StraightLine Module |
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Directory List
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ConstantAccel
| ConstantAccelDV | Estimate DV using constant acceleration approximation |
| MassFuelElectricConstantPower | Fuel mass for a constant accel/power electric propulsion system |
| MassFuelElectricConstantUE | Fuel mass for a constant accel/exhaust velocity electric propulsion system. |
| StraightLineConstantAccel | Constant acceleration simulation |
| StraightLineDataStructure | Returns data structure for straight line functions |
| TOFConstAccel | Compute the transit time and exhaust velocity for constant acceleration |
| ThrustElectric | Computes power and thrust, constant accel, as a function of specific power. |
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ConstantThrust
| ComputeDuration | Compute straight-line duration given power and distance (analytic) |
| ComputeDurationFraction | Compute the duration from the desired payload fraction |
| ComputePayload | Compute payload mass given power, distance, and time (analytic). |
| ComputePayloadFraction | Compute payload fraction given time, distance, and uE (analytic) |
| ComputeThrust | Compute the thrust for a mission, given time and distance |
| DVConstantThrust | Velocity change with constant thrust given fuel and time |
| DVForTime | Straight-line DV given payload, power and engine properties |
| DVLimit | Straight-line DV limit from engine parameters and time. |
| DryMass | Dry mass of vehicle from thrust: payload + engine + fuel tanks |
| EngineReport | Report of constant-thrust engine properties |
| MassFuelElectricConstantThrust | Fuel mass for a constant thrust electric propulsion system. |
| MaximumDV | Maximum DV calculated from power level |
| OptimalCharacteristicVelocity | Optimal velocity ratio for straight-line mission |
| OptimalExhaustVelocity | Find a mass-optimal straight-line exhaust velocity using fminbnd |
| OptimalTripTime | Optimal straight-line trip time for an ideal rocket |
| PlotPayloadFraction | Plot the payload fraction for a range of transfer times |
| RoundTripTime | Round trip time for a straight-line, constant thrust (Kammash) |
| SimulateStraightLineTrajectory | Simulate a straight line, constant-thrust trajectory |
| SolveSigma | Solve for a sigma given a time, distance, and payload (fzero) |
| Straight2DStructure | Data structure for straight line mission analysis |
| StraightLineConstantThrust | Compute straight line bang-bang trajectory with constant thrust |
| StraightLineOptimal | Compute exhaust velocity and thrust for a minimum mass trajectory |
| StraightLineReport | Text report for straight line trajectory output |
| SwitchTime | Calculate the switch time for a straight line trajectory |
| TOFConstExVel | Compute the transit timefor constant thrust & exhaust velocity |
| TOFConstThrust | Compute the transit time and exhaust velocity for constant thrust |
| TripDistance | Distance traveled in time for straight-line constant thrust. |
| TripTime | Compute the trip time and thrust from distance and total mass (analytic) |
| UToMF | Calculate masses for a spacecraft with an electric propulsion system. |
| ZeroPayloadDistance | Maximum straight-line distance achievable in specified time. |
| ZeroPayloadTime | Compute minimum time to achieve a straight-line distance. |
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Data
| PlutoLander_Stowed.mat | CAD model of stowed lander |
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Demos/AlphaCentauri
| AlphaCentauriFlyby | AlphaCentauri flyby at constant thrust |
| DataRateAlphaCentauri | Data Rate Alpha Centauri |
| StraightLineAlphaCentauri | Straight-line rendezvous to Alpha Centauri |
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Demos/ConstantThrust
| DVLimitDemo | Delta-V limits for a selected mission |
| DVMapDemo | Demo of attainable DV for a given payload mass |
| DVvsTripTime | DV vs trip time demo for specific missions |
| DurationDemo | Solar system performance plot for straight-line trajectories. |
| MaxDistanceDemo | Demo of the mimimum time and maximum distance straight-line functions. |
| NASADemos | NASA roadmap mission point solutions to Jupiter, Pluto, 125 AU |
| NASAMissionChart | Mission capability chart using straight-line trajectories |
| OptimalImpulseDemo | Optimal impulse for straight-line trajectories |
| PayloadDemo | Straight-line payload study to 125 AU |
| PayloadFractionDemo | Payload fraction demo for a variety of reference missions |
| PointSolution | Straight line Point solution |
| TripTimeDemo | Trip time vs. power demo |
| UEVsSigma | Compute exhaust velocity vs specific power |
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Demos/Flyby
| DistanceForFixedTime | >100 MW engine analysis to interstellar distances, flyby and rendezvous |
| FlybyForFixedTime | Straight-line, constant-thrust flyby demo |
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Demos/Rectilinear
| RectilinearDemo | Demonstrate RectilinearMission - burn, coast, burn. |
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Demos/SLPowerLimited
| PowerLimitedRocket | Power-Limited Rocket (SLPL) Demo |
| SLPLComparisonDemo | Compare a constant-thrust mission to optimal linear acceleration |
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ElectricEngine
| EngineMass | Compute engine mass given straight-line thrust |
| EnginePower | Compute engine power from thrust |
| EngineThrust | Compute engine thrust given power |
| FuelMass | Fuel mass from the thrust and duration |
| InitialMass | Initial mass of vehicle from straight-line thrust and time |
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Flyby
| FlybyConstantThrust | Flyby distance and velocity for constant thrust. |
| FlybyOptimalImpulse | Find exhaust velocity to maximise payload fraction (fminsearch) |
| FlybyReport | Report of engine properties for a straight-line flyby mission |
| SimulateFlyby | Straight line constant thrust flyby simulation |
| SolveFlybyPower | Solve a flyby problem and compute engine power for the payload |
| SolveLambdaFlyby | Compute the payload fraction for a straight-line flyby (fminbnd). |
| ZeroPayloadFlyby | Compute the zero payload flyby distance for duration, or time for distance |
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Rectilinear
| RectilinearMission | Generate a mission plan for a burn, coast burn mission. |
| RectilinearMotion | Simulate rectilinear motion. |
| TimeToVelocity | Compute the time to reach a given velocity. |
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SLPowerLimited
| OptimalSLPL | Compute optimal engine and fuel mass ratios for SLPL rendezvous |
| SLPLDataStructure | Straight-line, power-limited data structure |
| SLPLDeltaV | Compute delta-V of an ideal power-limited rocket (straight-line) |
| SLPLFindDistance | Finds duration, ideal power-limited rocket, straight-line trajectory |
| SLPLFindDuration | Finds duration, ideal power-limited rocket, straight-line trajectory |
| SLPLFindMass | Finds final mass, ideal power-limited rocket, straight-line trajectory |
| SLPLFindPower | Finds required power, ideal power-limited rocket, straight-line traj. |
| SLPLReport | Print a summary of an SLPL problem |
| SLPLSolver | Solve a straight-line power-limited rocket problem. |
| SLPLTrajectory | Compute trajectory for an ideal power-limited rocket (straight-line) |
| SLPLTrajectoryLambda | Trajectory for an ideal power-limited rocket (straight-line) from lambda |
| TOFLinearAccel | Compute the transit time and exhaust velocity for constant thrust |
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