Pub Date : 2001-03-10DOI: 10.1109/AERO.2001.931422
A.L. White
A method is proposed for quantifying the expected number of accidents for a transportation system during some operating period. The operating period is divided into two parts. There is normal operation where everything is working correctly. These intervals can be studied deterministically by arguments-from-design or by tests. There is unsafe operation where equipment has failed, an error has occurred, or traffic perturbations have produced unusual circumstances. Such stochastic phenomena can be studied by experiments or simulation. These two types of operation create a natural partition. This paper proposes a Monte Carlo method based on this partition that appears appropriate for studying scarce events. Estimators for this method are developed. It is shown they are unbiased, and confidence intervals derived. There is also a discussion of integrating random failures with traffic flow in discrete event simulation.
{"title":"A statistics of rare events method for transportation systems","authors":"A.L. White","doi":"10.1109/AERO.2001.931422","DOIUrl":"https://doi.org/10.1109/AERO.2001.931422","url":null,"abstract":"A method is proposed for quantifying the expected number of accidents for a transportation system during some operating period. The operating period is divided into two parts. There is normal operation where everything is working correctly. These intervals can be studied deterministically by arguments-from-design or by tests. There is unsafe operation where equipment has failed, an error has occurred, or traffic perturbations have produced unusual circumstances. Such stochastic phenomena can be studied by experiments or simulation. These two types of operation create a natural partition. This paper proposes a Monte Carlo method based on this partition that appears appropriate for studying scarce events. Estimators for this method are developed. It is shown they are unbiased, and confidence intervals derived. There is also a discussion of integrating random failures with traffic flow in discrete event simulation.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"21 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125914604","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 : 2001-03-10DOI: 10.1109/AERO.2001.931349
N. Mysoor, S. Kayalar, C. Andricos, G. Walsh
A new Spacecraft Transponding Modem (STM) is being developed for deep space communication applications. The STM receives an X-band (7.17 GHz) uplink signal and generates an X-band (8.4 GHz) and a Ka-band (32.0 GHz) coherent or noncoherent downlink signals. The STM architecture incorporates three miniature dielectric-resonator-oscillators (DRO). These DROs are used in receiver and exciter frequency synthesis phase-locked loops (PLL) in the STM. The DROs are designed with custom developed monolithic microwave integrated circuit (MMIC) negative resistance oscillator chips. DROs are laid out on alumina substrates in RF cavity fixtures of 18 mm/spl times/18 mm/spl times/8 mm. The receiver and the exciter DRO designs meet the following requirements: frequency stability of /spl plusmn/2 ppm//spl deg/C, the free running single-sideband phase noise of -50 dBc at 1-kHz offset frequency, tuning linearity of /spl plusmn/10% over the /spl plusmn/1.75-MHz locking range, and output power of +10 dBm/spl plusmn/1 dB over a design temperature range of -55/spl deg/C to +85/spl deg/C. The phase-locked loop DRO frequency synthesizers are designed using sampling downconverter and phase detector MMIC chips. These PLL frequency synthesizers meet the following requirements: pull-in range of /spl plusmn/1.75 MHz, loop noise bandwidth of 100 kHz, and a single-sideband phase noise of -144 dBc at 1-kHz offset frequency.
{"title":"Performance of dielectric resonator oscillator for spacecraft transponding modem","authors":"N. Mysoor, S. Kayalar, C. Andricos, G. Walsh","doi":"10.1109/AERO.2001.931349","DOIUrl":"https://doi.org/10.1109/AERO.2001.931349","url":null,"abstract":"A new Spacecraft Transponding Modem (STM) is being developed for deep space communication applications. The STM receives an X-band (7.17 GHz) uplink signal and generates an X-band (8.4 GHz) and a Ka-band (32.0 GHz) coherent or noncoherent downlink signals. The STM architecture incorporates three miniature dielectric-resonator-oscillators (DRO). These DROs are used in receiver and exciter frequency synthesis phase-locked loops (PLL) in the STM. The DROs are designed with custom developed monolithic microwave integrated circuit (MMIC) negative resistance oscillator chips. DROs are laid out on alumina substrates in RF cavity fixtures of 18 mm/spl times/18 mm/spl times/8 mm. The receiver and the exciter DRO designs meet the following requirements: frequency stability of /spl plusmn/2 ppm//spl deg/C, the free running single-sideband phase noise of -50 dBc at 1-kHz offset frequency, tuning linearity of /spl plusmn/10% over the /spl plusmn/1.75-MHz locking range, and output power of +10 dBm/spl plusmn/1 dB over a design temperature range of -55/spl deg/C to +85/spl deg/C. The phase-locked loop DRO frequency synthesizers are designed using sampling downconverter and phase detector MMIC chips. These PLL frequency synthesizers meet the following requirements: pull-in range of /spl plusmn/1.75 MHz, loop noise bandwidth of 100 kHz, and a single-sideband phase noise of -144 dBc at 1-kHz offset frequency.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"11 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125535638","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 : 2001-03-10DOI: 10.1109/AERO.2001.931191
D. Keymeulen, A. Stoica, M. Buehler, R. Zebulum, V. Duong
In-situ exploration as required for example by missions to comets and planets with unknown environmental conditions, has recently been approached with new ideas, such as the use of biology-inspired mechanisms for hardware sensor adaptation. The application of evolution-inspired formalisms to hardware design and self-configuration lead to the concept of evolvable hardware (EHW). EHW refers to self reconfiguration of electronic hardware by evolutionary/genetic reconfiguration mechanisms. In this paper we describe the initial development of efficient mechanisms for smart on-board adaptive sensing, adaptively controlling the reconfigurable pre-processing analog electronics using evolvable hardware, which will lead to higher quality, lean data.
{"title":"Evolutionary mechanisms for smart on-board adaptive sensing applied to the MECA electrometer","authors":"D. Keymeulen, A. Stoica, M. Buehler, R. Zebulum, V. Duong","doi":"10.1109/AERO.2001.931191","DOIUrl":"https://doi.org/10.1109/AERO.2001.931191","url":null,"abstract":"In-situ exploration as required for example by missions to comets and planets with unknown environmental conditions, has recently been approached with new ideas, such as the use of biology-inspired mechanisms for hardware sensor adaptation. The application of evolution-inspired formalisms to hardware design and self-configuration lead to the concept of evolvable hardware (EHW). EHW refers to self reconfiguration of electronic hardware by evolutionary/genetic reconfiguration mechanisms. In this paper we describe the initial development of efficient mechanisms for smart on-board adaptive sensing, adaptively controlling the reconfigurable pre-processing analog electronics using evolvable hardware, which will lead to higher quality, lean data.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"18 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122435789","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 : 2001-03-10DOI: 10.1109/AERO.2001.931711
B. Horais, R. Twiggs, C. Byvik
Schafer Corporation and Stanford University's SSDL were awarded a contract to investigate new, revolutionary approaches to facilitate low-cost space technology demonstrations. The Schafer Team is developing approaches that can restore the timelines and risk-acceptance environment necessary to stimulate innovation for space technology development programs. We are proactively matching a critical category of payload developers with space launch services: the new/innovative developers of space component technology that do not have the knowledge, resources, or contacts necessary to successfully test their technologies in space. Restoration and expansion of the U.S. Space industry's innovative foundations must include rapid access to space for testing of new ideas and must be closely coupled to hands-on university programs in space technologies that will train future generations of US space technologists. This paper addresses an innovative technology "pull" approach to achieving these objectives.
{"title":"Proactive rideshare opportunity brokering services (PROBS) for secondary payloads","authors":"B. Horais, R. Twiggs, C. Byvik","doi":"10.1109/AERO.2001.931711","DOIUrl":"https://doi.org/10.1109/AERO.2001.931711","url":null,"abstract":"Schafer Corporation and Stanford University's SSDL were awarded a contract to investigate new, revolutionary approaches to facilitate low-cost space technology demonstrations. The Schafer Team is developing approaches that can restore the timelines and risk-acceptance environment necessary to stimulate innovation for space technology development programs. We are proactively matching a critical category of payload developers with space launch services: the new/innovative developers of space component technology that do not have the knowledge, resources, or contacts necessary to successfully test their technologies in space. Restoration and expansion of the U.S. Space industry's innovative foundations must include rapid access to space for testing of new ideas and must be closely coupled to hands-on university programs in space technologies that will train future generations of US space technologists. This paper addresses an innovative technology \"pull\" approach to achieving these objectives.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"390 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122768283","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 : 2001-03-10DOI: 10.1109/AERO.2001.931541
R. Laskin
Optical and infrared interferometry will open new vistas for astronomy over the next decade. Space based interferometers, operating unfettered by the Earth's atmosphere, will offer the greatest scientific payoff. They also present the greatest technological challenge: laser metrology systems must perform with sub-nanometer precision; mechanical vibrations must be controlled to nanometers requiring orders of magnitude disturbance rejection; a multitude of actuators and sensors must operate flawlessly and in concert. The Jet Propulsion Laboratory along with its industry partners, LMA and TRW, are addressing these challenges with a development program that plans to establish technology readiness for the Space Interferometry Mission by end of 2003.
{"title":"Technology development for the Space Interferometry Mission (SIM)-status and plans","authors":"R. Laskin","doi":"10.1109/AERO.2001.931541","DOIUrl":"https://doi.org/10.1109/AERO.2001.931541","url":null,"abstract":"Optical and infrared interferometry will open new vistas for astronomy over the next decade. Space based interferometers, operating unfettered by the Earth's atmosphere, will offer the greatest scientific payoff. They also present the greatest technological challenge: laser metrology systems must perform with sub-nanometer precision; mechanical vibrations must be controlled to nanometers requiring orders of magnitude disturbance rejection; a multitude of actuators and sensors must operate flawlessly and in concert. The Jet Propulsion Laboratory along with its industry partners, LMA and TRW, are addressing these challenges with a development program that plans to establish technology readiness for the Space Interferometry Mission by end of 2003.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"166 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122587634","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 : 2001-03-10DOI: 10.1109/AERO.2001.931539
Brian Cox, Parviz Danesh, E. Konefat
This paper describes Instrument Control Electronics (ICE) for the Starlight mission. The mission is a dual-spacecraft formation-flying Michelson interferometer designed to perform the first long-baseline optical interferometry in space. Starlight is planned for launch in late 2005, and will demonstrate enabling technologies in the areas of separated spacecraft control systems, precise optical pathlength control, and interspacecraft laser metrology, all of which are critical to the performance of future planned NASA missions such as the Terrestrial Planet Finder. The interferometer flight instrument is based on laboratory instrument that been developed over the past ten years. The flight instrument is planning maximum use of the developed hardware and software. There are many challenges in designing flight equivalent instrument electronics that are rugged, lower mass, lower power and reliable. This paper describes the methods, approaches and processes that are being used to design instrument electronics that will meet the project requirements for cost, mass, power and performance.
{"title":"Converting from a lab experiment to a flight instrument","authors":"Brian Cox, Parviz Danesh, E. Konefat","doi":"10.1109/AERO.2001.931539","DOIUrl":"https://doi.org/10.1109/AERO.2001.931539","url":null,"abstract":"This paper describes Instrument Control Electronics (ICE) for the Starlight mission. The mission is a dual-spacecraft formation-flying Michelson interferometer designed to perform the first long-baseline optical interferometry in space. Starlight is planned for launch in late 2005, and will demonstrate enabling technologies in the areas of separated spacecraft control systems, precise optical pathlength control, and interspacecraft laser metrology, all of which are critical to the performance of future planned NASA missions such as the Terrestrial Planet Finder. The interferometer flight instrument is based on laboratory instrument that been developed over the past ten years. The flight instrument is planning maximum use of the developed hardware and software. There are many challenges in designing flight equivalent instrument electronics that are rugged, lower mass, lower power and reliable. This paper describes the methods, approaches and processes that are being used to design instrument electronics that will meet the project requirements for cost, mass, power and performance.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"2 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128459595","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 : 2001-03-10DOI: 10.1109/AERO.2001.931277
E. Criscuolo, K. Hogie, R. Parise
An Internet datagram delivery service between space systems only provides end-to-end addressability. Building systems and performing actual spacecraft operations requires a variety of services operating over the Internet datagram delivery service. This paper discusses ways to use the capabilities of the upper layer Internet protocols to support the varied communication needs of satellites. It focuses on protocols in the transport layer (layer 4) and application layer (layer 7) which use the basic packet delivery capabilities of the Internet Protocol (IP) and the network layer (layer 3). The transport layer primarily adds data stream multiplexing and reliable data delivery options for use by applications. Data stream multiplexing is provided by the port mechanism in the User Datagram Protocol (UDP) and the Transport Control Protocol (TCP). UDP provides a basic packet delivery service similar to that used in today's spacecraft while TCP provides an automatic retransmission capability for reliable data stream delivery. Data streaming is also supported by the Real Time Protocol (RTP) which operates over UDP. Each of these protocols has benefits and limitations in various space communication environments with a range of link errors, propagation delays, and bit rates. Transport protocol selection and operational usage are discussed with respect to satellite communication requirements. Finally, actual spacecraft operations are performed by using applications running over transport protocols. The use of standard Internet applications such as NTP, FTP, SMTP, and telnet is discussed with respect to satellite operational requirements. The actual use and performance of many of these protocols by the Operating Missions as Nodes on the Internet (OMNI) project at NASA/GSFC on orbit with the UoSAT-12 spacecraft is also described.
{"title":"Transport protocols and applications for Internet use in space","authors":"E. Criscuolo, K. Hogie, R. Parise","doi":"10.1109/AERO.2001.931277","DOIUrl":"https://doi.org/10.1109/AERO.2001.931277","url":null,"abstract":"An Internet datagram delivery service between space systems only provides end-to-end addressability. Building systems and performing actual spacecraft operations requires a variety of services operating over the Internet datagram delivery service. This paper discusses ways to use the capabilities of the upper layer Internet protocols to support the varied communication needs of satellites. It focuses on protocols in the transport layer (layer 4) and application layer (layer 7) which use the basic packet delivery capabilities of the Internet Protocol (IP) and the network layer (layer 3). The transport layer primarily adds data stream multiplexing and reliable data delivery options for use by applications. Data stream multiplexing is provided by the port mechanism in the User Datagram Protocol (UDP) and the Transport Control Protocol (TCP). UDP provides a basic packet delivery service similar to that used in today's spacecraft while TCP provides an automatic retransmission capability for reliable data stream delivery. Data streaming is also supported by the Real Time Protocol (RTP) which operates over UDP. Each of these protocols has benefits and limitations in various space communication environments with a range of link errors, propagation delays, and bit rates. Transport protocol selection and operational usage are discussed with respect to satellite communication requirements. Finally, actual spacecraft operations are performed by using applications running over transport protocols. The use of standard Internet applications such as NTP, FTP, SMTP, and telnet is discussed with respect to satellite operational requirements. The actual use and performance of many of these protocols by the Operating Missions as Nodes on the Internet (OMNI) project at NASA/GSFC on orbit with the UoSAT-12 spacecraft is also described.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"19 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128792543","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 : 2001-03-10DOI: 10.1109/AERO.2001.931211
M. Henry, D. Brinza
The Deep Space One mission is demonstrating the long-duration use of an ion propulsion subsystem (IPS). The NASA Solar Electric Propulsion Technology Applications Readiness Project developed the NSTAR Diagnostics Package (NDP) to monitor the effects of the IPS on the spacecraft environment. The NDP measures contamination, plasma characteristics, electric fields, and magnetic fields. This paper describes the different electrostatic and electromagnetic emissions of the ion engine for each of the thrust levels at which the engine has operated in space and in the test chamber. It shows the E and B fields data from the spectrometer and the associated time domain samples. It identifies the unexpected differences between the engine emissions for different thrust levels. It shows the peculiarities of the transitions from one thrust level to another. Also, it shows the differences in the space and ground test emissions. Examples of other spacecraft emissions are shown for comparisons to the ion engine emissions.
{"title":"DS1 ion propulsion emissions characterization","authors":"M. Henry, D. Brinza","doi":"10.1109/AERO.2001.931211","DOIUrl":"https://doi.org/10.1109/AERO.2001.931211","url":null,"abstract":"The Deep Space One mission is demonstrating the long-duration use of an ion propulsion subsystem (IPS). The NASA Solar Electric Propulsion Technology Applications Readiness Project developed the NSTAR Diagnostics Package (NDP) to monitor the effects of the IPS on the spacecraft environment. The NDP measures contamination, plasma characteristics, electric fields, and magnetic fields. This paper describes the different electrostatic and electromagnetic emissions of the ion engine for each of the thrust levels at which the engine has operated in space and in the test chamber. It shows the E and B fields data from the spectrometer and the associated time domain samples. It identifies the unexpected differences between the engine emissions for different thrust levels. It shows the peculiarities of the transitions from one thrust level to another. Also, it shows the differences in the space and ground test emissions. Examples of other spacecraft emissions are shown for comparisons to the ion engine emissions.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"28 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130514420","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 : 2001-03-10DOI: 10.1109/AERO.2001.931424
M.J. Zukoski, Robert C. Durst
Satellite links and other "advantaged" resources are increasingly becoming available in tactical networks. When such resources are used to multicast data, significant reductions in traffic and delay are possible, though not guaranteed. Furthermore, use of these resources is relatively expensive and should be efficiently allocated. This paper presents ARDUP, the Advantaged Resource Discovery and Use Protocol, which re-forms the existing terrestrial route to include the advantaged resource in an efficient manner. It addresses the cost-effectiveness of the advantaged resource by introducing a method of global cost assessment of the multicast paths. This assessment provides a measure of the relative benefit - if any - that using the advantaged resource will bring. The paper also describes the admission control mechanism by which access to the advantaged resource is managed. Results from an OPNET simulation study are then presented to illustrate the performance and benefits of the protocol.
{"title":"Multicasting with advantaged resources","authors":"M.J. Zukoski, Robert C. Durst","doi":"10.1109/AERO.2001.931424","DOIUrl":"https://doi.org/10.1109/AERO.2001.931424","url":null,"abstract":"Satellite links and other \"advantaged\" resources are increasingly becoming available in tactical networks. When such resources are used to multicast data, significant reductions in traffic and delay are possible, though not guaranteed. Furthermore, use of these resources is relatively expensive and should be efficiently allocated. This paper presents ARDUP, the Advantaged Resource Discovery and Use Protocol, which re-forms the existing terrestrial route to include the advantaged resource in an efficient manner. It addresses the cost-effectiveness of the advantaged resource by introducing a method of global cost assessment of the multicast paths. This assessment provides a measure of the relative benefit - if any - that using the advantaged resource will bring. The paper also describes the admission control mechanism by which access to the advantaged resource is managed. Results from an OPNET simulation study are then presented to illustrate the performance and benefits of the protocol.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"12 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130528015","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 : 2001-03-10DOI: 10.1109/AERO.2001.931221
D. Carico, Chengjian He, P. Blemel
Work is ongoing to develop a web-based capability to support flight testing and mishap investigations. Fewer new aircraft are being procured today compared to aircraft procurement a couple decades ago. As the older members of the test force retire or change jobs, more pressure is placed on the more junior engineers to conduct the testing. Flight test training is accomplished at government and commercial test pilot schools, but after graduating the flight test engineers and pilots must primarily work with on-the-job training. One approach to improve flight test training support, currently being developed as part of a small business innovative research program, involves combining advanced technology programs associated with a physics-based analysis model structure and the World Wide Web. This paper discusses the results of the ongoing program to enhance and integrate an advanced simulation model structure with a collaborative network and with advanced microprocessors.
{"title":"Web-based flight test training & mishap investigation support","authors":"D. Carico, Chengjian He, P. Blemel","doi":"10.1109/AERO.2001.931221","DOIUrl":"https://doi.org/10.1109/AERO.2001.931221","url":null,"abstract":"Work is ongoing to develop a web-based capability to support flight testing and mishap investigations. Fewer new aircraft are being procured today compared to aircraft procurement a couple decades ago. As the older members of the test force retire or change jobs, more pressure is placed on the more junior engineers to conduct the testing. Flight test training is accomplished at government and commercial test pilot schools, but after graduating the flight test engineers and pilots must primarily work with on-the-job training. One approach to improve flight test training support, currently being developed as part of a small business innovative research program, involves combining advanced technology programs associated with a physics-based analysis model structure and the World Wide Web. This paper discusses the results of the ongoing program to enhance and integrate an advanced simulation model structure with a collaborative network and with advanced microprocessors.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"145 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123814880","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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