Relevant bibliographies by topics / Aircraft Thermal Management Systems

Academic literature on the topic 'Aircraft Thermal Management Systems'

Author: Grafiati
Published: 10 December 2022
Last updated: 29 January 2023

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Journal articles on the topic "Aircraft Thermal Management Systems"

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Affonso, Walter, RenataT Tavares, Felipe R. Barbosa, Ricardo Gandolfi, Ricardo J. N. dos Reis, Carlos R. I. da Silva, Timoleon Kipouros, et al. "System architectures for thermal management of hybrid-electric aircraft - FutPrInt50." IOP Conference Series: Materials Science and Engineering 1226, no. 1 (February 1, 2022): 012062. http://dx.doi.org/10.1088/1757-899x/1226/1/012062.

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Abstract Electric and Hybrid-Electric Aircraft (HEA) propulsion system designs shall bring challenges at aircraft and systems level, mainly in propulsion, electric and thermal management systems (TMS). The electrification of the propulsion system relies on large and high-power electrical equipment (e.g., electrical motors, converters, power electronics, batteries, and others) that dissipate heat at a rate at least one order of magnitude higher than conventional propulsion aircraft systems. As a result, high impacts on weight, drag and power consumption of the TMS/cooling systems at the aircraft level are expected. This paper proposes potential technologies to perform the thermal management of future electric and HEA, in the context of FUTPRINT50 project. For each technology, relevant aspects such as its integration to aircraft, safety, operational and maintenance impacts, certification, technologies readiness level (TRL) and the latest research works are analysed. A quantitative comparison of the several technologies is also proposed considering weight, volume, electric power consumption, pneumatic air flow and cooling air flow per cooling effect. Lastly, we present a set of potential TMS architectures for HEA.
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Kellermann, Hagen, Michael Lüdemann, Markus Pohl, and Mirko Hornung. "Design and Optimization of Ram Air-Based Thermal Management Systems for Hybrid-Electric Aircraft." Aerospace 8, no. 1 (December 23, 2020): 3. http://dx.doi.org/10.3390/aerospace8010003.

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Ram air-based thermal management systems (TMS) are investigated herein for the cooling of future hybrid-electric aircraft. The developed TMS model consists of all components required to estimate the impacts of mass, drag, and fuel burn on the aircraft, including the heat exchangers, coldplates, ducts, pumps, and fans. To gain a better understanding of the TMS, one- and multi-dimensional system sensitivity analyses were conducted. The observations were used to aid with the numerical optimization of a ram air-based TMS towards the minimum fuel burn of a 180-passenger short-range turboelectric aircraft with a power split of up to 30% electric power. The TMS was designed for the conditions at the top of the climb. For an aircraft with the maximum power split, the additional fuel burn caused by the TMS is 0.19%. Conditions occurring at a hot-day takeoff represent the most challenging off-design conditions for TMS. Steady-state cooling of all electric components with the designed TMS is possible during a hot-day takeoff if a small puller fan is utilized. Omitting the puller fan and instead oversizing the TMS is an alternative, but the fuel burn increase on the aircraft level grows to 0.29%.
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Grosu, Vicentiu, Chris Lindgren, Tamas Vejsz, Ya-Chi Chen, and Avijit Bhunia. "Thermal Management Solutions for Network File Server Used in Avionics Applications." International Symposium on Microelectronics 2014, no. 1 (October 1, 2014): 000419–27. http://dx.doi.org/10.4071/isom-wa24.

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In the modern era of commercial aviation there is an increasing need for establishing on-aircraft networks that interconnect legacy avionics systems for the purpose of data collection, health monitoring, and software management. At the heart of these networks are flightworthy file servers that perform similar functions to servers used in ground-based IT infrastructures. However, the size, weight, and power constraints for airborne servers are significantly more challenging than the constraints placed on groundbased equipment. As a result, the critical goals in the development of aircraft network systems are reducing the size and weight, maximizing the performance and reliability, and reducing cost. One of the main challenges includes dissipating high power in small packages within a confined space. This makes thermal management a critical component of the overall LRU (Line-Replaceable Unit) design. In addition, passive cooling systems are often required in place of internal fans in order to improve long-term reliability of the system. This presents another set of challenges, such as optimizing the airflow provided by the aircraft in the electronics compartment. This paper will present some of the critical elements of thermal management such as heat sinking, component placement, thermal interface materials, thermal vias, thermal links, heat spreader, packaging approaches and cooling strategies. The design and optimization of this system are based on analytical solutions, conjugated heat transfer and experimental results. Thermal management solutions must enable reliable operation under various environmental conditions: ground operation, flight operation, high operating temperature and loss of cooling air. Each environmental condition has different parameters for coolant airflow rate, effect of the surroundings, and ambient and coolant air temperature. Cooling airflow analyses were performed using CFD (Computational Fluid Dynamics). We have identified multiple approaches to remove heat from the critical components through optimization of the components and subsystems. These same approaches also serve to increase the system's performance and reliability.
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Grosu, Vicentiu, Chris Lindgren, and Tamas Vejsz. "Thermal Management Solutions for enhanced Digital Flight Data Acquisition Unit in Avionics Applications." International Symposium on Microelectronics 2015, no. 1 (October 1, 2015): 000517–25. http://dx.doi.org/10.4071/isom-2015-wp64.

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According to the Federal Aviation Administration, the commercial airline industry should expect to see the number of passengers traveling per year to grow from its current level of 750 million to nearly 1 billion by 2030. To meet this demand, airlines are placing orders for thousands of new aircraft over the next decade and beyond. With this increase in airline traffic, newer aircraft systems will generate an ever increasing amount of data per flight, data that allows airlines to further enhance their flight operations, flight safety, and reliability. For commercial avionics, the migration of the data acquisition and reporting functions from the traditional interface environments to newer, faster, and more network-centric architectures is creating a new generation of “smart” aircraft. Teledyne Controls' enhanced Digital Flight Data Acquisition Unit is an integral part of a new generation of aircraft and combines the functions of Mandatory Data Acquisition and Recording with a sophisticated Aircraft Conditioning Monitoring System that the aircraft operator uses to monitor the performance and reliability of each aircraft in its fleet. Some of the critical goals in the development of the Digital Flight Data Acquisition Unit are reducing the size and weight over previous generations, while maximizing performance and reducing cost. All of these opposing requirements make the design and fabrication very challenging. One such challenge includes dissipating high power in a confined space, and this makes thermal management a critical component of the overall LRU (line-replaceable unit) design. In addition, to increase the reliability over the lifespan of the unit, passive cooling systems are often required in place of internal fans. This presents another set of challenges, such as optimizing the airflow provided by the aircraft in the electronics bay compartment. This paper will present some of the critical elements in thermal management such as heat sinks, components placement, thermal interface materials, thermal vias, thermal links, packaging approaches and cooling strategy. The design and optimization of the system are based on analytical solutions, conjugated heat transfer and experimental results. The LRU should safely operate under various environmental conditions: ground operation, flight operation, high operating temperature and loss of cooling air where each environmental condition has different parameters for coolant airflow rate, effect of the surroundings, and ambient and coolant air temperature. Draw-Through and Blow-Through cooling analysis were performed using CFD (Computational Fluid Dynamics). The thermal analysis problems solved are conjugated heat transfer for laminar flow with radiation in steady-state or transient regimes. Multiple approaches were identified to remove heat from the critical components through optimization of the components and subsystems. These same approaches can also be used to increase the system's performance and reliability.
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Lei, Tao, Zhihao Min, Qinxiang Gao, Lina Song, Xingyu Zhang, and Xiaobin Zhang. "The Architecture Optimization and Energy Management Technology of Aircraft Power Systems: A Review and Future Trends." Energies 15, no. 11 (June 2, 2022): 4109. http://dx.doi.org/10.3390/en15114109.

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With the development of More/All-Electric Aircraft, especially the progress of hybrid electrical propulsion or electrical propulsion aircraft, the problem of optimizing the energy system design and operation of the aircraft must be solved regarding the increasing electrical power demand-limited thermal sink capability. The paper overviews the state of the art in architecture optimization and an energy management system for the aircraft power system. The basic design method for power system architecture optimization in aircraft is reviewed from the multi-energy form in this paper. Renewable energy, such as the photo-voltaic battery and the fuel cell, is integrated into the electrical power system onboard which can also make the problem of optimal energy distribution in the aircraft complex because of the uncertainty and power response speed. The basic idea and research progress for the optimization, evaluation technology, and dynamic management control methods of the aircraft power system are analyzed and presented in this paper. The trend in optimization methods of engineering design for the energy system architecture in aircraft was summarized and derived from the multiple objective optimizations within the constraint conditions, such as weight, reliability, safety, efficiency, and characteristics of renewable energy. The cost function, based on the energy efficiency and power quality, was commented on and discussed according to different power flow relationships in the aircraft. The dynamic control strategies of different microgrid architectures in aircraft are compared with other methods in the review paper. Some integrated energy management optimization strategies or methods for electrical propulsion aircraft and more electric aircraft were reviewed. The mathematical consideration and expression of the energy optimization technologies of aircraft were analyzed and compared with some features and solution methods. The thermal and electric energy coupling relationship research field is discussed with the power quality and stability of the aircraft power system with some reference papers. Finally, the future energy interaction optimization problem between the airport microgrid and electric propulsion aircraft power system was also discussed and predicted in this review paper. Based on the state of the art technology development for EMS and architecture optimization, this paper intends to present the industry’s common sense and future trends on aircraft power system electrification and proposes an EMS+TMS+PHM to follow in the electrified aircraft propulsion system architecture selection
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Sanchez, Florian, Susan Liscouët-Hanke, and Tanmay Bhise. "Influence of Ventilation Flow Rate and Gap Distance on the Radiative Heat Transfer in Aircraft Avionics Bays." Aerospace 9, no. 12 (December 8, 2022): 806. http://dx.doi.org/10.3390/aerospace9120806.

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The feasibility of the future more-electric, hybrid-electric, and all-electric aircraft configurations will depend on a good understanding of thermal aspects early in the design. However, thermal analysis of aircraft equipment bays is typically performed at later design stages to validate if the design meets the minimal certification requirements rather than to optimize the cooling strategy. The presented work aims to provide new insight into thermal aspects in typical aircraft equipment bays. In particular, system thermal interactions, such as radiation, play a more significant role in tightly packaged bays, such as avionics bays. This paper investigates the influence of radiation on the overall system heat dissipation in two representative avionics bays. Using Computational Fluid Dynamics (CFD) simulation, combined with an analytical approach, the authors analyze the impact of several parameters, such as varying mass flow rates and distances between adjacent systems, on their thermal interaction. The results suggest that the radiative effects must be considered when the gap distance between the systems is larger than 0.1 m, the flow rate between two systems is not strong enough to have high convective heat exchanges, when the systems of interest are hidden by other systems from the ventilation sources, and when the system’s internal heat dissipation is significant. Overall, this paper’s results will contribute enhance conceptual design methods, such as the previously developed Thermal Risk Analysis, and help optimize thermal management strategies for future aircraft.
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Jafari, Soheil, and Theoklis Nikolaidis. "Thermal Management Systems for Civil Aircraft Engines: Review, Challenges and Exploring the Future." Applied Sciences 8, no. 11 (October 24, 2018): 2044. http://dx.doi.org/10.3390/app8112044.

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This paper examines and analytically reviews the thermal management systems proposed over the past six decades for gas turbine civil aero engines. The objective is to establish the evident system shortcomings and to identify the remaining research questions that need to be addressed to enable this important technology to be adopted by next generation of aero engines with complicated designs. Future gas turbine aero engines will be more efficient, compact and will have more electric parts. As a result, more heat will be generated by the different electrical components and avionics. Consequently, alternative methods should be used to dissipate this extra heat as the current thermal management systems are already working on their limits. For this purpose, different structures and ideas in this field are stated in terms of considering engines architecture, the improved engine efficiency, the reduced emission level and the improved fuel economy. This is followed by a historical coverage of the proposed concepts dating back to 1958. Possible thermal management systems development concepts are then classified into four distinct classes: classic, centralized, revolutionary and cost-effective; and critically reviewed from challenges and implementation considerations points of view. Based on this analysis, the potential solutions for dealing with future challenges are proposed including combination of centralized and revolutionary developments and combination of classic and cost-effective developments. The effectiveness of the proposed solutions is also discussed with a complexity-impact correlation analysis.
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Qiao, Guan, Geng Liu, Zhenghong Shi, Yawen Wang, Shangjun Ma, and Teik C. Lim. "A review of electromechanical actuators for More/All Electric aircraft systems." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 232, no. 22 (December 28, 2017): 4128–51. http://dx.doi.org/10.1177/0954406217749869.

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Conventional hydraulic actuators in aircraft systems are high maintenance and more vulnerable to high temperatures and pressures. This usually leads to high operating costs and low efficiency. With the rapid development of More/All Electric technology, power-by-wire actuators are being broadly employed to improve the maintainability, reliability, and manoeuvrability of future aircraft. This paper reviews the published application and development of the airborne linear electromechanical actuator. First, the general configuration, merits, and limitations of the gear-drive electromechanical actuator and the direct-drive electromechanical actuator are analysed. Second, the development state of the electromechanical actuator testing systems is elaborated in three aspects, namely the performance testing based on room temperature, testing in a thermal vacuum environment, and iron bird. Common problems and tendencies of the testing systems are summarized. Key technologies and research challenges are revealed in terms of fault-tolerant motor, high-thrust mechanical transmission, multidisciplinary modelling, thermal management, and thermal analysis. Finally, the trend for future electromechanical actuators in More/All Electric Aircraft applications is summarized, and future research on the airborne linear electromechanical actuators is discussed.
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Figueiras, Iara, Maria Coutinho, Frederico Afonso, and Afzal Suleman. "On the Study of Thermal-Propulsive Systems for Regional Aircraft." Aerospace 10, no. 2 (January 24, 2023): 113. http://dx.doi.org/10.3390/aerospace10020113.

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Life without mobility is inconceivable. To enable this connectivity, one must find a way to progress towards a more sustainable transportation. In the aviation industry, a comprehensive understanding of greening technologies such as electrification of the propulsion system for commercial aircraft is required. A hybrid-electric propulsion concept applied to a regional aircraft is studied in the context of the FutPrInt50 project. To this end, the hybrid-electric propulsive system components are modeled, validated, and evaluated using computational and experimental data presented in the literature. The components are then assembled to construct the three powertrains for the hybrid-electric propulsion systems (Series, Parallel and Turboelectric) and parametric studies are carried out to study the influence of various battery parameters and hybridization factor. The performance results for a simple mission profile are generated. Together with a thermal management system, multi-objective optimization studies for the different architectures are then performed, with the power hybridization factor as the design variable and minimization of total mass and emissions as objective functions.
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Dong, Yiwei, Ertai Wang, Yancheng You, Chunping Yin, and Zongpu Wu. "Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects." Energies 12, no. 2 (January 14, 2019): 240. http://dx.doi.org/10.3390/en12020240.

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Combined-cycle engine is a potential propulsion system for hypersonic aircraft. To ensure long-term, normal operation of combined-cycle engine under the harsh environment of high thermal load, it is of great significance to study the thermal protection and management of the propulsion system. In this study, the objective and development status of thermal protection and thermal management systems for the combined-cycle propulsion system were described. The latest research progresses of thermal protection, thermal barrier coating, and thermal management system of the combined-cycle propulsion system were summarized. Moreover, the problems and shortcoming in current researches were summarized. In addition, a prospect for the future development of thermal protection and management of the combined-cycle propulsion system was presented, pointing out a direction of great value and vital research significance to thermal protection and management of the combined-cycle propulsion system.
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Dissertations / Theses on the topic "Aircraft Thermal Management Systems"

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Reed, William Cody. "Comparison of Heat Exchanger Designs for Aircraft Thermal Management Systems." Thesis, Virginia Tech, 2015. http://hdl.handle.net/10919/75142.

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Thermal management has become a major concern in the design of current and future more and all electric aircraft (M/AEA). With ever increasing numbers of on-board heat sources, higher heat loads, limited and even decreasing numbers of heat sinks, integration of advanced intelligence, surveillance and reconnaissance (ISR) and directed energy weapons, requirements for survivability, the use of composite materials, etc., existing thermal management systems and their components have been pushed to the limit. To address this issue, more efficient methods of thermal management must be implemented to ensure that these new M/AEA aircraft do not overheat and prematurely abort their missions. Crucial to this effort is the need to consider advanced heat exchanger concepts, comparing their designs and performance with those of the conventional compact exchangers currently used on-board aircraft thermal management systems. As a step in this direction, the work presented in this thesis identifies two promising advanced heat exchanger concepts, namely, microchannel and phase change heat exchangers. Detailed conceptual design and performance models for these as well as for a conventional plate-fin compact heat exchanger are developed and their design and performance optimized relative to the criterion of minimum dry weight. Results for these optimizations are presented, comparisons made, conclusions drawn, and recommendations made for future research. These results and comparisons show potential performance benefits for aircraft thermal management incorporating microchannel and phase change heat exchangers.
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Tipton, Austin L. "Simulation, Experimentation, Control and Management of a Novel Fuel Thermal System." Wright State University / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=wright1578320719632833.

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Maser, Adam Charles. "Optimal allocation of thermodynamic irreversibility for the integrated design of propulsion and thermal management systems." Diss., Georgia Institute of Technology, 2012. http://hdl.handle.net/1853/45913.

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More electric aircraft systems, high power avionics, and a reduction in heat sink capacity have placed a larger emphasis on correctly satisfying aircraft thermal management requirements during conceptual design. Thermal management systems must be capable of dealing with these rising heat loads, while simultaneously meeting mission performance. Since all subsystem power and cooling requirements are ultimately traced back to the engine, the growing interactions between the propulsion and thermal management systems are becoming more significant. As a result, it is necessary to consider their integrated performance during the conceptual design of the aircraft gas turbine engine cycle to ensure that thermal requirements are met. This can be accomplished by using thermodynamic modeling and simulation to investigate the subsystem interactions while conducting the necessary design trades to establish the engine cycle. As the foundation for this research, a parsimonious, transparent thermodynamic model of propulsion and thermal management systems performance was created with a focus on capturing the physics that have the largest impact on propulsion design choices. A key aspect of this approach is the incorporation of physics-based formulations involving the concurrent usage of the first and second laws of thermodynamics to achieve a clearer view of the component-level losses. This is facilitated by the direct prediction of the exergy destruction distribution throughout the integrated system and the resulting quantification of available work losses over the time history of the mission. The characterization of the thermodynamic irreversibility distribution helps give the designer an absolute and consistent view of the tradeoffs associated with the design of the system. Consequently, this leads directly to the question of the optimal allocation of irreversibility across each of the components. An irreversibility allocation approach based on the economic concept of resource allocation is demonstrated for a canonical propulsion and thermal management systems architecture. By posing the problem in economic terms, exergy destruction is treated as a true common currency to barter for improved efficiency, cost, and performance. This then enables the propulsion systems designer to better fulfill system-level requirements and to create a system more robust to future requirements.
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Thomas, Kevin P. "System architecture for real time power management." Thesis, University of Bristol, 1996. http://hdl.handle.net/1983/b4d196a1-d1f8-4141-b6e3-a32eb4f2073f.

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A major characteristic of aircraft evolution is the rapid growth in the electrical and electronic content of each subsequenat ircraft generation.T he dominant technology used in an aircraft electrical power distribution network to switch power and to protect the aircraft wiring from hazardous electrical faults is the electro-mechanical relay switch and the electro-thermal circuit breaker. Despite the maturity of these devices they do however suffer from a number of problems relating to reliability, accuracy, and limited operational lifetime. The design, fabrication and testing of a novel Solid State Power Controller (SSPC) is described. The design uses power MOSFET's to provide both the power switching operation of a relay, and the power interruption capability of a circuit breaker. The majority of the control functions required by this device are performed digitally by virtue of a real time program executed on an embedded microcontroller. A number of methods are derived for characterising existing I2t wire protection trip response curves. Reproduction of a true 1 2t trip response in real time using iterative computational methods is described. An examination of the semiconductor thermal characteristics was undertaken. The methods adopted for extracting the power semiconductor thermal response involved direct measurement using infrared thermal imaging techniques and simulation using a computer based modelling tool. Knowledge of the semiconductor die temperature is of vital importance in the context of the overall protection strategy. A finite difference calculation performed in real time has been demonstrated as a viable method to predict the operational temperature of the MOSFET power switching devices used in the design
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Jones, Andy. "Component-led integrative optimisation methodology for avionic thermal management." Thesis, Loughborough University, 2017. https://dspace.lboro.ac.uk/2134/24785.

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The modern military aircraft can be defined as a System of Systems (SoS); several distinct systems operating simultaneously across boundary interfaces. As the on-board subsystems have become more complex and diverse, the development process has become more isolated. When considering thermal management of distributed heat loads, the aircraft has become a collection of individually optimised components and subsystems, rather than the implementation of a single system to perform a given task. Avionic thermal management is quickly becoming a limiting factor of aircraft performance, reliability and effectiveness. The challenge of avionic thermal management is growing with the increasing complexity and power density of avionic packages. The aircraft relies on a heat rejection growth capacity to accommodate the additional through-life avionic heat loads. Growth capacity is defined as an allowable thermal loading growth designed into the system by the underutilisation of spatial and cooling supply at aircraft introduction; however, this is a limited resource and aircraft subsystem cooling capability is reaching a critical point. The depleted growth capacity coupled with increased avionic power demands has led to component thermal failure. However, due to the poor resolution of existing data acquisition, experimental facilities or thermodynamic modeling, the exact inflight-operating conditions remain relatively unknown. The knowledge gap identified in this work is the lack of definitive methodology to generate high fidelity data of in-flight thermal conditions of fast-jet subsystems and provide evidence towards effective future thermal management technologies. It is shown that, through the development of a new methodology, the knowledge gap can be reduced and as an output of this approach the unknown system behaviour can be defined. A multidisciplinary approach to the replication, analysis and optimisation of a fast-jet TMS is detailed. The development of a new Ground Test Facility (GTF) allows previously unidentified system thermal behaviour to be evaluated at component, subsystem and system level. The development of new data to characterise current thermal performance of a fast jet TMS allows recommendations of several new technologies to be implemented through a component led integrative system optimisation. This approach is to consider the TMS as a single system to achieve a single goal of component thermal management. Three technologies are implemented to optimise avionic conditions through the minimisation of bleed air consumption, improve avionic reliability through increased avionic component isothermalisation and increase growth capacity through improved avionic heat exchanger fin utilisation. These component level technologies improved system level performance. A reduction in TMS bleed air consumption from 1225kg to 510kg was found to complete a typical flight profile. A peak predicted aircraft specific fuel consumption saving of 1.23% is seen at a cruise flight condition because of this approach to avionic thermal management.
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Lammers, Zachary A. "Thermal Management of Electromechanical Actuation System for Aircraft Primary Flight Control Surfaces." University of Dayton / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1399021324.

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Allen, Christopher T. "Global Optimization of an Aircraft Thermal Management System through Use of a Genetic Algorithm." Wright State University / OhioLINK, 2008. http://rave.ohiolink.edu/etdc/view?acc_num=wright1220969610.

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Payne, Nathaniel M. "Development of a Combined Thermal Management and Power Generation System using a Multi-Mode Rankine Cycle." Wright State University / OhioLINK, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=wright1622657194320193.

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Butt, Nathaniel J. "Development and Thermal Management of a Dynamically Efficient, Transient High Energy Pulse System Model." Wright State University / OhioLINK, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=wright1527602141695356.

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Khanna, Yash. "Conceptual design and development of thermal management system for hybrid electric aircraft engine. : A study to develop a physical model and investigate the use of Mobil Jet Oil II as coolant for aircraft electrical propulsion under different scenarios and time horizons." Thesis, Mälardalens högskola, Framtidens energi, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:mdh:diva-46612.

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The ever-increasing levels of greenhouse gas emissions has led to the scientific community starting to explore the viability of electrical aircraft system, with the most prominent research and product development for hybrid electric system, which forms the transition phase from combustion to fully electric aircrafts. The primary objective of this thesis is to find solutions towards thermal management of the electrical components of a hybrid electric aircraft propulsion system, which generate a significant amount of heat while operating at heavy load conditions required to propel an aircraft. In view of these objectives a micro channel cold plate liquid cooling system, has been dynamically modelled using a combination of lumped parameter and thermal resistance methods of heat transfer analysis. The study investigates the prospects of using Mobil Jet Oil II, typically used as an aircraft lubricant as a coolant for the thermal management system. The primary components of this model are lithium ion battery, DC-AC inverter, permanent magnet motor, cross flow finned micro channel heat exchanger, centrifugal pump and ducts. The electrical components have been dimensioned according to energy storage and load requirements considering their efficiencies and gravimetric power/energy. The system has been simulated and analyzed under different scenarios considering the coolant inlet temperature, air temperature across the heat exchanger and on two-time horizons. Analysis has been done to study the dynamic trends of the component temperature and the coolant at different stages of the system. The scope of the study includes an evaluation of the added weight of the thermal management system under different time horizons and their comparison with results from a reference study. From the simulation results it can be concluded that Mobil Jet Oil II is a promising option as a coolant and therefore its use as a common fluid for gas turbine lubrication and as coolant, will benefit the aircraft as now no extra coolant reservoir is required, allowing reduction in weight carried by the aircraft.
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Books on the topic "Aircraft Thermal Management Systems"

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Ahlers, Mark F., ed. Aircraft Thermal Management: Systems Architectures. Warrendale, PA: SAE International, 2016. http://dx.doi.org/10.4271/pt-177.

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Ahlers, Mark F., ed. Aircraft Thermal Management: Integrated Energy Systems Analysis. Warrendale, PA: SAE International, 2016. http://dx.doi.org/10.4271/pt-178.

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Hoogendoorn, C. J., R. A. W. M. Henkes, and C. J. M. Lasance, eds. Thermal Management of Electronic Systems. Dordrecht: Springer Netherlands, 1994. http://dx.doi.org/10.1007/978-94-011-1082-2.

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Beyne, E., C. J. M. Lasance, and J. Berghmans, eds. Thermal Management of Electronic Systems II. Dordrecht: Springer Netherlands, 1997. http://dx.doi.org/10.1007/978-94-011-5506-9.

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Moran, Matthew E. Micro-scale avionics thermal management. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2001.

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Vehicle, Thermal Management Systems Conference (1993 Columbus Ohio). 1993 Vehicle Thermal Management Systems Conference proceedings. Warrendale, PA: SAE, 1993.

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Dinçer, ibrahim, Halil S. Hamut, and Nader Javani. Thermal Management of Electric Vehicle Battery Systems. Chichester, UK: John Wiley & Sons, Ltd, 2017. http://dx.doi.org/10.1002/9781118900239.

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Sacharny, David, and Thomas C. Henderson. Lane-Based Unmanned Aircraft Systems Traffic Management. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-030-98574-5.

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Benson, Mark. The Art of Software Thermal Management for Embedded Systems. New York, NY: Springer New York, 2014. http://dx.doi.org/10.1007/978-1-4939-0298-9.

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Patrick, Campbell. Interfacing technical document management systems within aircraft rotables maintenance. [S.l: The author], 1993.

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Book chapters on the topic "Aircraft Thermal Management Systems"

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Qian, Zhao, Pei Yang, Ge Yuxue, and Li Wan. "Analysis of Aircraft Fuel Thermal Management System Under Different Architectures." In Lecture Notes in Electrical Engineering, 841–53. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-16-7423-5_84.

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Dhir, Sanjay, and Sushil. "National Thermal Power Corporation." In Flexible Systems Management, 183–206. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-7064-9_11.

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Baum, Michael S. "Unmanned Traffic Management (“UTM”)." In Introduction to Unmanned Aircraft Systems, 439–41. 3rd ed. Third editon. | Boca Raton: CRC Press, 2021.: CRC Press, 2021. http://dx.doi.org/10.1201/9780429347498-19.

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Petrecca, Giovanni. "Thermal Fluid Distribution Systems." In Energy Conversion and Management, 125–39. Cham: Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-06560-1_8.

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Baum, Michael Scott. "Conclusions." In Unmanned Aircraft Systems Traffic Management, 137–270. Boca Raton: CRC Press, 2021. http://dx.doi.org/10.1201/9781003124689-7.

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Baum, Michael Scott. "The Future of UTM." In Unmanned Aircraft Systems Traffic Management, 125–36. Boca Raton: CRC Press, 2021. http://dx.doi.org/10.1201/9781003124689-6.

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Baum, Michael Scott. "Standards-Making for UTM." In Unmanned Aircraft Systems Traffic Management, 53–70. Boca Raton: CRC Press, 2021. http://dx.doi.org/10.1201/9781003124689-3.

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Baum, Michael Scott. "UTM Governance." In Unmanned Aircraft Systems Traffic Management, 71–108. Boca Raton: CRC Press, 2021. http://dx.doi.org/10.1201/9781003124689-4.

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Baum, Michael Scott. "Selected Initiatives and Implementations." In Unmanned Aircraft Systems Traffic Management, 109–24. Boca Raton: CRC Press, 2021. http://dx.doi.org/10.1201/9781003124689-5.

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Baum, Michael Scott. "Introduction." In Unmanned Aircraft Systems Traffic Management, 1–10. Boca Raton: CRC Press, 2021. http://dx.doi.org/10.1201/9781003124689-1.

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Conference papers on the topic "Aircraft Thermal Management Systems"

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Hudson, William A., and Mark L. Levin. "Integrated Aircraft Fuel Thermal Management." In Intersociety Conference on Environmental Systems. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1986. http://dx.doi.org/10.4271/860911.

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Hitzigrath, Richard W. "Improving Aircraft Fuel-Thermal Management." In International Conference On Environmental Systems. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1993. http://dx.doi.org/10.4271/932086.

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Dooley, Matthew, NIcholas Lui, Robb Newman, and Clarence Lui. "Aircraft Thermal Management -Heat Sink Challenge." In SAE 2014 Aerospace Systems and Technology Conference. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2014. http://dx.doi.org/10.4271/2014-01-2193.

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Russ, Benjamin, and Mark Drela. "Ram Air Heat Exchangers for Very High-Altitude Subsonic Aircraft." In Vehicle Thermal Management Systems Conference. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1993. http://dx.doi.org/10.4271/931145.

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Gambill, J. M., D. E. Wiese, H. M. Claeys, D. S. Matulich, and C. F. Weiss. "Integrated Aircraft Thermal Management and Power Generation." In International Conference On Environmental Systems. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1993. http://dx.doi.org/10.4271/932055.

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Kasitz, Joshua, and David Huitink. "Characterization of High-Density Aircraft Electronic and Thermal Management Systems." In ASME 2021 International Technical Conference and Exhibition on Packaging and Integration of Electronic and Photonic Microsystems. American Society of Mechanical Engineers, 2021. http://dx.doi.org/10.1115/ipack2021-73287.

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Abstract As aircrafts move toward electrification with the research and development of hybrid-electric powertrains, the focus has begun to shift to the reliability challenges of electronic devices subject to flight. Electronic components in aircraft applications are subject to two main sources of failure inducing stresses: the thermomechanical stresses that develop due to unequal coefficients of thermal expansion of different materials used in the components, and the stresses developing due to shocks and vibrations during flight as well as landing and takeoff. While the challenge of dealing with CTE mismatches is applicable to electronic devices in general, the ambient conditions surrounding the aircraft in flight, combined with weight and space constrains add significant logistical issues to any cooling mechanism. This paper will focus on the environmental influence on the thermal dissipation profile that will ultimately lead to CTE failures. The push toward more-electric-aircraft (MEA) increases the need to further advance the power and versatility of electronic cooling systems to adequately manage high density power modules, which until recently were not highly incorporated in aviation systems. Environmental conditions will play a large role in the design space and limitations of potential cooling solutions and will dictate the effectiveness of current thermal management systems. In arising scenarios where high-density electronics cannot be contained within a pressurized and temperature-controlled cabin, drastic pressure and temperature swings, facilitated by the external environment, will lead to an extra source of fluctuating stress on the cooling system. This is likely to be a prevalent factor in hybrid-electric and all-electric powertrains as requiring environmental controlled spaces for major components could be limited. This can easily be seen in current attempts to examine and redesign local cooling systems for electric motors in aviation. Representing just one of the major cooling requirements on an electric aircraft, motor cooling systems demonstrate the universal cooling problems limiting all aspects of the powertrains system. This paper aims to define the impact of the changing environment, through a flight profile of an aircraft, on high density electronic cooling systems by assessing the potential system stressors that significantly impact performance, efficiency, and reliability of the cooling systems. It will also utilize local cooling efforts for motors to relate the general problems to applicable design considerations that must be understood to further the performance capability of the overall propulsion system.
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Wang, Y., Z. Li, G. Zhang, H. Zhang, Y. Zhao, and X. Tong. "Energy optimization of aircraft thermal management system." In CSAA/IET International Conference on Aircraft Utility Systems (AUS 2022). Institution of Engineering and Technology, 2022. http://dx.doi.org/10.1049/icp.2022.1856.

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Wiese, Douglas E. "Thermal Management of Hypersonic Aircraft Using Noncryogenic Fuels." In International Conference On Environmental Systems. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1991. http://dx.doi.org/10.4271/911443.

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Iya, Sridhar K. "Thermal Management of Advanced Aircraft Secondary Power Systems." In Aerospace Technology Conference and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1990. http://dx.doi.org/10.4271/901959.

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Schlabe, Daniel, and Jens Lienig. "Model-Based Thermal Management Functions for Aircraft Systems." In SAE 2014 Aerospace Systems and Technology Conference. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2014. http://dx.doi.org/10.4271/2014-01-2203.

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Reports on the topic "Aircraft Thermal Management Systems"

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Bejan, Adrian. Constructal Technology for Thermal Management of Aircraft. Fort Belvoir, VA: Defense Technical Information Center, May 2010. http://dx.doi.org/10.21236/ada593178.

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Salah, M. H., T. H. Mitchell, J. R. Wagner, and D. M. Dawson. Adaptive and Robust Control for Thermal Management Systems. Fort Belvoir, VA: Defense Technical Information Center, January 2006. http://dx.doi.org/10.21236/ada462591.

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Thomas, Scott K., and Andrew J. Fleming. Thermal Management of Next-Generation Power Electronics for the More-Electric Aircraft Initiative. Fort Belvoir, VA: Defense Technical Information Center, July 2005. http://dx.doi.org/10.21236/ada452622.

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Bruder, Brittany, Alexander Renaud, Nicholas Spore, and Katherine Brodie. Evaluation of Unmanned Aircraft Systems for Flood Risk Management : Field Experiment Conspectus. Coastal and Hydraulics Laboratory (U.S.), July 2018. http://dx.doi.org/10.21079/11681/27799.

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Mohseni, Kamran. Microscale Convective Heat Transfer for Thermal Management of Compact Systems. Fort Belvoir, VA: Defense Technical Information Center, March 2012. http://dx.doi.org/10.21236/ada563595.

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Grisworld, Mary E. Spectrum Management: Key to the Future of Unmanned Aircraft Systems? (Maxwell Paper, Number 44). Fort Belvoir, VA: Defense Technical Information Center, May 2008. http://dx.doi.org/10.21236/ada490208.

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Renaud, Alexander, Michael Forte, Nicholas Spore, Brittany Bruder, Katherine Brodie, Jessamin Straub, and Jeffrey Ruby. Evaluation of Unmanned Aircraft Systems for flood risk management : results of terrain and structure assessments. Engineer Research and Development Center (U.S.), August 2022. http://dx.doi.org/10.21079/11681/45000.

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The 2017 Duck Unmanned Aircraft Systems (UAS) Pilot Experiment was conducted by the US Army Engineer Research and Development Center (ERDC), Coastal and Hydraulics Laboratory, Field Research Facility (FRF), to assess the potential for different UAS to support US Army Corps of Engineers coastal and flood risk management. By involving participants from multiple ERDC laboratories, federal agencies, academia, and private industry, the work unit leads were able to leverage assets, resources, and expertise to assess data from multiple UAS. This report compares datasets from several UAS to assess their potential to survey and observe coastal terrain and structures. In this report, UAS data product accuracy was analyzed within the context of three potential applications: (1) general coastal terrain survey accuracy across the FRF property; (2) small-scale feature detection and observation within the experiment infrastructure area; and (3) accuracy for surveying coastal foredunes. The report concludes by presenting tradeoffs between UAS accuracy and the cost to operate to aid in selection of the best UAS for a particular task. While the technology and exact UAS models vary through time, the lessons learned from this study illustrate that UAS are available at a variety of costs to satisfy varying coastal management data needs.
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Mattick, A. T., and A. Hertsberg. Radiative Energy Transfer and Thermal Management in Advanced Space Power and Propulsion Systems. Fort Belvoir, VA: Defense Technical Information Center, March 1986. http://dx.doi.org/10.21236/ada170838.

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Bass, Samuel D. The Challenges of Information Management in the Networked Battlespace: Unmanned Aircraft Systems, Raw Data and the Warfighter. Fort Belvoir, VA: Defense Technical Information Center, June 2006. http://dx.doi.org/10.21236/ada453983.

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Goff, F. Caldera processes and magma-hydrothermal systems continental scientific drilling program: thermal regimes, Valles caldera research, scientific and management plan. Edited by D. L. Nielson. Office of Scientific and Technical Information (OSTI), May 1986. http://dx.doi.org/10.2172/5467724.

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