Pub Date : 2009-03-07DOI: 10.1109/AERO.2009.4839434
D. Dibiase, J. Laramee
In 2011 NASA will launch the Mars Science Laboratory (MSL) as part of its Mars Exploration Program to learn more about the red planet's environment and geological history. To fulfill that goal, the MSL rover, built by NASA's Jet Propulsion Laboratory (JPL), is outfitted with the most extensive array of scientific instruments ever landed on the Martian surface. The Mars Hand Lens Imager (MAHLI), mounted on the end of the rover's robotic arm, is one of the primary science cameras for MSL. This camera affords many improvements over those used on previous Mars missions, particularly the ability to focus throughout a wide spatial range. A novel mechanism uses one motor to actuate an internal lens group, enabling focus capability, and manipulate a protective dust cover. This mechanism is designed to operate in the severe thermal environment of the MSL mission (−120° C to +40° C) and to survive for one Martian year with 3x margin (about 2000 Earth days) using non-standard materials and techniques in order to meet mass and optical requirements. Several issues involving lubrication and wear were encountered in developing this instrument; each solved through sound engineering and/or system level redesign. The qualification model passed full level life testing at temperatures throughout the operating range with negligible reduction in performance. Alliance Spacesystems, LLC supplied the flight model mechanism to Malin Space Science Systems (MSSS) where it was integrated with electronics and in turn delivered to JPL in October 2008.
{"title":"Mars hand lens imager: Lens mechanical design","authors":"D. Dibiase, J. Laramee","doi":"10.1109/AERO.2009.4839434","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839434","url":null,"abstract":"In 2011 NASA will launch the Mars Science Laboratory (MSL) as part of its Mars Exploration Program to learn more about the red planet's environment and geological history. To fulfill that goal, the MSL rover, built by NASA's Jet Propulsion Laboratory (JPL), is outfitted with the most extensive array of scientific instruments ever landed on the Martian surface. The Mars Hand Lens Imager (MAHLI), mounted on the end of the rover's robotic arm, is one of the primary science cameras for MSL. This camera affords many improvements over those used on previous Mars missions, particularly the ability to focus throughout a wide spatial range. A novel mechanism uses one motor to actuate an internal lens group, enabling focus capability, and manipulate a protective dust cover. This mechanism is designed to operate in the severe thermal environment of the MSL mission (−120° C to +40° C) and to survive for one Martian year with 3x margin (about 2000 Earth days) using non-standard materials and techniques in order to meet mass and optical requirements. Several issues involving lubrication and wear were encountered in developing this instrument; each solved through sound engineering and/or system level redesign. The qualification model passed full level life testing at temperatures throughout the operating range with negligible reduction in performance. Alliance Spacesystems, LLC supplied the flight model mechanism to Malin Space Science Systems (MSSS) where it was integrated with electronics and in turn delivered to JPL in October 2008.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"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":"133672850","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.2009.4839632
H. Hua, E. Fetzer, A. Braverman, Seungwon Lee, Mathew Henderson, S. Lewis, V. Dang, M. de la Torre Juárez, A. Guillaume
To simplify access to large and complex satellite data sets for climate analysis and model verification, a service-oriented architecture-based tool was developed to help study long-term and global-scale trends in climate, water and energy cycle, and weather variability. NASA's A-Train satellite constellation set of Level 2 data can be used to enable creation of climatologies that include correlation between observed temperature, water vapor and cloud properties from the A-Train sensors. However, the volume and inhomogeneity of Level 2 data have typically been difficult or time consuming to search and acquire. This tends to result in small-scale or short-term analysis. Instead of imposing on the user an often rigid and limiting web-based analysis environment, we recognize the need for well-designed distributed services so that users can perform analysis in their own familiar computing environments. Voluminous merged Level 2 data containing the various instrument data from the A-Train have recently been generated. Scientists next want to efficiently access selected sets of this merged data and perform their analysis. Server-side capabilities were developed to off-load processing and reduce the amount of data to be transferred to the client. Correspondingly, client-side processing APIs were developed to enable scientists to perform analysis of voluminous server-side data from within their own familiar computing environment (Java, Python, Matlab, IDL, C/C++, and Fortran90).
{"title":"Web services for multiplatform exploratory analysis of level 2 and 3 NEWS merged A-Train data","authors":"H. Hua, E. Fetzer, A. Braverman, Seungwon Lee, Mathew Henderson, S. Lewis, V. Dang, M. de la Torre Juárez, A. Guillaume","doi":"10.1109/AERO.2009.4839632","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839632","url":null,"abstract":"To simplify access to large and complex satellite data sets for climate analysis and model verification, a service-oriented architecture-based tool was developed to help study long-term and global-scale trends in climate, water and energy cycle, and weather variability. NASA's A-Train satellite constellation set of Level 2 data can be used to enable creation of climatologies that include correlation between observed temperature, water vapor and cloud properties from the A-Train sensors. However, the volume and inhomogeneity of Level 2 data have typically been difficult or time consuming to search and acquire. This tends to result in small-scale or short-term analysis. Instead of imposing on the user an often rigid and limiting web-based analysis environment, we recognize the need for well-designed distributed services so that users can perform analysis in their own familiar computing environments. Voluminous merged Level 2 data containing the various instrument data from the A-Train have recently been generated. Scientists next want to efficiently access selected sets of this merged data and perform their analysis. Server-side capabilities were developed to off-load processing and reduce the amount of data to be transferred to the client. Correspondingly, client-side processing APIs were developed to enable scientists to perform analysis of voluminous server-side data from within their own familiar computing environment (Java, Python, Matlab, IDL, C/C++, and Fortran90).","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"127 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":"131899689","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.2009.4839645
A. Murray, M. Schoppers, Steve F. Scandore
Mars Science Laboratory (MSL), NASA's next mission to Mars, will deploy a large Rover carrying a battery of eleven science instruments, representing a wide variety of payload types. The Rover's flight software (FSW) has the task of monitoring, commanding, collecting, managing and in some cases calibrating data from these instruments. Though the instruments represent a large variety of requirements, complexity, data volumes, fault protection, and commanding logic, the FSW is designed to exploit the commonality among the instruments' requirements in order to maximize reuse of software and to minimize design, implementation and testing effort. To achieve this, we developed an architectural pattern in which all of the common features and patterns of behavior required to manage an instrument are supported, and clear adaptation points are identified and provided to allow expression of the unique behaviors needed for each instrument. For each instrument there is a FSW module called an Instrument Manager (IM), and each of these is an instance of the common pattern. The common IM architecture is expressed in the design as a FSW module called the Instrument Manager Framework (IMF), along with a supporting library for handling instrument communications, the Instrument Manager Library (IML). The IMF module includes a code generator that reads specifications of the ground command set for an instrument, their associated behaviors, and other internal behaviors (e.g. fault response behaviors), expressed in spreadsheets, and produces a set of source code files containing implementations of these commands and behaviors, and their supporting types and variables. The IML module also includes a code generator which transforms a spreadsheet specifying the set of commands that the instrument accepts into C code that parameterizes communications with the instruments. We first describe the instrument management requirements on the Rover FSW, and then continue with an exposition of the IM architectural pattern. We conclude with some statistics on the efficiencies gained in the application of this pattern.
{"title":"A reusable architectural pattern for auto-generated payload management flight software","authors":"A. Murray, M. Schoppers, Steve F. Scandore","doi":"10.1109/AERO.2009.4839645","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839645","url":null,"abstract":"Mars Science Laboratory (MSL), NASA's next mission to Mars, will deploy a large Rover carrying a battery of eleven science instruments, representing a wide variety of payload types. The Rover's flight software (FSW) has the task of monitoring, commanding, collecting, managing and in some cases calibrating data from these instruments. Though the instruments represent a large variety of requirements, complexity, data volumes, fault protection, and commanding logic, the FSW is designed to exploit the commonality among the instruments' requirements in order to maximize reuse of software and to minimize design, implementation and testing effort. To achieve this, we developed an architectural pattern in which all of the common features and patterns of behavior required to manage an instrument are supported, and clear adaptation points are identified and provided to allow expression of the unique behaviors needed for each instrument. For each instrument there is a FSW module called an Instrument Manager (IM), and each of these is an instance of the common pattern. The common IM architecture is expressed in the design as a FSW module called the Instrument Manager Framework (IMF), along with a supporting library for handling instrument communications, the Instrument Manager Library (IML). The IMF module includes a code generator that reads specifications of the ground command set for an instrument, their associated behaviors, and other internal behaviors (e.g. fault response behaviors), expressed in spreadsheets, and produces a set of source code files containing implementations of these commands and behaviors, and their supporting types and variables. The IML module also includes a code generator which transforms a spreadsheet specifying the set of commands that the instrument accepts into C code that parameterizes communications with the instruments. We first describe the instrument management requirements on the Rover FSW, and then continue with an exposition of the IM architectural pattern. We conclude with some statistics on the efficiencies gained in the application of this pattern.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"23 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":"132299319","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.2009.4839646
S.F. Hishmeh, T. Doering, J. Lumpp
This paper1 2 describes the design, implementation and testing of flight software for KySat-1 a picosatellite scheduled to launch in 2009. The paper also discusses the challenges of developing dependable software in an academic environment and the development of dependable software for commercial off the shelf (COTS) hardware in space applications. Techniques employed to design for reuse and examples of software reuse in recent sub-orbital and near-space missions are also described. The software architecture, software engineering practices, and testing techniques developed for KySat-1 will serve as the basis for a series of future Kentucky Space Consortium missions.
{"title":"Design of flight software for the KySat CubeSat bus","authors":"S.F. Hishmeh, T. Doering, J. Lumpp","doi":"10.1109/AERO.2009.4839646","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839646","url":null,"abstract":"This paper1 2 describes the design, implementation and testing of flight software for KySat-1 a picosatellite scheduled to launch in 2009. The paper also discusses the challenges of developing dependable software in an academic environment and the development of dependable software for commercial off the shelf (COTS) hardware in space applications. Techniques employed to design for reuse and examples of software reuse in recent sub-orbital and near-space missions are also described. The software architecture, software engineering practices, and testing techniques developed for KySat-1 will serve as the basis for a series of future Kentucky Space Consortium missions.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"282 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":"134495152","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.2009.4839447
D. Stoker, G. Fathi, P. Ionov, S. Beck
A dual UV, Rayleigh/nitrogen Raman LIDAR system was developed for the purpose of profiling aerosols at vertical ranges between 0.025 and 5 km. The 355 nm LIDAR was operated in El Segundo, California during June and July 2008, during a period of intense wildfire activity in Northern California. From the two independent measurements we calculated the particle backscatter, and using the humidity-corrected LIDAR backscatter-to-extinction ratios given by Ackermann[1] we calculated aerosol optical thickness (AOT) profiles. Preliminary validation studies revealed that under most conditions the calculated LIDAR AOT data agreed with total AOT measured from a collocated sun photometer, except for cases when high-altitude smoke from wildfires was present. To account for high-altitude smoke, a two-layer atmospheric model was assumed, where the lower layer's AOT was calculated using the backscatter-to-extinction method and the high-altitude AOT was found through direct attenuation of the Raman signal. A comparison of AOT measurements from the ground-based LIDAR and the MODIS (Aqua and Terra) overpasses was then performed during the peak period of transport of smoke from Northern California, between 19 June 2008 and 2 July 2008. While the LIDAR and Sun Photometer were found to be in good agreement, it was found that the MODIS overpasses consistently indicated a larger AOT.
{"title":"LIDAR versus satellite-measured optical thickness of a wildfire aerosol","authors":"D. Stoker, G. Fathi, P. Ionov, S. Beck","doi":"10.1109/AERO.2009.4839447","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839447","url":null,"abstract":"A dual UV, Rayleigh/nitrogen Raman LIDAR system was developed for the purpose of profiling aerosols at vertical ranges between 0.025 and 5 km. The 355 nm LIDAR was operated in El Segundo, California during June and July 2008, during a period of intense wildfire activity in Northern California. From the two independent measurements we calculated the particle backscatter, and using the humidity-corrected LIDAR backscatter-to-extinction ratios given by Ackermann[1] we calculated aerosol optical thickness (AOT) profiles. Preliminary validation studies revealed that under most conditions the calculated LIDAR AOT data agreed with total AOT measured from a collocated sun photometer, except for cases when high-altitude smoke from wildfires was present. To account for high-altitude smoke, a two-layer atmospheric model was assumed, where the lower layer's AOT was calculated using the backscatter-to-extinction method and the high-altitude AOT was found through direct attenuation of the Raman signal. A comparison of AOT measurements from the ground-based LIDAR and the MODIS (Aqua and Terra) overpasses was then performed during the peak period of transport of smoke from Northern California, between 19 June 2008 and 2 July 2008. While the LIDAR and Sun Photometer were found to be in good agreement, it was found that the MODIS overpasses consistently indicated a larger AOT.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"60 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":"134559030","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.2009.4839684
A. Ahmadi, T. Fransson, Anneli Crona, Markus Klein, P. Soderholm
With global cuts in defense budgets, air forces have to sustain the same level of readiness with a reduced number of aircraft. To succeed with this challenge, it is not sufficient to improve current maintenance concepts, but also new ones have to be introduced.
{"title":"Integration of RCM and PHM for the next generation of aircraft","authors":"A. Ahmadi, T. Fransson, Anneli Crona, Markus Klein, P. Soderholm","doi":"10.1109/AERO.2009.4839684","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839684","url":null,"abstract":"With global cuts in defense budgets, air forces have to sustain the same level of readiness with a reduced number of aircraft. To succeed with this challenge, it is not sufficient to improve current maintenance concepts, but also new ones have to be introduced.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"14 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":"133823361","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.2009.4839331
Erik B. Johnson, E. Chapman, P. Linsay, S. Mukhopadhyay, C. Stapels, J. Christian, E. Benton
A dosimeter-on-a-chip (DoseChip) comprised of a tissue-equivalent scintillator coupled to a solid-state photomultiplier (SSPM) built using CMOS technology represents an ideal technology for a space-worthy, real-time solar-particle monitor for astronauts. It provides a tissue-equivalent response to the relevant energies and types of radiation for low-Earth orbit and interplanetary space flight to the moon or Mars. The DoseChip will complement the existing Crew Passive Dosimeters by providing real-time dosimetry and as an alarming monitor for solar particle events (SPEs). A prototype of the DoseChip was exposed to protons at three incident energies at the NASA space radiation laboratory at Brookhaven National Laboratory. The prototype provides an unambiguous, proportional response for 200, 500, and 1000 MeV protons. The measured response produced a detector response function that was used to model the behavior of an improved instrument. The data presented here indicate that a 3 × 3 × 3 mm3 piece of BC-430 plastic scintillator coupled to a 2000-pixel SSPM can accommodate the needed dynamic range for protons with an incident energy of 20 MeV and greater.
{"title":"Tissue-equivalent solar particle dosimeter using CMOS SSPMs","authors":"Erik B. Johnson, E. Chapman, P. Linsay, S. Mukhopadhyay, C. Stapels, J. Christian, E. Benton","doi":"10.1109/AERO.2009.4839331","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839331","url":null,"abstract":"A dosimeter-on-a-chip (DoseChip) comprised of a tissue-equivalent scintillator coupled to a solid-state photomultiplier (SSPM) built using CMOS technology represents an ideal technology for a space-worthy, real-time solar-particle monitor for astronauts. It provides a tissue-equivalent response to the relevant energies and types of radiation for low-Earth orbit and interplanetary space flight to the moon or Mars. The DoseChip will complement the existing Crew Passive Dosimeters by providing real-time dosimetry and as an alarming monitor for solar particle events (SPEs). A prototype of the DoseChip was exposed to protons at three incident energies at the NASA space radiation laboratory at Brookhaven National Laboratory. The prototype provides an unambiguous, proportional response for 200, 500, and 1000 MeV protons. The measured response produced a detector response function that was used to model the behavior of an improved instrument. The data presented here indicate that a 3 × 3 × 3 mm3 piece of BC-430 plastic scintillator coupled to a 2000-pixel SSPM can accommodate the needed dynamic range for protons with an incident energy of 20 MeV and greater.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"62 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":"115842063","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.2009.4839355
B. Cohanim, T. Fill, S. Paschall, L. Major, T. Brady
The Autonomous Landing and Hazard Avoidance Technology (ALHAT) Project is studying the lunar landing descent phase from lunar orbit to the surface. In this paper, we give an overview of the timing and ΔV implications for key activities during the lunar landing approach phase. Timing and ΔV performance are evaluated while varying the approach phase design and key hazard detection parameters. Results show that there are significant system tradeoffs when considering ΔV, hazard detection schemes, and the time available for crew to select a safe point to land.
{"title":"Approach phase ΔV considerations for lunar landing","authors":"B. Cohanim, T. Fill, S. Paschall, L. Major, T. Brady","doi":"10.1109/AERO.2009.4839355","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839355","url":null,"abstract":"The Autonomous Landing and Hazard Avoidance Technology (ALHAT) Project is studying the lunar landing descent phase from lunar orbit to the surface. In this paper, we give an overview of the timing and ΔV implications for key activities during the lunar landing approach phase. Timing and ΔV performance are evaluated while varying the approach phase design and key hazard detection parameters. Results show that there are significant system tradeoffs when considering ΔV, hazard detection schemes, and the time available for crew to select a safe point to land.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"12 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":"131453864","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.2009.4839707
L. Wickman, Grant A. Anderson
Accurate estimation of required working volumes is a vital aspect of the design process for any vehicle involving humans. This is all the more important when such a vehicle must serve as the crew's sole habitable volume during a mission of any duration in the harsh environment of space.
{"title":"Activity-based habitable volume estimating for human spaceflight vehicles","authors":"L. Wickman, Grant A. Anderson","doi":"10.1109/AERO.2009.4839707","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839707","url":null,"abstract":"Accurate estimation of required working volumes is a vital aspect of the design process for any vehicle involving humans. This is all the more important when such a vehicle must serve as the crew's sole habitable volume during a mission of any duration in the harsh environment of space.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"10 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":"131670122","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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