Pub Date : 2009-03-07DOI: 10.1109/AERO.2009.4839634
J. Joswig, M. Powell
This paper presents a case study of the various interfaces and underlying architectures used to monitor and control a variety of different robots and test scenarios at the Jet Propulsion Laboratory (JPL). It includes a description of both the software developed and the hardware adapted for the purpose of providing real-time and near-real time interaction with remote assets. Robots range from the prototype lunar exploration robot ATHLETE[1] (All Terrain Hex Limbed Extra Terrestrial Explorer) to Aerobot, a propeller driven lighter then air blimp to an assortment of Unmanned Aerial Vehicles (UAV) being tested at White Sands Missile Range (WSMR). The paper focuses primarily on three Virtuoso software tools: the Telemetry Canvas, Scratchpad, and Stereo Display Views. We also describe robot specific implementations of various off-the-shelf hardware input devices. An overview of the existing telemetry distribution networks for each implementation is also covered.
{"title":"Flexible command and control interfaces for teleoperations","authors":"J. Joswig, M. Powell","doi":"10.1109/AERO.2009.4839634","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839634","url":null,"abstract":"This paper presents a case study of the various interfaces and underlying architectures used to monitor and control a variety of different robots and test scenarios at the Jet Propulsion Laboratory (JPL). It includes a description of both the software developed and the hardware adapted for the purpose of providing real-time and near-real time interaction with remote assets. Robots range from the prototype lunar exploration robot ATHLETE[1] (All Terrain Hex Limbed Extra Terrestrial Explorer) to Aerobot, a propeller driven lighter then air blimp to an assortment of Unmanned Aerial Vehicles (UAV) being tested at White Sands Missile Range (WSMR). The paper focuses primarily on three Virtuoso software tools: the Telemetry Canvas, Scratchpad, and Stereo Display Views. We also describe robot specific implementations of various off-the-shelf hardware input devices. An overview of the existing telemetry distribution networks for each implementation is also covered.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"293 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":"132044247","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.2009.4839508
J. Samson, E. Grobelny
Space exploration, science, and autonomy missions are requiring ever-increasing bandwidth and processing capacity to the extent that the ability to apply high-performance COTS processors for onboard computing in space is becoming a critical need. To date, Dependable Multiprocessor (DM) technology has been developed as part of NASA's New Millennium Program (NMP) ST8 (Space Technology 8) project. DM was one of four technologies selected for the ST8 flight experiment. The objective of the NMP ST8 effort is to combine high-performance, SEU-tolerant, COTS-based cluster processing and SEU-tolerant middleware in an architecture and software framework capable of supporting a wide variety of mission applications. The goal of the Dependable Multiprocessor project is to provide spacecraft/payload processing capability at speeds 10x — 100x of what is available today, enabling heretofore unrealizable levels of science and autonomy.
{"title":"NMP ST8 dependable multiprocessor: TRL6 validation — preliminary results","authors":"J. Samson, E. Grobelny","doi":"10.1109/AERO.2009.4839508","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839508","url":null,"abstract":"Space exploration, science, and autonomy missions are requiring ever-increasing bandwidth and processing capacity to the extent that the ability to apply high-performance COTS processors for onboard computing in space is becoming a critical need. To date, Dependable Multiprocessor (DM) technology has been developed as part of NASA's New Millennium Program (NMP) ST8 (Space Technology 8) project. DM was one of four technologies selected for the ST8 flight experiment. The objective of the NMP ST8 effort is to combine high-performance, SEU-tolerant, COTS-based cluster processing and SEU-tolerant middleware in an architecture and software framework capable of supporting a wide variety of mission applications. The goal of the Dependable Multiprocessor project is to provide spacecraft/payload processing capability at speeds 10x — 100x of what is available today, enabling heretofore unrealizable levels of science and autonomy.","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":"128887135","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.2009.4839490
U. Orguner, T. Schon, F. Gustafsson
In this paper we consider the problem of tracking targets, which can move both on-road and off-road, with particle filters utilizing the road-network information. It is argued that the constraints like speed-limits and/or one-way roads generally incorporated into on-road motion models make it necessary to consider additional high-bandwidth off-road motion models. This is true even if the targets under consideration are only allowed to move on-road due to the possibility of imperfect road-map information and drivers violating the traffic rules. The particle filters currently used struggles during sharp mode transitions, with poor estimation quality as a result. This is due to the fact the number of particles allocated to each motion mode is varying according to the mode probabilities. A recently proposed interacting multiple model (IMM) particle filtering algorithm, which keeps the number of particles in each mode constant irrespective of the mode probabilities, is applied to this problem and its performance is compared to a previously existing algorithm. The results of the simulations on a challenging bearing-only tracking scenario show that the proposed algorithm, unlike the previously existing algorithm, can achieve good performance even under the sharpest mode transitions.
{"title":"Improved target tracking with road network information","authors":"U. Orguner, T. Schon, F. Gustafsson","doi":"10.1109/AERO.2009.4839490","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839490","url":null,"abstract":"In this paper we consider the problem of tracking targets, which can move both on-road and off-road, with particle filters utilizing the road-network information. It is argued that the constraints like speed-limits and/or one-way roads generally incorporated into on-road motion models make it necessary to consider additional high-bandwidth off-road motion models. This is true even if the targets under consideration are only allowed to move on-road due to the possibility of imperfect road-map information and drivers violating the traffic rules. The particle filters currently used struggles during sharp mode transitions, with poor estimation quality as a result. This is due to the fact the number of particles allocated to each motion mode is varying according to the mode probabilities. A recently proposed interacting multiple model (IMM) particle filtering algorithm, which keeps the number of particles in each mode constant irrespective of the mode probabilities, is applied to this problem and its performance is compared to a previously existing algorithm. The results of the simulations on a challenging bearing-only tracking scenario show that the proposed algorithm, unlike the previously existing algorithm, can achieve good performance even under the sharpest mode transitions.","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":"128910616","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.2009.4839351
E. M. Sims
The Department of Defense (DoD) Space Test Program (STP) was created in 1965 to provide flight opportunities for all DoD research and development activities in an economic and efficient manner. STP predominantly flies payloads that have gone through the Space Experiments Review Board (SERB) process, however the program does have the ability to fly other government-sponsored payloads on a reimbursable basis or as a rideshare opportunity. STP is a small, level-of-effort program that is charged with flying multiple space missions on a shoestring budget. The program is adept at getting the most out of a mission as possible and rarely flies the typical one-spacecraft-per-launch-vehicle mission. The Evolved Expendable Launch Vehicle (EELV) Secondary Payload Adaptor (ESPA) was developed and flown under the direction of STP. The same payload interface requirements and environments defined for ESPA are now being applied to other multi-payload adaptors (MPAs) for other launch vehicles. STP is working to fly ESPAs and other MPAs on a wide range of launch vehicles to take maximum advantage of each launch vehicle's capacity. The program also recognizes the increasing demand to fly CubeSats and has committed to flying multiple CubeSats on missions where technically feasible. STP also realizes that expensive expendable launch vehicle (LV) missions are not always practical or realistic. STP has at its disposal an arsenal of tools and techniques to get payloads access to space, be it on a free-flying spacecraft, the International Space Station (ISS), a high altitude balloon, or a sounding rocket. Space access is a challenge and can seem unattainable, but with STP's 40 years of experience it can be achieved.
{"title":"The Department of Defense Space Test Program: Come fly with us","authors":"E. M. Sims","doi":"10.1109/AERO.2009.4839351","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839351","url":null,"abstract":"The Department of Defense (DoD) Space Test Program (STP) was created in 1965 to provide flight opportunities for all DoD research and development activities in an economic and efficient manner. STP predominantly flies payloads that have gone through the Space Experiments Review Board (SERB) process, however the program does have the ability to fly other government-sponsored payloads on a reimbursable basis or as a rideshare opportunity. STP is a small, level-of-effort program that is charged with flying multiple space missions on a shoestring budget. The program is adept at getting the most out of a mission as possible and rarely flies the typical one-spacecraft-per-launch-vehicle mission. The Evolved Expendable Launch Vehicle (EELV) Secondary Payload Adaptor (ESPA) was developed and flown under the direction of STP. The same payload interface requirements and environments defined for ESPA are now being applied to other multi-payload adaptors (MPAs) for other launch vehicles. STP is working to fly ESPAs and other MPAs on a wide range of launch vehicles to take maximum advantage of each launch vehicle's capacity. The program also recognizes the increasing demand to fly CubeSats and has committed to flying multiple CubeSats on missions where technically feasible. STP also realizes that expensive expendable launch vehicle (LV) missions are not always practical or realistic. STP has at its disposal an arsenal of tools and techniques to get payloads access to space, be it on a free-flying spacecraft, the International Space Station (ISS), a high altitude balloon, or a sounding rocket. Space access is a challenge and can seem unattainable, but with STP's 40 years of experience it can be achieved.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"71 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":"127394005","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.2009.4839377
B. MacNeal, D. Abraham, R. Hastrup, Janet P. Wu, R. Machuzak, D. Heckman, R. Cesarone, Raffi P. Tikidjian, Kristy Tran
NASA's future scientific missions will place new demands on its Deep Space Network (DSN). Depending on which missions fly and their particular design, NASA's communications ground assets (antennas) may require upgrade or enhancement. The purpose of the Mission Set Analysis Tool is to help forecast future demand by (1) cataloguing the characteristics of potential future DSN-user missions consistent with NASA's Space Communications Mission Model, (2) calculating the demands that these missions will place on the DSN, and (3) generating mission requirements for other DSN architectural analysis tools.
{"title":"Mission set analysis tool for assessing future demands on NASA's Deep Space Network","authors":"B. MacNeal, D. Abraham, R. Hastrup, Janet P. Wu, R. Machuzak, D. Heckman, R. Cesarone, Raffi P. Tikidjian, Kristy Tran","doi":"10.1109/AERO.2009.4839377","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839377","url":null,"abstract":"NASA's future scientific missions will place new demands on its Deep Space Network (DSN). Depending on which missions fly and their particular design, NASA's communications ground assets (antennas) may require upgrade or enhancement. The purpose of the Mission Set Analysis Tool is to help forecast future demand by (1) cataloguing the characteristics of potential future DSN-user missions consistent with NASA's Space Communications Mission Model, (2) calculating the demands that these missions will place on the DSN, and (3) generating mission requirements for other DSN architectural analysis tools.","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":"115405748","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.2009.4839390
S. Shambayati
In this paper the performance of two preemptive retransmission schemes for protection of priority data over deep-space Ka-band links is evaluated. The first scheme merges the correctly received bit from each transmission to create the most complete set of priority data for each pass (bit merge). The second scheme (symbol combining) combines the soft symbols received from each transmission of the priority data to increase the priority data's signal to noise ratio (SNR), thus increasing the likelihood of their correct reception. These performances were then compared to an equivalent margin scheme in which the data rate used for the transmission of the priority data is reduced by a factor equal to the number of transmissions of the priority data. The performance of each scheme was evaluated through emulation using Water Vapor Radiometer (WVR) and Advanced Water Vapor Radiometer (AWVR) sky brightness temperature measurements along with models for Deep Space Network (DSN) Ka-band capable antenna using Mars Reconnaissance Orbiter's DSN tracking schedule and geometry. The results indicate that “bit merge” and “reduced rate” schemes perform roughly the same in terms of availability of the priority data (at least 97% compared to 93% without any data protections scheme) but for “bit merge” priority data losses occur over fewer passes than for the “reduced rate” scheme. The “symbol combining” scheme is superior to both the “bit merge” and the “reduced rate” schemes with at least 98.5% priority data availability with losses over a small number of passes. Receivers have a minimum demodulation threshold SNR and combining algorithms have combining losses; therefore, the performance of the “symbol combining” scheme was also evaluated with respect to these two factors. The results indicate that even with current receivers, the “symbol combining” scheme performs extremely well and the scheme is relatively robust with respect to combining losses.
{"title":"Deep-space Ka-band link priority data protection: Preemptive retransmission vs. margin.","authors":"S. Shambayati","doi":"10.1109/AERO.2009.4839390","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839390","url":null,"abstract":"In this paper the performance of two preemptive retransmission schemes for protection of priority data over deep-space Ka-band links is evaluated. The first scheme merges the correctly received bit from each transmission to create the most complete set of priority data for each pass (bit merge). The second scheme (symbol combining) combines the soft symbols received from each transmission of the priority data to increase the priority data's signal to noise ratio (SNR), thus increasing the likelihood of their correct reception. These performances were then compared to an equivalent margin scheme in which the data rate used for the transmission of the priority data is reduced by a factor equal to the number of transmissions of the priority data. The performance of each scheme was evaluated through emulation using Water Vapor Radiometer (WVR) and Advanced Water Vapor Radiometer (AWVR) sky brightness temperature measurements along with models for Deep Space Network (DSN) Ka-band capable antenna using Mars Reconnaissance Orbiter's DSN tracking schedule and geometry. The results indicate that “bit merge” and “reduced rate” schemes perform roughly the same in terms of availability of the priority data (at least 97% compared to 93% without any data protections scheme) but for “bit merge” priority data losses occur over fewer passes than for the “reduced rate” scheme. The “symbol combining” scheme is superior to both the “bit merge” and the “reduced rate” schemes with at least 98.5% priority data availability with losses over a small number of passes. Receivers have a minimum demodulation threshold SNR and combining algorithms have combining losses; therefore, the performance of the “symbol combining” scheme was also evaluated with respect to these two factors. The results indicate that even with current receivers, the “symbol combining” scheme performs extremely well and the scheme is relatively robust with respect to combining losses.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"71 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":"114330008","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.2009.4839694
M. Bester
UC Berkeley has been operating eight spacecraft from its multi-mission control center at Space Sciences Laboratory, using the local Berkeley Ground Station as well as multiple government and commercial ground networks for space-to-ground communications. This paper describes challenges associated with developing multi-mission contact schedules in a constraint-based environment involving several ground networks with competing users, and presents a solution that provides short turn-around times and applies a high degree of systems automation.
{"title":"Automated multi-mission scheduling and control center operations at UC Berkeley","authors":"M. Bester","doi":"10.1109/AERO.2009.4839694","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839694","url":null,"abstract":"UC Berkeley has been operating eight spacecraft from its multi-mission control center at Space Sciences Laboratory, using the local Berkeley Ground Station as well as multiple government and commercial ground networks for space-to-ground communications. This paper describes challenges associated with developing multi-mission contact schedules in a constraint-based environment involving several ground networks with competing users, and presents a solution that provides short turn-around times and applies a high degree of systems automation.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"29 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":"114608514","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.2009.4839334
Tao Yang, G. Radice, Weihua Zhang, Xiaoqian Chen, Zhongwei Wang
This paper investigates the applicability of Pursuit Algorithm (PA), including Classic Pursuit Algorithm in Circle (ClaPAIC) and Cyclic Pursuit Algorithm (CyPA) into the field of space missions. The implementation of PA has been applied to a number of typical scenarios: formation replenishment, rendezvous and docking and formation reconfiguration. Simulation results show the effectiveness when ClaPAIC and CyPA are accurately designed for the mission, and indicate that PA may be a promising tool in the design of spacecraft maneuvers. The small fuel cost in the case of TPF deployment and formation maintenance shows that PA control is also effective when ClaPAIC and CyPA are arranged, and control gain kα is selected properly.
{"title":"Application of Pursuit Algorithms for space missions","authors":"Tao Yang, G. Radice, Weihua Zhang, Xiaoqian Chen, Zhongwei Wang","doi":"10.1109/AERO.2009.4839334","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839334","url":null,"abstract":"This paper investigates the applicability of Pursuit Algorithm (PA), including Classic Pursuit Algorithm in Circle (ClaPAIC) and Cyclic Pursuit Algorithm (CyPA) into the field of space missions. The implementation of PA has been applied to a number of typical scenarios: formation replenishment, rendezvous and docking and formation reconfiguration. Simulation results show the effectiveness when ClaPAIC and CyPA are accurately designed for the mission, and indicate that PA may be a promising tool in the design of spacecraft maneuvers. The small fuel cost in the case of TPF deployment and formation maintenance shows that PA control is also effective when ClaPAIC and CyPA are arranged, and control gain kα is selected properly.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"16 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":"115100263","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.2009.4839472
Y. R. Zheng, Tiange Shao
A new variable step-size Least Mean p-norm (VSS-LMP) algorithm is proposed for phased array radar application with space-time adaptive processing to combat heavy-tailed non-Gaussian clutters. The algorithms automatically change the step size according to the estimated p-th and (2p - 2)-th moments of the error, where 1 ≤ p ≤ 2. The algorithm is evaluated via a space-slow-time STAP example and the excess Mean Square Error (MSE) and misadjustment results show that the proposed VSS-LMP converges fast and reaches lower steady-state error than the fixed stepsize LMP. It also provides a better compromise between convergence speed and low steady state error than existing VSS Least Mean Square (LMS) algorithms in both Gaussian and Compound K clutter environments.
{"title":"A variable step-size lmp algorithm for heavy-tailed interference suppression in phased array radar","authors":"Y. R. Zheng, Tiange Shao","doi":"10.1109/AERO.2009.4839472","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839472","url":null,"abstract":"A new variable step-size Least Mean p-norm (VSS-LMP) algorithm is proposed for phased array radar application with space-time adaptive processing to combat heavy-tailed non-Gaussian clutters. The algorithms automatically change the step size according to the estimated p-th and (2p - 2)-th moments of the error, where 1 ≤ p ≤ 2. The algorithm is evaluated via a space-slow-time STAP example and the excess Mean Square Error (MSE) and misadjustment results show that the proposed VSS-LMP converges fast and reaches lower steady-state error than the fixed stepsize LMP. It also provides a better compromise between convergence speed and low steady state error than existing VSS Least Mean Square (LMS) algorithms in both Gaussian and Compound K clutter environments.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"18 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":"117069873","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.2009.4839367
D. Bagri, W. Majid
At present spacecraft angular position with Deep Space Network (DSN) is determined using group delay estimates from very long baseline interferometer (VLBI) phase measurements employing differential one way ranging (DOR) tones. As an alternative to this approach, we propose estimating position of a spacecraft to half a fringe cycle accuracy using time variations between measured and calculated phases as the Earth rotates using DSN VLBI baseline(s). Combining fringe location of the target with the phase allows high accuracy for spacecraft angular position estimate. This can be achieved using telemetry signals of at least 4–8 MSamples/sec data rate or DOR tones.
{"title":"Accurate spacecraft angular position from DSN VLBI phases using X-band telemetry or DOR tones","authors":"D. Bagri, W. Majid","doi":"10.1109/AERO.2009.4839367","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839367","url":null,"abstract":"At present spacecraft angular position with Deep Space Network (DSN) is determined using group delay estimates from very long baseline interferometer (VLBI) phase measurements employing differential one way ranging (DOR) tones. As an alternative to this approach, we propose estimating position of a spacecraft to half a fringe cycle accuracy using time variations between measured and calculated phases as the Earth rotates using DSN VLBI baseline(s). Combining fringe location of the target with the phase allows high accuracy for spacecraft angular position estimate. This can be achieved using telemetry signals of at least 4–8 MSamples/sec data rate or DOR tones.","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":"116296432","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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