The structural analysis of AlainSat-1: An earth observation 3U CubeSat (original) (raw)

Vibration and Modal Analysis of Low Earth Orbit Satellite

Shock and Vibration, 2014

This paper presents design, modeling, and analysis of satellite model used for remote sensing. A detailed study is carried out for the design and modeling of the satellite structure focusing on the factors such as the selection of material, optimization of shape and geometry, and accommodation of different subsystems and payload. The center of mass is required to be kept within the range of (1-2) cm from its geometric center. Once the model is finalized it is required to be analyzed by the use of Ansys, a tool for finite element analysis (FEA) under given loading and boundary conditions. Static, modal, and harmonic analyses in Ansys are performed at the time of ground testing and launching phase. The finite element analysis results are also validated and compared with the theoretical predictions. These analyses are quite helpful and suggest that the satellite structure does not fail and retains its structural integrity during launch environment.

Structural Design, Development and Testing of a Small Experimental Satellite: SATEX-1

1993

A 50 kg. satellite is being developed at the University of Mexico as an engineering test bed. SATEX-l is programmed to be launched to polar orbit early in 1995 by Ariane. The satellite structure comprises aluminum sandwich panels and composites in the form of a cube made with two matting U-shaped parts. This solution was selected for simplicity during assembly and testing. The sIc body is further stiffened by an internal panel which supports a pressurized gas tank and other hardware. All panels are joined by standard comer and edge close-outs and splices. At present, a finite element model for the validation of the design, regarding static and dynamic behaviour is being conducted. The paper presents numerical results for quasi static and dynamic analysis, such as eigen-values, free vibration and sinusoidal vibrations. The testing program follows closely launcher agency requirements and is supported by previous similar experiences in our laboratory. Also,a general description of the project is included.

Development and analysis of a Brazilian CubeSat Structure

This paper presents the processes of developing a physical solution to the structural subsystem of the Brazilian Technological Institute of Aeronautics – ITA CubeSat, the AESP-14 Project. This work also shows static and modal structural analysis through computational methods, in order to predict the structural response to launch environment. The INPE’s capacities for manufacturing CubeSat main structures, are also discussed and proved through Reverse Engineering applied to a Commercial Off The Shelf - COTS structure. Results of analysis showed that in average launch environment levels, the structure developed reaches maximum stresses quite below used material’s limits. Natural frequencies found are also eligible to major piggy-back launch requirements.

Structural Design and Analysis of a 3U Standardized CubeSat for a Future Mexican Mission

This paper introduces the conceptual design, and analysis of a 3U standard CubeSat for a future Mexican space mission; one of the first nanosatellites developed in Mexico. Its mission is to take photographs of our territory using a low-resolution camera. Additionally, this project will increase the aerospace technologic knowledge and to generate new specialists in this field. A structural design concept is introduced and validated, for the worst-case scenario, using Finite Element Analysis (FEA) and compared with hand calculations. Structure's CAD model was designed using SolidWorks Student Edition 2017 and corresponding analysis carried-out using its FEA tool. Buckling and vibration analysis were performed to find the structural deformation and the natural frequencies, to ensure that the CubeSat could withstand the severe launch conditions as well as the hazardous space environment. Results of these analyses are described.

Basic Principles and Mechanical Considerations of Satellites: A Short Review

Transactions on Aerospace Research

Satellites are used for navigation, communication, oceanography, astronomy, etc.. Satellites come in a diversity of sizes and forms. Depending on the satellite’s mission, different subsystems are used. These subsystems are installed inside a housing to protect them from the space environment. This housing, which is also known as the satellite primary structure or mechanical structure, is made of durable materials that can endure severe conditions during launch and in the orbit. The optimisation of satellite mass is crucial right now since satellites are losing mass every day to reduce the cost of manufacturing and launching. This review first introduces an overview of the satellite classifications and subsystems. Then, the different types of mechanical load analysis the satellite subjects itself to are demonstrated. The advanced approaches for promoting the performance of the mechanical structures of satellites are explored, with a spotlight on the effect of the optimisation paramet...

CubeSat System Structural Design

This work presents a cubeSat metallic structure design, which considered vitroceramics coatings. Nowadays, existing commercial options of cubeSat are availables, nevertheless they do not solve all the requirements for a specific mission. Therefore, it is proposed to follow a design protocol to satisfy the structural requirements. This protocol has four stages: 1) planning and clarification, 2) conceptual design, 3) preliminary design and 4) detail design. Thereby, it is described the structural dynamics as a consequence of the induced loads by the launch vehicle. Also, it includes a verification process that assess numerical simulations performed using ANSYS, such as convergence analysis. The results are presented in two parts: 1) the metallic structure geometry and 2) behavior evaluation on special-mechanics loads conditions, which must to bear. This evaluation is supported by statics, modal & harmonic response, random vibration and response spectra analysis. Finally, according the proposed protocol, a metallic structure was obtained, which complies with the requirements and specifications defined by the first stage of the design protocol allowing the integration with other CubeSat subsystems.

Finite element analysis of a cubesat

2017

This paper aims to analyse the behaviour of a selected aluminium CubeSat frame subjected under static and vibrational loads using finite element analysis. Failures of CubeSats due to instability caused by vibration during launch can result in damage of the CubeSats and Launch Vehicle. Hence there is the need to analyse the maximum von-mises stress and strain of the CubeSat before production and launch to avoid these failures and losses. The CubeSat is modelled and analysed using Solidworks 2014. Finally, the results obtained are an indication of whether or not the frame structure is able to safely withstand the worst-case scenario static loading and imposed failure modes.

Design, Analysis, Optimization, Manufacturing, and Testing of a 2U Cubesat

International Journal of Aerospace Engineering, 2018

The design optimization, development, and verification by analysis and testing of the 1st Greek cubesat, developed by the University of Patras and Libre Space Foundation (UPSat (University of Patras Satellite)), is presented. The key innovative approach includes the replacement of the aluminum side faces with structural composite components, keeping the commonly used aluminum frame. A “hybrid” double-unit (2U) cubesat structure was optimized, built, and tested for all launch and thermal loads/specifications required for launch and mission operations as imposed from the EU-funded FP7-QB50 project. Results show that the new design of the structure using CFRP can offer similar levels of performance in terms of stiffness, while saving 30% of the mass, for the entire cubesat platform.

Finite Element Analysis of Vibration Amplification Distribution in Lean Satellites

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, 2016

This paper presents a part of the basic research for establishing the unit Qualification Test (QT) conditions within the framework of an international project to make ISO standard, namely, "Space Systems-Design Qualification and Acceptance Tests for Small-Scale Satellites and Units Requiring Low Costs and Fast Delivery". A laboratory test is conducted to study how vibration acceleration is distributed in a satellite body, so as to define the unit QT random vibration test level. The range of natural frequency and the amplification of acceleration are identified through statistical analysis of the test results. Finite element analysis is carried out to extend the findings to other structural types of micro/nanosatellites. Three structural types are analyzed, i.e., Yojo han, T-type and Pi-type. Based on the results, a unit QT vibration level that provides the minimum reliability assurance for use in space is proposed.

On the static and dynamic analysis of a small satellite (MESBAH)

Acta Astronautica, 2003

The static and dynamic structural behavior of a micro-satellite has been studied using Finite Element Method. At first, the micro-satellite has been modeled parametrically using ANSYS code and after several computations and initial satisfaction for static loads with an acceptable safety factor, the geometry parameters initially freezed for dynamic analysis. Then, based on the data provided by ARIANE-5 launcher, the criteria for safe vibration range are extracted. The natural frequencies of the satellite have been derived by changing the most effective geometry parameters like tray thickness and stringer height. By using these results, the optimum shape of the satellite has been designed.