Development and analysis of a Brazilian CubeSat Structure

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.

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.

4th Symposium on Space Educational Activities

This paper presents the structural analysis of a remote sensing CubeSat planned for launch in Q4 2022. AlainSat-1 is a collaborative endeavour between the IEEE Geoscience and Remote Sensing Society and the National Space Science and Technology Center at United Arab Emirates University. To ensure that the conceptual design of the satellite satisfies design requirements Quasi-Static Analysis, Modal Analysis and Random Vibration Analysis are conducted using SIEMENS NX. These analyses identify the satellite’s fundamental frequencies along with measuring the resulting deformations and stresses it experiences as a response to both the static and dynamic loads exerted by SpaceX’s Falcon 9 launch vehicle. Modal Analysis results show that the satellite’s lowest fundamental frequency 120.405Hz, complies with standards set by the QB50 Project and both Quasi-Static and Random Vibration analysis indicated that stress values are within safe limits. Issues detected during the various phases of the...

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.

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.

1999

The French-Brazilian Micro Satellite (FBMS) is a scientific satellite, which will be piggyback launched by the rocket Ariane 5. Its most critical design constraints are: the lower bound of 40.0 Hz on the first natural frequency, in order to avoid coupling between the rocket excitation modes and the natural vibration modes of the satellite; and the upper bound of 10.5 kg on the structural mass. The structure of the FBMS is composed of a cylindrical aluminum alloy adapter for connection with the rocket, and eight sandwich panels (each composed of three layers) that define its topology. In this paper, we show the importance of structural optimization and design sensitivity analysis in the redesign cycles of Space Structures, by presenting all the steps taken and the difficulties encountered as we tried to maximize the first natural frequency from the low value of 18.78 Hz obtained with the first trial design, while maintaining the structural mass bellow the predefined upper bound. All the modal and sensitivity analyses as well as the optimization steps were performed using MSC/NASTRAN. The design variable space for the structural optimization steps was composed of the thicknesses of the faces and core of the sandwich panels.

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.

The present work describes the design, structural analysis, and qualification by analysis and experimental validation of the 1st Greek cube-satellite developed at the University of Patras (UPSat - University of Patras Satellite). The key innovative approach includes the replacement of the aluminum parts of the primary structure with structural composite components, something that has never been attempted in the past by other mission following such an approach. A Single-Unit (1U) CubeSat structure made entirely of composite materials was designed, analyzed, manufactured and tested. A comparison with the state-of-the-art, commercially available, structure made out of aluminum (CubeSat-kit) already certified for space use also took place. The work was performed under the vision to prove the feasibility of manufacturing and certifying the structure for space use in the near future. Finite element analysis, confirmed by testing of a 1U Cube Sat, is used to examine trade-offs for the materials and layups. Based on these analyses, recommendations are given for a viable design solution. Results have shown that the redesign of the structure using CFRP can offer similar levels of performance in terms of stiffness while reducing mass by approximately 40%. KeyWords: CubeSat, Composite Materials, Finite Element Analysis, Modal Survey

Applied Mechanics and Materials, 2014

This paper presents the stress and thermal analysis on the CubeSat structure to study the survivability of the CubeSat during the launching process or operating condition at the orbit is presented. Various design of mechanical structures were analyzed to determine the best design for different mission requirements. Analysis on the temperature of the batteries will be conducted as it is one of the most critical components that must operate in the required temperature to avoid failure of the CubeSat. ANSYS 13.0 was used to simulate both the structural and thermal analysis. Static structural was used to study the impact of G-force on the CubeSat during the launching process and Icepak was used to study the internal temperature. All of the result will be compiled in the table and comparisons were made among different designs to determine the advantages and disadvantages of each design. Results from simulation such as: safety factor, weight, internal available space and battery discharge rate were analyzed. From the findings, there is no best design in the CubeSat structure but only the most suitable design for the mission purposes. Battery discharge rate will play an important role to determine the requirement of heater in CubeSat.

Aerospace

CubeSats usually adopt aluminum alloys for primary structures, and a number of studies exist on Carbon Fiber Reinforced Plastic (CFRP) primary structures. The internal volume of a spacecraft is usually occupied by battery arrays, reducing the volume available to the payload. In this paper, a CFRP structural/battery array configuration has been designed in order to integrate the electrical power system with the spacecraft bus primary structure. The configuration has been designed according to the modular design philosophy introduced in the AraMiS project. The structure fits on an external face of a 1U CubeSat. Its external side houses two solar cells and the opposite side houses power system circuitry. An innovative cellular structure concept has been adopted and a set of commercial LiPo batteries has been embedded between two CFRP panels and spaced out with CFRP ribs. Compatibility with launch mechanical loads and vibrations has been shown with a finite element analysis. The results...