The article highlights the components of a laser navigation system and analyzes them. A mathematical model of an optical navigation system formed by a radiation source, a transmission medium (space vacuum) and a receiver are constructed. A technique for estimating the energy characteristics of the photosensitive matrix of the orbiter's receiver has been developed. Based on the constructed technique, an algorithm was developed for calculating the energy characteristics of the electron-optical components of the lunar beacon according to the given energy characteristics of the light-sensitive matrix and the optical system of the orbiter. Examples of practical calculations for lunar day and lunar night are given. The correctness of the results obtained in the examples of calculations was checked. The algorithm developed during the study can be used to select electro-optical components while solving the problem of creating a navigation system based on laser beacons. Object of research: laser navigation system. Subject of research: a generalized algorithm for calculating the energy characteristics of the electro-optical components of laser navigation system operating in space vacuum. Main results: a generalized algorithm for calculating the energy characteristics of the electron-optical components of laser navigation system and a mathematical model of a navigation system formed by a radiation source, a transmission medium (cosmic vacuum) and a receiver included in it.

The paper presents proposals to create a lunar radio-optical navigation beacon based on the light-emitting diodes with the selenodesic reference points. Introduction of the semiconductor emitters in the infrared (0.85 microns) and ultraviolet (0.24 microns) ranges makes it possible to improve reliability in the beacon signal reception and take the measurements both in the day and nighttime intervals. As a device in creating such beacons, the paper proposes to use a two-component penetrator equipped with a thermoelectric generator to convert thermal energy into the electrical energy due to the temperature gradient in the lunar regolith and a heat pipe connecting the penetrator bow and the tail parts to ensure higher heat transfer. Technology to create such a beacon system for long-term operations under the lunar environment is analyzed.

The article discusses the features of the occurrence of an inertial explosion (IE) in the problems of high-speed impacts on a solid barrier of two types of impactors: metal penetrators into the studied celestial body for space contact scientific research and meteor-technogenic particles into the elements of spacecraft. The features of IE, the conditions of its occurrence and the results of theoretical and experimental studies are analyzed. The ratio of the calculated impact velocity, leading to the appearance of willows, to the speed of sound in different metals tending to a certain average value is discussed. The influence of contact and thermoelectric phenomena and the temperature of the impactor on the occurrence of IE, as well as its dependence on the cross-sectional area of the impactor, is discussed. The ways of preventing the occurrence of IE are considered.

The article discusses the issues of improving strainresistive pressure sensors (PS) for their joint use with modern achievements of fiber optics (FO). The possibilities of implementation and features of FO pyrometric compensation of the temperature error of semiconductor and resistive strain-resistor, optical and/or electrical heating of the strain gage for selfcalibration of the pyrometer, power supply by optical radiation transmitted through a light guide with galvanic isolation of the PS circuit, increased noise reduction and fire and explosion safety are considered. Noise properties of semiconductor and resistive strainresistor are also considered.

The article discusses the features of the inertial explosion of metal products and the prevention of its occurrence during its impact introduction of a metal penetrator into the ground of celestial bodies. The possibility of an inertial explosion in metal penetrators is determined when calculating the critical overload of the Gcr that exceeds a certain threshold value for each metal. These values are determined for a number of alloys and high-purity metals widely used in rocket and space technology for Earth and space temperatures. The features of reducing the critical overload threshold of the Gcr for space conditions at cryogenic temperatures and ways to prevent an inertial explosion are discussed

В статье обсуждаются вопросы внедрении в грунт исследуемого небесного тела двухблочного инерциального пенетратора, состоящего из антенного и головного блоков. Показано, что при ударном внедрении в грунт небесного тела такого пенетратора без отделения антенного блока от головного создание канала устойчивой радиосвязи возможно при образовании кратера c большим углом раскрытия с формой от конусообразного до полусферического. Для существенного снижения скорость сближения антенного блока с небесным телом и возникающей соответствующей перегрузки наиболее перспективно высокоскоростное отделение, например, за счет отстрела антенного блока от головного.

Представлен макет конструкции солнечного паруса, в котором применены монокристаллы Cu

Two objects belonging to the interstellar medium have already been registered in the Solar system. For earth science the opportunity to study interstellar wanderers without the implementation of interstellar travel. However, technically it is extremely difficult to detect and intercept bodies flying through the Central part of the Solar system. Therefore, he possibility of sending research probes in pursuit is being considered. After leaving the vicinity of the Sun proper speed their removal from the Sun is 50 km/s or more, so to intercept such bodies at distances, where transmission of information from a research probe is still possible, the speed probe should be even higher. The high rate of approach of the probe and the interstellar wanderer raises the very difficult question of breaking the probe to a safe speed for research equipment. A solution of this task to use is discovered by patent RU 2626792 “Method of delivery of a payload into celestial body soil, maintenance of soil investigations and the celestial bodies”, which allows to ensure the safety and the efficiency of equipment when the speed of the probe up to several kilometers per second. This option would allow the probe’s propulsion resources to be used to homing the probe on a small target in the absence of accurate trajectory data on the interstellar wanderer motion.

The article explores scanning system for monitoring the electrization of metallized polymer films based on jet droplet optical measuring systems (JDOMS) for monitoring the electrization of products such as metallized polymer films during their laser perforation. The article shows that the main reason for the electrization of films is the removal of matter by a laser pulse with the formation in the microvolume of the plasma, a gaseous ionizing substance and its partial deposition on the edge of the perforated hole in the absence of contact with the metallization of the film. The JDOMS operating mode with the formation of a monodisperse coherent controlled charged droplet flow and video recording of the trajectory of charged droplets along the centers of perforated holes near the film is described, based on the measurements of which electrization is controlled. The maximum charges of the perforated holes of the film and moving drops are determined. The displacements from their interaction are calculated. The requirements to the means of video recording and processing of the obtained stroboscopic micrographs are determined.

Clogging near-Earth outer space by spacecrafts that have failed is a threat of collision with functioning objects in space. To solve the problem of man-made debris, which may affect the development of cosmonautics in the future, a lot of collision avoidance maneuvers are proposed. The most feasible method is to use spherical braking devices providing a predictable descent of the satellite from the orbit, regardless of the orientation of its body, and the shortest time of departure from low earth orbits. Based on the results of the system analysis, the rational composition and configuration design of the device using spherical brake shells for deorbiting CubeSat nanosatellites from low Earth orbits were determined, taking into account the mass and size limitations of the standard 1U CubeSat module.

Abstract—The paper analyzes the Russian scientific and technological capabilities to manufacture a space-borne observation platform for high-precision monitoring of the Earth’s gravitational field. It is shown that some Russian space systems manufacturing technologies may well be used for this purpose; however, in general, the level of the domestic technologies must be substantially improved so as to meet stringent requirements of such a project. Nevertheless, it can be confidently stated that it is quite feasible to carry out this project using Russian technologies.

The paper discusses the problem of developing an optical system for global positioning on the Moon to within one meter designed to service a limited number of users. It was demonstrated that the optimal solution of the problem would be to continuously monitor the positions of laser light beacons on the lunar surface from on-board an artificial satellite of the Moon equipped with an onboard TV camera, as well as from onboard a spacecraft placed at the L1 and L2 Lagrange points of the Earth-Moon system. The paper demonstrates the feasibility of a global lunar optical navigation and communications system based on space systems projects that are being developed at NPO Lavochkin: Spektr-UV observatory, lunar spacecraft Luna-25 and Luna-26. The use of these space systems will make it possible to start working in realistic terms on the navigation/communications system as a part of the future engineering infrastructure for lunar exploration. Keywords: telescope, optical navigation system, lunar base, Lagrange point, Spektr-UV, Luna-25, Luna-26.

The article discusses the control of parameters of laser-perforated metallized polymer films used in the manufacture of screenvacuum thermal insulation (SVTI) mats of spacecraft. The design, operating principle and operating mode of the laser perforator are described. It is shown that the most important operational parameters of perforated SVTI films are strength and dust release. Experimental studies have shown that laser perforation leads to increased strength and reduced dispersion for different samples of films SVTI compared with similar indicators for manual mechanical or semi-automatic thermomechanical perforation. When measuring the profile of the edge of the perforated hole, the optimal geometric parameters of the carbon Deposit zone consisting mainly of carbon corresponding to the effective mode of laser perforation and the maximum strength are determined. It is also shown experimentally that laser perforation does not lead to an increase in the dust release of SVTI films.

The article is devoted to the use of jet-droplet optical measuring systems (JDOMS) for monitoring the electrization of products such as metallized polymer films during their laser perforation. The article shows that the main reason for the electrization of films is the removal of matter by a laser pulse with the formation in the microvolume of the plasma, a gaseous ionizing substance and its partial deposition on the edge of the perforated hole in the absence of contact with the metallization of the film. The JDOMS operating mode with the formation of a monodisperse coherent controlled charged droplet flow and video recording of the trajectory of charged droplets along the centers of perforated holes near the film is described based on the measurements of which electrization is controlled. The maximum charges of the perforated holes of the film and moving drops are determined. The displacements from their interaction and the JDOMS sensitivity limit for electrification control are calculated. The requirements to the means of video recording and processing of the obtained stroboscopic micrographs are determined.