters of the Earth’s orbit: the inclination of the rotation axis, eccentricity, and precession angle. The surplus of thermal energy in the Northern Hemisphere has been preserved since then until the present day and will continue for at least 3000 years, after which the next period of glaciation will begin. Similar data are given for the Southern Hemisphere. It is shown that the melting of northern glaciers has been spread over many millennia due to the high heat of ice fusion and a pronounced phase transition. During melting, thermal energy is spent on the destruction of the ice crystal lattice, and the melt temperature does not increase. During freezing, the reverse process occurs: the energy released during ice crystallization prevents the temperature from decreasing. This process also occurs at a constant temperature. The heat-stabilizing properties of ice have manifested themselves in the form of “temperature shelves” on the graphs of the dependence of the average annual temperature on time, constructed based on the results of the analysis of ice cores obtained in the Southern Hemisphere at the Vostok station and in the Northern Hemisphere in central Greenland. At present, ice reserves in the Northern Hemisphere are coming to an end. Accordingly, the ability of glaciers to stabilize temperature is decreasing. As a result, the frequency and power of natural disasters in the world is growing. The problem of preserving the existing climate is becoming urgent. There is less and less time left for preparing and implementing measures to counteract climate change. Decarbonization cannot resist the ongoing process of destruction of the unique mechanism of natural climate stabilization. It is necessary to look for other ways to solve the problem of preserving the current climate. Among them, on the one hand, various methods of increasing albedo can be considered, and on the other hand, methods of reducing the permeability of the atmosphere by spraying special chemicals with short periods of complete decomposition in the upper layers of the atmosphere over certain areas.

This paper presents the results of numerical simulation of a transonic flow around a blunt body at a zero angle of attack in a test section with porous walls of the T-128 wind tunnel (WT) (Russia, Central Aerohydrodynamic Institute (TsAGI)). The calculations are performed using the EWT-128 TsAGI software package, which uses Darcy-type boundary conditions on the walls of the test section, whose porosity coefficient depends on the direction of the gas flow through the perforated surface. A comparison is made of the calculated and experimental drag coefficients of the model, as well as distributions of the isentropic Mach number on the model and on the perforated walls of the test section of the WT. A method is proposed for determining the correction to the Mach number of the oncoming flow to eliminate the wall interference of the test section in an aerodynamic experiment. The drag coefficients obtained as a result of calculations under WT conditions are corrected for the influence of the flow boundaries and compared with the free flow data. The calculated corrections are used to correct the experimental data.

We present the results of an analysis of flows in a gap between the reentry vehicle of a manned spacecraft and the propulsion bay located behind it in the case of their separation due to an emergency situation of the rocket in the active region of its trajectory. Emphasis is placed on different-in-nature oscillation processes occurring in transonic flight regimes. An approach to the estimation of the regimes of self-oscillation existence and their frequencies is proposed on the basis of the problem geometry and the flow conditions.

A discussion is presented of the effects generated by the imbalance between the insolation energy of polar-day zones and the radiation energy of polar-night zones on multicentennial changes in the Earth’s climate. The dependence of this imbalance on the Earth’s orbital parameters is determined. The energy imbalance curves are compared with the known temperature curves for the polar regions, which have been estimated from the results of an analysis of ice cores taken in Antarctica and Greenland. The curves clearly reveal a difference between the contributions of cosmic and terrestrial factors to the temperature profiles for the regions in question and demonstrate a synchronicity of these factors. Algorithms are obtained for calculating the magnitude of fluctuations in the size of the Earth’s polar caps relative to their averages. The results obtained within the assumptions taken in this work enable predictions to be made about the development of the current global warming and about changes in the size of the Arctic and Antarctic polar caps. It is predicted that over the next three millennia, changes in the Earth’s orbital parameters will contribute to the slow melting of the northern polar cap. Then, the trend for a new growth of the northern polar cap will again manifest itself. In the Southern Hemisphere, a trend towards increased glaciation has already formed. Influenced by the cosmic factor, it will intensify over the next 20 000 years.

Представлены результаты анализа исследований течения в зазоре между возвращаемым аппаратом пилотируемого космического корабля и расположенным за ним двигательным отсеком при их разделении в случае аварии ракеты на активном участке траектории. Особое внимание уделено автоколебательным процессам различной природы, возникающим при определенных расстояниях разделения на трансзвуковых режимах полета. Предложен подход к оценке режимов существования и частот автоколебаний на основе геометрии задачи и условий обтекания.

The results of the numerical modeling of the impact of the wakes of the nozzles of an emergency rescue rocket unit (ERRU) on the surface of a manned spacecraft are presented. The calculations are performed in the context of the two-stage zonal RANS-LES methodology proposed and validated by the authors earlier. In this methodology, the wall-modeled LES (WMLES) is based on the well-known eddy-resolving approach IDDES. In this paper, this technique is improved by including in the WMLES-subdomain the first row of the ERRU’s nozzles and performing calculations in the entire (360°) azimuthal domain. This makes it possible to increase the accuracy of the calculations due to a more correct description of the wakes of these nozzles and to analyze the flow around the spacecraft at nonzero angles of attack. The effect of the flight’s Mach number on the amplitude-frequency characteristics of the pressure fluctuations on the surface of the spacecraft, including their alteration at the sonic barrier, is analyzed. In addition, at the transonic Mach number value of M∞ = 0.95, the effects of the angle of attack and the mutual azimuthal position of the nozzles of the first and second rows are studied.

A two-stage RANS-DDES model and the results of calculations of the turbulent trans- and supersonic flow around a manned spacecraft (MSC) in the course of the emergency separation of the reentry module (RM) after actuation of the propulsion device (PD) of the crew’s emergency rescue system (ERS) in the initial flight stage are presented. The study is focused on determining the unsteady aerodynamic and acoustic loads on the screen of the RM and the fairing of the engine compartment (EC). It is shown that the maximum level of the unsteady loads is reached on the fairing of the EC in the region of impingement of the turbulent structures of the shear layer separated from the command module. In addition, it is found that at the transonic flight in the initial stage of the detachment process, self-exciting oscillations are observed in the gap between the RM and the EC.

Paleontological studies of the distant past and historical chronicles of the last millennia indicate that warming and cooling of the climate on our planet, replacing each other, have taken place in a continuous series. An important role in this process has been and is played by cosmic factors: variations in solar activity and parameters of the Earth’s orbital motion in the gravitational field of the Sun and the planets of the Solar System. It is suggested that the currently observed climate change is associated with a decrease in the eccentricity of the Earth’s orbit and the inclination of the axis of its rotation relative to the plane of the ecliptic, which has been going on for almost 30 thousand years. Both processes lead to changes in the boundaries of climatic zones. In the foreseeable future, these processes will proceed in the same direction. Therefore, the current trend towards climate change will continue. Despite the importance of addressing the problem of reducing greenhouse-gas emissions as soon as possible, this paper expresses doubts about the possibility of fending off climate warming in this way. It is proposed to focus on the development of mathematical climate models taking into account space factors and on finding the best ways to adapt industry, transport systems, and the environment to the conditions of expected climate change.

The paper discusses an integrated system for spacecraft rendezvous docking using measurements from satellite navigation equipment combined and with the optical final approach subsystem (OFAS) which generates high-precision relative 2Space Research Institute of the Russian Academy of Sciences (SRI RAS) 84/32 Profsoyuznaya str., Moscow, 117997, Russian Federation, e-mail: iki@cosmos.ru position vector during final approach. It addresses issues involved in designing an an on OFAS which has to operate in an environment exposed to sunlight and provides estimate for the accuracy of the relative position measurements depending the current range and OFAS configuration. Simulations have been run of the final approach involving simultaneous control from the satellite navigation equipment and OFAS. It was shown that at the moment of initial contact the approach accuracy of 2–5 cm for relative position, and of 1 cm/s for velocity is achieved.

The paper reviews a possible lunar mission architecture, where lunar modules are integrated on the lunar Orbital Station (OS), placed in a high lunar orbit (HLO). It discusses the concept of transfers from HLO to an intermediate low lunar orbit (LLO), transfer to a descent orbit, landing at a designated point on the Moon, and return to the OS. An approach was defined, and algorithms were determined and run in simulations for rough and fine control during various phases of the flight. An approach was defined for implementing propellant consumption-optimized descent from LLO to the designated landing target, the lowest possible value for the braking burn required for the descent was defined. Algorithms were developed for quasi-optimal descent during braking phase using measurements from lunar navigation satellites, with the braking burn value which is close to the optimal landing. Relationship between the braking burn and the ratio of the engine thrust to the mass of the Lunar Ascent/Descent Vehicle (LADV) was studied. Relationship between the braking burn of the quasi-optimal landing and the ratio of the engine thrust to the mass of LADV was studied. An approach to and control algorithms for providing operator support for lunar landing were developed, which provide the capability to visually asses the suitability of the landing target from the standpoint of landing safety and, if need be, the ability for the operator to intervene into the control process in order to move the landing target to a safer site.

Международная космическая станция (МКС) создаёт идеальные условия для исследований перспективных приборов, методов и технологий.Подготавливаемый Институтом космических исследований РАН и Ракетно-космической корпорацией «Энергия» эксперимент «Планета» предназначен для сбора данных и отработки технологии автономной навигации космических аппаратов (КА) на основе измерений направлений на звёзды, горизонт планеты и на объекты её поверхности с заранее известными планетоцентрическими координатами.В состав научной аппаратуры (НА) эксперимента входят две цифровые телевизионные камеры: широкоугольная и узкоугольная, а также блок предварительной обработки данных.НА доставляется на борт МКС с помощью грузового КА «Прогресс».Космонавты монтируют НА на обращённой к Земле стороне служебного модуля станции.Получаемые НА данные

The study makes an approach to the problem of circumlunar spacecraft navigation using the measurements from the global navigation satellite systems (GNSS) GLONASS, GPS, Galileo and BeiDou. Algorithms have been developed for determining the orbits of low- and high-orbit circumlunar spacecraft, based on the method of dynamic filtering of pseudo-range measurements from “reverse” navigation satellites (NS). The solution to the navigation problem has been simulated by the measurements from four GNSS, and by those from the NS of GLONASS and GPS only. Accuracy and dynamic characteristics of the obtained solutions have been determined and compared to similar solutions for geostationary spacecraft.

A concept of a global lunar navigation satellite system (GLNSS) based on the existing navigation infrastructure of the GLONASS is proposed. It is supposed to be implemented through the creation of a constellation of navigation satellites in the Earth orbit to serve the needs of both lunar spacecraft and objects on the lunar surface. Two variants for the deployment of the orbital constellation are considered. The navigation solution in the vicinity of the Moon was simulated using signals from the proposed GLNSS. The accuracy of the GLNSS navigation solutions has been estimated for all types of users.

The paper discusses the functionality of the Satellite Navigation Equipment (SNE) for the advanced Crew Transportation Spacecraft (CTS) Federatsiya, algorithms for determining its attitude exclusively from measurements of a global satellite navigation system without using any additional navigational or gyroscopic devices. It proposes methods for determining the attitude with successive increases in accuracy, providing attitude determination in minimal time: - the method based on the filling of fields of view of the antennae with signals from navigation satellites, which provides a rough determination of the attitude to within 20-30° over a period of 2 to 3 seconds; - the method based on phase increments, which provides attitude determination to within 2-3° over a period of 50 to 100 seconds; - the method based on phase measurements, which provides continuous attitude determination to within -0,5° in 10 seconds after the mode is started. The paper defines the solvability criterion for the attitude problem, introduces the notion of Attitude Dilution of Precision (ADOP) and provides its rigorous definition by analogy with the standard notion of Geometric Dilution of Precision (GDOP) in the navigation problem. The paper compares the performance of an SNE, which fulfils the functions of a Strapdown Inertial Navigation System (SINS) with the performance of a conventional SINS built around various gyroscopic devices.

The necessity of taking many force components disturbing spacecraft (SC) orbits into account is demonstrated for the example of forecasts of GLONASS ephemerides. The disturbances of SCs in high-earth orbits (HEO) and low-earth orbits (LEO) are systematized, and the degree of their effect on SC motion is estimated. Disturbance models are developed that provide essential increases of the accuracy of one-day forecasts of GLONASS and GPS ephemerides. Modeling results are presented that allow, depending on the required accuracy of SC orbit forecasts, the determination of the necessary list of disturbances included in the model.

Фундаментальные составляющие параметров вращения Земли играют важную роль в решении задач навигации и управления движением космических аппаратов. Рассматриваются математические модели движения полюса Земли и рассогласования dUT1 временных шкал UT1 и UTC адекватные данным наблюдений и измерений Международной службы вращения Земли. Показано, что предложенные модели обеспечивают достаточную автономность в формировании параметров вращения Земли на борту космического аппарата. Учет этих параметров в реальном времени необходим на борту космического аппарата для решения задач его навигационного обеспечения. Приведены графики ошибок суточного прогноза орбит навигационных спутников ГЛОНАСС, обусловленные смещением полюса. Сравнительный анализ графиков показывает, что возмущения орбит навигационных спутников соизмеримы с гравитационным воздействием Луны и Солнца и возмущениями, вызванными аномальной частью гравитационного поля Земли. Установлено, что значительное повышение точности прогноза эфемерид спутников достигается учетом в уравнениях движения космического аппарата вращательно-колебательного движения Земли.