ImpulsiveLPManeuver:
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Computes the delta-v sequence for a relative orbit maneuver.
A fixed thrust actuator is assumed when converting delta-v to burn duration.
Algorithms do not account for gravitational perturbations or disturbances.
The reference orbit may be circular or eccentric.
The linear program "Simplex" is used to compute the delta-v sequence.
Since version 7.
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Format:
[maneuver,maxDV] = ImpulsiveLPManeuver( state, goals, window, parameters );
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Inputs
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state (.) Data structure of the orbit state with following fields
- el Measured mean orbital elements of reference
- xH Measured Hills-frame state: [x;y;z;xdot;ydot;zdot]
- mass Spacecraft mass [kg]
- tM Timetag of measurement [sec]
goals (.) Data structure of geometric goal information.
Describes the desired trajectory.
window (.) Data structure of commanded time window with following fields
- startTime Earliest possible start time [sec since 1970]
- nOrbMin Minimum number of orbits maneuver may last [orbits]
- nOrbMax Maximum number of orbits maneuver may last [orbits]
- nManeuvers Number of maneuvers to search over
- timeWeightExp Time-weighting exponent (greater than 0)
parameters (.) Data structure of planning parameters with following fields
- fNom Nominal Thruster force [kN]
- dTMax Maximum allowable burn duration [sec]
- horizon Minimum time between planning and first burn [sec]
- tDelayOOP Minimum time between final IP burn and OOP burn [sec]
- nSPOCoarse Number of samples per orbit for LP (coarse computation)
- nSPOFine Number of samples per orbit for LP (fine computation)
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Outputs
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maneuver (.) Maneuver data structure with following fields
- t0 Earliest burn start time
- tF Latest burn finish time
- nBurns Number of burns required
+ burnData[] Array of burn data structures with following fields
- t Burn start time [sec since 1970]
- dT Burn duration [sec]
- dV Delta-V [km/s]
- uX unit x Hills direction
- uY unit y Hills direction
- uZ unit z Hills direction
maxDV (1) The maximum delta-v of the sequence
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Children:
FormationFlying: Coord/IsCircGeom
FormationFlying: Coord/IsEccGeom
FormationFlying: DataStructures/Maneuver_Structure
FormationFlying: DataStructures/PlanningParameters_Structure
FormationFlying: DataStructures/Window_Structure
FormationFlying: Dynamics/HillsEqns
FormationFlying: EccDynamics/FFEccDiscreteHills
FormationFlying: EccDynamics/FFEccLawdensEqns
FormationFlying: LP/LPCircular
FormationFlying: LP/LPCircularTimeWeight
FormationFlying: LP/LPEccentric
FormationFlying: LP/LPEccentricGVE
FormationFlying: LP/LPEccentricTimeWeight
FormationFlying: Transformation/FFEccGoals2Hills
FormationFlying: Transformation/FFEccHills2DeltaElem
FormationFlying: Transformation/GeometryCirc2Ecc
FormationFlying: Transformation/GeometryEcc2Circ
FormationFlying: Utility/AccelVector2ManeuverStruct
FormationFlying: Utility/FFEccTargetTrueAnom
Math: Linear/Mag
Math: Trigonometry/UnwrapPhase
OrbitMiniToolbox: Support/M2Nu
SC: BasicOrbit/Nu2MAbs
SC: BasicOrbit/OrbRate
SC: BasicOrbit/Period
