Path: FormationFlying/Collision
% Collision monitoring algorithm for maneuvering spacecraft.
Discretizes orbit according to input time and anomaly vectors. Handles
high eccentricity and maneuvers input through acceleration vector.
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Form:
[prob, dMin, Shat, xhat] = CollisionMonAlg( y, t, M, nu, accel, aDiff, d )
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Inputs
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y (6,m) Relative state(s)
t (1,n) Time vector [s]
M (1,n) Mean anomaly vector
nu (1,n) True anomaly vector
accel {m} Accelerations due to maneuvers
aDiff (3,m) Differential accelerations
d (.) Algorithm data structure
.el0 Initial elements
.eRef Eccentricity
.MRef Mean anomaly
.initBounds Error in measurement (6,1) [km, km/s]
.scalev Sigma for measurement noise
.lenSC Spacecraft length [m]
.Pmin Probability of scalev
.Ssc Spacecraft hard-body sphere
.S0 Initial ellipsoid
Outputs
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prob {n}(1,:) probability of collision
d {n}(1,:) minimum distance between spacecraft position ellipsoids
xhat {n}(6,:) xhat, ellipsoid centers
Shat {n}(6,6,:) Shat, ellipsoid size matrices
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Reference: Mark Campbell, Collision Monitoring Within Satellite
Clusters. IEEE Transactions on Control Systems
Technology, Jan. 2005
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