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SUPPORT SITE |
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SUPPORT SITE |
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Path: Orbit/OrbitPropagator
% Stopping conditions for an orbit.
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Form:
[value, direction] = StoppingConditions( r, v, jD, mu, stopping, planet )
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Inputs
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r (3,1) Position vector in ECI frame
v (3,1) Velocity vector in ECI frame
jD (1,1) Time
mu (1,1) Gravitational potential
stopping (1,1) Stopping condition structure
condition (:) Stopping condition structure
.name (1,:) Name of the condition
.value (1,1) Value of the condition
vInit (3,1) Initial velocity
planet (1,:) Planet name
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Outputs
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value (1,1) Value of the stopping condition
direction (1,1) Direction (-1,0,1)
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AerospaceUtils: Coord/EFToLatLonAlt AerospaceUtils: Coord/R2LatLon Math: Linear/Mag Orbit: OrbitCoord/RV2AE Orbit: OrbitMechanics/Energy Orbit: OrbitMechanics/FlightPathAngle SC: BasicOrbit/Period SC: BasicOrbit/RV2El SC: Ephem/ECIToPlanet
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