


Vol 52, No 7 (2018)
- Year: 2018
- Articles: 20
- URL: https://journal-vniispk.ru/0038-0946/issue/view/10419
Article
Aerial Vehicles Developed at Lavochkin Research and Production Association (On the 80th Anniversary of the Lavochkin Association)
Abstract
The article provides a review of aerial vehicles developed and constructed by the company and a description of automated spacecraft under development in the near-term outlook. The tasks and objectives solved by the spacecraft and how they are implemented are briefly summarized.






Software Package for the Development of Thermal Protection Systems for Spacecraft Descent into the Atmospheres of Planets
Abstract
The paper presents a mathematical model and a computational algorithm and describes a programming and computing suite (PCS) for the development of thermal protection systems for spacecraft designed to descend into the atmospheres of planets. The mathematical model and the PCS are implemented based on the development of thermal protection for the descent module of the EXOMARS 2020 surface platform.



Design Experience of a Demonstrator Descent Vehicle Introducing Aeroelastic Deployable Structural Elements to Space Engineering
Abstract
The development project of a prototype demonstrator for a descent vehicle and the possibilities of descent from orbit using aero-elastic braking devices deployable in space and in the atmosphere is considered. The project was carried out jointly by the Lavochkin Scientific Production Association and the Moscow Aviation Institute teams in 2013–2015. The results are evaluated for both the project itself and the cooperation of the two organizations.



The Space System for Remote Sensing of the Earth Based on the Arkon Satellite (On the 20th Anniversary of the First Launch)
Abstract
On the eve of the 20th anniversary of the first launch of the Arkon satellite, the article provides a retrospective of the birth, implementation, and development of this unique project that has no comparable counterparts. The authors also single out those remarkable teams of developers and their leaders whose activities have become part of the history of the Lavochkin Research and Production Association and its pride.



Proposal for Creating a Device for Deorbiting Low-Earth-Orbit CubeSats
Abstract
The article discusses proposals for creating a standard unit based on CubeSat technology, an independent autonomous aerobraking device based on inflatable balloons or a solar sail cone section. The proposed devices have a simple start-up system and are an additional component in the CubeSat assembly for deorbiting from low-Earth orbits.



Use of Programs for Two-Parameter Multiple Impulse Correction of Altitude and Inclination of Circular Orbits
Abstract
The paper describes the method for the development of programs for two-parameter multiple impulse correction of altitude and inclination of circular orbits. The considered corrections feature the simultaneous adjustment of altitude and inclination of the orbit under limited thrust of the propulsion system of the spacecraft. Low thrust-to-weight ratio of the spacecraft leads to the need for a correction program consisting of several burns of the propulsion system. Thrust vector orientation, burn time, and its operation duration are determined as propulsion system parameters.



Spacecraft Equipped with a Space Debris Removal System (Aerothermodynamics, Bulk–Mass Characteristics and Trajectories of Spacecraft Descent from Near-Earth Orbits)
Abstract
The processes of space debris formation are described; the urgency of the problem of its removal from near-Earth space is noted. A method to prevent the clogging of space by equipping a spacecraft to be launched into orbit with additional devices, simple in design and mode of operation, is presented. The results of the estimation of aerothermodynamics, bulk–mass characteristics and trajectories of low-orbit spacecraft equipped with a space debris disposal system are presented.



Linearization Methods for Problems of Optimizing Low-Thrust Spacecraft Trajectories: Verification Procedure
Abstract
Several well-studied problems for optimizing low-thrust spacecraft trajectories are solved using the modified linearization method (MLM). The results are compared with the results obtained by other authors. On this basis, conclusions are drawn on the possible use of the modified linearization method for optimizing low-thrust spacecraft trajectories.



On Increasing the Accuracy of Star Trackers to Subsecond Levels
Abstract
Modern star trackers are based on photodetector arrays such as CCD or CMOS arrays. The accuracy of commercially available devices is ~1–3 arcseconds. However, the development of the space industry calls for higher orientation accuracies, which are needed in laser space communications, monitoring of near-Earth space and space debris, high-precision global mapping, and remote sensing of the Earth. The problems associated with enhancing the accuracy of modern star trackers are discussed.



A Numerical Study of the Force Effects of Solar Radiation on Spacecraft Surfaces Considering their Real Geometry
Abstract
The effect of solar radiation on two typical external surfaces of a spacecraft is studied using numerical simulation by considering real geometry (geometry deviation from the nominal shape). The results of simulation are presented in this paper. Geometry deviations are simulated by two types of regular external heterogeneities. We compare the force and torque characteristics of solar radiation on nonuniform surfaces with similar characteristics for nominal surfaces and we find that the disagreement between them can reach 90% both in absolute value and sign. This means that it is necessary to consider the deviations in geometry from nominal for proper design and operation of spacecraft.






The Effect on Small Spacecraft of the Shock Loading Level by Actuation of the Separation System
Abstract
This paper focuses on the loading of small spacecraft induced by the triggering of separation systems. The article presents the experimental results for the shock loading level of small spacecraft manufactured by Lavochkin Association and analyses the causes of its observed increase. Recommendations are given for changing the testing techniques for the response to shock-impulse loading for similar objects.



Engineering Methodology for Assessment оf Spacecraft Structure Shock Load Levels During Pyromechanical Separation
Abstract
In this paper, we consider an algorithm for estimating the dynamic shock loads on sensitive units, assemblies, systems, and payloads of a spacecraft, as well as on precision elements of its construction occurring near separation belts that are based on linear cumulative and noncumulative pyromechanisms.



Improvement of Methods for Evaluating the Resolving Power of a Space Synthetic Aperture Radar
Abstract
An improved way for determining the resolving power of a space synthetic aperture radar is proposed. The model allows one to relate the geometric and radiometric quality to characteristics of the observed object and background. Some features of the radar image during visual examination are explained. Datapath errors are taken into account.



Experimental and Methodical Assurance of Studies of Hydrodynamic Processes in Fuel Tanks with Capillary Systems of Cryogenic Component Management
Abstract
The article presents a description of the experimental methodology for studies of capillary phase separator operations of fuel tanks of liquid rocket engines in a pendulum-type installation, which allows defining unambiguous initial boundary conditions in the case of the nonlinear nature of liquid sloshing. The results confirm the feasibility of the developed experimental technique for performing model studies for the development of advanced fuel tank management systems for cryogenic liquid rocket engines.



On Developing the Design of the Protective Heat Shield for the Interhelio-Zond Spacecraft
Abstract
This article describes the design of the protective heat shield for the Interhelio-Zond spacecraft, accepted for full-scale engineering development. The material proposed for making the shield’s parts is a carbon-carbon composite material (CCCM). The technology of making and mating of the CCCM shield parts is determined.



Radiosounding of the High-Latitude Ionosphere with the Arktika-M Hydrometeorological Complex
Abstract
The satellite ionosondes in highly elliptical orbits are proposed to be used for the task of continuous monitoring of the Arctic ionosphere. The monitoring scheme with the ionosonde location aboard the Arktika-M satellites is presented. The calculations of the vertical topside and transionospheric sounding using the SIMP1 ionospheric model are performed, which show the feasibility of continuous monitoring.



Analysis of Design Characteristics of Snake-Type Atmospheric Probes (Vetrolets) for Studying the Atmosphere of Venus
Abstract
In Russia, work aimed at designing a spacecraft for the long-term exploration of Venus is currently underway as part of the VENUS-D project. The R&D work proposes the concept of a snake-type atmospheric probe intended for exploring the atmosphere of Venus. This article describes the principles of flight, considers the main design features and engineering characteristics of the probes, and provides recommendations for engineering solutions.



On Continuous Observations of Thin Walls of High-Density Plasma in the High-Latitude Ionosphere from Arktika-M Satellites
Abstract
A new structure element of the Arctic ionosphere has been detected from the data of topside sounding of the ionosphere: quasi-vertical walls of high-density plasma. The importance of studying this phenomenon for geophysics and the practice of radio wave propagation in high latitudes is noted. The Arktika-M hydrometeorological space complex with an onboard ionosonde is proposed for its study. The possibility of observing and analyzing all life-cycle phases of this ionospheric inhomogeneity is shown.


