Pub Date : 2019-05-01DOI: 10.23919/AeroEMC.2019.8788917
X. Liu, F. Grassi, G. Spadacini, S. Pignari
In this paper, a novel approach for modelling hand-assembled random cable bundles is presented. The proposed method foresees to represent each cable position in the bundle via analytical polynomial curves, assuring smoothness of trajectories, as well as flexibility in accounting for bundle randomness. The generated bundle geometry is used in combination with full-wave and transmission-line based simulation, providing accurate predictions of the noise induced at the bundle terminals due to crosstalk between wires and due to an external EM field. The proposed examples, run in comparison with the more computationally-efficient yet approximate model in [1], prove the validity of the proposed generation algorithm and the need for accurate representation and discretization of the bundle if reliable predictions in a wide frequency interval are the target.
{"title":"Enhanced Geometrical Model of Complex Cable Bundles Through Polynomial Representation of Cable Trajectories","authors":"X. Liu, F. Grassi, G. Spadacini, S. Pignari","doi":"10.23919/AeroEMC.2019.8788917","DOIUrl":"https://doi.org/10.23919/AeroEMC.2019.8788917","url":null,"abstract":"In this paper, a novel approach for modelling hand-assembled random cable bundles is presented. The proposed method foresees to represent each cable position in the bundle via analytical polynomial curves, assuring smoothness of trajectories, as well as flexibility in accounting for bundle randomness. The generated bundle geometry is used in combination with full-wave and transmission-line based simulation, providing accurate predictions of the noise induced at the bundle terminals due to crosstalk between wires and due to an external EM field. The proposed examples, run in comparison with the more computationally-efficient yet approximate model in [1], prove the validity of the proposed generation algorithm and the need for accurate representation and discretization of the bundle if reliable predictions in a wide frequency interval are the target.","PeriodicalId":436679,"journal":{"name":"2019 ESA Workshop on Aerospace EMC (Aerospace EMC)","volume":"16 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116219044","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 : 2019-05-01DOI: 10.23919/AeroEMC.2019.8788933
B. Lavraud, A. Cara, D. Payan, Y. Ballot, J. Sauvaud, R. Mathon, T. Camus, O. Chassela, H. Séran, H. Tap, O. Bernal, M. Berthomier, P. Devoto, A. Fedorov, J. Rouzaud, J. Rubiella-Romeo, J. Techer, D. Zely, S. Galinier, D. Bruno
The Active Monitor Box of Electrostatic Risks (AMBER) is a double-head thermal electron and ion electrostatic analyzer (energy range 0–30 keV) that was launched onboard the Jason-3 spacecraft in 2016. The next generation AMBER instrument, for which a first prototype was developed and then calibrated at the end of 2017, constitutes a significant evolution that is based on a single head to measure both species alternatively. The instrument developments focused on several new sub-systems (front-end electronics, highvoltage electronics, mechanical design) that permit to reduce instrument resources down to ∼ 1 kg and 1.5 W. AMBER is designed as a generic radiation monitor with a twofold purpose: (1) measure magnetospheric thermal ion and electron populations in the range 0–35 keV, with significant scientific potential (e.g., plasmasphere, ring current, plasma sheet), and (2) monitor spacecraft electrostatic charging and the plasma populations responsible for it, for electromagnetic cleanliness and operational purposes.
{"title":"AMBRE: A Compact Instrument to Measure Thermal Ions, Electrons and Electrostatic Charging Onboard Spacecraft","authors":"B. Lavraud, A. Cara, D. Payan, Y. Ballot, J. Sauvaud, R. Mathon, T. Camus, O. Chassela, H. Séran, H. Tap, O. Bernal, M. Berthomier, P. Devoto, A. Fedorov, J. Rouzaud, J. Rubiella-Romeo, J. Techer, D. Zely, S. Galinier, D. Bruno","doi":"10.23919/AeroEMC.2019.8788933","DOIUrl":"https://doi.org/10.23919/AeroEMC.2019.8788933","url":null,"abstract":"The Active Monitor Box of Electrostatic Risks (AMBER) is a double-head thermal electron and ion electrostatic analyzer (energy range 0–30 keV) that was launched onboard the Jason-3 spacecraft in 2016. The next generation AMBER instrument, for which a first prototype was developed and then calibrated at the end of 2017, constitutes a significant evolution that is based on a single head to measure both species alternatively. The instrument developments focused on several new sub-systems (front-end electronics, highvoltage electronics, mechanical design) that permit to reduce instrument resources down to ∼ 1 kg and 1.5 W. AMBER is designed as a generic radiation monitor with a twofold purpose: (1) measure magnetospheric thermal ion and electron populations in the range 0–35 keV, with significant scientific potential (e.g., plasmasphere, ring current, plasma sheet), and (2) monitor spacecraft electrostatic charging and the plasma populations responsible for it, for electromagnetic cleanliness and operational purposes.","PeriodicalId":436679,"journal":{"name":"2019 ESA Workshop on Aerospace EMC (Aerospace EMC)","volume":"35 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126582131","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 : 2019-05-01DOI: 10.23919/AeroEMC.2019.8788914
P. Edwards, Jarek A. Tracz, D. Trout, Noel Sargent
In this paper, we discuss the need for international requirements to assure the EMC of Payload (Instruments/Experiments) use on multi-agency, multinational collaborations and multi-platform re-use. We examine possible environment exposures through mission life-cycle stages and the impact to EMC requirements and environment limits based on the processing path. We comment on existing Agency/National space standards, the level of harmonization between them, and possible integration to provide a common International Space Standard that would provide reasonable product assurance for EMC. We look at ISO 14302, and suggest revision/creation of a top-tier management document that facilitates the necessary EMI control methodology for multi-Agency, multi-national and multi-platform programs; integrated use of the individual agency/national space standards and international consensus on mandatory minimum environment levels.
{"title":"International Requirements for Payload Multi-Platform Reuse Methodology","authors":"P. Edwards, Jarek A. Tracz, D. Trout, Noel Sargent","doi":"10.23919/AeroEMC.2019.8788914","DOIUrl":"https://doi.org/10.23919/AeroEMC.2019.8788914","url":null,"abstract":"In this paper, we discuss the need for international requirements to assure the EMC of Payload (Instruments/Experiments) use on multi-agency, multinational collaborations and multi-platform re-use. We examine possible environment exposures through mission life-cycle stages and the impact to EMC requirements and environment limits based on the processing path. We comment on existing Agency/National space standards, the level of harmonization between them, and possible integration to provide a common International Space Standard that would provide reasonable product assurance for EMC. We look at ISO 14302, and suggest revision/creation of a top-tier management document that facilitates the necessary EMI control methodology for multi-Agency, multi-national and multi-platform programs; integrated use of the individual agency/national space standards and international consensus on mandatory minimum environment levels.","PeriodicalId":436679,"journal":{"name":"2019 ESA Workshop on Aerospace EMC (Aerospace EMC)","volume":"104 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125538821","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 : 2019-05-01DOI: 10.23919/AeroEMC.2019.8788951
X. Liu, L. Crosta, F. Grassi, G. Spadacini, S. Pignari, F. Trotti, N. Mora, W. Hirschi
In this paper, a SPICE model of a typical nanocrystalline core used for the manufacturing of pulse current injection probes is presented. The model aims at accounting for the frequency response of the material initial complex permeability spectra (small-signal model) as well as for possible saturation occurring within the magnetic core due to the injection of high-amplitude stress waveforms. Strengths and limitations of the proposed prediction model are assessed versus time-domain measurement of the voltage induced at the terminations of the wiring structure under test, when a damped-sinusoidal waveform is injected at the core input port.
{"title":"Spice Modeling of Probes for Pulse Current Injection","authors":"X. Liu, L. Crosta, F. Grassi, G. Spadacini, S. Pignari, F. Trotti, N. Mora, W. Hirschi","doi":"10.23919/AeroEMC.2019.8788951","DOIUrl":"https://doi.org/10.23919/AeroEMC.2019.8788951","url":null,"abstract":"In this paper, a SPICE model of a typical nanocrystalline core used for the manufacturing of pulse current injection probes is presented. The model aims at accounting for the frequency response of the material initial complex permeability spectra (small-signal model) as well as for possible saturation occurring within the magnetic core due to the injection of high-amplitude stress waveforms. Strengths and limitations of the proposed prediction model are assessed versus time-domain measurement of the voltage induced at the terminations of the wiring structure under test, when a damped-sinusoidal waveform is injected at the core input port.","PeriodicalId":436679,"journal":{"name":"2019 ESA Workshop on Aerospace EMC (Aerospace EMC)","volume":"6 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122219722","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 : 2019-05-01DOI: 10.23919/AeroEMC.2019.8788937
O. Kerfin, Marvin Schwarz, R. Geise
GNSSs (global navigation satellite systems) are an important worldwide standard for localisation methods. Prospective applications such as air transport with unmanned aircraft systems (UAS) in complex nonstatic urban environments will rely on GNSS signal integrity more than ever. Therefore, a basic approach for the analysis of timevariant GNSS propagation channels in a scaled measurement environment is introduced. A laboratory test bench is set up for the analysis of various generic GPS (Global Positioning System) channel configurations on a scale of 1:10. Time domain zero span measurements and a quasistatic channel characterisation are discussed. Corresponding measurement results are presented for different artificial interference scenarios. Finally, performance mitigation of a hardware GPS receiver due to the modulation of artificial navigation data with the measured channel properties is assessed.
{"title":"Scaled Measurements of Timevariant GNSS Propagation Channels","authors":"O. Kerfin, Marvin Schwarz, R. Geise","doi":"10.23919/AeroEMC.2019.8788937","DOIUrl":"https://doi.org/10.23919/AeroEMC.2019.8788937","url":null,"abstract":"GNSSs (global navigation satellite systems) are an important worldwide standard for localisation methods. Prospective applications such as air transport with unmanned aircraft systems (UAS) in complex nonstatic urban environments will rely on GNSS signal integrity more than ever. Therefore, a basic approach for the analysis of timevariant GNSS propagation channels in a scaled measurement environment is introduced. A laboratory test bench is set up for the analysis of various generic GPS (Global Positioning System) channel configurations on a scale of 1:10. Time domain zero span measurements and a quasistatic channel characterisation are discussed. Corresponding measurement results are presented for different artificial interference scenarios. Finally, performance mitigation of a hardware GPS receiver due to the modulation of artificial navigation data with the measured channel properties is assessed.","PeriodicalId":436679,"journal":{"name":"2019 ESA Workshop on Aerospace EMC (Aerospace EMC)","volume":"225 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134156960","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 : 2019-05-01DOI: 10.23919/AeroEMC.2019.8788960
M. Pudney, S. King, C. Trenkel, F. Liebold, S. Strandmoe, P. Meyer, M. Ehinger
Scientific spacecraft that measure the local magnetic environment in which they fly need to minimize any disturbance caused by the spacecraft itself. Attitude control reaction wheels, often accommodated to meet pointing requirements, are a known source of disturbance to both the DC and AC magnetic fields. Previous missions (such as on Cassini and MESSENGER) have typically reduced the disturbance effect by using a shield applied externally on standard commercial wheels. We present a reaction wheel assembly that applies a broader strategy of both internal and external disturbance field reductions within the context of the Solar Orbiter mission. Compared to standard commercial wheels with no mitigation, a resulting improvement of the magnetic field generated at the fundamental rotation rate of the reaction wheel by approximately 100dB is predicted.
{"title":"Advances in Reaction Wheel Design for Magnetic Cleanliness","authors":"M. Pudney, S. King, C. Trenkel, F. Liebold, S. Strandmoe, P. Meyer, M. Ehinger","doi":"10.23919/AeroEMC.2019.8788960","DOIUrl":"https://doi.org/10.23919/AeroEMC.2019.8788960","url":null,"abstract":"Scientific spacecraft that measure the local magnetic environment in which they fly need to minimize any disturbance caused by the spacecraft itself. Attitude control reaction wheels, often accommodated to meet pointing requirements, are a known source of disturbance to both the DC and AC magnetic fields. Previous missions (such as on Cassini and MESSENGER) have typically reduced the disturbance effect by using a shield applied externally on standard commercial wheels. We present a reaction wheel assembly that applies a broader strategy of both internal and external disturbance field reductions within the context of the Solar Orbiter mission. Compared to standard commercial wheels with no mitigation, a resulting improvement of the magnetic field generated at the fundamental rotation rate of the reaction wheel by approximately 100dB is predicted.","PeriodicalId":436679,"journal":{"name":"2019 ESA Workshop on Aerospace EMC (Aerospace EMC)","volume":"49 1-2 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123519710","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 : 2019-05-01DOI: 10.23919/AeroEMC.2019.8788959
M. Michelena, M. Á. Rivero, J. de Frutos, A. Ordoñez‐Cencerrado, J. Mesa
Scientific goals in magnetometry require extremely high resolution magnetometers, a very good program of magnetic cleanliness and a powerful processing methodology. When magnetic cleanliness reaches its limits the exhaustive characterisation of the magnetic signature of the different subsystems together with compensation systems (HW) and algorithms (SW) may be the only way to achieve the performance demanded by the scientific objectives. Furthermore, exploration horizons, only within the limits of our Solar System, present scientific challenges in harsh conditions which comprise, among others, extreme swings of temperature. The magnetic properties of materials depend on temperature and the electrical resistance of wires and coils too. Therefore in wide temperature ranges the behaviour of the magnetic signature with temperature needs to be analysed, minimized when possible, and introduced in the retrieval algorithms for an optimal response. The requirements for the subsystems are present in their testing route documentation. However there are not standards or norms with the established procedures to develop these tests. In this work the INTA Space Magnetism Laboratory will overview different methodologies implemented for standard tests, will introduce some of the upcoming and challenging requirements and will present some of the solutions implemented.
{"title":"Adaption of Magnetic Cleanliness Facilities and Procedures to Overcome the New Challenges of the Scientific Missions","authors":"M. Michelena, M. Á. Rivero, J. de Frutos, A. Ordoñez‐Cencerrado, J. Mesa","doi":"10.23919/AeroEMC.2019.8788959","DOIUrl":"https://doi.org/10.23919/AeroEMC.2019.8788959","url":null,"abstract":"Scientific goals in magnetometry require extremely high resolution magnetometers, a very good program of magnetic cleanliness and a powerful processing methodology. When magnetic cleanliness reaches its limits the exhaustive characterisation of the magnetic signature of the different subsystems together with compensation systems (HW) and algorithms (SW) may be the only way to achieve the performance demanded by the scientific objectives. Furthermore, exploration horizons, only within the limits of our Solar System, present scientific challenges in harsh conditions which comprise, among others, extreme swings of temperature. The magnetic properties of materials depend on temperature and the electrical resistance of wires and coils too. Therefore in wide temperature ranges the behaviour of the magnetic signature with temperature needs to be analysed, minimized when possible, and introduced in the retrieval algorithms for an optimal response. The requirements for the subsystems are present in their testing route documentation. However there are not standards or norms with the established procedures to develop these tests. In this work the INTA Space Magnetism Laboratory will overview different methodologies implemented for standard tests, will introduce some of the upcoming and challenging requirements and will present some of the solutions implemented.","PeriodicalId":436679,"journal":{"name":"2019 ESA Workshop on Aerospace EMC (Aerospace EMC)","volume":"16 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116194404","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 : 2019-05-01DOI: 10.23919/AeroEMC.2019.8788924
R. Kebel, Uwe Schwark, M. Schirrmacher
The directive 2014/53/EU [1] formulates in contrast to the EMC directive 2014/30/EU [2] not only the essential requirement of electromagnetic compatibility (EMC), but also the essential requirements of safety, health and efficient use of spectrum for any radio transmitting equipment for the European market. The radio equipment directive 2014/53/EU (RED) shall ensure that equipment is not causing any harm to the public and operates safely without interfering other communication services. Aeronautic equipment had been exempt from application of either directive. The applicability question is a bit more complex for aircraft equipment which transmits radio signals within non-aeronautic frequency bands, e.g. a Wi-Fi access point. Technically, the aircraft mounted access point should not interfere with the ground networks, for example when the aircraft is parking on ground. Annex I of the RED exempts products, parts and equipment on board aircraft which fall within the scope of the article 3 of Regulation (EC) No 216/2008 of the European Parliament and of the Council [3]. This exception clearly applies to aeronautical equipment operating in the aeronautical frequency band. For equipment not covered by Article 3 of Regulation (EC) No 216/2008 of the European Parliament and of the Council [3] operating outside the aeronautical frequency band, the basic requirements are laid down in the RED. Since a decade, there are aeronautical devices, for example wireless access points for Wi-Fi, which transmit signals in the non-aeronautical radio frequency bands, but also could seemingly fall under the scope of the RED and the telecommunication regime. This leads to the question if and how far the RED is applicable. Unnecessary duplication of qualifications against aviation and also non-aviation standards, for example for demonstrating electromagnetic compatibility has to be avoided strictly in order to achieve EMC and avoid incompatibilities. This paper clarifies the applicability of standards and the essential requirements of the RED. It explains measures which have to be taken to avoid conflicting with the technically relevant essential requirements of RED or the aviation requirements. It explains by the example of an aircraft-installed access point formal and technical needs of equipment qualification.
指令2014/53/EU[1]与EMC指令2014/30/EU[2]相比，不仅制定了电磁兼容性(EMC)的基本要求，而且还制定了欧洲市场上任何无线电发射设备的安全，健康和有效使用频谱的基本要求。无线电设备指令2014/53/EU (RED)应确保设备不会对公众造成任何伤害，并且在不干扰其他通信服务的情况下安全运行。航空设备不受这两项指令的适用。对于在非航空频带(例如Wi-Fi接入点)内传输无线电信号的飞机设备，适用性问题稍微复杂一些。从技术上讲，飞机上安装的接入点不应该干扰地面网络，例如当飞机停在地面上时。RED附件1豁免了欧洲议会和理事会法规(EC) No 216/2008第3条范围内的飞机上的产品、零件和设备[3]。这一例外显然适用于在航空频带内工作的航空设备。对于欧洲议会和理事会[3]条例(EC) No 216/2008第3条未涵盖的在航空频段外运行的设备，基本要求在RED中规定。十年来，出现了航空设备，例如Wi-Fi无线接入点，它们在非航空无线电频带中传输信号，但似乎也可能属于RED和电信制度的范围。这就引出了RED是否适用以及在多大程度上适用的问题。必须严格避免不必要地重复航空和非航空标准的资格，例如为了证明电磁兼容性，以实现EMC和避免不兼容。本文阐明了标准的适用性和RED的基本要求。它解释了为避免与RED的技术相关基本要求或航空要求相冲突而必须采取的措施。并以某飞机安装接入点为例，说明了设备鉴定的形式和技术要求。
{"title":"Aviation Equipment and the Application of the Radio Equipment Directive (RED)","authors":"R. Kebel, Uwe Schwark, M. Schirrmacher","doi":"10.23919/AeroEMC.2019.8788924","DOIUrl":"https://doi.org/10.23919/AeroEMC.2019.8788924","url":null,"abstract":"The directive 2014/53/EU [1] formulates in contrast to the EMC directive 2014/30/EU [2] not only the essential requirement of electromagnetic compatibility (EMC), but also the essential requirements of safety, health and efficient use of spectrum for any radio transmitting equipment for the European market. The radio equipment directive 2014/53/EU (RED) shall ensure that equipment is not causing any harm to the public and operates safely without interfering other communication services. Aeronautic equipment had been exempt from application of either directive. The applicability question is a bit more complex for aircraft equipment which transmits radio signals within non-aeronautic frequency bands, e.g. a Wi-Fi access point. Technically, the aircraft mounted access point should not interfere with the ground networks, for example when the aircraft is parking on ground. Annex I of the RED exempts products, parts and equipment on board aircraft which fall within the scope of the article 3 of Regulation (EC) No 216/2008 of the European Parliament and of the Council [3]. This exception clearly applies to aeronautical equipment operating in the aeronautical frequency band. For equipment not covered by Article 3 of Regulation (EC) No 216/2008 of the European Parliament and of the Council [3] operating outside the aeronautical frequency band, the basic requirements are laid down in the RED. Since a decade, there are aeronautical devices, for example wireless access points for Wi-Fi, which transmit signals in the non-aeronautical radio frequency bands, but also could seemingly fall under the scope of the RED and the telecommunication regime. This leads to the question if and how far the RED is applicable. Unnecessary duplication of qualifications against aviation and also non-aviation standards, for example for demonstrating electromagnetic compatibility has to be avoided strictly in order to achieve EMC and avoid incompatibilities. This paper clarifies the applicability of standards and the essential requirements of the RED. It explains measures which have to be taken to avoid conflicting with the technically relevant essential requirements of RED or the aviation requirements. It explains by the example of an aircraft-installed access point formal and technical needs of equipment qualification.","PeriodicalId":436679,"journal":{"name":"2019 ESA Workshop on Aerospace EMC (Aerospace EMC)","volume":"97 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115931699","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 : 2019-05-01DOI: 10.23919/AeroEMC.2019.8788932
H. Kuegler, D. Lentz
A new test facility was designed and built in order to heat up the Solar Orbiter Heat-Shield to 560° Celsius in vacuum conditions. A heated plate of steal with the dimension of 3m x 2.4m was used as a heat source. This heated plate was heated by radiated heat flux of a heating system with seven heating circles consisted of nine heating coils running. The electric current was up to 300A RMS at a voltage up to 60V at the power grid frequency of 50Hz in vacuum conditions. In order to ensure the magnetic requirements of Solar Orbiter it was indicated that no piece of flight hardware shall be exposed to magnetic fields higher than $200 mumathrm{T}$. The decision was taken to monitor the process of development with respect to magnetic cleanliness. The overall magnetic design/modelling process is presented as well as the verification steps performed on the real 600°C Hot Plate Setup.
为了在真空条件下将太阳轨道隔热板加热到560摄氏度，设计并建造了一个新的测试设备。热源采用尺寸为3m x 2.4m的加热钢板。该加热板由一个由九个加热盘管组成的七个加热循环的加热系统的辐射热流加热。在真空条件下，电网频率50Hz，电压60V，电流RMS可达300A。为了保证太阳轨道飞行器的磁场要求，指出任何飞行硬件都不能暴露在高于200美元的磁场中。决定监测磁洁净度的发展过程。介绍了整体磁性设计/建模过程以及在实际600°C热板设置上执行的验证步骤。
{"title":"Determination of Magnetic Effect of the 600°C Hot Plate Setup for Testing the Heat Shield of Solar-Orbiter","authors":"H. Kuegler, D. Lentz","doi":"10.23919/AeroEMC.2019.8788932","DOIUrl":"https://doi.org/10.23919/AeroEMC.2019.8788932","url":null,"abstract":"A new test facility was designed and built in order to heat up the Solar Orbiter Heat-Shield to 560° Celsius in vacuum conditions. A heated plate of steal with the dimension of 3m x 2.4m was used as a heat source. This heated plate was heated by radiated heat flux of a heating system with seven heating circles consisted of nine heating coils running. The electric current was up to 300A RMS at a voltage up to 60V at the power grid frequency of 50Hz in vacuum conditions. In order to ensure the magnetic requirements of Solar Orbiter it was indicated that no piece of flight hardware shall be exposed to magnetic fields higher than $200 mumathrm{T}$. The decision was taken to monitor the process of development with respect to magnetic cleanliness. The overall magnetic design/modelling process is presented as well as the verification steps performed on the real 600°C Hot Plate Setup.","PeriodicalId":436679,"journal":{"name":"2019 ESA Workshop on Aerospace EMC (Aerospace EMC)","volume":"19 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134551789","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 : 2019-05-01DOI: 10.23919/AeroEMC.2019.8788911
M. Cucca, M. Marzot, A. Del Prete, A. Leone, E. Ferrari
The experience done by Thales Alenia Space on magnetic cleanliness [1] and characterization during Rosetta and Bepi Colombo reveal some limitations on the measurement system used. For this reason, it was decided to design and manufacture a new MCF (Magnetic Cleanliness Facility), adequate to enlarge the capabilities to support testing of spacecraft with stringent magnetic requirements, to allow the repeatability of the measurement and the possibility to use user defined magnetic patterns. The main test activities supported by the new facility are: ‐DC (Direct Current) and AC (Alternate Current) magnetic field measurements; ‐Magnetic cleanliness on electronic equipments or mechanical parts of the S/C (Space/Craft) ‐Magnetic field susceptibilty tests (DC or low freq. magnetic fields and AC fields). This paper aims to describe in details the design of this new facility, the validation activities performed and the first testing activities on going in TASInI TO (Thales Alenia Space in Italy Torino).
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