DESIGN OF A 1U CUBESAT PLATFORM FOR - UNSAM · DESIGN OF A 1U CUBESAT PLATFORM FOR EDUCATIONAL...
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DESIGN OF A 1U CUBESAT PLATFORM FOR EDUCATIONAL PURPOSES A. O. Rêgo (*) , M. C. Pereira (*) , M. Greco (*) , E. Peiró (**) (*) Universidade Federal de Minas Gerais – Belo Horizonte, MG – Brazil (**) Unidad de Formación Superior CONAE/ UTN - Argentina Objective: Develop and analyse an 1U picossatellite platform for Aerospace Engineering courses. Suggest two different internal configurations. Studies of typical launching conditions to determine accelerations and loads. Develop a complete modelling of the structure in 3D CAD. Methodology: Systemic analysis Environment and interfaces Conceptual development Need analysis Operational analysis Functional analysis Viability definition Comparative Method Simulation using FEM Conceptual Design: Monocoque structure Preliminary modelling Basic components OBDS Reaction wheels Battery Solar sensor Transmitter Structure assembly Structural Analysis Aluminium alloy Al 7075 T6 Static Analysis von Mises tension Dynamic Analysis Natural frequencies Requirements: CubeSat Design Specification Tests Phylosophy Qualification Protoflight Admission Mandatory tests Design Modifications Modifications for mass reducing and new simulations for structural analysis Conclusions: In this paper the CubeSat was considered as a system, the structure being one subsystem, with expected behavior. CDS was used for the requirements and tests philosophy. A monocoque structure was chosen and simulations based on FEM were performed, using Femap and Nx Nastran, both of the structure itself and with components. Static load analysis showed that inertial forces do not produce significant tensions. Also the influence of each natural frequency on mass allocation was evaluated, showing that only the 10 first natural frequencies are relevant. Tests of alleatory vibration were performed, and, based on them, it is known that fatigue was not expected for the mandatory 3 minutes. Sinusoidal vibration and impact tests show that no plastic deformation or fatigue damage is expected. The structure was optimized for mass reduction and all simulation was performed again, showing that requirements are met for the new structure, that weights 114.4g. Figure 1– Comparison between tensions on the base – original and modified structure Figure 2: Initial suggested structure Figure 3: Structure modification Figure 4 – Modified structure levels of tension for spectral analysis
Transcript of DESIGN OF A 1U CUBESAT PLATFORM FOR - UNSAM · DESIGN OF A 1U CUBESAT PLATFORM FOR EDUCATIONAL...
DESIGN OF A 1U CUBESAT PLATFORM FOR EDUCATIONAL PURPOSES
A. O. Rêgo (*), M. C. Pereira(*), M. Greco (*), E. Peiró (**)
(*) Universidade Federal de Minas Gerais – Belo Horizonte, MG – Brazil(**) Unidad de Formación Superior CONAE/ UTN - Argentina
Objective:Develop and analyse an 1Upicossatellite platform forAerospace Engineering courses.Suggest two different internalconfigurations. Studies of typical launching
conditions to determineaccelerations and loads.
Develop a complete modelling ofthe structure in 3D CAD.
Methodology: Systemic analysis Environment and interfaces Conceptual development Need analysis Operational analysis Functional analysis Viability definition
Comparative Method Simulation using FEM
ConceptualDesign: Monocoque structure Preliminary modelling Basic components OBDS Reaction wheels Battery Solar sensor Transmitter
Structure assembly
Structural Analysis Aluminium alloy Al 7075 T6 Static Analysis von Mises tension
Dynamic Analysis Natural frequencies
Requirements: CubeSat Design Specification Tests Phylosophy Qualification Protoflight Admission
Mandatory tests
DesignModifications Modifications for mass reducing
and new simulations for structuralanalysis
Conclusions:In this paper the CubeSat was consideredas a system, the structure being onesubsystem, with expected behavior. CDSwas used for the requirements and testsphilosophy. A monocoque structure waschosen and simulations based on FEMwere performed, using Femap and NxNastran, both of the structure itself andwith components. Static load analysisshowed that inertial forces do notproduce significant tensions. Also theinfluence of each natural frequency onmass allocation was evaluated, showingthat only the 10 first natural frequenciesare relevant. Tests of alleatory vibrationwere performed, and, based on them, itis known that fatigue was not expectedfor the mandatory 3 minutes. Sinusoidalvibration and impact tests show that noplastic deformation or fatigue damage isexpected. The structure was optimizedfor mass reduction and all simulation wasperformed again, showing thatrequirements are met for the newstructure, that weights 114.4g.
Figure 1– Comparison betweentensions on the base – original and
modified structure
Figure 2: Initial suggested structure
Figure 3: Structure modification
Figure 4 – Modified structure levels of tension for spectral analysis
