Journal articles on the topic 'Aircraft Thermal Management Systems'
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1
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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Sibilli, Thierry, Capucine Senne, Hugo Jouan, Askin T. Isikveren, and Sabrina Ayat. "Synergistic hybrid-electric liquid natural gas drone: S.H.I.E.L.D." Aircraft Engineering and Aerospace Technology 92, no. 5 (February 27, 2020): 757–68. http://dx.doi.org/10.1108/aeat-10-2019-0211.
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Purpose With the objective to assess potentially performant hybrid-electric architectures, this paper aims to present an aircraft performance level evaluation, in terms of range and payload, of the synergies between a hybrid-electric energy system configuration and a cryogenic fuel system. Design/methodology/approach An unmanned aerial vehicle (UAV) is modeled using an aircraft performance tool, modified to take into account the hybrid nature of the system. The fuel and thermal management systems are modeled looking to maximize the synergistic effects. The electrical system is defined in series with the thermal engine and the performance, in terms of weight and efficiency, are tracked as a function of the cooling temperature. Findings The results show up to a 46 per cent increase in range and up to 7 per cent gain on a payload with a reference hybrid-electric aircraft that uses conventional drop-in JP-8 fuel. The configuration that privileges a reduction in mass of the electric motors by taking advantage of the cryogenic coolant temperature shows the highest benefits. A sensitivity study is also presented showing the dependency on the modeling capabilities. Practical implications The synergistic combination of a cryogenic fuel and the additional heat sources of a hybrid-electric system with a tendency to higher electric component efficiency or reduced weight results in a considerable performance increase in terms of both range and payload. Originality/value The potential synergies between a cryogenic fuel and the electrical system of a hybrid-electric aircraft seem clear; however, at the present, no detailed performance evaluation at aircraft level that includes the fuel, thermal management and electric systems, has been published.
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Moran, Christopher J., Valentijn Hoff, Russell A. Parsons, Lloyd P. Queen, and Carl A. Seielstad. "Mapping Fine-Scale Crown Scorch in 3D with Remotely Piloted Aircraft Systems." Fire 5, no. 3 (April 29, 2022): 59. http://dx.doi.org/10.3390/fire5030059.
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Remotely piloted aircraft systems (RPAS) are providing fresh perspectives for the remote sensing of fire. One opportunity is mapping tree crown scorch following fires, which can support science and management. This proof-of-concept shows that crown scorch is distinguishable from uninjured canopy in point clouds derived from low-cost RGB and calibrated RGB-NIR cameras at fine resolutions (centimeter level). The Normalized Difference Vegetation Index (NDVI) provided the most discriminatory spectral data, but a low-cost RGB camera provided useful data as well. Scorch heights from the point cloud closely matched field measurements with a mean absolute error of 0.52 m (n = 29). Voxelization of the point cloud, using a simple threshold NDVI classification as an example, provides a suitable dataset worthy of application and further research. Field-measured scorch heights also showed a relationship to RPAS-thermal-camera-derived fire radiative energy density (FRED) estimates with a Spearman rank correlation of 0.43, but there are many issues still to resolve before robust inference is possible. Mapping fine-scale scorch in 3D with RPAS and SfM photogrammetry is a viable, low-cost option that can support related science and management.
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Fielding, J. P., and M. A. F. Vaziry-Z. "Avionics cooling-rate trade-off modelling for ultra-high capacity aircraft." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 211, no. 6 (June 1, 1997): 403–12. http://dx.doi.org/10.1243/0954410971532767.
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A computer aided conceptual aircraft design methodology (CACAD) has been developed to size ultra-high capacity jet transport aircraft. Modules were also developed for predicting maintenance costs of each airframe and avionics system and these were incorporated into CACAD. A methodology was developed to enhance the reliability of avionics systems, based on experimentally-proven engineering design solutions. A number of avionics cooling techniques were investigated, and reliability and maintainability models of thermal management were developed and linked to an avionics maintenance cost module. Further models were produced to investigate the impact of proposed changes on the environmental control systems, engine-provided bleeds and power off-takes. It was found that increased flowrates above the normally recommended values for the avionics bay, and to the flight deck instruments, may increase the reliability of the avionics systems, and also increase aircraft dispatch reliability. They may not, however, greatly improve direct operating costs (DOC), due to significant fuel penalties. A separate refrigeration unit was investigated and found to be a feasible cost-effective measure, even allowing for increased engine fuel consumption caused by the effect of the engine power off-take required to drive the refrigeration unit.
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Chen, Mingguang, Junzhu Li, Bo Tian, Yas Mohammed Al-Hadeethi, Bassim Arkook, Xiaojuan Tian, and Xixiang Zhang. "Predicting Interfacial Thermal Resistance by Ensemble Learning." Computation 9, no. 8 (August 2, 2021): 87. http://dx.doi.org/10.3390/computation9080087.
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Interfacial thermal resistance (ITR) plays a critical role in the thermal properties of a variety of material systems. Accurate and reliable ITR prediction is vital in the structure design and thermal management of nanodevices, aircraft, buildings, etc. However, because ITR is affected by dozens of factors, traditional models have difficulty predicting it. To address this high-dimensional problem, we employ machine learning and deep learning algorithms in this work. First, exploratory data analysis and data visualization were performed on the raw data to obtain a comprehensive picture of the objects. Second, XGBoost was chosen to demonstrate the significance of various descriptors in ITR prediction. Following that, the top 20 descriptors with the highest importance scores were chosen except for fdensity, fmass, and smass, to build concise models based on XGBoost, Kernel Ridge Regression, and deep neural network algorithms. Finally, ensemble learning was used to combine all three models and predict high melting points, high ITR material systems for spacecraft, automotive, building insulation, etc. The predicted ITR of the Pb/diamond high melting point material system was consistent with the experimental value reported in the literature, while the other predicted material systems provide valuable guidelines for experimentalists and engineers searching for high melting point, high ITR material systems.
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A, Rong, Liping Pang, Xinying Jiang, Bin Qi, and Yong Shi. "Analysis and comparison of potential power and thermal management systems for high-speed aircraft with an optimization method." Energy and Built Environment 2, no. 1 (January 2021): 13–20. http://dx.doi.org/10.1016/j.enbenv.2020.06.006.
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Lykins, R., M. Ramalingam, B. Donovan, E. Durkin, and J. Beam. "SECONDARY POWER SYSTEM EVALUATIONS FOR ADVANCED AIRCRAFT." Transactions of the Canadian Society for Mechanical Engineering 23, no. 1B (May 1999): 117–27. http://dx.doi.org/10.1139/tcsme-1999-0008.
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A computerized analytical program is being developed to help investigate the impact of power system requirements on aircraft performance. The program has an user interface that operates in MS-EXCEL, linking several subsystems analysis programs for execution and data transfer in the power systems analysis. The program presently includes an encoded propulsion engine cycle code, which allows the inspection of power extraction effects on engine performance. To validate the results of the encoded engine program, a study was conducted to investigate the separate effects of shaft power extraction and pneumatic bleed. The selected engine cycle was that for a standard tactical fighter, with a flight condition of varied altitude (sea level to 40,000 ft) and constant Mach Number (0.9). As expected the resultant data showed that the engine performance was more sensitive to pneumatic bleed than to shaft power extraction. The paper’s efficiency comparisons between shaft power and bleed air power helps indicate the higher efficiency for the power system of a more-electric type aircraft. Present efforts on the analytical interface are to incorporate a fuel thermal management analysis capability.
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Bhatti, Sandeep, Derek M. Heeren, Susan A. O’Shaughnessy, Steven R. Evett, Mitchell S. Maguire, Suresh P. Kashyap, and Christopher M. U. Neale. "Comparison of Stationary and Mobile Canopy Sensing Systems for Maize and Soybean in Nebraska, USA." Applied Engineering in Agriculture 38, no. 2 (2022): 331–42. http://dx.doi.org/10.13031/aea.14945.
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HighlightsMultispectral sensors mounted on the center pivot lateral were able to capture differences between rainfed and irrigated crop.Canopy temperature was strongly associated among stationary and pivot-mounted sensors with coefficient of determination ranging between 0.88 and 0.99.A cooling effect of about 2°C was observed in canopy temperature data collected from pivot mounted sensors for irrigated soybean crop.Abstract. Accurate knowledge of plant and field characteristics is crucial for irrigation management. Irrigation can potentially be better managed by utilizing data collected from various sensors installed on different platforms. The accuracy and repeatability of each data source are important considerations when selecting a sensing system suitable for irrigation management. The objective of this study was to compare data from multispectral (red and near-infrared bands) and thermal (long wave thermal infrared band) sensors mounted on different platforms to investigate their comparative usability and accuracy. The different sensor platforms included stationary posts fixed on the ground, the lateral of a center pivot irrigation system, unmanned aircraft systems (UAS), and Planet (PlanetScope multispectral imager, Planet Labs, Inc., San Francisco, Calif.) satellites. The surface reflectance data from multispectral (MS) sensors were used to compute the Normalized Difference Vegetation Index (NDVI) and Soil Adjusted Vegetation Index (SAVI). The experimental plots were managed with rainfed and irrigated treatments. Irrigation was applied according to a spatial evapotranspiration model informed with Planet satellite imagery. The NDVI and SAVI curves computed from the different sensing systems exhibited similar patterns and were able to capture differences between the rainfed and irrigated treatments when the crops were approaching senescence. Strong correlations were observed for canopy temperature measurements between the stationary and pivot-mounted infrared thermometer (IRT) sensors (p-value of less than 0.01 for the correlations) when canopy were scanned with no irrigation application (dry scans). The best correlation was obtained for the irrigated maize, which yielded r2 of 0.99, RMSE of 0.4°C, and MAE of 0.3°C. The correlation for the canopy temperature data collected during dry scan between UAS and pivot-mounted thermal sensors was weak with r2 = 0.26 to 0.28, larger RMSE values of 3.7°C and MAE values of 3.4°C. Secondary analysis between thermal data from stationary and pivot-mounted IRTs collected during wet scans (during an irrigation event) demonstrated reduced canopy temperature from pivot-mounted IRTs by approximately 2°C for irrigated soybean due to wetting of the canopy by the irrigation. Understanding the performance of these sensor systems is valuable in configuring practical design and operational considerations when using sensor feedback for irrigation management. Keywords: Center pivots, Irrigation, Multispectral, Remote sensing, Thermal, Unmanned aircraft systems.
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Seitz, Arne, Markus Nickl, Anne Stroh, and Patrick C. Vratny. "Conceptual study of a mechanically integrated parallel hybrid electric turbofan." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 14 (July 27, 2018): 2688–712. http://dx.doi.org/10.1177/0954410018790141.
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In the paper, options for mechanically integrated parallel hybrid propulsion are evaluated, and a conceptual sizing and performance study of a mechanically integrated parallel hybrid electric turbofan engine for a short-range aircraft application is presented and discussed. Through a methodical down-selection procedure, a most promising power plant system architectural concept is identified from an initial cloud of concept candidates. The design of the preferred configuration is conceptualized including initial performance analyses, both at the isolated power plant as well as at the integrated aircraft level. Beside the basic power plant definition, the multidisciplinary concept elaboration includes solutions proposed for the electric systems architectural layout, the major electrical components involved as well as important airframe integration aspects. The components of the electrical power management and distribution system are sized, and efficiency and weights are evaluated under special consideration of thermal management requirements. In result, a best and balanced degree of power hybridization is determined for the studied mechanically integrated parallel hybrid power plants taking account of electric system design and weight impacts as well as power plant operational robustness in case of electric system failure. The overall system assessment includes the evaluation of fuel reduction potentials through a parametric aircraft sizing study including the derivation of key technological requirements for onboard electrical energy storage. In the paper, essential design and sizing strategies for mechanically integrated parallel hybrid aero propulsion systems are derived, and a brief characterization of the associated key technological challenges is provided.
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Dyko, M. P., and K. Vafai. "Fundamental Issues and Recent Advancements in Analysis of Aircraft Brake Natural Convective Cooling." Journal of Heat Transfer 120, no. 4 (November 1, 1998): 840–57. http://dx.doi.org/10.1115/1.2825903.
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A heightened awareness of the importance of natural convective cooling as a driving factor in design and thermal management of aircraft braking systems has emerged in recent years. As a result, increased attention is being devoted to understanding the buoyancy-driven flow and heat transfer occurring within the complex air passageways formed by the wheel and brake components, including the interaction of the internal and external flow fields. Through application of contemporary computational methods in conjunction with thorough experimentation, robust numerical simulations of these three-dimensional processes have been developed and validated. This has provided insight into the fundamental physical mechanisms underlying the flow and yielded the tools necessary for efficient optimization of the cooling process to improve overall thermal performance. In the present work, a brief overview of aircraft brake thermal considerations and formulation of the convection cooling problem are provided. This is followed by a review of studies of natural convection within closed and open-ended annuli and the closely related investigation of inboard and outboard subdomains of the braking system. Relevant studies of natural convection in open rectangular cavities are also discussed. Both experimental and numerical results obtained to date are addressed, with emphasis given to the characteristics of the flow field and the effects of changes in geometric parameters on flow and heat transfer. Findings of a concurrent numerical and experimental investigation of natural convection within the wheel and brake assembly are presented. These results provide, for the first time, a description of the three-dimensional aircraft braking system cooling flow field.
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Baxter, Glenn, Panarat Srisaeng, and Graham Wild. "An Assessment of Airport Sustainability: Part 3—Water Management at Copenhagen Airport." Resources 8, no. 3 (July 29, 2019): 135. http://dx.doi.org/10.3390/resources8030135.
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Sustainable water management is critical for airports as they consume substantial volumes of water to maintain their infrastructure and operations. Airports also generate large volumes of surface and waste waters. The aim of this study was to examine Copenhagen Airport’s sustainable water management strategies and systems from 2006 to 2016. The study used a longitudinal qualitative research design. The annual water consumption at Copenhagen Airport has risen from 2006 to 2016 in line with the increased passenger volumes and aircraft movements. Drinking water is sourced from the Taarnby and Dragør municipal water works. Non-potable water is used wherever possible and is sourced from a local remedial drilling. Copenhagen Airport uses two separate sewer systems for handling surface and wastewater. These waters are not discharged to same system due to their different nature. To mitigate environmental risks and impacts on soil, water, and local communities; the quality of drinking, ground, and surface water are regularly monitored. The airport has implemented various water saving initiatives, such as, an aquifer thermal energy system, to reduce water consumption. The strategies, systems, and the water-saving initiatives have successfully underpinned Copenhagen Airport’s sustainable water management.
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Arnold, M., C. A. Featherston, Matthew R. Pearson, J. Lees, and Aleksander Kural. "Energy Management Systems for Energy Harvesting in Structural Health Monitoring Applications." Key Engineering Materials 518 (July 2012): 137–53. http://dx.doi.org/10.4028/www.scientific.net/kem.518.137.
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Autonomous structural health monitoring systems with independent power sources and wireless sensor nodes are increasingly seen as the best solution for monitoring a diverse range of machines and structures including pumps, bridges and aircraft. Powering these systems using harvested energy from ambient sources provides an attractive alternative to the use of batteries which may be either inaccessible for routine maintenance or unsuitable (for example in aerospace applications). A number of techniques are currently being considered including harvesting energy from vibration and thermal gradients. Harvesting energy can however lead to a highly variable power supply in opposition to the requirements of a wireless sensor node which requires continuous standby power with an additional capacity for power peaks during transmission of data. A power management system with embedded energy storage is therefore necessary in order to match supply and demand. Due to the low levels of power harvested in a number of applications, an important factor in the design of such a system is its efficiency to ensure sufficient power reaches the sensor node. Based on the requirements for a simple power management system for thermoelectric power harvesting consisting of a rectifier, a DC/DC convertors and a battery, this paper first examines the possibilities in terms of basic components with a number of commercially available units tested and characterised. Potential designs for a management system incorporating these components are then discussed and a blueprint for an optimal system is suggested.
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Thorp, Kelly R., Sebastian Calleja, Duke Pauli, Alison L. Thompson, and Diaa Eldin Elshikha. "Agronomic Outcomes of Precision Irrigation Management Technologies with Varying Complexity." Journal of the ASABE 65, no. 1 (2022): 135–50. http://dx.doi.org/10.13031/ja.14950.
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HighlightsCotton yield and water productivity were measured for different precision irrigation management solutions.Agronomic improvements from site-specific irrigation based on spatial FAO-56 crop coefficient data were minor.Thermal remote sensing data from unoccupied aircraft systems were able to identify crop water limitations.Integrated sensing and modeling tools that can achieve intended agronomic outcomes should be prioritized.Abstract. Diverse technologies, methodologies, and data sources have been proposed to inform precision irrigation management decisions, and the technological complexity of different solutions is highly variable. Additional field studies are needed to identify solutions that achieve intended agronomic outcomes in simple and cost-effective ways. The objective of this study was to compare cotton yield and water productivity outcomes resulting from different solutions for scheduling and conducting precision irrigation management. A cotton field study was conducted at Maricopa, Arizona, in 2019 and 2020 that evaluated the outcomes of four management solutions with varying technological complexity: (1) a stand-alone evapotranspiration-based soil water balance model with field-average soil parameters (MDL), (2) using site-specific soil data to spatialize the modeling framework (SOL), (3) driving the model with spatial crop coefficients estimated from an unoccupied aircraft system (UAS), and (4) using commercial variable-rate irrigation technology for site-specific irrigation applications (VRI). Soil water content data and thermal UAS data were also collected but used only in post hoc data analysis. Applied irrigation, cotton fiber yield, and water productivity were statistically identical for MDL and SOL. As compared to MDL, the UAS crop coefficient approach significantly reduced applied irrigation by 7% and 14% but also reduced yield by 5% and 26% in 2019 and 2020, respectively (p = 0.05). In 2019 only, the VRI approach maintained yield while significantly reducing applied irrigation by 8% compared to MDL, and water productivity was significantly increased from 0.200 to 0.211 kg m-3 when one outlier datum was removed (p = 0.05). Post hoc data analysis showed that crop water stress information, particularly from UAS thermal imaging data, would likely benefit the irrigation scheduling protocol. Efforts to develop integrated sensing and modeling tools that can guide precision irrigation management to achieve intended agronomic outcomes should be prioritized and will be relevant whether irrigation applications are site-specific or uniform. Keywords: Cotton, Crop coefficient, Drone, FAO-56, Irrigation scheduling, Remote sensing, Site-specific irrigation, Soil mapping, Unoccupied aircraft system, Variable-rate irrigation, Water stress.
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Tamburrano, P., L. Romagnuolo, E. Frosina, G. Caramia, E. Distaso, F. Sciatti, A. Senatore, P. De Palma, and R. Amirante. "Fuels systems and components for future airliners fuelled with liquid hydrogen." Journal of Physics: Conference Series 2385, no. 1 (December 1, 2022): 012041. http://dx.doi.org/10.1088/1742-6596/2385/1/012041.
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Abstract The prospect of using liquid hydrogen as fuel in airliners in place of kerosene-based fuels is regarded as one of the most effective solutions to achieve low-carbon air transport in the near future, which is a target defined by the EU to reduce global warming caused by CO2 emissions. The development of hydrogen-fuelled airliners must face issues related to the production and supply chain of green hydrogen, to the fuel systems for hydrogen handling aboard aircraft, and to the combustion of hydrogen. This paper is concerned with the literature study of fuel systems for hydrogen, keeping in mind that the other two aspects are currently being studied extensively in industries and universities. This paper analyses difficulties, proposals and advances related to the four main parts composing future fuel systems for hydrogen-fuelled airliners: fuel storage, fuel delivery, thermal management and fuel metering.
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Azzam, H. "Mathematical networks for thermal transient and non-transient progressive fatigue of engine components." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 212, no. 2 (February 1, 1998): 125–36. http://dx.doi.org/10.1243/0954410981532199.
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Engine components can experience varying centrifugal loads, gas loads, oxidation, micro- structure transformation at high temperatures and stresses induced by temperature gradients. The life consumption of hot engine components depends not only on these factors but also on the time spent at constant-amplitude loads. The damage mechanism of engine components is therefore complex and requires formidable models. These models are not suitable for fatigue management or on-board systems because of their high computational costs. There is a need for efficient simulations that can accurately portray this complex damage mechanism and, at the same time, can be embedded in fatigue management and on-board systems. Mathematical networks were developed to fulfil this need and successfully synthesized the fatigue damage of aircraft structural components from flight parameters. In this paper, the feasibility of training the mathematical networks to synthesize fatigue of engine components is demonstrated. The mathematical attributes of the networks were based on information supplied by Rolls-Royce. The networks’ training mechanism was targeted at the minimization of errors in synthesized accumulative damage values. The mathematical networks synthesized the accumulative fatigue damage of three engine components successfully. One component was subject to non-thermal transient stresses and two components were subject to thermal transient stresses.
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Kalarikovilagam Srinivasan and Bertram. "Preliminary Design and System Considerations for an Active Hybrid Laminar Flow Control System." Aerospace 6, no. 10 (October 1, 2019): 109. http://dx.doi.org/10.3390/aerospace6100109.
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Hybrid laminar flow control or HLFC design is a complex and multi-disciplinary process, which demands a thorough understanding of all aspects from a global systems viewpoint. The objective of the paper is to present a preliminary design of important components of an HLFC system that helps in quick assessment of conceptual system architectures. This is important to evaluate feasibility, system performance, and overall aircraft benefits at early stages of system development. This paper also discusses the various important system requirements and issues concerning the design of active HLFC systems, and the interfaces between various disciplines are presented. It can be emphasized from the study that the future compressor design for the HLFC system should consider the thermal management aspects and additional mass flow requirements from the aerodynamics-structure design optimization and also from water drain system solutions. A method to calculate the accumulated water content inside the plenum chambers is presented, and the effect of a drain hole on the power consumption is studied. A low order thermal management study of the HLFC compressor motor shows a high temperature rise in the windings for very high speed motors for long duration operation and calls for effective cooling solutions.
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Galvao, J., P. Faria, A. Mateus, T. Pereira, and S. Fernandes. "Heatsinks to Cool Batteries for Unmanned Aerial Vehicles." Renewable Energy and Power Quality Journal 19 (September 2021): 327–32. http://dx.doi.org/10.24084/repqj19.287.
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This study aims to develop several different models of heatsinks, designed to cool a vertical take-off and landing unmanned aerial vehicle (UAV) battery, through topology optimization, aimed at being manufactured through selective laser melting (SLM) technology. A battery’s temperature must be properly managed for a safe and efficient operation. The methodology developed was with the support of software to carry out several simulations which, starting from several scenarios and restrictions imposed by the small space available to accommodate these small batteries in this type of aircraft. The conception resulted in several battery thermal management systems (BTMS) models, with different applications and efficiency degrees. A relevant aspect is the topology optimization being coupled to computational thermal analysis to reduce the mass of the heatsink whilst ensuring a maximum battery temperature threshold. Together with the use of topology optimization, the SLM process was selected to manufacture the heat sinks, under conditions of geometric freedom, using several high thermal conductivity metal alloys, such as, aluminium and copper to obtain the designed models.
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Mazur, Anna Maria, and Roman Domanski. "Hybrid energy systems in unmanned aerial vehicles." Aircraft Engineering and Aerospace Technology 91, no. 5 (May 13, 2019): 736–46. http://dx.doi.org/10.1108/aeat-08-2018-0218.
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Purpose The presented research is carried out in reaction to the soaring costs of fuel and tight control over environmental issues such as carbon dioxide emissions and noise. The purpose of this paper is to study the feasibility of applying the environmental-friendly energy source in an unmanned aerial vehicles (UAVs) propulsion system. Design/methodology/approach Currently, the majority of UAVs are still powered by conventional combustion engines. An electric propulsion system is most commonly found in civilian micro and mini UAVs. The UAV classification is reviewed in this study. This paper focuses mainly on application of electric propulsion systems in UAVs. Investigated hybrid energy systems consist of fuel cells, Li-ion batteries, super-capacitors and photovoltaic (PV) modules. Current applications of fuel cell systems in UAVs are also presented. Findings The conducted research shows that hybridization allows for better energy management and operation of every energy source onboard the UAV within its limits. The hybrid energy system design should be created to maximize system efficiency without compromising the performance of the aircraft. Practical implications The presented study highlights the reduction of the energy consumption, necessary to perform the mission and maximizing of the endurance with simultaneous decrease in emissions and noise level. Originality/value The conducted research studies the feasibility of implementing the environmental-friendly hybrid electric propulsion systems in UAVs that offers high efficiency, reliability, controllability, lack of thermal and noise signature, thus, providing quiet and clean drive with low vibration levels. This paper highlights the main challenges and current research on fuel cell in aviation and draws attention to fuel cell – electric system modeling, hybridization and energy management.
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Blankson, I. M. "Air-Breathing Hypersonic Cruise: Prospects for Mach 4–7 Waverider Aircraft." Journal of Engineering for Gas Turbines and Power 116, no. 1 (January 1, 1994): 104–15. http://dx.doi.org/10.1115/1.2906779.
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There is currently a renewal of world-wide interest in hypersonic flight. Vehicle concepts being considered range from cruise missiles to SSTO and TSTO vehicles. The new characteristics of these vehicles are that they will be powered by air-breathing engines and have long residence times in the air-breathing corridor. In the Mach 4–7 regime, waverider aircraft are being considered as candidates for both long-range and short-range cruise missions, as hypersonic missiles, and as high-L/D highly maneuverable vehicles. This paper will discuss the potential for near-term and far-term application of air-breathing engines to the above-mentioned waverider vehicle concepts and missions. In particular, the cruise mission is discussed in detail and attempts are made to compare and contrast it with the accelerator mission. Past criticisms levied against waveriders alleging low volumetric efficiency, lack of engine/airframe integration studies, poor off-design performance, poor take-off and landing capability, have been shown by ongoing research to be unfounded. A discussion is presented of some of the technical challenges and ongoing research aimed at realizing such vehicles: from turboramjet and scramjet technology development, propulsion-airframe integration effects on vehicle performance, aeroservothermoelastic systems analysis, hypersonic stability and control with aeroservothermoelastic and propulsion effects, etc. A unique and very strong aspect of hypersonic vehicle design is the integration and interaction of the propulsion system, aerodynamics, aerodynamic heating, stability and control, and materials and structures. This first-order multidisciplinary situation demands the ability to integrate highly coupled and interacting elements in a fundamental and optimal fashion to achieve the desired performance. Some crucial technology needs are found in propulsion-airframe integration and its role in configuration definition, hypersonic boundary-layer transition and its impact on vehicle gross-weight and mission success, scramjet combustor mixing length and its impact on engine weight and, CFD (turbulence modeling, transition modeling, etc) as a principal tool for the design of hypersonic vehicles. Key technology implications in thermal management, structures, materials, and flight control systems will also be briefly discussed. It is concluded that most of the technology requirements in the Mach 4–7 regime are relatively conventional, making cited applications near-term, yet offering very significant advancements in aircraft technology.
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Shamaoma, Hastings, Paxie W. Chirwa, Abel Ramoelo, Andrew T. Hudak, and Stephen Syampungani. "The Application of UASs in Forest Management and Monitoring: Challenges and Opportunities for Use in the Miombo Woodland." Forests 13, no. 11 (October 31, 2022): 1812. http://dx.doi.org/10.3390/f13111812.
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The Miombo woodland is the most extensive tropical woodland in south-central Africa. However, field sample plot data on forest cover changes, species distribution and carbon stocks in the Miombo ecoregion are inadequate for effective forest management. Owing to logistical challenges that come with field-based inventory methods, remote sensing plays an important role in supplementing field methods to fill in data gaps. Traditional satellite and manned aircraft remote sensing platforms have their own advantages and limitations. The advent of unmanned aerial systems (UASs) has made it possible to acquire forest data at unprecedented spatial and temporal scales. UASs are adaptable to various forest applications in terms of providing flexibility in data acquisition with different sensors (RGB, multispectral, hyperspectral, thermal and light detection and ranging (lidar)) at a convenient time. To highlight possible applications in the Miombo woodlands, we first provide an overview of the Miombo woodlands and recent progress in remote sensing with small UASs. An overview of some potential forest applications was undertaken to identify key prospects and challenges for UAS applications in the Miombo region, which will provide expertise and guidance upon which future applications in the Miombo woodlands should be based. While much of the potential of using UASs for forest data acquisition in the Miombo woodlands remains to be realized, it is likely that the next few years will see such systems being used to provide data for an ever-increasing range of forest applications.
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Altan, M. O., and G. Kemper. "INNOVATIV AIRBORNE SENSORS FOR DISASTER MANAGEMENT." ISPRS - International Archives of the Photogrammetry, Remote Sensing and Spatial Information Sciences XLI-B8 (June 22, 2016): 11–16. http://dx.doi.org/10.5194/isprs-archives-xli-b8-11-2016.
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Modern Disaster Management Systems are based on 3 columns, crisis preparedness, early warning and the final crisis management. In all parts, special data are needed in order to analyze existing structures, assist in the early warning system and in the updating after a disaster happens to assist the crises management organizations. How can new and innovative sensors assist in these tasks? <br><br> Aerial images have been frequently used in the past for generating spatial data, however in urban structures not all information can be extracted easily. Modern Oblique camera systems already assist in the evaluation of building structures to define rescue paths, analyze building structures and give also information of the stability of the urban fabric. For this application there is no need of a high geometric accurate sensor, also SLC Camera based Oblique Camera system as the OI X5, which uses Nikon Cameras, do a proper job. Such a camera also delivers worth full information after a Disaster happens to validate the degree of deformation in order to estimate stability and usability for the population. <br><br> Thermal data in combination with RGB give further information of the building structure, damages and potential water intrusion. Under development is an oblique thermal sensor with 9 heads which enables nadir and oblique thermal data acquisition. Beside the application for searching people, thermal anomalies can be created out of humidity in constructions (transpiration effects), damaged power lines, burning gas tubes and many other dangerous facts. <br><br> A big task is in the data analysis which should be made automatically and fast. This requires a good initial orientation and a proper relative adjustment of the single sensors. Like that, many modern software tools enable a rapid data extraction. Automated analysis of the data before and after a disaster can highlight areas of significant changes. Detecting anomalies are the way to get the focus on the prior area. <br><br> Also Lidar supports Disaster management by analyzing changes in the DSM before and after the “event”. Advantage of Lidar is that beside rain and clouds, no other weather conditions limit their use. As an active sensor, missions in the nighttime are possible. <br><br> The new mid-format cameras that make use CMOS sensors (e.g. Phase One IXU1000) can capture data also under poor and difficult light conditions and might will be the first choice for remotely sensed data acquisition in aircrafts and UAVs. <br><br> UAVs will surely be more and more part of the disaster management on the detailed level. Today equipped with video live cams using RGB and Thermal IR, they assist in looking inside buildings and behind. Thus, they can continue with the aerial survey where airborne anomalies have been detected.
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Altan, M. O., and G. Kemper. "INNOVATIV AIRBORNE SENSORS FOR DISASTER MANAGEMENT." ISPRS - International Archives of the Photogrammetry, Remote Sensing and Spatial Information Sciences XLI-B8 (June 22, 2016): 11–16. http://dx.doi.org/10.5194/isprsarchives-xli-b8-11-2016.
Full textAbstract:
Modern Disaster Management Systems are based on 3 columns, crisis preparedness, early warning and the final crisis management. In all parts, special data are needed in order to analyze existing structures, assist in the early warning system and in the updating after a disaster happens to assist the crises management organizations. How can new and innovative sensors assist in these tasks? <br><br> Aerial images have been frequently used in the past for generating spatial data, however in urban structures not all information can be extracted easily. Modern Oblique camera systems already assist in the evaluation of building structures to define rescue paths, analyze building structures and give also information of the stability of the urban fabric. For this application there is no need of a high geometric accurate sensor, also SLC Camera based Oblique Camera system as the OI X5, which uses Nikon Cameras, do a proper job. Such a camera also delivers worth full information after a Disaster happens to validate the degree of deformation in order to estimate stability and usability for the population. <br><br> Thermal data in combination with RGB give further information of the building structure, damages and potential water intrusion. Under development is an oblique thermal sensor with 9 heads which enables nadir and oblique thermal data acquisition. Beside the application for searching people, thermal anomalies can be created out of humidity in constructions (transpiration effects), damaged power lines, burning gas tubes and many other dangerous facts. <br><br> A big task is in the data analysis which should be made automatically and fast. This requires a good initial orientation and a proper relative adjustment of the single sensors. Like that, many modern software tools enable a rapid data extraction. Automated analysis of the data before and after a disaster can highlight areas of significant changes. Detecting anomalies are the way to get the focus on the prior area. <br><br> Also Lidar supports Disaster management by analyzing changes in the DSM before and after the “event”. Advantage of Lidar is that beside rain and clouds, no other weather conditions limit their use. As an active sensor, missions in the nighttime are possible. <br><br> The new mid-format cameras that make use CMOS sensors (e.g. Phase One IXU1000) can capture data also under poor and difficult light conditions and might will be the first choice for remotely sensed data acquisition in aircrafts and UAVs. <br><br> UAVs will surely be more and more part of the disaster management on the detailed level. Today equipped with video live cams using RGB and Thermal IR, they assist in looking inside buildings and behind. Thus, they can continue with the aerial survey where airborne anomalies have been detected.
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Howell, Lachlan G., John Clulow, Neil R. Jordan, Chad T. Beranek, Shelby A. Ryan, Adam Roff, and Ryan R. Witt. "Drone thermal imaging technology provides a cost-effective tool for landscape-scale monitoring of a cryptic forest-dwelling species across all population densities." Wildlife Research 49, no. 1 (December 20, 2021): 66–78. http://dx.doi.org/10.1071/wr21034.
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Abstract Context Drones, or remotely piloted aircraft systems, equipped with thermal imaging technology (RPAS thermal imaging) have recently emerged as a powerful monitoring tool for koala populations. Before wide uptake of novel technologies by government, conservation practitioners and researchers, evidence of greater efficiency and cost-effectiveness than with other available methods is required. Aims We aimed to provide the first comprehensive analysis of the cost-effectiveness of RPAS thermal imaging for koala detection against two field-based methods, systematic spotlighting (Spotlight) and the refined diurnal radial search component of the spot-assessment technique (SAT). Methods We conducted various economic comparisons, particularly comparative cost-effectiveness of RPAS thermal imaging, Spotlight and SAT for repeat surveys of a low-density koala population. We compared methods on cost-effectiveness as well as long-term costs by using accumulating cost models. We also compared detection costs across population density using a predictive cost model. Key results Despite substantial hardware, training and licensing costs at the outset (>A$49 900), RPAS thermal imaging surveys were cost-effective, detecting the highest number of koalas per dollar spent. Modelling also suggested that RPAS thermal imaging requires the lowest survey effort to detect koalas within the range of publicly available koala population densities (~0.006–18 koalas ha−1) and would provide long-term cost reductions across longitudinal monitoring programs. RPAS thermal imaging would also require the lowest average survey effort costs at a landscape scale (A$3.84 ha−1), providing a cost-effective tool across large spatial areas. Conclusions Our analyses demonstrated drone thermal imaging technology as a cost-effective tool for conservation practitioners monitoring koala populations. Our analyses may also form the basis of decision-making tools to estimate survey effort or total program costs across any koala population density. Implications Our novel approach offers a means to perform various economic comparisons of available survey techniques and guide investment decisions towards developing standardised koala monitoring approaches. Our results may assist stakeholders and policymakers to confidently invest in RPAS thermal imaging technology and achieve optimal conservation outcomes for koala populations, with standardised data collection delivered through evidence-based and cost-effective monitoring programs.
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M, Sadashiva, M. Yunus Sheikh, Nouman Khan, Ramesh Kurbet, and T. M. Deve Gowda. "A Review on Application of Shape Memory Alloys." International Journal of Recent Technology and Engineering 9, no. 6 (March 30, 2021): 111–20. http://dx.doi.org/10.35940/ijrte.f5438.039621.
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SMA has drawn massive interest and hobby in today’s years in a great form of an extensive sort of commercial applications, due to their precise and superior properties, this concern improvement has been bearing with the useful resource of way of improvement and carried out research studies. SMA can heal its original shape at a certain temperature even under maximum loads applied and huge inelastic deformation. In this overview, we describe the primary functions of SMAs, their constitutive models, and their features. We also explained various properties that help to build a device/system. These devices help in cueing health issues such as heart treatment emptying urine so on. SMA has important in reducing the vibration of structures by increasing damping of the materials and this has effective in energy dissipating comparing with other materials. In the aerospace industry wing aircraft, rotorcraft, spacecraft, and micro-electromechanical systems are made up of SMA. In the automobile sector, fuel injectors and thermal valves are constructed with SMA materials. Current work focuses on various applications and properties of SMA, in the field of Medical, Civil structure, Automobile, and Aerospace industry.
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Бичков, С. А., О. Д. Донець, and В. Г. Читак. "ОСОБЛИВОСТІ СЕРІЙНОГО ВИРОБНИЦТВА РЕГІОНАЛЬНИХ ПАСАЖИРСЬКИХ ЛІТАКІВ АН-148 ТА АН-158." Open Information and Computer Integrated Technologies, no. 84 (July 2, 2019): 125–43. http://dx.doi.org/10.32620/oikit.2019.84.06.
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The main results and peculiarities of putting the family of regional passenger airplanes An-148/An-158 into the batch production are presented. Based on the results of audits of the Aviation Register of the Interstate Aviation Committee and the State Aviation Service of Ukraine the complex of works that had been performed allowed to obtain approval for putting of airplanes into the batch production. The production is carried out in accordance with the requirements of «Guidelines21.2Cfor the Certification and Supervision of Aircraft Production», «Guidelines 21.2D of Certification and Control Procedures over the Civil Aircraft Production», Standards ISO9001-2009 and EN9100 of «Quality Management Systems. Requirements». The functioning of the quality system is constantly monitored by internal inspections.To put the AN-148-100/158 airplanes into the batch production: technological preparation of production for about 65 000 parts, units and assemblies has been made; more than 19 300 items of special technological equipment and tools have been designed and manufactured; more than 75 000 sets of design documentation for the processes of manufacturing, assembling, controlling and testing parts, units, assemblies and systems of airplanes have been worked out; new technological processes in the forging and stamping, mechanical assembly production, aggregate and assembly manufacturing have been completed, improved and implemented; advanced metalworking tools have been tested and implemented in the production; works on restoration of efficiency and improvement of technological equipment have been performed; new technological processes of manufacturing parts and units on numerically controlled programmable machines have been completed and implemented; complex manufacturing and new production processes of manufacturing products from composite and nonmetallic materials, forging and stamping products, foundry and thermal production have been completed and implemented; new equipment and production processes of welding have been mastered and implemented; the information infrastructure of the company has been organized and is being developed; an integrated automated production management system (ASC) has been developed. It functions based on the main data scope computation on a central computer capable to connect users to view the data; automated workplaces based on personal computers have been organized; measures on recruitment and training of the personnel have been organized and carried out.
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Reese, Douglas C., Robert T. O'Malley, Richard D. Brodeur, and James H. Churnside. "Epipelagic fish distributions in relation to thermal fronts in a coastal upwelling system using high-resolution remote-sensing techniques." ICES Journal of Marine Science 68, no. 9 (July 13, 2011): 1865–74. http://dx.doi.org/10.1093/icesjms/fsr107.
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Abstract Reese, D. C., O'Malley, R. T., Brodeur, R. D., and Churnside, J. H. 2011. Epipelagic fish distributions in relation to thermal fronts in a coastal upwelling system using high-resolution remote-sensing techniques. – ICES Journal of Marine Science, 68: 1865–1874. Coastal upwelling systems are characterized by substantial spatial and temporal variability with respect to surface conditions, with fauna patchily distributed and high abundances in localized areas. Examining habitat associations on finer spatial scales than previous studies have been able to achieve would advance the understanding of important marine coastal ecosystems. This study evaluates the spatial and temporal relationships of single fish and fish schools with sea surface temperature (SST) fronts in the northern California Current upwelling system, using lidar (light detection and ranging) from an aircraft to sample surface waters over the continental shelf. High-resolution data were collected on the distribution of surface nekton and SST, then the locations of fish were analysed with respect to their proximity to SST fronts using GIS spatial analyses. Both fish schools and solitary fish were located significantly closer to fronts than would be expected by chance. The association of fish to fronts varied with the progression of the upwelling season such that fish associated less with fronts under stronger upwelling conditions. The relationships observed indicate the importance of thermal features to fish as a habitat component in a variable upwelling environment and have implications for management and conservation.
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Koeln, Justin P., Herschel C. Pangborn, Matthew A. Williams, Malia L. Kawamura, and Andrew G. Alleyne. "Hierarchical Control of Aircraft Electro-Thermal Systems." IEEE Transactions on Control Systems Technology 28, no. 4 (July 2020): 1218–32. http://dx.doi.org/10.1109/tcst.2019.2905221.
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Sundaram, Rajyashree M., Atsuko Sekiguchi, Mizuki Sekiya, Takeo Yamada, and Kenji Hata. "Copper/carbon nanotube composites: research trends and outlook." Royal Society Open Science 5, no. 11 (November 2018): 180814. http://dx.doi.org/10.1098/rsos.180814.
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We present research progress made in developing copper/carbon nanotube composites (Cu/CNT) to fulfil a growing demand for lighter copper substitutes with superior electrical, thermal and mechanical performances. Lighter alternatives to heavy copper electrical and data wiring are needed in automobiles and aircrafts to enhance fuel efficiencies. In electronics, better interconnects and thermal management components than copper with higher current- and heat-stabilities are required to enable device miniaturization with increased functionality. Our literature survey encouragingly indicates that Cu/CNT performances (electrical, thermal and mechanical) reported so far rival that of Cu, proving the material's viability as a Cu alternative. We identify two grand challenges to be solved for Cu/CNT to replace copper in real-life applications. The first grand challenge is to fabricate Cu/CNT with overall performances exceeding that of copper. To address this challenge, we propose research directions to fabricate Cu/CNT closer to ideal composites theoretically predicted to surpass Cu performances (i.e. those containing uniformly distributed Cu and individually aligned CNTs with beneficial CNT–Cu interactions ). The second grand challenge is to industrialize and transfer Cu/CNT from lab bench to real-life use. Toward this, we identify and propose strategies to address market-dependent issues for niche/mainstream applications. The current best Cu/CNT performances already qualify for application in niche electronic device markets as high-end interconnects. However, mainstream Cu/CNT application as copper replacements in conventional electronics and in electrical/data wires are long-term goals, needing inexpensive mass-production by methods aligned with existing industrial practices. Mainstream electronics require cheap CNT template-making and electrodeposition procedures, while data/electrical cables require manufacture protocols based on co-electrodeposition or melt-processing. We note (with examples) that initiatives devoted to Cu/CNT manufacturing for both types of mainstream applications are underway. With sustained research on Cu/CNT and accelerating its real-life application, we expect the successful evolution of highly functional, efficient, and sustainable next-generation electrical and electronics systems.
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Di Lorenzo, Giuseppe, Emma Frosina, Luigi De Petrillo, Davide Lauria, Adolfo Senatore, Francesco Curreri, Guido Saccone, Marcello Kivel Mazuy, and Ciro Pascarella. "Design and Development of Hybrid-Electric Propulsion Model for Aeronautics." MATEC Web of Conferences 304 (2019): 03012. http://dx.doi.org/10.1051/matecconf/201930403012.
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Nowadays, worldwide environmental issue, associated to reduction of pollutant and greenhouse emissions are gaining considerable attention. Aviation sector contribution to the whole CO2 released accounts to around 2%, but it is expected to grow in the next future due to increase of demand. Probably, combustion engine design and fuel efficiency have already reached their optimum technology level and only a breakthrough as hybrid-electric propulsion could be able to satisfy the new international more demanding requirements. However, an improvement of the technology readiness level of hybrid-electric propulsion is strongly necessary and many operational and safety challenges should be addressed. In the work here reported, a hybrid-electric model was designed and developed for general aviation aircrafts, by means of the Mathworks® Matlab – Simulink 1D/0D simulation environment. Both thermal and electric energy storage units, transmission systems and power management devices were considered and the overall performances were evaluated during cruise phase and a conventional training mission, characterized by several run(lap) “touch-and-go”. Furthermore, an innovative mathematical methodology was implemented for battery pack discharge profile interpolation. Finally, reliability and accuracy of the new proposed model were evaluated through comparison with the commercial code Simcenter AMESim® software and an average bias only equal to 5% was achieved.
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Doman, David B. "Optimal Cruise Altitude for Aircraft Thermal Management." Journal of Guidance, Control, and Dynamics 38, no. 11 (November 2015): 2084–95. http://dx.doi.org/10.2514/1.g000845.
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Oliveira, J. L. G., C. Tecchio, K. V. Paiva, M. B. H. Mantelli, R. Gandolfi, and L. G. S. Ribeiro. "Passive aircraft cooling systems for variable thermal conditions." Applied Thermal Engineering 79 (March 2015): 88–97. http://dx.doi.org/10.1016/j.applthermaleng.2015.01.021.
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Zhang, Xi, Jing Li, and Yao Bao Yin. "Thermal Analysis and Simulation of Aircraft Hydraulic System." Advanced Materials Research 204-210 (February 2011): 1984–89. http://dx.doi.org/10.4028/www.scientific.net/amr.204-210.1984.
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Thermal analysis of aircraft hydraulic systems is an important subject for system’s design. Heat generation and dissipation of aircraft hydraulic systems had been discussed in this article. Heat exchange was calculated based on heat transfer theory. A formula of temperature variation was derived based on the assumption that oil flow in the hydraulic system was one-dimension unsteady flow. Take the hydraulic system of a certain commercial aircraft for example, a model was established to simulate the temperature change of aircraft hydraulic systems based on AMESim. The simulation results are in consistent with test data.
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Freeman, Jeffrey, Philip Osterkamp, Michael Green, Andrew Gibson, and Benjamin Schiltgen. "Challenges and opportunities for electric aircraft thermal management." Aircraft Engineering and Aerospace Technology 86, no. 6 (September 30, 2014): 519–24. http://dx.doi.org/10.1108/aeat-04-2014-0042.
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Kim, Karl, and Jennifer Davidson. "Unmanned Aircraft Systems Used for Disaster Management." Transportation Research Record: Journal of the Transportation Research Board 2532, no. 1 (January 2015): 83–90. http://dx.doi.org/10.3141/2532-10.
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Krasiński, Wojciech. "Unmanned Aircraft Systems in Crisis Management in Poland After 2007." Safety & Defense 6, no. 2 (September 7, 2020): 42–50. http://dx.doi.org/10.37105/sd.79.
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This article discusses the employment of unmanned aircraft systems in crisis management in Poland after 2007. The conceptual framework and organization of crisis management in Poland is presented as an introduction to further discussion. This article then analyses capabilities of various categories of unmanned aircraft systems taking into account specific requirements of crisis management. This article also points at preliminary lessons learned from employment of unmanned aircraft systems for crisis management in Poland in recent years. Due attention is paid to missions and the organization of employment of unmanned aircraft systems in crisis management operations. Perspectives of employing unmanned aircraft systems in crisis management are presented in the final part of the article.
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Li, Dong, Sujun Dong, Jun Wang, and Yunhua Li. "Thermal dynamics and thermal management strategy for a civil aircraft hydraulic system." Thermal Science 24, no. 4 (2020): 2311–18. http://dx.doi.org/10.2298/tsci2004311l.
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Addressing the growing severe heat-generation and temperature-rise issues of the civil aircraft hydraulic system, this paper proposes a thermal dynamic model and thermal management strategies for the system within full mission profile. Firstly, a new thermal dynamic modeling towards general hydraulic components is conducted. Secondly, thermal dynamic governing equations are derived. Then a thermal management mechanism of the system is proposed. The conducted research is prerequisite to future numerical simulation of the thermal dynamic characteristics, evaluation and improvement of thermal management strategies for the system.
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Binbin, Lu, JI Honghu, TANG Mei, and Wang Guofeng. "Modeling and simulation of aircraft integrated thermal management system." Journal of Physics: Conference Series 1314 (October 2019): 012107. http://dx.doi.org/10.1088/1742-6596/1314/1/012107.
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German, Brian J. "Tank Heating Model for Aircraft Fuel Thermal Systems with Recirculation." Journal of Propulsion and Power 28, no. 1 (January 2012): 204–10. http://dx.doi.org/10.2514/1.b34240.
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SARVAR, FARHAD, and DAVID C. WHALLEY. "THERMAL DESIGN OF HIGH POWER SEMICONDUCTOR PACKAGES FOR AIRCRAFT SYSTEMS." Journal of Electronics Manufacturing 09, no. 04 (December 1999): 269–74. http://dx.doi.org/10.1142/s0960313199000180.
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Speijker, Lennaert, Xiaogong Lee, and Ron Van de Leijgraaf. "Framework for Unmanned Aircraft Systems Safety Risk Management." SAE International Journal of Aerospace 4, no. 2 (October 18, 2011): 1228–42. http://dx.doi.org/10.4271/2011-01-2688.
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Сілакова, Тамара Тимофіївна. "Mechanical systems in the management of the aircraft." MECHANICS OF GYROSCOPIC SYSTEMS, no. 35 (May 15, 2018): 19–30. http://dx.doi.org/10.20535/0203-3771352018143826.
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