def CalculatePerformance(self, dv, pressure):
if self.sfb is None and self.liquidfuel is not None:
# liquid fuel only
self.performance = physics.lf_performance(dv,
physics.engine_isp(self.mainengine, pressure),
physics.engine_force(self.mainenginecount, self.mainengine, pressure),
pressure, self.mass - self.liquidfuel, self.liquidfuel*8/9, 1/8)
elif self.sfb is None and self.liquidfuel is None:
# atomic fuel, monopropellant or xenon
f_e = self.mainengine.f_e
self.performance = physics.lf_performance(dv,
physics.engine_isp(self.mainengine, pressure),
physics.engine_force(self.mainenginecount, self.mainengine, pressure),
pressure, self.mass - self.specialfuel, self.specialfuel/(1+f_e), f_e)
else:
# liquid fuel + solid fuel
self.performance = physics.sflf_performance(dv,
physics.engine_isp(self.mainengine, pressure),
physics.engine_isp(self.sfb, pressure),
physics.engine_force(self.mainenginecount, self.mainengine, pressure),
physics.engine_force(self.sfbcount, self.sfb, pressure),
pressure,
self.mass - self.liquidfuel - self.sfbmountmass - self.sfbcount*self.sfb.m_full,
self.liquidfuel*8/9,
self.sfbmountmass,
self.sfbcount*self.sfb.m_full,
self.sfbcount*self.sfb.m_empty)
def CalculatePerformance(self, dv, pressure):
if self.sfb is None and self.liquidfuel is not None:
# liquid fuel only
self.performance = physics.lf_performance(
dv, physics.engine_isp(self.mainengine, pressure),
physics.engine_force(self.mainenginecount, self.mainengine,
pressure), pressure,
self.mass - self.liquidfuel, self.liquidfuel * 8 / 9, 1 / 8)
elif self.sfb is None and self.liquidfuel is None:
# atomic fuel, monopropellant or xenon
f_e = self.mainengine.f_e
self.performance = physics.lf_performance(
dv, physics.engine_isp(self.mainengine, pressure),
physics.engine_force(self.mainenginecount, self.mainengine,
pressure), pressure,
self.mass - self.specialfuel, self.specialfuel / (1 + f_e),
f_e)
else:
# liquid fuel + solid fuel
self.performance = physics.sflf_performance(
dv, physics.engine_isp(self.mainengine, pressure),
physics.engine_isp(self.sfb, pressure),
physics.engine_force(self.mainenginecount, self.mainengine,
pressure),
physics.engine_force(self.sfbcount, self.sfb, pressure),
pressure, self.mass - self.liquidfuel - self.sfbmountmass -
self.sfbcount * self.sfb.m_full, self.liquidfuel * 8 / 9,
self.sfbmountmass, self.sfbcount * self.sfb.m_full,
self.sfbcount * self.sfb.m_empty)
def CreateRadialLFESFBDesign(payload, pressure, dv, acc, eng, size, count, sfb, sfbcount):
design = Design(payload, eng, count, size)
design.AddSFB(sfb, sfbcount)
lf = physics.sflf_needed_fuel(dv, physics.engine_isp(eng, pressure),
physics.engine_isp(sfb, pressure),
design.mass - design.sfbmountmass - sfbcount*sfb.m_full,
design.sfbmountmass, sfbcount*sfb.m_full, sfbcount*sfb.m_empty)
if lf is None:
return None
design.AddLiquidFuelTanks(9/8 * lf)
design.CalculatePerformance(dv, pressure)
if not design.EnoughAcceleration(acc):
return None
design.SetSFBLimit(pressure, acc)
return design
def CreateSingleLFESFBDesign(payload, pressure, dv, acc, eng, sfb, sfbcount):
design = Design(payload, eng, 1, eng.size)
design.AddSFB(sfb, sfbcount)
lf = physics.sflf_needed_fuel(
dv, physics.engine_isp(eng,
pressure), physics.engine_isp(sfb, pressure),
design.mass - design.sfbmountmass - sfbcount * sfb.m_full,
design.sfbmountmass, sfbcount * sfb.m_full, sfbcount * sfb.m_empty)
if lf is None:
return None
design.AddLiquidFuelTanks(9 / 8 * lf)
design.CalculatePerformance(dv, pressure)
if not design.EnoughAcceleration(acc):
return None
design.SetSFBLimit(pressure, acc)
return design
def CreateRadialLFEnginesDesign(payload, pressure, dv, acc, eng, size, count):
design = Design(payload, eng, count, size)
lf = physics.lf_needed_fuel(dv, physics.engine_isp(eng, pressure), design.mass, 1/8)
if lf is None:
return None
design.AddLiquidFuelTanks(9/8 * lf)
design.CalculatePerformance(dv, pressure)
if not design.EnoughAcceleration(acc):
return None
return design
def CreateRadialLFEnginesDesign(payload, pressure, dv, acc, eng, size, count):
design = Design(payload, eng, count, size)
lf = physics.lf_needed_fuel(dv, physics.engine_isp(eng, pressure),
design.mass, 1 / 8)
if lf is None:
return None
design.AddLiquidFuelTanks(9 / 8 * lf)
design.CalculatePerformance(dv, pressure)
if not design.EnoughAcceleration(acc):
return None
return design
def CreateMonoPropellantEngineDesign(payload, pressure, dv, acc, engine, tank, count):
design = Design(payload, engine, count, tank.size)
f_e = engine.f_e
mp = physics.lf_needed_fuel(dv, physics.engine_isp(engine, pressure),
design.mass, f_e)
if mp is None:
return None
design.AddMonoPropellantTanks((1+f_e) * mp, tank)
design.CalculatePerformance(dv, pressure)
if not design.EnoughAcceleration(acc):
return None
return design
def CreateElectricPropulsionSystemDesign(payload, pressure, dv, acc):
design = Design(payload, parts.ElectricPropulsionSystem, 1, parts.RadialSize.Tiny)
f_e = parts.ElectricPropulsionSystem.f_e
xf = physics.lf_needed_fuel(dv, physics.engine_isp(parts.ElectricPropulsionSystem, pressure),
design.mass, f_e)
if xf is None:
return None
design.AddXenonTanks((1+f_e) * xf)
design.CalculatePerformance(dv, pressure)
if not design.EnoughAcceleration(acc):
return None
return design
def CreateAtomicRocketMotorDesign(payload, pressure, dv, acc):
design = Design(payload, parts.AtomicRocketMotor, 1, parts.RadialSize.Small)
f_e = parts.AtomicRocketMotor.f_e
af = physics.lf_needed_fuel(dv, physics.engine_isp(parts.AtomicRocketMotor, pressure),
design.mass, f_e)
if af is None:
return None
design.AddAtomicFuelTanks((1+f_e) * af)
design.CalculatePerformance(dv, pressure)
if not design.EnoughAcceleration(acc):
return None
return design
def CreateMonoPropellantEngineDesign(payload, pressure, dv, acc, engine, tank,
count):
design = Design(payload, engine, count, tank.size)
f_e = engine.f_e
mp = physics.lf_needed_fuel(dv, physics.engine_isp(engine, pressure),
design.mass, f_e)
if mp is None:
return None
design.AddMonoPropellantTanks((1 + f_e) * mp, tank)
design.CalculatePerformance(dv, pressure)
if not design.EnoughAcceleration(acc):
return None
return design
def CreateElectricPropulsionSystemDesign(payload, pressure, dv, acc):
design = Design(payload, parts.ElectricPropulsionSystem, 1,
parts.RadialSize.Tiny)
f_e = parts.ElectricPropulsionSystem.f_e
xf = physics.lf_needed_fuel(
dv, physics.engine_isp(parts.ElectricPropulsionSystem, pressure),
design.mass, f_e)
if xf is None:
return None
design.AddXenonTanks((1 + f_e) * xf)
design.CalculatePerformance(dv, pressure)
if not design.EnoughAcceleration(acc):
return None
return design
def CreateAtomicRocketMotorDesign(payload, pressure, dv, acc):
design = Design(payload, parts.AtomicRocketMotor, 1,
parts.RadialSize.Small)
f_e = parts.AtomicRocketMotor.f_e
af = physics.lf_needed_fuel(
dv, physics.engine_isp(parts.AtomicRocketMotor, pressure), design.mass,
f_e)
if af is None:
return None
design.AddAtomicFuelTanks((1 + f_e) * af)
design.CalculatePerformance(dv, pressure)
if not design.EnoughAcceleration(acc):
return None
return design