Structural Finite Element Analysis of Stiffened and Honeycomb Panels of the RASAT Satellite

Ontac, S.; Dağ, Serkan; Gökler, Mustafa İlhan

doi:10.1109/rast.2007.4283971

Cited by 9 publications

(8 citation statements)

References 2 publications

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“…Structural analyses of the ″RASAT″ satellite were carried out, (Ontac, Dag, & Gokler, 2007). The objective was to ensure the strength and vibration response properties of the stiffened and honeycomb panels.…”

Section: Introductionmentioning

confidence: 99%

Configuration design and modeling of an efficient small satellite structure

Aborehab¹,

Kassem²,

Nemnem³

et al. 2020

10.5267/j.esm

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The satellite structural mass is considered a crucial parameter during the process of satellite structural design. Sandwich structures acquire a considerable role in minimizing such mass while maintaining structural integrity. This article discusses the structural configuration, design, and analysis of a small satellite. A small Earth remote sensing satellite is chosen from the published data as a case study. Its structural design configuration is of a rectangular box that is based upon metallic alloys. Through a comprehensive study, the most suitable design configuration for the given mission is selected. A contribution has been made in developing a novel hexagonal primary structure that is based upon Aluminum honeycomb sandwich panels. The satellite configuration process and structural design procedure are thoroughly presented. The finite element modeling of honeycomb sandwich panels according to sandwich theory is introduced. Such modeling is validated numerically in comparison with published data. The analysis process is implemented using finite element analysis considering the loads during the ground and launch phases. The proposed structural design results in a significant mass reduction of 15% when compared with the baseline case study.

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Section: Introductionmentioning

confidence: 99%

Configuration design and modeling of an efficient small satellite structure

Aborehab¹,

Kassem²,

Nemnem³

et al. 2020

10.5267/j.esm

View full text Add to dashboard Cite

show abstract

“…With the increase of tray thickness to 10 mm, the first natural frequency increased both in longitudinal and lateral directions. RASAT satellite [4] described the analysis carried out on the main stiffened and honeycomb panel. Normal mode and stress analysis were performed by the use of Ansys.…”

Section: Introductionmentioning

confidence: 99%

Vibration and Modal Analysis of Low Earth Orbit Satellite

Israr

2014

Shock and Vibration

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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 ofAnsys, a tool for finite element analysis (FEA) under given loading and boundary conditions. Static, modal, and harmonic analyses inAnsysare 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.

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“…After BILSAT-1, the institute then built its second generation microsatellite, RASAT. Therefore, both microsatellites are used as sample for the University of Surrey design heritage [20][21][22][23].…”

Section: S T Sat-1 S T Sat-3 R Asatmentioning

confidence: 99%

System Designs of Microsatellites: A Review of Two Schools of Thoughts

Robertus¹

2021

Satellite Systems - Design, Modeling, Simulation and Analysis

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Microsatellite has been considered as disruptive technologies in satellite engineering. Its development cost and time provide advantages for new kind of Earth observations, telecommunications, and science missions. The increasing trend of microsatellite launches and operations means that the approach was so successful that it could create funding sustainability. Major contributing factors of its success were due to the system design of the microsatellites. This chapter discusses two microsatellite system design approaches, namely Technical University of Berlin heritage and University of Surrey heritage. Both Universities provide approaches for system design and build of microsatellite systems. The design approaches are being compared along with lessons learned. The choices of microsatellites to be compared in this chapter will be those that are manufactured about the same time such that the technology compared is mostly the same and flown in-orbit. The chapter shows that the differences between the two system design approaches are on the choice of main computer and associated link configuration and in the attitude control modes. Another major different is in the satellites’ structure design. For some satellite’s components, incoming technologies have made the design choices from the two schools of thoughts converged.

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Structural Finite Element Analysis of Stiffened and Honeycomb Panels of the RASAT Satellite

Cited by 9 publications

References 2 publications

Configuration design and modeling of an efficient small satellite structure

Configuration design and modeling of an efficient small satellite structure

Vibration and Modal Analysis of Low Earth Orbit Satellite

System Designs of Microsatellites: A Review of Two Schools of Thoughts

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