Enhanced Power Split Evaluation Capabilities

Version 0.4.1 - 05 Mar 2026

Added

1. Added a DiversionMission to simulate climbing to an altitude of 10,000 ft and then diverting to another airport.

Changed

1. Updated EvalSplit to accommodate more power splits.

Battery Modeling Updates

Version 0.4.0 - 20 Jan 2026

Added

1. CostPkg with a battery replacement cost estimation model.

2. Battery state of health model to capture long term effects of using a battery during flight operations.

Changed

1. Reorganized battery (dis)charging model and broke into seperate files for readibility.

Fixed

1. Fixed C-rate assumption error and battery resizing error.

Regression Overhaul

Version 0.3.0 - 26 Nov 2025

Added

1. CeRAS CSR-01 aircraft added to aircraft specs with requisite engine and mission profile specifications.

2. Database of hobby scale electric motors added, which consists of SunnySky brand motors.

3. FLOPS OEW method added internally. Note that this would need to be integrated on the user side if it is to be used in place of the default OEW method (built-in regressions).

4. New variables added to the database:

   • Aircraft.Specs.TLAR.ADG: "Aircraft Design Group, which is used in airport planning to decide gate, runway, and taxiway requirements.
   • Aircraft.Specs.TLAR.ADGPercent: Ratio of aircraft wingspan or tail height to the maximum allowable wingspan or tail height for the given ADG.
   • Aircraft.Specs.TLAR.ADGLimitor: FLag to indicate whether the aircraft is limited by wingspan or tail height for the given ADG.

5. RandomizeDB function added which randomizes the validation datatype variables in the database. This is useful for testing the robustness of the regression models with respect to the training and validation data. This function only affects the outputs of regressions if the the user has specifically downselected the training data to be used in a regression call.

Changed

1. Internal regression restructuring.

   • Separated the large data-matrix inversion from the main regression call, this allows it to be called during specification processing, saving computation time during iterations for known input-output pair regressions.
   • Vectorized some internal calculations to improve regression performance.

Propulsion System Analysis Updates

Version 0.2.0 - 17 Sep 2025

Added

1. The README file now contains a paper to cite when using FAST for your own research.

Changed

1. Developed a new approach to analyze the propulsion system performance.
   If you use a pre-defined propulsion architecture ("C", "E", "PHE", "SHE", "TE", or "PE"), the propulsion architecture does not need to be redefined.
   If you use a custom propulsion architecture ("O"), then the matrices need to be redefined using the following five matrices:

   • Aircraft.Specs.Propulsion.PropArch.Arch: architecture matrix (defines the propulsion architecture)

   • Aircraft.Specs.Propulsion.PropArch.OperUps: upstream operational matrix (for computing power available, still a function of the mission segment)

   • Aircraft.Specs.Propulsion.PropArch.OperDwn: downstream operational matrix (for sizing and propulsion system analysis, still a function of the mission segment)

   • Aircraft.Specs.Propulsion.PropArch.EtaUps: upstream efficiency matrix (accounts for losses while propagating power upstream)

   • Aircraft.Specs.Propulsion.PropArch.EtaDwn: downstream efficiency matrix (accounts for losses while propagating power downstream)

   Additionally, the user must define which components are "sources" and "transmitters", using:

   • Aircraft.Specs.Propulsion.PropArch.SrcType: defines the types of sources used (fuel, battery, etc.)

   • Aircraft.Specs.Propulsion.PropArch.TrnType: defines the types of transmitters used (gas-turbine engine, electric motor, electric generator, propeller/fan, etc.)

   Instead of defining the power splits using LamTS/TSPS/PSPS/PSES, new variables are used:

   • Aircraft.Specs.Power.LamUps.SLS/Tko/Clb/Crs/Des/Lnd: defines the power splits for the upstream operational matrix as a function of the segment

   • Aircraft.Specs.Power.LamDwn.SLS/Tko/Clb/Crs/Des/Lnd: defines the power splits for the downstream operational matrix as a function of the segment

   Refer to the following paper to learn about the matrices:

   Mokotoff, P. and Cinar, G. (2025). Graph Theory-based propulsion system analysis. Aerospace Science and Technology, in press.