Path: FormationFlying/Dynamics
% Integrate two neighboring orbits, with applied relative accelerations
Since version 7.
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Form:
[xRef,xRel,xH] = FFIntegrate( xRef0, xRel0, time, aH );
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Inputs
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xRef0 (6,1) Initial ECI position & velocity of reference sat
xRel0 (6,1) Initial ECI position & velocity of relative sat
time (1,N) Time vector (seconds)
aH (3,N) Relative accel. in Hill's frame over time [km/s/s]
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Outputs
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xRef (6,N) Integrated ECI position and velocity of reference
xRel (6,N) Integrated ECI position and velocity of relative
xH (6,N) Relative Hill's frame position and velocity
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Copyright 2004 Princeton Satellite Systems, Inc.
All rights reserved.
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FormationFlying: Coord/GetHillsMats FormationFlying: Transformation/ECI2Hills SC: BasicOrbit/E2M SC: BasicOrbit/Nu2E SC: BasicOrbit/Nu2M SC: BasicOrbit/RV2El Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Math: Integration/RK4TI Math: Linear/Cross Math: Linear/Dot Math: Linear/DupVect Math: Linear/Mag
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