Since Gagarin’s flight on April 12th, 1961, the dream of making human space flight routine and making Homo sapiens a multiplanetary species seemed to have become closer to reality. Nonetheless, on average less than 10 human flights a year have happened along the past 60 years. Unmanned spacecrafts, on the other hand, have changed the way the human race sees itself and the universe it is surrounded by. They have explored all planets in the solar system, as well as comets, asteroids and the Sun. Presently, there are four unmanned spacecrafts on Mars’ surface and eight satellites in its orbit. Since the launching of Sputnik in 1957, more than 11,000 satellites have been sent into Earth’s orbit. Nowadays, it is impossible to imagine life on Earth without the services provided by the space-based infrastructure resulting from the Space Age. They have changed the modus vivendi of the human civilization and become a commodity, like potable water and electricity. The so-called satellite industry generates around US$ 300 billion a year, mostly related to the sale of satellite services and ground equipment. The era of exponential growth and disruption has reached Earth’s orbit, and beyond, through the minds, initiatives and boldness of the NewSpace generation, from which Elon Musk is its exponent. Twenty-five thousand satellites are expected to be launched in the next 10 years to provide, among other applications, worldwide broadband internet access. The scientific community and the military, however, have already expressed their concerns regarding space debris and, as a consequence, space sustainability. For the scientific community, the long-waited launch of the James Webb Space Telescope (JWST) promises to be the 2021 main event. In a time in which Spaceship Earth faces so many challenges, the dream of making its dwellers a multiplanetary species got a revival trough the minds and actions of Elon Musk and Jeff Bezos. There are those who, through public-private partnerships, intend to establish a 1,000 people community working and living in space by 2045. Cooperation among nations has been usual in space, but they are still shy when compared to the efforts required to colonize the Moon, Mars and other places in the solar system. As the 21st century advances, Spaceship Earth faces its greatest challenge ever. Space-based assets provide all the tools required to monitor Earth’s health, but if the human species intends to survive as the only identified intelligent civilization, it will have to think and act united in a truly cooperative way. Otherwise, the civilizational and technological effort hitherto undertaken may prove to be useless.
{"title":"Space Age: Past, Present and Possible Futures","authors":"José Bezerra Pessoa Filho","doi":"10.1590/jatm.v13.1226","DOIUrl":"https://doi.org/10.1590/jatm.v13.1226","url":null,"abstract":"Since Gagarin’s flight on April 12th, 1961, the dream of making human space flight routine and making Homo sapiens a multiplanetary species seemed to have become closer to reality. Nonetheless, on average less than 10 human flights a year have happened along the past 60 years. Unmanned spacecrafts, on the other hand, have changed the way the human race sees itself and the universe it is surrounded by. They have explored all planets in the solar system, as well as comets, asteroids and the Sun. Presently, there are four unmanned spacecrafts on Mars’ surface and eight satellites in its orbit. Since the launching of Sputnik in 1957, more than 11,000 satellites have been sent into Earth’s orbit. Nowadays, it is impossible to imagine life on Earth without the services provided by the space-based infrastructure resulting from the Space Age. They have changed the modus vivendi of the human civilization and become a commodity, like potable water and electricity. The so-called satellite industry generates around US$ 300 billion a year, mostly related to the sale of satellite services and ground equipment. The era of exponential growth and disruption has reached Earth’s orbit, and beyond, through the minds, initiatives and boldness of the NewSpace generation, from which Elon Musk is its exponent. Twenty-five thousand satellites are expected to be launched in the next 10 years to provide, among other applications, worldwide broadband internet access. The scientific community and the military, however, have already expressed their concerns regarding space debris and, as a consequence, space sustainability. For the scientific community, the long-waited launch of the James Webb Space Telescope (JWST) promises to be the 2021 main event. In a time in which Spaceship Earth faces so many challenges, the dream of making its dwellers a multiplanetary species got a revival trough the minds and actions of Elon Musk and Jeff Bezos. There are those who, through public-private partnerships, intend to establish a 1,000 people community working and living in space by 2045. Cooperation among nations has been usual in space, but they are still shy when compared to the efforts required to colonize the Moon, Mars and other places in the solar system. As the 21st century advances, Spaceship Earth faces its greatest challenge ever. Space-based assets provide all the tools required to monitor Earth’s health, but if the human species intends to survive as the only identified intelligent civilization, it will have to think and act united in a truly cooperative way. Otherwise, the civilizational and technological effort hitherto undertaken may prove to be useless.","PeriodicalId":14872,"journal":{"name":"Journal of Aerospace Technology and Management","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2021-06-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"48224349","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
The regional navigation satellite system (RNSS) is recently used in some countries to cover or enhance their local navigation. The most important satellite navigation systems to date are in the Earth medium orbit (MEO) and Earth synchronous Earth orbit (GEO), which are characterized by big satellites, and high launch, construction, and operation costs. In contrast, low Earth orbit (LEO) small-satellite constellations have recently become attractive because of their advantages, such as a significant reduction in system cost, an increase in communication volume, and a reduction in latency. Therefore, in this study, the spatial geometry of a LEO constellation is designed for Iran to increase the required regional navigation performance. For this purpose, the optimal constellation configuration is obtained through a multi-objective genetic algorithm (MOGA) utilizing a cost function with a combination of the geometry dilution of precision (GDOP), the number of satellites, and orbital height in the form of a design procedure. Moreover, reducing the feasible region of longitude of the ascending nodes of orbit planes is applied in the design process to reduce the search space. The simulation results indicate the constellation designed performance.
{"title":"Spatial Geometry Design of a Low Earth Orbit Constellation for Iranian Regional Navigation Satellite System","authors":"R. Zardashti, Shiva Emami","doi":"10.1590/JATM.V13.1215","DOIUrl":"https://doi.org/10.1590/JATM.V13.1215","url":null,"abstract":"The regional navigation satellite system (RNSS) is recently used in some countries to cover or enhance their local navigation. The most important satellite navigation systems to date are in the Earth medium orbit (MEO) and Earth synchronous Earth orbit (GEO), which are characterized by big satellites, and high launch, construction, and operation costs. In contrast, low Earth orbit (LEO) small-satellite constellations have recently become attractive because of their advantages, such as a significant reduction in system cost, an increase in communication volume, and a reduction in latency. Therefore, in this study, the spatial geometry of a LEO constellation is designed for Iran to increase the required regional navigation performance. For this purpose, the optimal constellation configuration is obtained through a multi-objective genetic algorithm (MOGA) utilizing a cost function with a combination of the geometry dilution of precision (GDOP), the number of satellites, and orbital height in the form of a design procedure. Moreover, reducing the feasible region of longitude of the ascending nodes of orbit planes is applied in the design process to reduce the search space. The simulation results indicate the constellation designed performance.","PeriodicalId":14872,"journal":{"name":"Journal of Aerospace Technology and Management","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2021-06-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43880503","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Paraffin wax has been identified as a hybrid rocket motor fuel, which offers enhanced regression rates and improved combustion performance. While various investigations into the performance of this class of fuels are being conducted around the world, the consideration of its structural performance is often overlooked. The research presented here establishes a simplified, yet accurate method of defining the structural performance of a paraffin wax hybrid fuel grain to be introduced early in the design phase of a motor. The use of the Johnson–Cook (J–C) material model has been verified to work within the “low speed” ignition range experienced in paraffin wax/N2O hybrid motors, and therefore is used to predict failure in a variety of motors. The resultant stress profiles within the grains indicate that the grain outer to inner diameter (OD/ID) ratio, as well as the outer diameter (OD) itself, play an important role in the grain ability to withstand the loading conditions applied. Additionally, the grain structural properties, and the stiffness of the combustion chamber affect the severity of the internal stresses in the grain. The feasibility of large-scale pure paraffin wax grains without structural enhancement additives is thus found to be poor. Fuel additives should be considered for structural enhancement.
{"title":"Explicit Modelling of the Ignition Transient Structural Response of a Paraffin Wax Hybrid Rocket Motor Fuel Grain","authors":"K. Veale, S. Adali, Jean Pitot, C. Bemont","doi":"10.1590/JATM.V13.1216","DOIUrl":"https://doi.org/10.1590/JATM.V13.1216","url":null,"abstract":"Paraffin wax has been identified as a hybrid rocket motor fuel, which offers enhanced regression rates and improved combustion performance. While various investigations into the performance of this class of fuels are being conducted around the world, the consideration of its structural performance is often overlooked. The research presented here establishes a simplified, yet accurate method of defining the structural performance of a paraffin wax hybrid fuel grain to be introduced early in the design phase of a motor. The use of the Johnson–Cook (J–C) material model has been verified to work within the “low speed” ignition range experienced in paraffin wax/N2O hybrid motors, and therefore is used to predict failure in a variety of motors. The resultant stress profiles within the grains indicate that the grain outer to inner diameter (OD/ID) ratio, as well as the outer diameter (OD) itself, play an important role in the grain ability to withstand the loading conditions applied. Additionally, the grain structural properties, and the stiffness of the combustion chamber affect the severity of the internal stresses in the grain. The feasibility of large-scale pure paraffin wax grains without structural enhancement additives is thus found to be poor. Fuel additives should be considered for structural enhancement.","PeriodicalId":14872,"journal":{"name":"Journal of Aerospace Technology and Management","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2021-06-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43179496","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Lifetime is a main factor restraining the application of low-power Hall thruster. Magnetic shielding configuration is regarded as a promising method to prolong the lifespan of Hall thruster. Aiming to demonstrate the feasibility and effectiveness of magnetic shielding configuration applying on low-power Hall thruster, a 60-mm diameter Hall thruster in partial magnetic shielding configuration was designated. Both the numerical and experimental methods were used to investigate the discharge characteristics of the Hall thruster and help understand the mechanism behind. The maximum anode efficiency was achieved as high as 29.7% with 1.7 mg·s–1 anode mass flow and 320 V discharge voltage. To evaluate the effectiveness of the magnetic shielding used for low-power Hall thruster, a 2000 h lifetime test has been carried out and the results indicate that the erosion rate has been decreased below 0.2 μm·h–1.
{"title":"Effects of Magnetic Shielding Configuration on Discharge Characteristics and Performance of a 60 mm-Diameter Low-Power Hall Thruster","authors":"W. Guo, Jun Gao, Zuo Gu, Ning Guo, Mingfang Sun","doi":"10.1590/JATM.V13.1223","DOIUrl":"https://doi.org/10.1590/JATM.V13.1223","url":null,"abstract":"Lifetime is a main factor restraining the application of low-power Hall thruster. Magnetic shielding configuration is regarded as a promising method to prolong the lifespan of Hall thruster. Aiming to demonstrate the feasibility and effectiveness of magnetic shielding configuration applying on low-power Hall thruster, a 60-mm diameter Hall thruster in partial magnetic shielding configuration was designated. Both the numerical and experimental methods were used to investigate the discharge characteristics of the Hall thruster and help understand the mechanism behind. The maximum anode efficiency was achieved as high as 29.7% with 1.7 mg·s–1 anode mass flow and 320 V discharge voltage. To evaluate the effectiveness of the magnetic shielding used for low-power Hall thruster, a 2000 h lifetime test has been carried out and the results indicate that the erosion rate has been decreased below 0.2 μm·h–1.","PeriodicalId":14872,"journal":{"name":"Journal of Aerospace Technology and Management","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2021-05-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"47740121","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2021-05-21DOI: 10.1590/JATM.V13.1195.2021
Sattar Mohammadi Esfarjani, M. Salehi
The purpose of the paper is to study the effect of temperature change on the theory of inner product vector (IPV). The IPV method can be used to detect structural damage. This study evaluates the IPV method ability to detect damage of an Airbus A320 slat-track, which is in the form of a longitudinal crack. The results show that the IPV method is able to detect defects in the structure as well as its location, with close approximation. Then, the Airbus A320 slat-track was investigated for the effect of changes in temperature on the IPV method, evaluated over a temperature between –73 and 260 °C. The effect of temperature on the performance of IPV damage detection method has not been investigated so far. The results of the IPV method show a spurious defect in the structure as the temperature changes; therefore, the IPV method is temperature-sensitive. Also, this study highlighted the importance of applying simulation methods to develop vibration-based damage detection (VBDD) techniques, especially for evaluating the effect of changes in environmental temperature when the structure is complex.
{"title":"Temperature Changes Effect on the Inner Product Vector Method and its Application to Structural Health Monitoring of Aircraft Industry","authors":"Sattar Mohammadi Esfarjani, M. Salehi","doi":"10.1590/JATM.V13.1195.2021","DOIUrl":"https://doi.org/10.1590/JATM.V13.1195.2021","url":null,"abstract":"The purpose of the paper is to study the effect of temperature change on the theory of inner product vector (IPV). The IPV method can be used to detect structural damage. This study evaluates the IPV method ability to detect damage of an Airbus A320 slat-track, which is in the form of a longitudinal crack. The results show that the IPV method is able to detect defects in the structure as well as its location, with close approximation. Then, the Airbus A320 slat-track was investigated for the effect of changes in temperature on the IPV method, evaluated over a temperature between –73 and 260 °C. The effect of temperature on the performance of IPV damage detection method has not been investigated so far. The results of the IPV method show a spurious defect in the structure as the temperature changes; therefore, the IPV method is temperature-sensitive. Also, this study highlighted the importance of applying simulation methods to develop vibration-based damage detection (VBDD) techniques, especially for evaluating the effect of changes in environmental temperature when the structure is complex.","PeriodicalId":14872,"journal":{"name":"Journal of Aerospace Technology and Management","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2021-05-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44544984","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Aircraft fuels, called jet propulsion, are used in several areas of activity within aeronautics. There are jet fuels based on kerosene, that is, those obtained commercially, and there are synthetics produced in the laboratory. All of these fuels are included within the so-called propellants. In this article, Jet propulsion-8 (JP 8) fuel was used as the basis for data analysis, and thus two temperature ranges were analyzed. The first range, from 300 to 2500 K, was analyzed for specific heat, enthalpy and entropy. Based on theoretical and experimental data, artificial neural networks (ANNs) were developed to identify these properties in other working conditions, that is, at other temperatures.
{"title":"Forecasting Chemical Characteristics of Aircraft Fuel Using Artificial Neural Networks","authors":"F. Rocha, K. Iha, T. A. G. Tolosa","doi":"10.1590/JATM.V13.1221","DOIUrl":"https://doi.org/10.1590/JATM.V13.1221","url":null,"abstract":"Aircraft fuels, called jet propulsion, are used in several areas of activity within aeronautics. There are jet fuels based on kerosene, that is, those obtained commercially, and there are synthetics produced in the laboratory. All of these fuels are included within the so-called propellants. In this article, Jet propulsion-8 (JP 8) fuel was used as the basis for data analysis, and thus two temperature ranges were analyzed. The first range, from 300 to 2500 K, was analyzed for specific heat, enthalpy and entropy. Based on theoretical and experimental data, artificial neural networks (ANNs) were developed to identify these properties in other working conditions, that is, at other temperatures.","PeriodicalId":14872,"journal":{"name":"Journal of Aerospace Technology and Management","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2021-05-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43938610","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Aircraft noise emissions are a problem that negatively affects human health, directly or indirectly. For this reason, examining and managing the noise effects caused by aircrafts at the airports is important for the sustainable development of aviation. In the present study, a noise management model based on the multiapproach method, including some actions related to aircraft noise, has been created. The model was applied to the International Eskisehir Hasan Polatkan Airport (LTBY). Within the scope of the model, in the first stage, in 365 days, day, evening and night noise levels around the airport were simulated using IMMI software under the European noise directive and European Civil Aviation Conference (ECAC) doc 29-interim was also used to measure aircraft noise. In the second stage, the noise generated by the Cessna 172-S aircraft under different operating conditions experimentally measured was carried out. After the model had been applied to LTBY, improvement opportunities for aircraft noise were evaluated. It is thought that the study and its results will help other civil airports on the issue of noise problem at airports.
飞机噪音排放是一个直接或间接影响人类健康的问题。因此，检查和管理飞机在机场造成的噪音影响对航空业的可持续发展至关重要。在本研究中，建立了一个基于多途径方法的噪声管理模型，包括与飞机噪声相关的一些行为。该模型已应用于Eskisehir Hasan Polatkan国际机场（LTBY）。在该模型的范围内，在第一阶段，在365天内，根据欧洲噪音指令，使用IMMI软件模拟了机场周围的昼夜噪音水平，欧洲民航会议（ECAC）doc29临时文件也用于测量飞机噪音。在第二阶段，对塞斯纳172-S飞机在不同运行条件下产生的噪声进行了实验测量。将该模型应用于LTBY后，对飞机噪声的改善机会进行了评估。人们认为，这项研究及其结果将有助于其他民用机场解决机场噪音问题。
{"title":"Assessment of Aircraft Noise Emissions at International Eskisehir Hasan Polatkan Airport with Multiple Approach Model","authors":"H. Akdeniz, M. Sogut, O. Turan","doi":"10.1590/JATM.V13.1204","DOIUrl":"https://doi.org/10.1590/JATM.V13.1204","url":null,"abstract":"Aircraft noise emissions are a problem that negatively affects human health, directly or indirectly. For this reason, examining and managing the noise effects caused by aircrafts at the airports is important for the sustainable development of aviation. In the present study, a noise management model based on the multiapproach method, including some actions related to aircraft noise, has been created. The model was applied to the International Eskisehir Hasan Polatkan Airport (LTBY). Within the scope of the model, in the first stage, in 365 days, day, evening and night noise levels around the airport were simulated using IMMI software under the European noise directive and European Civil Aviation Conference (ECAC) doc 29-interim was also used to measure aircraft noise. In the second stage, the noise generated by the Cessna 172-S aircraft under different operating conditions experimentally measured was carried out. After the model had been applied to LTBY, improvement opportunities for aircraft noise were evaluated. It is thought that the study and its results will help other civil airports on the issue of noise problem at airports.","PeriodicalId":14872,"journal":{"name":"Journal of Aerospace Technology and Management","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2021-05-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45174207","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2021-04-28DOI: 10.1590/JATM.V13.1206.2021
Timothy J. Velthuysen, M. Brooks, Jean Pitot
The thrust produced by a hybrid rocket motor (HRM) can be controlled by varying the oxidizer flow rate to the combustion chamber. This feature is useful in shaping motor thrust profiles and optimizing a vehicle flight trajectory, but propellant throttling in solid-fuel hybrids is limited to the liquid component only, complicating the control scheme and potentially destabilizing combustion in the motor. While hybrid motor throttling ability remains a subject of considerable interest, there has been little investigation of throttling in motors that use high regression rate, liquefying fuels such as paraffin wax. This article describes the development and implementation of a closed loop thrust control scheme for a laboratory-scale paraffin wax/nitrous oxide HRM using a low-cost ball valve as the controlling hardware element. A model of motor performance is first developed from which proportional-integral-derivative (PID) controller constants are obtained through experimental testing. The control scheme is demonstrated through closed loop hot fire tests of a laboratory-scale motor in which thrust tracks a set-point value with feedback provided through a load cell. Upon reaching the setpoint, the motor remains throttled within ± 2.4% of the maximum thrust of the motor. Constant and ramping thrust profiles are demonstrated.
{"title":"Closed Loop Throttle Control of a Liquefying Fuel Hybrid Rocket Motor","authors":"Timothy J. Velthuysen, M. Brooks, Jean Pitot","doi":"10.1590/JATM.V13.1206.2021","DOIUrl":"https://doi.org/10.1590/JATM.V13.1206.2021","url":null,"abstract":"The thrust produced by a hybrid rocket motor (HRM) can be controlled by varying the oxidizer flow rate to the combustion chamber. This feature is useful in shaping motor thrust profiles and optimizing a vehicle flight trajectory, but propellant throttling in solid-fuel hybrids is limited to the liquid component only, complicating the control scheme and potentially destabilizing combustion in the motor. While hybrid motor throttling ability remains a subject of considerable interest, there has been little investigation of throttling in motors that use high regression rate, liquefying fuels such as paraffin wax. This article describes the development and implementation of a closed loop thrust control scheme for a laboratory-scale paraffin wax/nitrous oxide HRM using a low-cost ball valve as the controlling hardware element. A model of motor performance is first developed from which proportional-integral-derivative (PID) controller constants are obtained through experimental testing. The control scheme is demonstrated through closed loop hot fire tests of a laboratory-scale motor in which thrust tracks a set-point value with feedback provided through a load cell. Upon reaching the setpoint, the motor remains throttled within ± 2.4% of the maximum thrust of the motor. Constant and ramping thrust profiles are demonstrated.","PeriodicalId":14872,"journal":{"name":"Journal of Aerospace Technology and Management","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2021-04-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43623880","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Suborbital flight experiments, carried out through sounding rockets, have been employed for scientific and technological research since the beginning of the space age, in the late 1950s. In Brazil, sounding rocket campaigns have been carried out since 1965, when the Centro de Lancamento Barreira do Inferno (CLBI) began its operation, having the Instituto de Aeronautica e Espaco (IAE)as the primary provider of vehicles. IAE has also provided vehicles for international programs, such as the TEXUS and MASER microgravity programs, implemented by the European Space Agency (ESA), with launching campaigns based in the European territory. To implement each Brazilian mission that uses IAE’s sounding rockets, a set of activities focused on mission objectives is planned and implemented. Although structured and executed quite similarly to a project, such sounding rocket campaigns do not have their complete life-cycle studied and formally described in phases, review meetings, management processes and verification and validation philosophy. In the present work, the attempt has been to characterize a sounding rocket mission as a project and then, based on European Cooperation for Space Standardization (ECSS) standards, propose a reduced life-cycle to develop such projects, tailored to meet Brazilian sounding rocket missions. The proposed life-cycle, adapted to Brazilian sounding rocket missions, is then compared with two other sounding rocket campaigns life-cycles: one from the European Programme for Life and Physical Sciences in Space and the other from the National Aeronautics and Space Administration (NASA) sounding rocket program. The study and availability of a framework for implementing and managing sounding rocket missions will improve the reliability of such endeavors and speed up their organization.
{"title":"A Proposal of a Life-Cycle for the Development of Sounding Rockets Missions","authors":"Felipe da Motta Silva, L. Perondi","doi":"10.1590/JATM.V13.1193","DOIUrl":"https://doi.org/10.1590/JATM.V13.1193","url":null,"abstract":"Suborbital flight experiments, carried out through sounding rockets, have been employed for scientific and technological research since the beginning of the space age, in the late 1950s. In Brazil, sounding rocket campaigns have been carried out since 1965, when the Centro de Lancamento Barreira do Inferno (CLBI) began its operation, having the Instituto de Aeronautica e Espaco (IAE)as the primary provider of vehicles. IAE has also provided vehicles for international programs, such as the TEXUS and MASER microgravity programs, implemented by the European Space Agency (ESA), with launching campaigns based in the European territory. To implement each Brazilian mission that uses IAE’s sounding rockets, a set of activities focused on mission objectives is planned and implemented. Although structured and executed quite similarly to a project, such sounding rocket campaigns do not have their complete life-cycle studied and formally described in phases, review meetings, management processes and verification and validation philosophy. In the present work, the attempt has been to characterize a sounding rocket mission as a project and then, based on European Cooperation for Space Standardization (ECSS) standards, propose a reduced life-cycle to develop such projects, tailored to meet Brazilian sounding rocket missions. The proposed life-cycle, adapted to Brazilian sounding rocket missions, is then compared with two other sounding rocket campaigns life-cycles: one from the European Programme for Life and Physical Sciences in Space and the other from the National Aeronautics and Space Administration (NASA) sounding rocket program. The study and availability of a framework for implementing and managing sounding rocket missions will improve the reliability of such endeavors and speed up their organization.","PeriodicalId":14872,"journal":{"name":"Journal of Aerospace Technology and Management","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2021-03-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43628245","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Turboelectric distributed propulsion systems are paving the way for more electric aircraft systems (TeDP). This type of system provides a solution for some of the drawbacks of current low-energy-density batteries, which limit the ability of long-endurance electric aircraft. However, turboelectric propulsion requires the use of advanced turboelectric motors, superconductive materials and cryogenic cooling technologies, which are still under development and may be in production in the near future. This paper investigates a turboelectric propulsion system that can be considered an initial step in the production of TeDP in a remotely piloted aircraft system with the use of existing technology. This is achieved by replacing the gear and the starter motor of a turboprop with a high-speed permanent magnet electric machine to generate electrical power and propelling the aircraft through a distributed electric propulsion system. In this theoretical study, an augmentation to Breguet’s range and endurance equation is developed. This study confirmed that the new system is 31% lighter than the turboprop engine. Then the effect of the weight savings is used in the distributed electric propulsion (DEP) aerodynamic studies and found that there is a drastic increase in the range for a TeDP developed with the high-speed machine.
{"title":"Development of a Turbo Electric Distribution System for Remotely Piloted Aircraft Systems","authors":"M. Eqbal, N. Fernando, M. Marino, G. Wild","doi":"10.1590/JATM.V13.1209","DOIUrl":"https://doi.org/10.1590/JATM.V13.1209","url":null,"abstract":"Turboelectric distributed propulsion systems are paving the way for more electric aircraft systems (TeDP). This type of system provides a solution for some of the drawbacks of current low-energy-density batteries, which limit the ability of long-endurance electric aircraft. However, turboelectric propulsion requires the use of advanced turboelectric motors, superconductive materials and cryogenic cooling technologies, which are still under development and may be in production in the near future. This paper investigates a turboelectric propulsion system that can be considered an initial step in the production of TeDP in a remotely piloted aircraft system with the use of existing technology. This is achieved by replacing the gear and the starter motor of a turboprop with a high-speed permanent magnet electric machine to generate electrical power and propelling the aircraft through a distributed electric propulsion system. In this theoretical study, an augmentation to Breguet’s range and endurance equation is developed. This study confirmed that the new system is 31% lighter than the turboprop engine. Then the effect of the weight savings is used in the distributed electric propulsion (DEP) aerodynamic studies and found that there is a drastic increase in the range for a TeDP developed with the high-speed machine.","PeriodicalId":14872,"journal":{"name":"Journal of Aerospace Technology and Management","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2021-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"47789658","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
京公网安备 11010802042870号
京ICP备2023020795号-1
扫码关注我们
求助内容：
应助结果提醒方式：