Table 1. Comparison of GPCS systems (Ref. [3]).ConcordiaBorealisBorealisFigure 1. Ellipso TM Mobile Satellite System Orbits (Ref. [6]).The two critically-inclined orbit planes are known as the EllipsoBorealis TM subconstellation. The orbits of Borealis TM are Sun-Synchronous with a Frozen Line of Apsides (SSFLA). Its orbitplanes are aligned 180 deg apart, with one ascending node atnoon, and the other at midnight. Together with the Concordiaplane, they provide 24-hour coverage of the NorthernHemisphere with five spacecraft in each orbit Borealis TM plane.The two subconstellations of Ellipso TM give it unique flexibility inhow it covers the globe. The design is based on the distributionof land and population by latitude (Ref. [7]). The two Borealis TMplanes cover the northern hemisphere, where much of thecustomer base for the mobile communications system isprojected, with the use of elliptic orbits. The Concordiacomplements the Borealis TM planes by providing coverage to thepopulation and land masses in the equatorial and southernhemispheric zones. Since most of the relevant land masses lieabove the Southern 55th parallel, no requirement for satellitecoverage is stated below this line. Figure 2 illustrates theminimum elevation angles achievable by the Concordia andBorealis TM planes. The current plan is to use five satellites in eachBorealis TM plane, and seven satellites in the Concordia plane. Thisallows Ellipso TM to meet its coverage requirements with a 10-degminimum elevation angle in the southern hemisphere and a25-deg minimum elevation angle in the northern hemisphere.In previous work, Sabol (Refs. [9], [10]) analyzed the Dawn/Dusk(with ascending nodes at 10 deg and 190 deg) configuration ofthe Borealis TM subconstellation. He produced a set of refined orbitelements for this configuration, with a complete perturbation andstation-keeping analysis. His refined orbit has an 8:1 repeatground track cycle, i.e., eight revolutions of the orbit per nodalperiod.Recently, Sabol, Draim, and Cefola (Ref. [11]) revisited theBorealis TM analysis. There, it was noted that both atmosphericdrag and tesseral resonance produce strong perturbations on theAutomated Station-Keeping for Satellite Constellations3
Figure 2. Minimum elevation angles as function of latitude: six-,and seven-satellite Concordia arrays, and four-, and fivesatelliteBorealis arrays (Ref. [8]).8:1 repeat ground-track orbit, with undesirable implications onthe station-keeping fuel budget. The current baseline Ellipso TMsystem requires a Noon/Midnight orientation of the Borealis TMplanes (with nodes at 280 deg and 100 deg). This orientationintroduces significant solar radiation pressure effects. Theirresolution to these problems was to produce a slightly refined setof orbital elements for an 81:10 repeat ground track. The refinedelement set produces a significant savings in the fuel budget, andeliminates the need for out-of-plane maneuvers. Table 2 containsthe refined 8:1 orbital elements, while Table 3 contains the refined81:10 orbital elements for the Noon/Midnight configuration andelements for Concordia. In the remainder of this paper, adescription of the algorithms and architecture of ASKS will beprovided. Station-keeping strategies for the Ellipso Borealis TMTable 2. Borealis TM 8:1 mean element sets(Ref. [11]).global wireless communication system will be explored with theASKS tool.Automated Station-Keeping SimulatorASKS is an analysis and software package that combines anaccurate satellite orbit propagator and an optimal impulsiverendezvous planner. It is designed to develop and test controlmethodologies for the constellation station-keeping problem in aparallel, scaleable computing environment. It was designed to bean accurate, useful tool that can be applied to virtually any typeof satellite constellation. Special care was taken throughout thedevelopment process to avoid making assumptions about theconstellations to be considered, thus making ASKS as generallyapplicable as possible. It may be used to analyze satellite orbits ofvirtually any type: LEO, Medium Earth Orbit (MEO), High EarthOrbit (HEO), GEO, etc. ASKS is also a work in progress. It isexpected that more functionality will be added in the future.ASKS executes on a network of workstations using the MPIprotocol. The number of satellites in the constellation defines thenumber of processes that will execute in a parallel processingenvironment. Computing capability can be added by simplyadding more workstations to the parallel network anddistributing the workload. It employs the <strong>Draper</strong> SemianalyticalSatellite Theory (DSST) stand-alone propagator, which hasdemonstrated accuracy with low, medium, and highly eccentricorbits (Refs. [14], [15]). The DSST mean element dynamicsproduce precise mean elements, which include the followingperturbations:Table 3. Ellipso Borealis TM (81:10) and Concordia Planes(Refs. [11], [13]).ElementNode atNoon PlaneTrue of DateNode atMidnightPlaneConcordiaPlanea 10472.201km10472.200km14440.137kme 0.32652 0.32662 0.00001II 116.583¡ 116.582¡ 0.00001 ¡ωω 270¡ 270¡ 90¡ΩΩ 280¡ 100¡ 0.0¡M 0¡, 72¡, 144¡,216¡, and288¡0¡, 72¡, 144¡,216¡, and288¡0¡, 51.43¡,102.86 ¡,154.29 ¡,205.71 ¡,257.14¡, and308.57¡EpochMidnight, Jan1, 1997Midnight, Jan1, 1997Automated Station-Keeping for Satellite Constellations4
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Letter from thePresident and CEO,Vi
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Information TechnologyMilton AdamsE
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BiographyMilton Adams has been at D
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Figure 1 represents a functional de
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Programs. In effect, these controll
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Although the terminal area traffic
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Table 2. ATFM performance evaluatio
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In the experiments, a nominal capac
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[3] Wambsganss, Michael C. “Colla
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Guidance, Navigation, and Control A
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A Control Lyapunov FunctionApproach
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x( 0) ∈ X and w(t) ∈Wfor all t
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(b) Select a quadratic RCLF V i (x)
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at each grid point. In the case w 1
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control is employed to maintain the
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Table 1. Summary of automotive yaw
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Resolution (60 Hz) deg/h10000000100
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References[1] Greiff, P., B. Boxenh
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Guidance, Navigation, and Control A
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An Integrated Safety AnalysisMethod
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Infrastructure ModelsSystemRequirem
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Figures 6 and 7 illustrate the bloc
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Notice that each flight track descr
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Table 7. Safety statistics at 1700-
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Guidance, Navigation, and Control A
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An Optimal Guidance Law forPlanetar
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Note that the states in the three d
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Crossrange (Kft)10090807060504030Cl
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The 1997 Charles StarkDraper PrizeT
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The 1997 Charles StarkDraper Prize1
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“Draper encourages its personnel
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Gimballed Vibrating GyroscopeHaving
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“Draper encourages its personnel
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Optical Source Isolator withPolariz
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“Draper encourages its personnel
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Hunting Suppressor forPolyphase Ele
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“Draper encourages its personnel
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Sensor Having an Off-Frequency Driv
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proof mass from transients and enha
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1997 Published PapersThe following
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monitoring of space structures and
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measured by kinematic degrees of fr
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i.e., what percent of the earth’s
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McConley, M. W.; Dahleh, M. A.; Fer
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unaffordable, or even misguided. Bu
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The Draper DistinguishedPerformance
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Educational Activitiesat Draper Lab