Pub Date : 2019-09-01DOI: 10.1109/ESPC.2019.8932035
D. Lackner, J. Schwar, F. Dimroth, J. Schön, R. Lang, B. Godejohann, F. Predan, M. Schachtner, B. Boizot, J. Lefèvre, C. Flötgen
Electric orbit raising increases the radiation dose for space solar arrays significantly. This leads to the need for a more radiation resistant, highly efficient space solar cell. We propose a new wafer-bonded 4-junction structure which allows reaching begin-of-life efficiencies up to 34.7% (AMO) and efficiencies up to 30.8% (AMO) after 1*1015 cm−2 1-MeV electron irradiation. The high radiation hardness is a result of specific material properties of InP-rich compounds which benefit from significant defect annealing under typical operating conditions in space. A new four-j unction space solar cell, based on high InP fractions containing GaInAsP and Ge is currently under development in the EU project RadHard and first devices achieve an efficiency of 21.4% (AM0) before irradiation. After irradiation, as expected, a strong annealing effect after 3 days at AM0 & 60°C is found for this device. Already at this early development stage 78% of the end of life open circuit target voltage of 3.09 V under AM0 has been reached.
{"title":"Radiation hard four-junction space solar cell based on GaInAsP alloys","authors":"D. Lackner, J. Schwar, F. Dimroth, J. Schön, R. Lang, B. Godejohann, F. Predan, M. Schachtner, B. Boizot, J. Lefèvre, C. Flötgen","doi":"10.1109/ESPC.2019.8932035","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932035","url":null,"abstract":"Electric orbit raising increases the radiation dose for space solar arrays significantly. This leads to the need for a more radiation resistant, highly efficient space solar cell. We propose a new wafer-bonded 4-junction structure which allows reaching begin-of-life efficiencies up to 34.7% (AMO) and efficiencies up to 30.8% (AMO) after 1*1015 cm−2 1-MeV electron irradiation. The high radiation hardness is a result of specific material properties of InP-rich compounds which benefit from significant defect annealing under typical operating conditions in space. A new four-j unction space solar cell, based on high InP fractions containing GaInAsP and Ge is currently under development in the EU project RadHard and first devices achieve an efficiency of 21.4% (AM0) before irradiation. After irradiation, as expected, a strong annealing effect after 3 days at AM0 & 60°C is found for this device. Already at this early development stage 78% of the end of life open circuit target voltage of 3.09 V under AM0 has been reached.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"7 1","pages":"1-3"},"PeriodicalIF":0.0,"publicationDate":"2019-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"76547384","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 : 2019-09-01DOI: 10.1109/ESPC.2019.8932010
Hans Jensen
Although recent versions of Cadence PSpice contain functions that can derive regulation loop bode plots from a real time switching model, it is still very attractive and necessary for larger system analysis to have an accurate and precise linearized model of DC/DC converter stages, which covers both continuous and discontinuous conduction mode. It is also important that such a model provide the same transfer function as the simulated real time DC/DC converter, including Right Half Plane Zero (RHPZ) effects of boost family converters and load dependent inductance. A novel model, that fulfill these requirements has been developed and is presented in detail in this paper.
{"title":"DC-DC Converter Linearized Model","authors":"Hans Jensen","doi":"10.1109/ESPC.2019.8932010","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932010","url":null,"abstract":"Although recent versions of Cadence PSpice contain functions that can derive regulation loop bode plots from a real time switching model, it is still very attractive and necessary for larger system analysis to have an accurate and precise linearized model of DC/DC converter stages, which covers both continuous and discontinuous conduction mode. It is also important that such a model provide the same transfer function as the simulated real time DC/DC converter, including Right Half Plane Zero (RHPZ) effects of boost family converters and load dependent inductance. A novel model, that fulfill these requirements has been developed and is presented in detail in this paper.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"27 1","pages":"1-4"},"PeriodicalIF":0.0,"publicationDate":"2019-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"78153945","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 : 2019-09-01DOI: 10.1109/ESPC.2019.8932034
R. Campesato, E. Greco, A. Mezzetti, F. Di Fonzo, F. Bissoli, A. di Mezza
An important field to improve solar cell efficiency is the optimization of the antireflection coating (ARC) to allow more light to be converted; from a theoretical point of view this could increase the solar cell efficiency of 0.5%. Different ARC designs have been investigated, the most promising approaches are based on multi layers or gradient index approaches. These approaches have been theoretically and experimentally optimized to increase the photocurrent in the spectral range 300–1880 nm. Experimental results show that the solar cell efficiency can be increased of 0.5% both on thin and standard CESI space solar cells having 30% BOL efficiency.
{"title":"Effective Coating for High Efficiency Triple Junction Solar Cells","authors":"R. Campesato, E. Greco, A. Mezzetti, F. Di Fonzo, F. Bissoli, A. di Mezza","doi":"10.1109/ESPC.2019.8932034","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932034","url":null,"abstract":"An important field to improve solar cell efficiency is the optimization of the antireflection coating (ARC) to allow more light to be converted; from a theoretical point of view this could increase the solar cell efficiency of 0.5%. Different ARC designs have been investigated, the most promising approaches are based on multi layers or gradient index approaches. These approaches have been theoretically and experimentally optimized to increase the photocurrent in the spectral range 300–1880 nm. Experimental results show that the solar cell efficiency can be increased of 0.5% both on thin and standard CESI space solar cells having 30% BOL efficiency.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"69 1","pages":"1-5"},"PeriodicalIF":0.0,"publicationDate":"2019-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"79161117","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 : 2019-09-01DOI: 10.1109/ESPC.2019.8932013
V. Sazonov, I. Samylovskiy, O. Morozov, A. Sapelkin
At present, there are two parallel trends related to SA construction tasks and problems. From the one side, due to complexity of spacecrafts construction and growing use of high-power large-sized antennas, it is necessary to consider the effect of shading on the SA and research the effects accompanying this phenomenon. From the other side, modern computer tools, especially GPUs (graphics processing unit), allow one to create mini-supercomputer based on “common” desktop/laptop and perform CAE (computer-aided engineering)-based processes using 3D models of different LOD (Level-of-detail). In this paper, we present a conception of SA parameters computer modeling based on hierarchical, property-based 3D-model of spacecraft. Thus, one can model different work modes of spacecraft on the project stage, with real-time prediction of effects related to space factors complex combination impact. The result is easy-to-edit, easy-to-calibrate “digital copy” of spacecraft which allows engineer to model and investigate complex space factors combination results for a different orbital work mode
{"title":"Solar Arrays Thermal Conditions and Power Production Modeling with GPU-based Approach*","authors":"V. Sazonov, I. Samylovskiy, O. Morozov, A. Sapelkin","doi":"10.1109/ESPC.2019.8932013","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932013","url":null,"abstract":"At present, there are two parallel trends related to SA construction tasks and problems. From the one side, due to complexity of spacecrafts construction and growing use of high-power large-sized antennas, it is necessary to consider the effect of shading on the SA and research the effects accompanying this phenomenon. From the other side, modern computer tools, especially GPUs (graphics processing unit), allow one to create mini-supercomputer based on “common” desktop/laptop and perform CAE (computer-aided engineering)-based processes using 3D models of different LOD (Level-of-detail). In this paper, we present a conception of SA parameters computer modeling based on hierarchical, property-based 3D-model of spacecraft. Thus, one can model different work modes of spacecraft on the project stage, with real-time prediction of effects related to space factors complex combination impact. The result is easy-to-edit, easy-to-calibrate “digital copy” of spacecraft which allows engineer to model and investigate complex space factors combination results for a different orbital work mode","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"76 1","pages":"1-3"},"PeriodicalIF":0.0,"publicationDate":"2019-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"87047998","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 : 2019-09-01DOI: 10.1109/ESPC.2019.8932063
C. Barklay, D. Kramer, C. Whiting, R. Ambrosi, R. Mesalam
A multi-mission radioisotope thermoelectric generator (MMRTG) powers Curiosity, the National Aeronautics and Space Administration (NASA) Mars Science Laboratory rover on Mars. Consideration is being given to the feasibility of integrating a second thermoelectric circuit of bismuth telluride (Bi2Te3) into the MMRTG design in order to improve the beginning-of-life (BOL) and end-of-design life (EODL) performance. The maturity of Bi2Te3 and the design flexibility of a cascaded approach enable a low-risk system upgrade that is predicted to enhance the MMRTG's performance. Initial studies indicate that the integration of a second stage Bi2Te3 thermoelectric circuit could potentially provide an approximate 20% increase in power output at BOL and EODL (with EODL defined as 17 years from fueling). This paper presents an overview of the results of the study.
{"title":"Concept for a Cascaded Multi-Mission Radioisotope Thermoelectric Generator","authors":"C. Barklay, D. Kramer, C. Whiting, R. Ambrosi, R. Mesalam","doi":"10.1109/ESPC.2019.8932063","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932063","url":null,"abstract":"A multi-mission radioisotope thermoelectric generator (MMRTG) powers Curiosity, the National Aeronautics and Space Administration (NASA) Mars Science Laboratory rover on Mars. Consideration is being given to the feasibility of integrating a second thermoelectric circuit of bismuth telluride (Bi2Te3) into the MMRTG design in order to improve the beginning-of-life (BOL) and end-of-design life (EODL) performance. The maturity of Bi2Te3 and the design flexibility of a cascaded approach enable a low-risk system upgrade that is predicted to enhance the MMRTG's performance. Initial studies indicate that the integration of a second stage Bi2Te3 thermoelectric circuit could potentially provide an approximate 20% increase in power output at BOL and EODL (with EODL defined as 17 years from fueling). This paper presents an overview of the results of the study.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"20 1","pages":"1-5"},"PeriodicalIF":0.0,"publicationDate":"2019-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"72789817","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 : 2019-09-01DOI: 10.1109/ESPC.2019.8932030
Quentin Hilpert, S. Caux, F. Bonnet, M. Malagoli
This paper presents a research study on control strategies for satellite's Electrical Power System. SPACE Grid, which is a collaboration between the CNES, Airbus Defence and Space and the LAPLACE laboratory, consists in the modelling and determination of power management strategies on a new electrical architecture based on distributed Power Conditioning and Distribution Units. Are presented the models developed and the primary control implemented, inspired from ground-based DC micro-grids techniques. Future improvements and high level control are also discussed at the end of the paper.
{"title":"SPACE Grid: Smart and distributed Power Architecture and Control for Electrical Grid","authors":"Quentin Hilpert, S. Caux, F. Bonnet, M. Malagoli","doi":"10.1109/ESPC.2019.8932030","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932030","url":null,"abstract":"This paper presents a research study on control strategies for satellite's Electrical Power System. SPACE Grid, which is a collaboration between the CNES, Airbus Defence and Space and the LAPLACE laboratory, consists in the modelling and determination of power management strategies on a new electrical architecture based on distributed Power Conditioning and Distribution Units. Are presented the models developed and the primary control implemented, inspired from ground-based DC micro-grids techniques. Future improvements and high level control are also discussed at the end of the paper.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"54 1","pages":"1-6"},"PeriodicalIF":0.0,"publicationDate":"2019-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"75094998","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 : 2019-09-01DOI: 10.1109/ESPC.2019.8931986
Francesco Faleg, P. Zanella, S. Riva, Paolo Fidanzati, V. Inguimbert, G. Murat
In the framework of JUICE Photovoltaic Assembly, development and testing activities have been carried out in order to verify the effectiveness of grounding networks solution against ESDs occurrence in charging environment. During prequalification phase, dedicated coupons have been manufactured and submitted to environmental test campaigns, including ESD characterization. As the PVA design has progressed, a new ESD coupon with more representative technologies has been then manufactured and tested for electrons charging, so to compare results and assess new design and materials. This paper firstly describes the coupons manufactured for ESD testing, then an overview on ESD characterizations performed is provided. Lastly, relevant conclusions and comparisons between the results are discussed.
{"title":"Electrostatic Discharge Tests for JUICE Photovoltaic Assembly","authors":"Francesco Faleg, P. Zanella, S. Riva, Paolo Fidanzati, V. Inguimbert, G. Murat","doi":"10.1109/ESPC.2019.8931986","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8931986","url":null,"abstract":"In the framework of JUICE Photovoltaic Assembly, development and testing activities have been carried out in order to verify the effectiveness of grounding networks solution against ESDs occurrence in charging environment. During prequalification phase, dedicated coupons have been manufactured and submitted to environmental test campaigns, including ESD characterization. As the PVA design has progressed, a new ESD coupon with more representative technologies has been then manufactured and tested for electrons charging, so to compare results and assess new design and materials. This paper firstly describes the coupons manufactured for ESD testing, then an overview on ESD characterizations performed is provided. Lastly, relevant conclusions and comparisons between the results are discussed.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"38 1","pages":"1-5"},"PeriodicalIF":0.0,"publicationDate":"2019-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"76070188","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 : 2019-09-01DOI: 10.1109/ESPC.2019.8932079
Spiridon Savvas, Pavlos Ramnalis, Alexandros Manoudis, L. Benetti, Luca Onida, L. Fontani, T. Misuri
The Hollow Cathode is essential in determining the performance and reliability of the Hall Effect Thruster (HET) and is one of the main lifetime-limiting factors. Being such a critical element for the operation of the Thruster, the required Cathode Power Supply (CAPS) is playing an important role and constitutes a challenge from the power electronics design point of view, since a well-defined and demanding ignition procedure is required to succeed repeatable results alongside with proper isolation requirements. The Microsatellite Electric Propulsion System (MEPS) program aims at the qualification of an electric propulsion system based on a low power (up to 300 W) HET, embodying Rafael's Heaterless Hollow Cathode (RHHC) along with two types of Thruster Units (TUs) (SITAEL's HT100 and Rafael's CAM-200). In the frame of this program the required CAPS has been designed for the Elegant Bread Board (EBB) of the Power Processing Unit (PPU) as two discrete modules; 500 Vmax isolated current driven (settable up to 0.5 A) keeper power supply and 800 V isolated High Voltage (HV) igniter. The objective of this paper is to present the CAPS EBB modules design by showing the preliminary results obtained after a series of coupling tests of CAPS at Breadboard (BB) level with multiple configurations on which the EBB design was also based. Since RHHC has a wide operational range, the current EBB design along with the future progress of the program with the manufacturing and testing of the CAPS can become the driving factor for the successful implementation of an easily adjustable CAPS compatible with a wide range of Hollow Cathodes enabling the ignition of several low power HETs. In this direction, the feasibility for the already designed CAPS to drive also a different type of low power TU composed of a HET and a Heated Cathode (SITAEL's HC1) with minor modifications was investigated and a preliminary evaluation is presented.
{"title":"Discrete Cathode Power Supplies for Low Power Hall Effect Thrusters","authors":"Spiridon Savvas, Pavlos Ramnalis, Alexandros Manoudis, L. Benetti, Luca Onida, L. Fontani, T. Misuri","doi":"10.1109/ESPC.2019.8932079","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932079","url":null,"abstract":"The Hollow Cathode is essential in determining the performance and reliability of the Hall Effect Thruster (HET) and is one of the main lifetime-limiting factors. Being such a critical element for the operation of the Thruster, the required Cathode Power Supply (CAPS) is playing an important role and constitutes a challenge from the power electronics design point of view, since a well-defined and demanding ignition procedure is required to succeed repeatable results alongside with proper isolation requirements. The Microsatellite Electric Propulsion System (MEPS) program aims at the qualification of an electric propulsion system based on a low power (up to 300 W) HET, embodying Rafael's Heaterless Hollow Cathode (RHHC) along with two types of Thruster Units (TUs) (SITAEL's HT100 and Rafael's CAM-200). In the frame of this program the required CAPS has been designed for the Elegant Bread Board (EBB) of the Power Processing Unit (PPU) as two discrete modules; 500 Vmax isolated current driven (settable up to 0.5 A) keeper power supply and 800 V isolated High Voltage (HV) igniter. The objective of this paper is to present the CAPS EBB modules design by showing the preliminary results obtained after a series of coupling tests of CAPS at Breadboard (BB) level with multiple configurations on which the EBB design was also based. Since RHHC has a wide operational range, the current EBB design along with the future progress of the program with the manufacturing and testing of the CAPS can become the driving factor for the successful implementation of an easily adjustable CAPS compatible with a wide range of Hollow Cathodes enabling the ignition of several low power HETs. In this direction, the feasibility for the already designed CAPS to drive also a different type of low power TU composed of a HET and a Heated Cathode (SITAEL's HC1) with minor modifications was investigated and a preliminary evaluation is presented.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"28 1","pages":"1-5"},"PeriodicalIF":0.0,"publicationDate":"2019-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"78583496","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 : 2019-09-01DOI: 10.1109/ESPC.2019.8932075
Erik Mache, F. Forrisi, Alan Mallmann, Martin Blaser
Digital control of a power supply is the use of digitally implemented functions to provide configuration, monitoring and supervising which extend to full loop control using digital hardware and software algorithms. Digital Power Control is widely used in industrial applications and is getting more and more into the focus for space applications as well. This technology is not only limited to transferring from analog to Digital Control. It additionally allows superior controller structures and even complete new control strategies. This paper describes possibilities of digital power control for space applications.
{"title":"Advanced Digital Control for Rugged Power Supplies","authors":"Erik Mache, F. Forrisi, Alan Mallmann, Martin Blaser","doi":"10.1109/ESPC.2019.8932075","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932075","url":null,"abstract":"Digital control of a power supply is the use of digitally implemented functions to provide configuration, monitoring and supervising which extend to full loop control using digital hardware and software algorithms. Digital Power Control is widely used in industrial applications and is getting more and more into the focus for space applications as well. This technology is not only limited to transferring from analog to Digital Control. It additionally allows superior controller structures and even complete new control strategies. This paper describes possibilities of digital power control for space applications.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"24 1","pages":"1-5"},"PeriodicalIF":0.0,"publicationDate":"2019-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"74322913","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 : 2019-09-01DOI: 10.1109/ESPC.2019.8932033
Franz Stoegerer, T. Panhofer
The new-space market expects significantly reduced price of space borne equipment while still maintaining high performance and reliability. One significant factor is to reduce recurring parts costs by using components in lower quality such as automotive-grade. Since those parts are not designed for the space environment, radiation effects have to be considered even more than when using space-grade components. For short in-orbit durations or in LEO orbits the total ionizing dose (TID) value might be quite low and uncritical. However, single event effects (SEE) are severe even for such applications. This paper presents the design of a low-power DCDC converter (5 V, 2.5 A output) based on automotive parts and optimized for maximum SEE immunity.
{"title":"Low Power DCDC Converter Based on Automotive-Grade Components Featuring Maximum SEE Immunity","authors":"Franz Stoegerer, T. Panhofer","doi":"10.1109/ESPC.2019.8932033","DOIUrl":"https://doi.org/10.1109/ESPC.2019.8932033","url":null,"abstract":"The new-space market expects significantly reduced price of space borne equipment while still maintaining high performance and reliability. One significant factor is to reduce recurring parts costs by using components in lower quality such as automotive-grade. Since those parts are not designed for the space environment, radiation effects have to be considered even more than when using space-grade components. For short in-orbit durations or in LEO orbits the total ionizing dose (TID) value might be quite low and uncritical. However, single event effects (SEE) are severe even for such applications. This paper presents the design of a low-power DCDC converter (5 V, 2.5 A output) based on automotive parts and optimized for maximum SEE immunity.","PeriodicalId":6734,"journal":{"name":"2019 European Space Power Conference (ESPC)","volume":"223 1","pages":"1-6"},"PeriodicalIF":0.0,"publicationDate":"2019-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"77432668","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}
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