TestFFEccLinOrb:
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Test the FFEccLinOrb function. An initial reference state in the ECI frame
is provided, along with an initial relative state in Hill's frame.
First, the relative state is propagated one time-step dT using FFEccLinOrb,
with the given acceleration in Hill's frame applied.
Next, we integrate the reference and secondary states in the ECI frame,
applying the given accleration (now transformed to ECI). We then
transform the two resulting ECI states back to the Hill's frame and
compare.
Since version 7.
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Form:
[xH_int,xH_lin] = TestFFEccLinOrb( x0, xH0, dT, aH );
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Inputs
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x0 (6,1) ECI position and velocity of reference
[km; km/s]
xH0 (6,1) Hill's-frame position and velocity of relative sat
[km; km/s]
dT (1) Time-step to integrate over [sec]
aH (3,1) Acceleration to be applied (in Hill's frame)
[km/s/s]
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Outputs
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xH_int (6,1) Hill's-frame state from integrating inertial states
xH_lin (6,1) Hill's-frame state from propagating linear system
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Copyright 2004 Princeton Satellite Systems, Inc.
All rights reserved.
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Children:
FormationFlying: Coord/GetHillsMats
FormationFlying: EccDynamics/FFEccDiscreteHills
FormationFlying: EccDynamics/FFEccGoals
FormationFlying: EccDynamics/FFEccRMat
FormationFlying: Transformation/ECI2Hills
FormationFlying: Transformation/Hills2ECI
FormationFlying: Utility/NuDot
Math: Integration/RK4TI
OrbitMiniToolbox: Support/El2RV
OrbitMiniToolbox: Support/M2Nu
SC: BasicOrbit/OrbRate
SC: BasicOrbit/RV2El
