Pub Date : 2009-03-07DOI: 10.1109/AERO.2009.4839608
P. Wu, D. Campbell, T. Merz
A system for automated mission planning is presented with a view to operate Unmanned Aerial Vehicles (UAVs) in the National Airspace System (NAS). This paper describes methods for modelling decision variables, for enroute flight planning under Visual Flight Rules (VFR). For demonstration purposes, the task of delivering a medical package to a remote location was chosen. Decision variables include fuel consumption, flight time, wind and weather conditions, terrain elevation, airspace classification and the flight trajectories of other aircraft. The decision variables are transformed, using a Multi-Criteria Decision Making (MCDM) cost function, into a single cost value for a grid-based search algorithm (e.g. A*). It is shown that the proposed system provides a means for fast, autonomous generation of near-optimal flight plans, which in turn are a key enabler in the operation of UAVs in the NAS.
{"title":"On-board multi-objective mission planning for Unmanned Aerial Vehicles","authors":"P. Wu, D. Campbell, T. Merz","doi":"10.1109/AERO.2009.4839608","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839608","url":null,"abstract":"A system for automated mission planning is presented with a view to operate Unmanned Aerial Vehicles (UAVs) in the National Airspace System (NAS). This paper describes methods for modelling decision variables, for enroute flight planning under Visual Flight Rules (VFR). For demonstration purposes, the task of delivering a medical package to a remote location was chosen. Decision variables include fuel consumption, flight time, wind and weather conditions, terrain elevation, airspace classification and the flight trajectories of other aircraft. The decision variables are transformed, using a Multi-Criteria Decision Making (MCDM) cost function, into a single cost value for a grid-based search algorithm (e.g. A*). It is shown that the proposed system provides a means for fast, autonomous generation of near-optimal flight plans, which in turn are a key enabler in the operation of UAVs in the NAS.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"83 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-03-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121708171","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 : 2009-03-07DOI: 10.1109/AERO.2009.4839517
Kimberly J. Cornett, Guoyuan Fu, I. Escorcia, H. Alan Mantooth
A BiCMOS fully differential amplifier was designed for use with a specified power supply of 3.3 V, requiring a 100 μA current bias and utilizing only heterojunction bipolar npn and PMOS transistors because of their demonstrated performance in both extreme temperature ranges (−180 °C to +120 °C) and radiation-rich environments. One unique feature of this design is that two common-mode feedback circuits were employed to control both the input stage and output stage independently. Regulating the common-mode level between the input and output stages produced better stability over temperature for each stage. Special considerations were taken in the layout to increase the immunity of latch-up and noise and decrease mismatch. The BiCMOS amplifier described successfully demonstrates the use of the commercially available IBM SiGe 5AM process to produce reliable operation in extreme temperature and radiation environments.
{"title":"SiGe BiCMOS fully differential amplifier for extreme temperature range applications","authors":"Kimberly J. Cornett, Guoyuan Fu, I. Escorcia, H. Alan Mantooth","doi":"10.1109/AERO.2009.4839517","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839517","url":null,"abstract":"A BiCMOS fully differential amplifier was designed for use with a specified power supply of 3.3 V, requiring a 100 μA current bias and utilizing only heterojunction bipolar npn and PMOS transistors because of their demonstrated performance in both extreme temperature ranges (−180 °C to +120 °C) and radiation-rich environments. One unique feature of this design is that two common-mode feedback circuits were employed to control both the input stage and output stage independently. Regulating the common-mode level between the input and output stages produced better stability over temperature for each stage. Special considerations were taken in the layout to increase the immunity of latch-up and noise and decrease mismatch. The BiCMOS amplifier described successfully demonstrates the use of the commercially available IBM SiGe 5AM process to produce reliable operation in extreme temperature and radiation environments.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"577 1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-03-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122716274","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 : 2009-03-07DOI: 10.1109/AERO.2009.4839688
J.B. Schroede, G.J. Clark
Designing and implementing health management systems for current and future aircraft poses many challenges, including interfacing with legacy onboard and offboard hardware and software systems, determining and justifying new functional requirements, and validating and verifying a robust, scalable system. Lessons learned from a current research and development program as well as prior health management system development experiences are presented as a road map to focus on the process of system development and integration. This paper also provides an overview of the concept and the coordination required to develop a working health management system.
{"title":"Developing health management for current and future inventory aircraft","authors":"J.B. Schroede, G.J. Clark","doi":"10.1109/AERO.2009.4839688","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839688","url":null,"abstract":"Designing and implementing health management systems for current and future aircraft poses many challenges, including interfacing with legacy onboard and offboard hardware and software systems, determining and justifying new functional requirements, and validating and verifying a robust, scalable system. Lessons learned from a current research and development program as well as prior health management system development experiences are presented as a road map to focus on the process of system development and integration. This paper also provides an overview of the concept and the coordination required to develop a working health management system.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"69 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-03-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122739812","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 : 2009-03-07DOI: 10.1109/AERO.2009.4839467
Stefan R. Martin, A. Booth, F. Loya
The Planet Detection Testbed has been developed to simulate and test the detection process for an infrared nulling interferometer observing an earthlike planet orbiting a nearby star within about 15 pc of the solar system. The testbed combines eight beams of infrared light, four from the star and four from the planet, simulating an ‘Xa-rray’ telescope spacecraft formation. The detection process involves stable nulling of the starlight, rotation of the spacecraft formation, averaging over a few hours and testing of the signal against predicted exoplanet signatures. The testbed simulates all parts of the detection process except operation in broadband light, which is a planned upgrade for the future. This paper describes the latest results and plans for exoplanet signal simulation, deep starlight nulling and planet detection at star to planet contrast ratios of one million to one. These results are planned to demonstrate the feasibility of exoplanet detection using nulling interferometry at near-flightlike contrast ratios.
{"title":"Demonstration of the exoplanet detection process using four-beam nulling interferometry","authors":"Stefan R. Martin, A. Booth, F. Loya","doi":"10.1109/AERO.2009.4839467","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839467","url":null,"abstract":"The Planet Detection Testbed has been developed to simulate and test the detection process for an infrared nulling interferometer observing an earthlike planet orbiting a nearby star within about 15 pc of the solar system. The testbed combines eight beams of infrared light, four from the star and four from the planet, simulating an ‘Xa-rray’ telescope spacecraft formation. The detection process involves stable nulling of the starlight, rotation of the spacecraft formation, averaging over a few hours and testing of the signal against predicted exoplanet signatures. The testbed simulates all parts of the detection process except operation in broadband light, which is a planned upgrade for the future. This paper describes the latest results and plans for exoplanet signal simulation, deep starlight nulling and planet detection at star to planet contrast ratios of one million to one. These results are planned to demonstrate the feasibility of exoplanet detection using nulling interferometry at near-flightlike contrast ratios.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"144 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-03-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123925795","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 : 2009-03-07DOI: 10.1109/AERO.2009.4839478
P. Willett, W. Blair, Xin Zhang
Via jointly processing multiple (sum, azimuth- and elevation-difference) monopulse matched filter samples it is possible to extract and localize several (more than two) targets spaced more closely than the classical interpretation of radar resolution. This paper derives the Cramér-Rao lower bound (CRLB) for sampled monopulse radar data.
{"title":"Performance limits for monopulse matched filter samples","authors":"P. Willett, W. Blair, Xin Zhang","doi":"10.1109/AERO.2009.4839478","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839478","url":null,"abstract":"Via jointly processing multiple (sum, azimuth- and elevation-difference) monopulse matched filter samples it is possible to extract and localize several (more than two) targets spaced more closely than the classical interpretation of radar resolution. This paper derives the Cramér-Rao lower bound (CRLB) for sampled monopulse radar data.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"31 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-03-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123946493","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 : 2009-03-07DOI: 10.1109/AERO.2009.4839350
L. Herrell, J. Peden
This paper summarizes the development from 2000 to the present of rideshare capabilities by various Government Agencies and Organizations. This development will allow acceptable, low-cost access to space for small satellites and payloads. The paper reviews the needs for such capabilities and provides an overview of the development and status of the enabling technologies, hardware, etc. required to achieve the desired capability. It reviews the development and status of each principal element necessary in developing an acceptable, low cost, access to space capability for small satellites and payloads.
{"title":"The development of small-payload rideshare capabilities: A 2000–2008 summary","authors":"L. Herrell, J. Peden","doi":"10.1109/AERO.2009.4839350","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839350","url":null,"abstract":"This paper summarizes the development from 2000 to the present of rideshare capabilities by various Government Agencies and Organizations. This development will allow acceptable, low-cost access to space for small satellites and payloads. The paper reviews the needs for such capabilities and provides an overview of the development and status of the enabling technologies, hardware, etc. required to achieve the desired capability. It reviews the development and status of each principal element necessary in developing an acceptable, low cost, access to space capability for small satellites and payloads.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"39 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-03-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124299698","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 : 2009-03-07DOI: 10.1109/AERO.2009.4839306
R. Bonitz, Lori. R. Shiraishi, Matthew. L. Robinson, Joseph. Carsten, R. Volpe, A. Trebi-Ollennu, R. Bonitz, Lori. R. Shiraishi, Matthew. L. Robinson, Joseph. Carsten, R. Arvidson
The Phoenix Mars Lander Robotic Arm (RA) has operated for 149 sols since the Lander touched down on the north polar region of Mars on May 25, 2008. During its mission it has dug numerous trenches in the Martian regolith, acquired samples of Martian dry and icy soil, and delivered them to the Thermal Evolved Gas Analyzer (TEGA) and the Microscopy, Electrochemistry, and Conductivity Analyzer (MECA). The RA inserted the Thermal and Electrical Conductivity Probe (TECP) into the Martian regolith and positioned it at various heights above the surface for relative humidity measurements. The RA was used to point the Robotic Arm Camera to take images of the surface, trenches, samples within the scoop, and other objects of scientific interest within its workspace. Data from the RA sensors during trenching, scraping, and trench cave-in experiments have been used to infer mechanical properties of the Martian soil. This paper describes the design and operations of the RA as a critical component of the Phoenix Mars Lander necessary to achieve the scientific goals of the mission.
{"title":"The Phoenix Mars Lander Robotic Arm","authors":"R. Bonitz, Lori. R. Shiraishi, Matthew. L. Robinson, Joseph. Carsten, R. Volpe, A. Trebi-Ollennu, R. Bonitz, Lori. R. Shiraishi, Matthew. L. Robinson, Joseph. Carsten, R. Arvidson","doi":"10.1109/AERO.2009.4839306","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839306","url":null,"abstract":"The Phoenix Mars Lander Robotic Arm (RA) has operated for 149 sols since the Lander touched down on the north polar region of Mars on May 25, 2008. During its mission it has dug numerous trenches in the Martian regolith, acquired samples of Martian dry and icy soil, and delivered them to the Thermal Evolved Gas Analyzer (TEGA) and the Microscopy, Electrochemistry, and Conductivity Analyzer (MECA). The RA inserted the Thermal and Electrical Conductivity Probe (TECP) into the Martian regolith and positioned it at various heights above the surface for relative humidity measurements. The RA was used to point the Robotic Arm Camera to take images of the surface, trenches, samples within the scoop, and other objects of scientific interest within its workspace. Data from the RA sensors during trenching, scraping, and trench cave-in experiments have been used to infer mechanical properties of the Martian soil. This paper describes the design and operations of the RA as a critical component of the Phoenix Mars Lander necessary to achieve the scientific goals of the mission.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"34 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-03-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125589015","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 : 2009-03-07DOI: 10.1109/AERO.2009.4839703
E. de Pasquale, L. Francillout, J. Wasbauer, J. Hatton, J. Albers, D. Steele
On 29th of September, 2008, the European spacecraft ATV-JV (Automated Transfer Vehicle Jules Verne) successfully completed its mission with a safe destructive re-entry into the South Pacific Ocean Uninhabited Area (SPOUA). Since the ATV-JV was the first ATV mission, the main events of re-entry have been observed by two aircrafts (equipped internally with a large number of optical devices) and from International Space Station (ISS): assessment of the break-up altitudes and identification of explosion events are the main objectives.
{"title":"ATV Jules Verne reentry observation: Mission design and trajectory analysis","authors":"E. de Pasquale, L. Francillout, J. Wasbauer, J. Hatton, J. Albers, D. Steele","doi":"10.1109/AERO.2009.4839703","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839703","url":null,"abstract":"On 29th of September, 2008, the European spacecraft ATV-JV (Automated Transfer Vehicle Jules Verne) successfully completed its mission with a safe destructive re-entry into the South Pacific Ocean Uninhabited Area (SPOUA). Since the ATV-JV was the first ATV mission, the main events of re-entry have been observed by two aircrafts (equipped internally with a large number of optical devices) and from International Space Station (ISS): assessment of the break-up altitudes and identification of explosion events are the main objectives.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"13 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-03-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126181659","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 : 2009-03-07DOI: 10.1109/AERO.2009.4839357
R. L. Balthazor, M. McHarg, C. Godbold, David Barnhart, T. Vladimirova
Distributed small satellite mission concepts are emerging for commercial, scientific, and military applications requiring constellations of many hundreds of satellites. Massively distributed missions allow both simultaneous multipoint observations and significant redundancy. This paper presents an application case study based on the US Air Force Academy's (USAFA) Ionospheric Multiple Plasma Sensors (IMPS) mission. IMPS is an integration of the satellite-on-a-Printed Circuit Board (PCBSat) miniaturization approach developed at the University of Surrey with the Miniaturized Electrostatic Analyzer (MESA) sensor developed at USAFA.
{"title":"Distributed space-based Ionospheric Multiple Plasma Sensor networks","authors":"R. L. Balthazor, M. McHarg, C. Godbold, David Barnhart, T. Vladimirova","doi":"10.1109/AERO.2009.4839357","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839357","url":null,"abstract":"Distributed small satellite mission concepts are emerging for commercial, scientific, and military applications requiring constellations of many hundreds of satellites. Massively distributed missions allow both simultaneous multipoint observations and significant redundancy. This paper presents an application case study based on the US Air Force Academy's (USAFA) Ionospheric Multiple Plasma Sensors (IMPS) mission. IMPS is an integration of the satellite-on-a-Printed Circuit Board (PCBSat) miniaturization approach developed at the University of Surrey with the Miniaturized Electrostatic Analyzer (MESA) sensor developed at USAFA.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"12 11 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-03-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125760579","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 : 2009-03-07DOI: 10.1109/AERO.2009.4839561
Swaminathan Balaraman, J. Shanmugam, K. Harendranath, Kiran
In an attempt to avoid the financial hurdle imposed by the physical constraints on objects orbiting in Low Earth Orbit (LEO), it is preferred to use High Elliptical Orbit (HEO) for broader coverage. It takes a huge amount of energy to be put objects in HEO. To provide similar benefits at a very low cost, the ‘Special Orbit’ was offered as an alternate. This paper examines the usability of launching a Hybrid control enabled multiple payload micro satellite in to elliptical orbit. The perigee and apogee distances are modified so that the orbital period is 1/3 of a day instead of 12 hours. This orbit provides the benefits of both low and medium altitudes. In addition to this the orbit doesn't require any onboard liquid fuel or thrusters as there is no orbit manoeuvres required in its mission time. Ground Simulations are done for various initial conditions and time of availability over targets is evaluated.
{"title":"Space Mission Analysis & design for tactical spacecraft","authors":"Swaminathan Balaraman, J. Shanmugam, K. Harendranath, Kiran","doi":"10.1109/AERO.2009.4839561","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839561","url":null,"abstract":"In an attempt to avoid the financial hurdle imposed by the physical constraints on objects orbiting in Low Earth Orbit (LEO), it is preferred to use High Elliptical Orbit (HEO) for broader coverage. It takes a huge amount of energy to be put objects in HEO. To provide similar benefits at a very low cost, the ‘Special Orbit’ was offered as an alternate. This paper examines the usability of launching a Hybrid control enabled multiple payload micro satellite in to elliptical orbit. The perigee and apogee distances are modified so that the orbital period is 1/3 of a day instead of 12 hours. This orbit provides the benefits of both low and medium altitudes. In addition to this the orbit doesn't require any onboard liquid fuel or thrusters as there is no orbit manoeuvres required in its mission time. Ground Simulations are done for various initial conditions and time of availability over targets is evaluated.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"7 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-03-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126029864","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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