scholarly journals GRADIENT-BASED OPTIMIZATION OF SPACECRAFT AND AIRCRAFT THERMAL DESIGN

Aviation ◽  
2020 ◽  
Vol 24 (3) ◽  
pp. 105-116
Author(s):  
Laurynas Mačiulis ◽  
Rimantas Belevičius
Keyword(s):  
Thermal Analysis ◽  
Thermal Control ◽  
Multidisciplinary Optimization ◽  
Thermal Design ◽  
Thermal Models ◽  
Computational Overhead ◽  
Gradient Based ◽  
Multidisciplinary System ◽  
Initial Starting ◽  
Derivatives Of

Steady-case thermal analysis plays an important role in dimensioning thermal control systems for spacecrafts and aircrafts. Usually a trial and error approach is used based on engineering judgement and experience. When thermal models become complex or there are conflicting thermal requirements, however, it becomes harder for an engineer to gain insight as to which design decisions will lead to better results. Numerical optimization, on the other hand, could provide a more robust approach for the thermal design of complex spacecraft or aircraft models. In this paper, we suggest a gradient-based multidisciplinary optimization of thermal models where the coupled derivatives of the multidisciplinary system are obtained with the adjoint method. We show that in the case of steady-state thermal analysis, there is an analytic solution of a partial derivatives of implicit heat-transfer equation that can be used to derive total derivatives of the system. We present a practical application of this method by solving a small interplanetary spacecraft thermal optimization problem consisting of one objective, 15 design variables, and 10 constraints. We found that by using gradient-based optimization with exact derivatives, the best results can be achieved by exploring the design space at multiple initial starting points without major computational overhead.

Structure Design for Heat Sink Based on Thermal Analysis

2011 ◽  
Vol 80-81 ◽  
pp. 767-773
Author(s):  
Hai Gang Sun ◽  
Yong Zhou
Keyword(s):  
Thermal Analysis ◽  
Thermal Performance ◽  
Heat Sink ◽  
Cfd Simulation ◽  
Thermal Control ◽  
Structure Design ◽  
Thermal Design ◽  
Structure Parameters ◽  
Igbt Module ◽  
Key Factor

Thermal design and the working temperature control have been a key factor in the design of electronic devices and system. In this paper, a sort of heat sink collocated with high-power IGBT module, which is commonly used in car-carrying motor control system, is designed based on thermal analysis by means of CFD simulation and computer-aided analyzing, also the influence relations of structure parameters with thermal performance are studied. With thermal control as the overall design objective, structure parameters of heat sink are determined according to the obtained relations. Further, thermal performance of the designed heat sink is simulated and analyzed in CFD software to examine the validity of the design result. In this way, a method of thermal analyzing and structure parameter design for heat sink, which is proved as an efficacious approach, is introduced and can be used to thermal design and analysis for similar products.

Software Development for Satellite Thermal Design

2013 ◽  
Vol 390 ◽  
pp. 703-707
Author(s):  
Abolfazl Shirazi ◽  
Mehran Mirshams
Keyword(s):  
Thermal Analysis ◽  
Temperature Gradient ◽  
Software Development ◽  
Research Laboratory ◽  
Thermal Control ◽  
Thermal Design ◽  
Temperature Gradients ◽  
Space Research ◽  
Accurate Analysis ◽  
Control Subsystem

Accurate thermal modeling for each part in the satellite is needed for achieving temperature gradients. The result of such a modeling will be the temperature gradients of each element of the satellite as a function of time. The aim of this paper is to present a new software which has been developed recently by the author at Space Research Laboratory for thermal analyzing of the satellites that is used to characterize the gradients of subsystems temperature as a function of time in space orbit. The software accomplishes accurate analysis of internal and external thermal loads of each part of the satellite and shows temperature gradients of each element. The purpose of designing this software is to create a useful application for thermal analysis of satellites, which is a helpful manner for testing satellite thermal subsystem. The most important usages of this software are designing thermal control subsystem, choosing proper equipment for thermal control subsystem and finding optimal configuration of satellite for having an ideal temperature gradient. The outputs of this software are validated by comparing them to a different thermal analyzing application.

Design and Analysis for Thermal Control System of Nanosatellite

2010 ◽  
Author(s):  
Murat Bulut ◽  
Adem Kahriman ◽  
Nedim Sozbir
Keyword(s):  
Thermal Analysis ◽  
Thermal Model ◽  
Thermal Control ◽  
Temperature Data ◽  
Thermal Design ◽  
Analysis Tool ◽  
Control Analysis ◽  
Preliminary Design ◽  
Thermal Control System ◽  
Early Phases

It is desirable to be able to turn-around thermal analysis results in a couple of minutes early phases of a satellite thermal design. Therefore, ThermXL-spreadsheet-based Thermal Analysis Tool is one of the very flexible and easy-to-use tool that is suited to preliminary design of a nanosatellite. This paper focuses on the thermal design and the results of an initial analysis of the nanosatellite by using ThermXL. The goal of this study is to take suitable measures to ensure all the components will operate in their safe range of temperatures and also a proper heat rejection. The nanosatellite such as Cube Satellite (CubeSat) is a miniaturized satellite that has dimensions of 10cm × 10cm × 10cm and weights of 1kg. The thermal model of CubeSat was modelled and the thermal analysis was performed. The thermal control analysis on this CubeSat with passive thermal control has been conducted by the ThermXL program that provided by ITP Engines. Temperature distribution of solutions was computed with ThermXL. Temperature data met the need of the mission. The results of the temperatures show that the thermal design of nanosatellite is feasible.

Study on Thermal Analysis of Main Mirror in Space Solar Telescope

2011 ◽  
Vol 328-330 ◽  
pp. 300-304 ◽  
Author(s):  
Rong Li ◽  
Hu Li Shi ◽  
Zhi Ping Chen
Keyword(s):  
Thermal Analysis ◽  
Temperature Field ◽  
Thermal Control ◽  
Thermal Design ◽  
Solar Observation ◽  
Solar Telescope ◽  
The Sun ◽  
Analysis Software ◽  
Primary Mirror ◽  
Space Solar Telescope

The proposed Chinese Space Solar Telescope (SST) is the first large aperture space telescope in China designed to observe the sun. With an effective aperture of Φ1m, the primary mirror faces the sun directly, which receives more than 1000W heat that will lead to unacceptable thermal distortion in such severe thermal condition. Therefore, the temperature field of SST, which is changing with its orbital position, is critical in its design. In this paper, an analysis of the thermal flux in the SST is presented firstly. Further more, the heat flux of orbit is calculated with the thermal softerware NEVADA (Net Energy Verification And Determination Analyzer) according to the orbit parameters of SST. The thermal design software SINDA/G (System Improved Numerical Differencing Analyzer/Gaski), the radiation analysis software NEVADA and the finite element analysis software MSC.Patran are used to simulate the temperature field of the SST. In the end, the temperature distribution of the primary mirror is calculated. The temperature level of the primary mirror indicates that the system can achieve high spatial resolution with 0.1″~0.15″. It also means that the thermal control design is effective. The optical requirements to the SST thermal control are met. The thoughts and methods of the thermal analysis are also useful for similar optical telescopes designed for solar observation.

scholarly journals Quasi-All-Passive Thermal Control System Design and On-Orbit Validation of Luojia 1-01 Satellite

Sensors ◽  
2019 ◽  
Vol 19 (4) ◽  
pp. 827 ◽  
Author(s):  
Lin Yang ◽  
Qiang Li ◽  
Lin Kong ◽  
Song Gu ◽  
Lei Zhang
Keyword(s):  
Thermal Analysis ◽  
Control System ◽  
Temperature Fluctuation ◽  
Thermal Control ◽  
Temperature Data ◽  
Thermal Design ◽  
Analysis Model ◽  
Telemetry Data ◽  
Thermal Control System ◽  
Fluctuation Range

In order to resolve the large fluctuations in temperature range problem of Luojia 1-01 satellite caused by low heat inertia and poor thermal conductivity of structure, a quasi-all-passive thermal control system (TCS) design is presented under the conditions of limited resources including mass and power consumption. The effectiveness of the TCS design is verified by both ground thermal balanced test and related telemetry data of on-orbit performance. Firstly, according to the structural features and working modes of the satellite, isothermal design was implemented and the effectiveness was verified by thermal analysis using finite element method. Secondly, based on the results of the thermal analysis, thermal design was optimized and verified by the thermal balanced test. Finally, the thermal design was proved to be effective by temperature data acquired from telemetry data of on-orbit performance, and the thermal analysis model was improved and updated based on the results of thermal balanced test and temperature data of on-orbit performance. The on-orbit data indicates that temperature of optical camera stables at about 12 °C, temperature of battery stables at 19 °C, temperature of instruments inside and outside the satellite cabin is ranging from 10 °C to 25 °C. Temperature fluctuation range of optical camera is less than 2 °C when it is not imaging. Temperature fluctuation range of instruments not facing the sun is less than 4 °C. The data suggests that the temperature level of the satellite meets general design requirements, and the quasi-all-passive TCS design of the satellite is practicable.

Development of the room temperature protocol based on room temperature ionic liquids and surfactant ionic liquids for the synthesis of derivatives of 2-amino-thiazoles and thermo-physical analysis of the synthesized derivatives using TGA-DSC.

2020 ◽  
Vol 10 ◽  
Author(s):  
Chandrakant Sarode ◽  
Sachin Yeole ◽  
Ganesh Chaudhari ◽  
Govinda Waghulde ◽  
Gaurav Gupta
Keyword(s):  
Thermal Analysis ◽  
Heat Capacity ◽  
Ionic Liquids ◽  
Specific Heat ◽  
Specific Heat Capacity ◽  
Room Temperature ◽  
Heat Capacity Data ◽  
General Strategy ◽  
Capacity Data ◽  
Derivatives Of

Aims: To develop an efficient protocol, which involves an elegant exploration of the catalytic potential of both the room temperature and surfactant ionic liquids towards the synthesis of biologically important derivatives of 2-aminothiazole. Objective: Specific heat capacity data as a function of temperature for the synthesized 2- aminothiazole derivatives has been advanced by exploring their thermal profiles. Method: The thermal gravimetry analysis and differential scanning calorimetry techniques are used systematically. Results: The present strategy could prove to be a useful general strategy for researchers working in the field of surfactants and surfactant based ionic liquids towards their exploration in organic synthesis. In addition to that, effect of electronic parameters on the melting temperature of the corresponding 2-aminothiazole has been demonstrated with the help of thermal analysis. Specific heat capacity data as a function of temperature for the synthesized 2-aminothiazole derivatives has also been reported. Conclusion: Melting behavior of the synthesized 2-aminothiazole derivatives is to be described on the basis of electronic effects with the help of thermal analysis. Additionally, the specific heat capacity data can be helpful to the chemists, those are engaged in chemical modelling as well as docking studies. Furthermore, the data also helps to determine valuable thermodynamic parameters such as entropy and enthalpy.

Synthesis and thermal analysis of some oligomeric silicon derivatives of ferrocene

1983 ◽  
Vol 21 (8) ◽  
pp. 2529-2534 ◽  
Author(s):  
L. P. Asatiani ◽  
A. A. El-Agamey ◽  
M. A. Diab
Keyword(s):  
Thermal Analysis ◽  
Derivatives Of

Thermal Analysis on the Shell Stiffeners of Double Steel Wall LNG Storage Tank

2011 ◽  
Vol 105-107 ◽  
pp. 403-407
Author(s):  
Xiao Chun Zhang ◽  
Yuan Qi Cai
Keyword(s):  
Thermal Analysis ◽  
Structural Design ◽  
Storage Tank ◽  
Thermal Field ◽  
Local Buckling ◽  
Thermal Design ◽  
Normal Operation ◽  
Analysis Of Results ◽  
Design Requirements ◽  
Lng Tank

Shell stiffeners are used effectively to prevent preferential local buckling of LNG tank shell. In this paper, Finite element method (FEM) is applied to pay attention to the thermal analysis on the shell stiffeners of double steel wall LNG storage tank. The structural requirements according to British Standard 7777-2:1993 has been considered and then some dimensional adjustments of shell stiffeners are made to evaluate their influence on the thermal field of double steel wall LNG storage tank. Temperature distributions and heat flux of different dimensional shell stiffeners are presented. Though the analysis of results, it puts forward the conclusion that the dimensional design of shell stiffeners used in double steel wall LNG storage tank shall take not only the structural design requirements but also the thermal design ones into consideration in order to finally save cost in both construction and normal operation.

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