Vibration and Modal Analysis of Low Earth Orbit Satellite

Israr, Asif

doi:10.1155/2014/740102

Cited by 14 publications

(9 citation statements)

References 8 publications

(8 reference statements)

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“…The vibration shock and thermal durability are important characteristics of the proposed spectrometer for space applications [30]. These simulation analyses confirm the static and dynamic behaviors, in response to the mechanical shock and vibrations of H2A rocket launch and to a hypothetical mission: landing on a planet.…”

Section: B Strength and Thermal Durability Analysis For Component Designsupporting

confidence: 61%

Development of a Molecular Assessment High-Resolution Observation Spectrometer (MAHOS) for Microsatellites

Nakagawa

Yamada

Sato

et al. 2022

IEEE J. Miniat. Air Space Syst.

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Compact and lightweight sensors with a high-frequency resolution are required for the passive observation of atmospheric water and oxygen emission lines at a reduced cost and power consumption. A molecular assessment high-resolution observation spectrometer (MAHOS) is developed as a compact, low power, digital fast Fourier transform spectrometer to be installed on a microsatellite. MAHOS has a compact design with dimensions of 0.154  0.125  0.040 m 3 and mass of 0.7 kg. It uses only a few materials including a field programmable gate array (FPGA) module with a lightweight aluminum alloy box. The highly stable spectrometer exhibits a sampling speed of 2.6624 GS/s and 16,384 frequency channels. The stability of the spectrometer is longer than 1200 s within the 1 GHz bandwidth. Thermal dissipation is achieved through a heat conductive gel filled in the gap between the most heat generating component, the FPGA and the aluminum alloy case. Results of a finite element analysis indicate that the design stiff and stable enough to survive in the launch environment. Thermal analysis indicates the durability of the system during operation. Even in space where heat dissipation is not possible, self-heating temperatures are not a problem for the FPGA. In the future, the performance of the spectrometer will be verified by conducting environmental tests.

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Section: B Strength and Thermal Durability Analysis For Component Designsupporting

confidence: 61%

Development of a Molecular Assessment High-Resolution Observation Spectrometer (MAHOS) for Microsatellites

Nakagawa

Yamada

Sato

et al. 2022

IEEE J. Miniat. Air Space Syst.

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“…Different analyses were carried out including static, modal, and harmonic response, spectrum, and on-orbit thermal deformation analysis. Based upon analyses results, the satellite structural integrity during ground and launch phases was verified.The design, modeling, and analysis of remote sensing satellite were implemented, (Israr, 2014). 3D model of the satellite structure was implemented on Pro-E software.…”

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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“…The vibrations generated by the static and dynamic forces of rotating equipment, which are generally the reaction wheels that are used for the Attitude Determination and Control Subsystem (ADCS) placed in the neighborhood of payload, are one of the most important factors affecting the pointing payloads and precision devices in space platforms. This reaction wheels has a complex configuration with gears more detail in Figure 2, which makes it has a complex vibration mechanism such as vibration coupling structure, these vibrations are caused by the speed control system of the wheels, and mainly due to the peaks of response in transitional regime [13][14].Therefore, it is necessary to analyze and minimize these peaks. On the basis of this, an implementation and an effective comparisons of three control algorithms.…”

Section: Problem Definition and Methodologymentioning

confidence: 99%

An implementation of optimal control methods (LQI, LQG, LTR) for geostationary satellite attitude control

Djaballah¹,

Mohammed²,

Boughanmi³

2019

IJECE

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This paper investigates a new strategy for geostationary satellite attitude control using Linear Quadratic Gaussian (LQG), Loop Transfer Recovery (LTR), and Linear Quadratic Integral (LQI) control techniques. The sub-system satellite attitude determination and control of a geostationary satellite in the presence of external disturbances, the dynamic model of sub-satellite motion is firstly established by Euler equations. During the flight mission at 35000 Km attitude, the stability characteristics of attitude motion are analyzed with a large margin error of pointing, then a height performance-order LQI, LQG and LTR attitude controller are proposed to achieve stable control of the sub-satellite attitude, which dynamic model is linearized by using feedback linearization method. Finally, validity of the LTR order controller and the advantages over an integer order controller are examined by numerical simulation. Comparing with the corresponding integer order controller (LQI, LQG), numerical simulation results indicate that the proposed sub-satellite attitude controller based on LTR order can not only stabilize the sub-satellite attitude, but also respond faster with smaller overshoot.

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Vibration and Modal Analysis of Low Earth Orbit Satellite

Cited by 14 publications

References 8 publications

Development of a Molecular Assessment High-Resolution Observation Spectrometer (MAHOS) for Microsatellites

Development of a Molecular Assessment High-Resolution Observation Spectrometer (MAHOS) for Microsatellites

Configuration design and modeling of an efficient small satellite structure

An implementation of optimal control methods (LQI, LQG, LTR) for geostationary satellite attitude control

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