[UAV]
[UAV.Aircraft]
  free  W_mto
  free  W_tilde
  free  W_zfw
  free  Engine.W
  free  Wing.W
  fixed CDA0
  fixed W_fixed
  fixed W_pay
  cons  W_tilde ≥ W_fixed + W_pay + Engine.W
  cons  W_zfw ≥ W_tilde + Wing.W
[UAV.Aircraft.Wing]
  free  A
  free  I_cap
  free  M_rbar
  free  S
  free  W_cap
  free  W_web
  free  W
  free  nu
  free  p
  free  q
  free  t_cap
  free  t_web
  free  tau
  free  W_tilde  [UAV.Aircraft]
  fixed C_Lmax
  fixed EI_ref
  fixed N_lift
  fixed W_ref
  fixed e
  fixed f_wadd
  fixed k_shear
  fixed r_h
  fixed rho_alum
  fixed sigma_max_shear
  fixed sigma_max
  fixed w
  fixed g
  cons (Geometry)  2⋅q ≥ 1 + p
  cons (Geometry)  p ≥ 1.9
  cons (Geometry)  tau ≤ 0.15
  cons (Geometry)  nu^3.94 ≥ 0.86⋅p^-2.38 + 0.14⋅p^0.56
  cons (Root bending stress)  M_rbar ≥ W_tilde⋅A⋅p/(24⋅W_ref)
  cons (Root bending stress)  0.423⋅w⋅tau²⋅t_cap ≥ I_cap⋅k_shear + 0.92⋅w⋅tau⋅t_cap²
  cons (Root bending stress)  N_lift⋅M_rbar⋅A⋅q²⋅tau⋅EI_ref/(S⋅I_cap⋅sigma_max) ≤ 8
  cons (Root bending stress)  A⋅W_tilde⋅N_lift⋅q²/(tau⋅S⋅t_web⋅sigma_max_shear) ≤ 12
  cons (Weight rollup)  W_cap ≥ 8⋅rho_alum⋅g⋅w⋅t_cap⋅S^1.5⋅nu/(3⋅A^0.5)
  cons (Weight rollup)  W_web ≥ 8⋅rho_alum⋅g⋅r_h⋅tau⋅t_web⋅S^1.5⋅nu/(3⋅A^0.5)
  cons (Weight rollup)  W/f_wadd ≥ W_cap + W_web
[UAV.Aircraft.Engine]
  free  P_max
  free  W
  fixed A_prop
  fixed W_eng_coeff
  fixed eta_eng
  fixed eta_v
  fixed h_fuel
  cons  W ≥ W_eng_coeff⋅P_max^0.803
[UAV.Mission]
  free  R
  free  W_fuel
  free  W_mto  [UAV.Aircraft]
  free  W_zfw  [UAV.Aircraft]
  free  Outbound.AircraftPerf.W
  free  Outbound.W_fuel
  free  Return.AircraftPerf.W
  free  Return.W_fuel
  free  SprintCondition.AircraftPerf.W
  fixed R_min
  cons  R ≥ R_min
  cons  Outbound.AircraftPerf.W ≥ W_zfw + Return.W_fuel
  cons  Return.AircraftPerf.W ≥ W_zfw
  cons  SprintCondition.AircraftPerf.W = Outbound.AircraftPerf.W
  cons  W_fuel ≥ Outbound.W_fuel + Return.W_fuel
  cons  W_mto ≥ W_zfw + W_fuel
[UAV.Mission.Outbound]
  free  W_fuel
  free  z_bre
  free  eta_0
  free  T
  free  W
  free  R  [UAV.Mission]
  fixed h_fuel  [UAV.Aircraft.Engine]
  fixed g
  cons  z_bre ≥ g⋅R⋅T/(h_fuel⋅eta_0⋅W)
  cons  W_fuel/W ≥ z_bre^1 + z_bre²/2 + z_bre³/6 + z_bre⁴/24
[UAV.Mission.Outbound.AircraftPerf]
  free  C_D
  free  C_Di
  free  T
  free  W
  free  A  [UAV.Aircraft.Wing]
  free  S  [UAV.Aircraft.Wing]
  free  C_Dp
  free  C_L
  free  V  [UAV.Mission.Outbound.FlightState]
  fixed CDA0  [UAV.Aircraft]
  fixed e  [UAV.Aircraft.Wing]
  fixed rho  [UAV.Mission.Outbound.FlightState]
  cons  W ≤ 0.5⋅rho⋅C_L⋅S⋅V²
  cons  T ≥ 0.5⋅rho⋅C_D⋅S⋅V²
  cons  C_Di ≥ C_L²/(π⋅e⋅A)
  cons  C_D ≥ CDA0/S + C_Dp + C_Di
[UAV.Mission.Outbound.FlightState]
  free  V
  fixed mu
  fixed rho
[UAV.Mission.Outbound.AircraftPerf.WingAero]
  free  C_Dp
  free  C_L
  free  Re
  free  A  [UAV.Aircraft.Wing]
  free  S  [UAV.Aircraft.Wing]
  free  tau  [UAV.Aircraft.Wing]
  free  V  [UAV.Mission.Outbound.FlightState]
  fixed mu  [UAV.Mission.Outbound.FlightState]
  fixed rho  [UAV.Mission.Outbound.FlightState]
  cons  Re = rho/mu⋅V⋅(S/A)^0.5
  cons  2.56⋅C_L^5.881/(Re^1.541⋅tau^3.319⋅C_Dp^2.617) + 3.82e-09⋅tau^6.229/(C_L^0.914⋅Re^1.379⋅C_Dp^9.57) + 0.00215⋅Re^0.1441⋅tau^0.03325/(C_L^0.0079⋅C_Dp^0.7337) + 1.19e+04⋅C_L^9.783⋅tau^1.764/(Re^0.998⋅C_Dp^0.909) + 6.14e-06⋅C_L^6.535/(Re^0.995⋅tau^0.521⋅C_Dp^5.192) ≤ 1
[UAV.Mission.Outbound.AircraftPerf.PropulsionPerf]
  free  eta_0
  free  eta_i
  free  eta_prop
  free  T  [UAV.Mission.Outbound.AircraftPerf]
  free  V  [UAV.Mission.Outbound.FlightState]
  fixed A_prop  [UAV.Aircraft.Engine]
  fixed eta_eng  [UAV.Aircraft.Engine]
  fixed eta_v  [UAV.Aircraft.Engine]
  fixed rho  [UAV.Mission.Outbound.FlightState]
  cons  eta_0 ≤ eta_eng⋅eta_prop
  cons  eta_prop ≤ eta_i⋅eta_v
  cons  4⋅eta_i + T⋅eta_i²/(0.5⋅rho⋅V²⋅A_prop) ≤ 4
[UAV.Mission.Return]
  free  W_fuel
  free  z_bre
  free  eta_0
  free  T
  free  W
  free  R  [UAV.Mission]
  fixed h_fuel  [UAV.Aircraft.Engine]
  fixed g
  cons  z_bre ≥ g⋅R⋅T/(h_fuel⋅eta_0⋅W)
  cons  W_fuel/W ≥ z_bre^1 + z_bre²/2 + z_bre³/6 + z_bre⁴/24
[UAV.Mission.Return.AircraftPerf]
  free  C_D
  free  C_Di
  free  T
  free  W
  free  A  [UAV.Aircraft.Wing]
  free  S  [UAV.Aircraft.Wing]
  free  C_Dp
  free  C_L
  free  V  [UAV.Mission.Return.FlightState]
  fixed CDA0  [UAV.Aircraft]
  fixed e  [UAV.Aircraft.Wing]
  fixed rho  [UAV.Mission.Return.FlightState]
  cons  W ≤ 0.5⋅rho⋅C_L⋅S⋅V²
  cons  T ≥ 0.5⋅rho⋅C_D⋅S⋅V²
  cons  C_Di ≥ C_L²/(π⋅e⋅A)
  cons  C_D ≥ CDA0/S + C_Dp + C_Di
[UAV.Mission.Return.FlightState]
  free  V
  fixed mu
  fixed rho
[UAV.Mission.Return.AircraftPerf.WingAero]
  free  C_Dp
  free  C_L
  free  Re
  free  A  [UAV.Aircraft.Wing]
  free  S  [UAV.Aircraft.Wing]
  free  tau  [UAV.Aircraft.Wing]
  free  V  [UAV.Mission.Return.FlightState]
  fixed mu  [UAV.Mission.Return.FlightState]
  fixed rho  [UAV.Mission.Return.FlightState]
  cons  Re = rho/mu⋅V⋅(S/A)^0.5
  cons  2.56⋅C_L^5.881/(Re^1.541⋅tau^3.319⋅C_Dp^2.617) + 3.82e-09⋅tau^6.229/(C_L^0.914⋅Re^1.379⋅C_Dp^9.57) + 0.00215⋅Re^0.1441⋅tau^0.03325/(C_L^0.0079⋅C_Dp^0.7337) + 1.19e+04⋅C_L^9.783⋅tau^1.764/(Re^0.998⋅C_Dp^0.909) + 6.14e-06⋅C_L^6.535/(Re^0.995⋅tau^0.521⋅C_Dp^5.192) ≤ 1
[UAV.Mission.Return.AircraftPerf.PropulsionPerf]
  free  eta_0
  free  eta_i
  free  eta_prop
  free  T  [UAV.Mission.Return.AircraftPerf]
  free  V  [UAV.Mission.Return.FlightState]
  fixed A_prop  [UAV.Aircraft.Engine]
  fixed eta_eng  [UAV.Aircraft.Engine]
  fixed eta_v  [UAV.Aircraft.Engine]
  fixed rho  [UAV.Mission.Return.FlightState]
  cons  eta_0 ≤ eta_eng⋅eta_prop
  cons  eta_prop ≤ eta_i⋅eta_v
  cons  4⋅eta_i + T⋅eta_i²/(0.5⋅rho⋅V²⋅A_prop) ≤ 4
[UAV.Mission.SprintCondition]
  free  P_max  [UAV.Aircraft.Engine]
  free  eta_0
  free  T
  free  V
  fixed V_reqt
  cons  P_max ≥ T⋅V/eta_0
  cons  V ≥ V_reqt
[UAV.Mission.SprintCondition.AircraftPerf]
  free  C_D
  free  C_Di
  free  T
  free  W
  free  A  [UAV.Aircraft.Wing]
  free  S  [UAV.Aircraft.Wing]
  free  C_Dp
  free  C_L
  free  V  [UAV.Mission.SprintCondition.FlightState]
  fixed CDA0  [UAV.Aircraft]
  fixed e  [UAV.Aircraft.Wing]
  fixed rho  [UAV.Mission.SprintCondition.FlightState]
  cons  W ≤ 0.5⋅rho⋅C_L⋅S⋅V²
  cons  T ≥ 0.5⋅rho⋅C_D⋅S⋅V²
  cons  C_Di ≥ C_L²/(π⋅e⋅A)
  cons  C_D ≥ CDA0/S + C_Dp + C_Di
[UAV.Mission.SprintCondition.FlightState]
  free  V
  fixed mu
  fixed rho
[UAV.Mission.SprintCondition.AircraftPerf.WingAero]
  free  C_Dp
  free  C_L
  free  Re
  free  A  [UAV.Aircraft.Wing]
  free  S  [UAV.Aircraft.Wing]
  free  tau  [UAV.Aircraft.Wing]
  free  V  [UAV.Mission.SprintCondition.FlightState]
  fixed mu  [UAV.Mission.SprintCondition.FlightState]
  fixed rho  [UAV.Mission.SprintCondition.FlightState]
  cons  Re = rho/mu⋅V⋅(S/A)^0.5
  cons  2.56⋅C_L^5.881/(Re^1.541⋅tau^3.319⋅C_Dp^2.617) + 3.82e-09⋅tau^6.229/(C_L^0.914⋅Re^1.379⋅C_Dp^9.57) + 0.00215⋅Re^0.1441⋅tau^0.03325/(C_L^0.0079⋅C_Dp^0.7337) + 1.19e+04⋅C_L^9.783⋅tau^1.764/(Re^0.998⋅C_Dp^0.909) + 6.14e-06⋅C_L^6.535/(Re^0.995⋅tau^0.521⋅C_Dp^5.192) ≤ 1
[UAV.Mission.SprintCondition.AircraftPerf.PropulsionPerf]
  free  eta_0
  free  eta_i
  free  eta_prop
  free  T  [UAV.Mission.SprintCondition.AircraftPerf]
  free  V  [UAV.Mission.SprintCondition.FlightState]
  fixed A_prop  [UAV.Aircraft.Engine]
  fixed eta_eng  [UAV.Aircraft.Engine]
  fixed eta_v  [UAV.Aircraft.Engine]
  fixed rho  [UAV.Mission.SprintCondition.FlightState]
  cons  eta_0 ≤ eta_eng⋅eta_prop
  cons  eta_prop ≤ eta_i⋅eta_v
  cons  4⋅eta_i + T⋅eta_i²/(0.5⋅rho⋅V²⋅A_prop) ≤ 4
[UAV.HeavyLandingCase]
  free  V_stall
  free  W_mto  [UAV.Aircraft]
  free  S  [UAV.Aircraft.Wing]
  fixed V_stallmax
  fixed rho_sl
  fixed C_Lmax  [UAV.Aircraft.Wing]
  cons  W_mto ≤ 0.5⋅rho_sl⋅V_stall²⋅C_Lmax⋅S
  cons  V_stall ≤ V_stallmax
