Small Spacecraft Research Articles

Анализ пространственно-временного распределения плотности потоков техногенного вещества в околоземном космическом пространстве

The task of ensuring safe operation of the orbital stations in conditions of the Near-Earth Space increasing pollution with the so-called space debris became especially significant in the International Space Station development. In addition, space debris poses a certain danger to spacecraft currently in operation. To assess the degree of risk, this paper presents a relational database developed by the authors making it possible to determine the number of the space debris particles collision and the impact parameters (particle size and collision speed) on the spacecraft staying in different orbits. Calculations in this case made it possible to determine potential number, probability of collisions and parameters of the space debris impact interaction with a group of small domestic spacecraft.

Application of Saturn’s Rings to Spacecraft Optical Navigation

This work explores the feasibility of using images of Saturn’s ring system as a navigation resource for spacecraft. The perspective geometry of Saturn’s rings provides closed-form expressions for estimating a spacecraft’s relative position as well as its analytical covariance. Numerical simulations detail the performance and sensitivity of the position estimates. An extended Kalman filter fuses the relative position estimates with spacecraft dynamics for more accurate relative position and velocity estimates. An Enceladus sample collection mission serves as a case study where the proposed method seems viable. With filtering, simulation of an Enceladus sample-collection mission achieves maximum bounds of 7.19 km and for relative position and velocity estimates, respectively, during its Enceladus encounter. Autonomous navigation may reduce the cost of such a mission to the point where several small spacecraft can achieve the science objectives.

Analysis of fragments larger than 2 mm generated by a picosatellite fragmentation experiment

Satellite breakup models rely on laboratory tests and in-space collision observations; current models can match fragments distributions generated by traditional satellites but may need to be improved for small spacecraft and modern satellites employing new configurations and materials. In the last years, ground tests have been employed to assess the influence of dimensions, materials and internal configurations on fragments distributions and to define the limits of the current models. In this context, an impact test was performed at the impact facility of the University of Padova to characterize the fragmentation of a picosatellite mock-up; more than 7000 fragments were collected, classified and analysed with automatic image recognition algorithms. It was observed that the experimental characteristic length distribution is line with the prediction of the NASA SBM even for the smallest size classes, while the fragments shape distribution is strongly affected by the materials employed in the picosatellite manufacturing.The subset of the collected fragments larger than 2 mm was recently subjected to a more detailed analysis: each fragment was individually weighed, and its three main dimensions were measured. In this paper, resulting fragments distributions are compared with literature data and the NASA Standard Breakup Model; in particular, an analytic relation between fragments characteristic length and size is found. In addition, results show that characteristic length and area-to-mass distributions are affected by the target materials and are clearly influenced by the size resolution of the analysed fragments.

The Symmetric Formulation of the Temperature Shock Problem for a Small Spacecraft with Two Elastic Elements

The paper considers the problem of a small-spacecraft elastic elements’ temperature shock that occurs when the spacecraft immerses into the Earth’s shadow or comes out of it. A small spacecraft with two elastic elements is simulated. In the first approximation, such a problem is considered to be a symmetric problem. Estimations of disturbing factors from the temperature shock in a symmetric formulation are obtained. The differences from the results for a small spacecraft with a single elastic element are analyzed. The results of the work can be used for promising small technological spacecraft development, as well as for solving problems of space debris removal and remote sensing of the Earth.

Modeling the deformation of an elastic element of a small spacecraft in its plane during temperature shock

A basic mathematical model of the deformation of a large elastic element of a small spacecraft in its plane is constructed. Deformations are caused by a temperature shock after a small spacecraft leaves the Earth’s shadow on the solar portion of the orbit. The model is used to conduct a computational experiment with the aim of assessing perturbations acting on a small spacecraft due to temperature shock. The temperature distribution during thermal shock is described by a one-dimensional model of thermal conductivity. The classical theory of thin plates is used to determine the deformations. The results of the estimation of disturbing factors are obtained as a result of a computational experiment for a model small spacecraft. These results indicate the need to compensate for the impact of temperature shock for small technological spacecraft. The data obtained can be used in the design of small space-craft for technological purposes.

Построение траектории малого космического аппарата для облета базового космического аппарата с целью наружного осмотра и оценка энергетических затрат на маневр облета

The paper presents a methodology for constructing a flyby trajectory of a base spacecraft for the purpose of inspecting it using a small spacecraft carried on board and estimating the required characteristic velocity reserves for the flyby maneuver. The use of approximate calculation methods made it possible to obtain the simplest dependences of trajectory parameters with high accuracy. The technique allows not only to estimate the energy costs for orbital maneuvers, but also allows one to calculate the values of control impulses for the real problem of controlling the motion of a small spacecraft relative to the base spacecraft.

Design and manufacturing of nano satellite frame

Currently, small spacecraft and their constellations are increasingly used in the rocket and space industry due to several their advantages. A version of a nano satellite frame made by a method of composite three-dimensional printing is presented in the research. A finite element analysis, a comparison of a designed structure with an aluminium analogue, and an economic substantiation of the proposed method for manufacturing the nano satellite frame have been carried out.

Development of methods for analysing telemetry of small spacecraft using machine learning methods

This article explores the influence of some averaged planetary geomagnetic indices, as well as solar activity indexes (Dst, Kp, Ap and Wolf numbers) on small spacecraft systems. The global experience in the field of research is described, and various directions in which leading specialists work are analysed. Methods of data analysis using Python are also provided. The procedure of correlation between space weather data and telemetry data of small spacecraft at a single moment in time is carried out. At the end of the experiment, a conclusion is drawn on which specific indicators should be focused on. Suggestions for further research on this topic are also provided.

Development of risk assessment technology for small spacecraft based on a space weather heat map

This study focuses on the development and implementation of a specialized technology to address the challenges posed by space weather on the performance and operational reliability of small spacecraft, particularly CubeSats and nanosatellites in Low Earth Orbit (LEO). The research emphasizes the importance of data acquisition, processing, and visualization of energy particle fluxes in near-Earth space, with a web application demonstrating visualization of average electron values in a heat map format. The proposed technology, in conjunction with space weather prediction methods, allows for quick response to adverse conditions, contributing to increased longevity and operational efficiency of small spacecraft. In the absence of comprehensive protection systems, the research suggests simple organizational methods as an effective approach for risk mitigation and reliability improvement, applicable even to spacecraft already in orbit.

Автономные экспериментальные исследования электротермического микродвигателя с двумя автономными нагревательными элементами для наноспутников

The purpose of the work is to conduct autonomous experimental studies of an resistojet with two autonomous heating elements with a diameter of 4 mm. As a result of experimental studies of the resistojet, the heating dynamics of the micromotor structure and the working fluid (isobutane) in the power range from 5 W to 60 W is determined. Experimental studies have shown the possibility of using the proposed resistojet design with two autonomous heating elements not only on small spacecraft, but also on micro- and nanosatellites under conditions of limited on-board energy.

Analysis of the requirements for microaccelerations and the design appearance of a small spacecraft for technological purposes

The article analyzes the possibility of implementing gravity-sensitive technological processes on board a small technological spacecraft. The requirements for microaccelerations imposed by the physical features of the flow of gravitation-sensitive processes are presented. The advantages and disadvantages of using small spacecraft for space technologies are analyzed. The design image of a small spacecraft for technological purposes is presented.

The design concept of a small technological spacecraft

The design concept of a small technological spacecraft

A High Gain Deployable L/S Band Conical Helix Antenna Integrated With Optical System for Earth Observation CubeSats

In this study, a new spiral dual-band antenna integrated with an optical system for a small CubeSat spacecraft was proposed. It is challenging to design an antenna with a limited space on a CubeSat platform. To improve the space utilization, an antenna was designed based on the concept of not occupying the sides of the CubeSat. A feature of the proposed antenna system is its compactness, dual-band operation in the L- and S-bands, and possibility of integration with spacecraft cameras. As a result of the study, reflection coefficients of -18 dB and -23 dB and gain of 6.8 dBi and 7.4 dBi, respectively, were achieved at resonant frequencies of 1.7 GHz and 2.45 GHz. The conical shape of the spiral antenna allows the optical system to increase the coverage area, and a simple deployment system with feedback ensures the mission safety. These properties make the proposed antenna suitable for CubeSat systems.

КОНСТРУКТОРСКО-ТЕХНОЛОГИЧЕСКИЕ РЕШЕНИЯ АДДИТИВНОГО ПРОИЗВОДСТВА КОРПУСНЫХ ДЕТАЛЕЙ МКА НК

In this article, research is carried out, technological recommendations are developed, including the choice of material, design solutions for hull parts of small spacecraft NC, taking into account the possibility of their manufacture by additive manufacturing methods and further robotic assembly on a turnkey basis.

Business model analysis of small-scale spacecraft projects

The use of data combined from various sources, including satellite data, expands the possibilities of predictive management of enterprises and organizations of all spheres of activity, contributing to the growth of economic entities’ efficiency in the conditions of digital transformation. The analysis of the satellite systems market and identification of the peculiarities of the growth of the commercial satellites and constellations segment is simultaneously reflected in the activity of investors, increased availability of small spacecraft, and improvement of their consumer characteristics. The study aims to analyze the business models of the projects of companies operating in the market of satellite systems, in particular, providing commercial opportunities for the use of satellites of ultra-small class to solve a wide range of problems. The basis of the research methods used in the work is a comparative analysis of the companies operating in the market of satellite systems, technical and economic analysis of the solutions proposed by them, and investment analysis of the projects implemented in the market. A classification of business models for commercial satellite systems was developed, which allowed identifying the pros and cons of different approaches, as well as cash flow modeling to justify the applicability and prospects of development of the identified business models.

Measurement of Transient Flash Evaporation Flow in Liquefied Gas Propulsion Using Dual-Plane ECT

In this paper, the transient flash evaporation flow in liquified gas propulsion (LGP) was measured using a dual-plane electrical capacitance tomography (ECT) sensor. The novelty mainly stems from a selection method for more accurate liquid holdup measurement, a constrained adaptive cross-correlation algorithm for more stable velocity, and compensation methods against the changes of temperature and pressure. By the selection method, inter-electrodes capacitances that contribute less to the flow measurement, are removed from each data frame and more accurate liquid holdup is derived via image reconstruction. The adaptive cross-correlation algorithm with a constraint on the correlation coefficient is adopted to alleviate the adverse effect of the fast changes of flow pattern on the velocity measurement. Then, the compensation methods are realized by correcting the deviations of phase density and permittivity caused by dramatic temperature and pressures changes. Simulations and experiments validated the effectiveness of the proposed methods to derive the mass flow rate of the two-phase flow via the measured liquid holdup, flow velocity and estimated phase density. It is shown that the remaining mass of propellant in the storage tank calculated from the mass flow rate is in good agreement with the measured reference by the electronic balance, where the average relative errors under different initial pressures are less than 10%. As the best of our knowledge, this is the first-time of transient flash evaporation flow measurement in a lab-built LGP device, which is promising to be applied for the effective online control to maximize the output impulse of LGP and estimate the remaining life of small spacecrafts.

Моделирование поля микроускорений в защищённой зоне виброзащитных устройств для реализации гравитационно-чувствительных процессов на борту малого космического аппарата технологического назначения

In this paper, models of the micro-acceleration field in the protected zone of various vibration-proof devices are constructed. An automatic rotary platform and a vibration-proof device based on the magnetic principle of operation are considered. Numerical simulation has been carried out for the platform of a small spacecraft of the Aist-2 type. Conclusions are drawn about the possibility of using vibration-proof devices when conducting gravity-sensitive processes on board a technological ICA. The results obtained can be used in the analysis of the satisfaction of conditions for micro-accelerations.

РАЗРАБОТКА ТЕХНОЛОГИИ 3D ПЕЧАТИ КОРПУСНЫХ ДЕТАЛЕЙ МКА НК

In this article, research is being carried out, a technological process is being developed, including the choice of material, the choice of equipment for the production of body parts for small spacecraft NC by the additive manufacturing method for further robotic assembly.

Development of the CYCLOPS CubeSat payload

The number of CubeSat satellites launched has been increasing over the past decades. These satellites have a number of advantages: short development time, low cost, possibility of modifications for certain scientific tasks and testing of technical solutions and new developments. This article describes payloads of a small spacecraft: CubeSat 3U CYCLOPS designed by D.F.Ustinov Baltic State Technical University "Voenmeh within grant under Space-Pi program. The purpose of the study: is to create, test and study the performance of payload modules of the vehicle, built using commercially available components, under space flight conditions. The text describes the structure of interaction between the payload and the OrbCraft-Pro 3U platform from Sputnix LLC. The process of development of payload control board is considered. The control system software for mechatronic and multi axis actuator modules with logging and error correction is described. Ln addition to the above-mentioned modules, the payload control system was also developed to carry out a series of experiments in die presence of a small spacecraft in orbit. The paper explains how the spacecraft communicates with the ground via special software Houston control application and Houston Telnet. The results describe tests performed on the mechanical components of the spacecraft. Examples of telemetry packets received from on-board the spacecraft are given. The article also reflects further plans for the project and the prospects of using the developed hardware for implementation in large-scale space systems and complexes. Also as part of the project students were able to gain engineering experience in the development of devices designed to work in space conditions.

Исследования проектного облика электротермического микродвигателя с пористой структурой для двигательных установок малых космических аппаратов

The results of experimental studies on nitrogen with an overpressure of 0,02 MPa resistojet propulsion system of a small spacecraft with a porous structure weighing 45 g and an autonomous heating element with a radius of 3 mm with a power consumption of up to 60 watts for a warm-up time of up to 300 s are presented. The possibility of using a porous structure as a volumetric fuel gas pipeline with an increase in heat transfer intensity has been experimentally proved and the actual specific heat capacity of the porous structure has been determined. Taking into account the actual specific heat capacity, theoretical studies of the mass and geometry of the porous structure in the resistojet composition are carried out, optimal with respect to the autonomous heating element used by the power and the amount of fuel heating in the range (573–1273) K. Taking into account the radius of the heating element, the fuel temperature range (573–973) K corresponding to the optimal masses and radii of the porous structure for the formation of the resistojet design layout is determined.