CollisionMonitor:
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Runs the collision monitoring algorithm. Checks the ellipsoids for self
and a neighboring spacecraft. Self "position measurement" should be
[0;0;0;0;0;0] at each time if relative measurements are used. Includes
options for continuous and discrete ellipsoid propagation for circular
and low-eccentricity reference orbits. All propagation is performed in
Hill's frame. Assumes that no maneuvers are taking place.
Since version 7.
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Form:
[prob, d, xhat, Shat] = CollisionMonitor( action, d, jD, y );
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Inputs
------
action (:) 'initialize' or 'run'
d : Data structure
.hRef Altitude of the reference orbit (km)
.eRef Eccentricity
.dR Reference length of Hill's orbit (km)
.initBounds Error in measurement
.nSC Number of S/C
.predictTime Total amount of time to predict for
.nSampleTimes Number of points in predictTime
.scalev Sigma for measurement noise
.discrete Flag for method type
.mSC Spacecraft mass (kg)
.lenSC Spacecraft length (m)
.diaSC Spacecraft diameter (m)
.Cd Drag coefficient
.Cr Reflectivity of s/c: 0.0 for translucent;
1.0 for black-body; 2.0 for flat mirror
jD (1) Epoch in Julian date
y (6,:) spacecraft current position in Hill's frame
Outputs
--------
prob (n) probability of collision
d (n) minimum distance between spacecraft position ellipsoids
xhat (6,n,2) xhat, ellipsoid centers, for both spacecraft
Shat (6,6,n,2) Shat, ellipsoid size matrices, for both spacecraft
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Children:
Common: Database/Constant
Common: Time/JD2000
FormationFlying: Collision/CollProbSet
FormationFlying: Collision/DistantPtToEll
FormationFlying: Collision/EllipsePropCirc
FormationFlying: Collision/MinDEllipsoid
FormationFlying: Collision/WorstCasePerturbations
FormationFlying: EccDynamics/FFEccLinOrb
Math: Linear/Mag
OrbitMiniToolbox: Support/M2Nu
SC: BasicOrbit/OrbRate
SC: BasicOrbit/Period
