Module:Rocketry

Documentation for this module may be created at Module:Rocketry/doc

local Gas = require("Module:Gas")
local Combustion = require("Module:Combustion")
local CombustionData = require("Module:Combustion/data")
local GasData = mw.loadData("Module:Gas/data")

local p = {}

function p.GetCombustionTemperature(fuel, oxidizer, reactiondata, combustionRatio, fuelTemperature, oxidizerTemperature)

local EnthalpyMultiplier = 1
fuelTemperature = fuelTemperature or 100
oxidizerTemperature = oxidizerTemperature or 100
combustionRatio = combustionRatio or 0.96

if not outputs then
    if not oxidizer then
        reactiondata = CombustionData[fuel]
    else
        reactiondata = CombustionData[fuel][oxidizer]
        EnthalpyMultiplier = Gas.GetGas(oxidizer).EnthalpyMultiplier
    end
end

local FuelEnthalpy = Gas.GetGas(fuel).Enthalpy
local FuelHeatEnergy = (Gas.GetGas(fuel).SpecificHeat*fuelTemperature)*reactiondata.FuelAmount
local OxidizerHeatEnergy = (Gas.GetGas(oxidizer).SpecificHeat*oxidizerTemperature)*reactiondata.OxidizerAmount
local CombustionEnergy = FuelEnthalpy*reactiondata.FuelAmount*combustionRatio*EnthalpyMultiplier
local TotalEnergy = FuelHeatEnergy + OxidizerHeatEnergy + CombustionEnergy

--add uncombusted contents to reaction outputs

if combustionRatio < 1 then
    table.insert(reactiondata.Outputs,
        {
            Gas = Gas.GetGas(fuel),
            Amount = reactiondata.FuelAmount*(1-combustionRatio)
        }
    )
    table.insert(reactiondata.Outputs,
        {
            Gas = Gas.GetGas(oxidizer),
            Amount = reactiondata.OxidizerAmount*(1-combustionRatio)
        }
    )
end

--calculate Heat Capacity of reaction output
local OutputHeatCapacity = 0
for k,v in pairs(reactiondata.Outputs) do
    OutputHeatCapacity = OutputHeatCapacity + (v.Gas.SpecificHeat * v.Amount)
end

return TotalEnergy / OutputHeatCapacity, reactiondata --i'll want that later on for exhaust velocity because of heat capacity ratio.

end

function p.GetExhaustVelocity(engineEfficiency, combustiontemperature, heatcapacityratio)
    if not heatcapacityratio then heatcapacityratio = GasData.TriatomicHeatCapacityRatio end
    if type(heatcapacityratio) == "table" and type(heatcapacityratio.Outputs) == "table" then
        --calculate heat capacity ratio by averaging out the heat capacity ratio of exhaust composition
        local TotalMoles = 0
        local TotalMolarHeatCapacityRatio = 0
        for k,v in pairs(heatcapacityratio.Outputs) do
            TotalMoles = TotalMoles + v.Amount
            TotalMolarHeatCapacityRatio = TotalMolarHeatCapacityRatio + (v.Amount * v.Gas.HeatCapacityRatio)
        end
        heatcapacityratio = TotalMolarHeatCapacityRatio/TotalMoles
    end
    if type(heatcapacityratio) == "string" then heatcapacityratio = tonumber(heatcapacityratio) end
    if type(heatcapacityratio) ~= number then
    mw.log.warn("WARN: UNABLE TO PARSE HEAT CAPACITY RATIO. ASSUMING TriatomicHeatCapacityRatio")
    heatcapacityratio = GasData.TriatomicHeatCapacityRatio
    end

    return 25*engineEfficiency*((8.3144*heatcapacityratio*combustiontemperature)^0.5)
    
end
function p.GetThrust(ExhaustVelocity, MassFlowRate)
    if type(MassFlowRate) == "table" and type(MassFlowRate.Outputs) == "table" then
        --calculate the molar mass of exhaust composition
        local TotalMoles = 0
        for k,v in pairs(heatcapacityratio.Outputs) do
            TotalMoles = TotalMoles + v.Amount
        end
        MassFlowRate = TotalMoles
    end
    return 2*ExhaustVelocity*MassFlowRate --2 ticks/second; MassFlowRate is given in mols/tick.
end

return p