recognition, evaluation, and detection of space radiation
Marjan Moghanipoor; Maryam Kiani; S. Hossein Pourtakdost; Amir Labibian
Volume 12, Issue 4 , December 2019, , Pages 91-102
Abstract
Temperature sensors have recently been proposed for attitude estimation (AE) of Low-Earth satellites. However, since half of the satellite surfaces do not receive any heat flux from the Sun, conduction occurs among the satellite surfaces. In this regard, the present study has focused on the effect of ...
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Temperature sensors have recently been proposed for attitude estimation (AE) of Low-Earth satellites. However, since half of the satellite surfaces do not receive any heat flux from the Sun, conduction occurs among the satellite surfaces. In this regard, the present study has focused on the effect of surfaces’ conduction as well as inner radiation on AE using temperature sensors. The nonlinear filter of Unsceted Kalman filter is adopted for AE, and the developed model to describe temperature rates is verified using Thermal Desktop and SINDA software. Monte Carlo simulations prove positive effect of the conduction on AE performance against negative role of the inner radiation.
Sohayla Abdolahi; Fskhri Etemadi; Mohammad Ebrahimi
Volume 8, Issue 3 , October 2015, , Pages 41-53
Abstract
In this study, the aerodynamic heating of the flying body during powered flight phase has been numerically investigated. The conjugate simulation of fluid heat transfer and solid heat conduction has been considered. To this aim, the coupling boundary condition has been used for body shell that allows ...
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In this study, the aerodynamic heating of the flying body during powered flight phase has been numerically investigated. The conjugate simulation of fluid heat transfer and solid heat conduction has been considered. To this aim, the coupling boundary condition has been used for body shell that allows the conjugate heat transfer investigation in the fluid and solid domains simultaneously. The model has been considered as a circular cylinder and spherically blunted cone nose with 350mm in diameter. The investigation has been carried out at different Mach number from 1.5 to 4.2 to cover range of supersonic flow. The advantage of this method is that the wall temperature and heat flux ââin any part of the nose and body shell with or without axial symmetry, connected components and other protuberances could be calculated at different angles of attack. Finally, the approach has been validated through the results of analytical and numerical methods for aerodynamic heating of axisymmetric vehicles.
