Novel Structure and Thermal Design and Analysis for CubeSats in Formation Flying

Park, Yeon-Kyu; Kim, Geuk-Nam; Park, Sang-Young

doi:10.3390/aerospace8060150

Cited by 14 publications

(5 citation statements)

References 13 publications

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“…In this work, the Nastran finite element solver was employed for all computational modal analyses, also known as normal modes analysis, which is a widely employed solver in the aerospace industry, such as in aircraft [51], rotorcraft [52], and spacecraft [33] analyses. The assembled models were meshed after defining the material properties of each constituent part.…”

Section: Computational Modal Analysis (Cma) Methodologymentioning

confidence: 99%

“…Perforations were implemented in systems falling in the smaller mass classifications, up to masses of around 30-40 kg. The most well-known small satellite design is the ISO standardized CubeSat Design [31] developed by the California Polytechnic State University (Cal-Poly) [32], in its basic configuration (the so-called 1U design, with a volume of 10 cubic centimeters and a mass of around 1.5 kg) and also its larger configurations (2U, 3U, 6U, and larger) [33,34]. However, a review of past works failed to identify satellite structures falling into higher satellite mass ranges, such as 40 kg and above, that employed the metal perforation technique.…”

Section: Introductionmentioning

confidence: 99%

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Modal Analysis of Conceptual Microsatellite Design Employing Perforated Structural Components for Mass Reduction

2022

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Mass reduction is a primary design goal pursued in satellite structural design, since the launch cost is proportional to their total mass. The most common mass reduction method currently employed is to introduce honeycomb structures, with space qualified composite materials as facing materials, into the structural design, especially for satellites with larger masses. However, efficient implementation of these materials requires significant expertise in their design, analysis, and fabrication processes; moreover, the material procurement costs are high, therefore increasing the overall program costs. Thus, the current work proposes a low-cost alternative approach through the design and implementation of geometrically-shaped, parametrically-defined metal perforation patterns, fabricated by standard processes. These patterns included four geometric shapes (diamonds, hexagons, squares, and triangles) implemented onto several components of a structural design for a conceptual satellite, with a parametric design space defined by two scale factors and also two aspect ratio variations. The change in the structure’s fundamental natural frequency, as a result of implementing each pattern shape and parameter variation, was the selection criterion, due to its importance during the launcher selection process. The best pattern from among the four alternatives was then selected, after having validated the computational methodology through implementing experimental modal analysis on a scaled down physical model of a primary load-bearing component of the structural design. From the findings, a significant mass reduction percentage of 23.15%, utilizing the proposed perforation concept, was achieved in the final parametric design iteration relative to the baseline unperforated case while maintaining the same fundamental frequency. Dynamic loading analysis was also conducted, utilizing both the baseline unperforated and the finalized perforated designs, to check its capability to withstand realistic launch loads through applying quasi-static loads. The findings show that the final perforated design outperformed the baseline unperforated design with respect to the maximum displacements, maximum Von Mises stresses, and also the computed margin of safety. With these encouraging outcomes, the perforated design concept proved that it could provide an opportunity to develop low-cost satellite structural designs with reduced mass.

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Section: Computational Modal Analysis (Cma) Methodologymentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Modal Analysis of Conceptual Microsatellite Design Employing Perforated Structural Components for Mass Reduction

2022

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“…These restrictions must be considered by the CubeSat antenna designer during the design and integration phase of the antenna with the CubeSat. [17,[39][40][41][42].…”

Section: Cubesat Antenna Specificationsmentioning

confidence: 99%

A Survey on CubeSat Missions and Their Antenna Designs

Theoharis

Raad

et al. 2022

Electronics

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CubeSats are a class of miniaturized satellites that have become increasingly popular in academia and among hobbyists due to their short development time and low fabrication cost. Their compact size, lightweight characteristics, and ability to form a swarm enables them to communicate directly with one another to inspire new ideas on space exploration, space-based measurements, and implementation of the latest technology. CubeSat missions require specific antenna designs in order to achieve optimal performance and ensure mission success. Over the past two decades, a plethora of antenna designs have been proposed and implemented on CubeSat missions. Several challenges arise when designing CubeSat antennas such as gain, polarization, frequency selection, pointing accuracy, coverage, and deployment mechanisms. While these challenges are strongly related to the restrictions posed by the CubeSat standards, recently, researchers have turned their attention from the reliable and proven whip antenna to more sophisticated antenna designs such as antenna arrays to allow for higher gain and reconfigurable and steerable radiation patterns. This paper provides a comprehensive survey of the antennas used in 120 CubeSat missions from 2003 to 2022 as well as a collection of single-element antennas and antenna arrays that have been proposed in the literature. In addition, we propose a pictorial representation of how to select an antenna for different types of CubeSat missions. To this end, this paper aims is to serve both as an introductory guide on CubeSats antennas for CubeSat enthusiasts and a state of the art for CubeSat designers in this ever-growing field.

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“…For this analysis, an enforced motion location from which to apply input vibrations is added to the model. In terms of constraints, only the axis in the direction of the enforced motion is allowed to be free and lastly a value of 2% for both hysteretic and viscous damping is declared [6].…”

Section: Random Vibration Analysismentioning

confidence: 99%

The structural analysis of AlainSat-1: An earth observation 3U CubeSat

Aasim¹,

AlMazrouei²,

Okasha³

et al. 2022

4th Symposium on Space Educational Activities

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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 analyses such as occurrence of unusually high concentrated stresses and discrepancies between different element stress results are highlighted and the subsequent approach towards overcoming them are explained. Future work will involve validating obtained results experimentally using a vibration shaker test equipment on the actual AlainSat-1 structure.

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Novel Structure and Thermal Design and Analysis for CubeSats in Formation Flying

Cited by 14 publications

References 13 publications

Modal Analysis of Conceptual Microsatellite Design Employing Perforated Structural Components for Mass Reduction

Modal Analysis of Conceptual Microsatellite Design Employing Perforated Structural Components for Mass Reduction

A Survey on CubeSat Missions and Their Antenna Designs

The structural analysis of AlainSat-1: An earth observation 3U CubeSat

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