Path: FormationFlying/Analysis
% 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.
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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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