-- unsigned char Name_;     //  Rocket name
    -- int           Escort_;   //  Escort(?): 0-no, 1-launch aircraft, 2-another aircraft, 3-from the ground
    -- int           Head_Type_;// Type of homing head (see above)
    --              sigma = {x, y, z}, maximum aiming error in meters, in coordinates of the target. x- logitudinal, y-vertical, z-transverse
    -- float         M_;        //  gross weight in kg
    -- float         H_max_;    //  maximum flight altitude
    -- float         H_min_;    //  minimum flight altitude
    -- float         Diam_;     //  case diameter in mm
    -- int           Cx_pil;    //  Cx как подвески (Cx like pendants?)
    -- float         D_max_;    //  Low launch maximum range
    -- float         D_min_;    //  Minimum starting range
    -- bool          Head_Form_;// false - hemispherical shape of head,true - animated (~conical)
    -- float         Life_Time_;//  lifetime (self-destruct time), sec
    -- double        Nr_max_;   // Maximum overload on turns
    -- float         v_min_;    // minimum speed
    -- float    v_mid_;  // average speed
    -- float         Mach_max_; // maximum mach number
    -- float         t_b_;      // engine start time
    -- float         t_acc_;    // acceleration run time
    -- float         t_marsh_;  // march time
    -- float         Range_max_;// maximum starting range at maximum height
    -- float         H_min_t_;  // minimum height of the target over the relief, m
    -- float         Fi_start_; // launch tracking and sighting angle
    -- float         Fi_rak_;   // allowable target angle (rad)
    -- float         Fi_excort_;// target tracking angle (sight) of the missile
    -- float          Fi_search_;// free angle limit
    -- float          OmViz_max_;// line of sight speed
    -- float         Damage_;// direct damage
    -- /*   int           Engine_Type_; // Engine type: 1 - solid;
                             -- // 2 - Liquid Rocket Engine (RD) (LRE);
                             -- // 3 - Direct-flow Air taxiway ;
                             -- // 4 - accelerator-1 + LRE
                             -- // 5 - turbojet
                             -- // 6 - turbojet + accelerator
    -- int           Stage_;    // number of steps*/
    -- float         X_back_;   // coordinates of the center of the nozzle in the axes of the rocket
    -- float         Y_back_;
    -- float         Z_back_;
    -- float         X_back_acc_; // coordinates of the center of the accelerator nozzle in the axes of the rocket
    -- float         Y_back_acc_;
    -- float         Z_back_acc_;
    -- float          Reflection;   // effective reflective surface, square meters


    -- double        KillDistance; Kill distances - this distance is used to fire a fuze

    -- // These are warheads used to simulate explosions
    -- // Due to the architecture of blocksim we have to use two schemes -
    -- // one for server object (which actually makes damage), and other for
    -- // client object (which does not make any damage)

    -- Instant rocket viewing angle:
    -- IR GOS +- 1 degree
    -- RS GOS +- 5 degrees



local MBDA_Mistral = {
  category = CAT_AIR_TO_AIR,
  name = "MBDA_Mistral",            -- unsigned char Name_; //  Rocket name
  user_name = _("MBDA Mistral"),
  wsTypeOfWeapon = {
    wsType_Weapon,
    wsType_Missile,
    wsType_AA_Missile,
    WSTYPE_PLACEHOLDER
  },
  Escort = 0,       -- int Escort_; Escort(support?): 0-no, 1-launch aircraft, 2-another aircraft, 3-from the ground
  Head_Type = 1,    -- int Head_Type_; Type of homing head (InfraredSeeker = 1, ActiveRadar = 2, AntiRadar = 3, LaserHoming = 4, Autopilot = 5, SemiActiveRadar = 6, SemiAutoAT = 7
  sigma = {1,1,1},  -- sigma = {x, y, z}; maximum aiming error in meters, in coordinates of the target. x- logitudinal, y-vertical, z-transverse
  M = 19.7,         -- float M_; gross weight in kg
  H_max = 18000,    -- float H_max_; maximum flight altitude
  H_min = -1,       -- float H_min_; minimum flight altitude
  Diam = 90,        -- float Diam_; case diameter in mm
  Cx_pil = 1.29,    -- int Cx_pil; Cx как подвески (Cx like pendants?)
  D_max = 7000,     -- float D_max_; maximum launch range at low alt
  D_min = 500,      -- float D_min_; Minimum launch range
  Head_Form = 0,    -- bool Head_Form_; false - hemispherical seeker head,true - animated (conical)
  Life_Time = 17,   -- float Life_Time_; lifetime (self-destruct time), sec
  Nr_max = 30,      -- double Nr_max_; Maximum G
  v_min = 669.8,    -- float v_min_; minimum speed
  v_mid = 904.4,    -- float v_mid_; average speed
  Mach_max = 2.66,  -- float Mach_max_; maximum mach number
  t_b = 0,          -- float t_b_; engine start time
  t_acc = 5,        -- float t_acc_; booster burn time
  t_marsh = 6.8,    -- float t_marsh_; sustainer burn time
  Range_max = 14000,-- float Range_max_; maximum launch range at maximum height
  H_min_t = 0,      -- float H_min_t_; minimum target altitude agl, m
  Fi_start = 1,     -- float Fi_start_; launch tracking and sighting angle
  Fi_rak = 3.14152, -- float Fi_rak_; allowable target angle (rad)
  Fi_excort = 1,    -- float Fi_excort_; target tracking angle (sight) of the missile
  Fi_search = 99.9, -- float Fi_search_; free angle limit
  OmViz_max = 99.9, -- float OmViz_max_; line of sight speed
  warhead = {
    mass = 3,
    expl_mass = 5.1,
    other_factors = {
      1,
      1,
      1
    },
    obj_factors = {1, 1},
    concrete_factors = {
      1,
      1,
      1
    },
    cumulative_factor = 0,
    concrete_obj_factor = 0,
    cumulative_thickness = 0,
    piercing_mass = 0.6,
    caliber = 90
  },
  Damage = 25,  -- float Damage_; direct damage
  exhaust = {
    0.7,
    0.7,
    0.7,
    0.2
  },
  X_back = -1,      -- float X_back_; coordinates of the center of the nozzle in the axes of the rocket
  Y_back = 0,       -- float Y_back_;
  Z_back = 0,       -- float Z_back_;
  Reflection = 0.0182,  -- float Reflection; effective reflective surface, square meters
  KillDistance = 7,     -- double KillDistance; Kill distances - this distance is used to fire a fuze
  SeekerSensivityDistance = 20000,  -- The range of target with IR value = 1. In meters.
  ccm_k0 = 0.5,         -- Counter Countermeasures Probability Factor. Value = 0 - missile has absolutely resistance to countermeasures. Default = 1 (medium probability)
  SeekerCooled = true,  -- True is cooled seeker and false is not cooled seeker.
  shape_table_data = {
    {
      name = "MBDA_Mistral",
      file = "MBDA_Mistral",
      life = 1,
      fire = {0, 1},
      username = "MBDA Mistral",
      index = WSTYPE_PLACEHOLDER
    }
  },
  ModelData = {
    58,         -- model params count
    0.2,        -- characteristic area

    -- Сx dependency parameters
    0.004,      -- Cx_k0 планка Сx0 на дозвуке ( M << 1)
    0.008,      -- Cx_k1 высота пика волнового кризиса
    0.004,      -- Cx_k2 крутизна фронта на подходе к волновому кризису
    0.012,      -- Cx_k3 планка Cx0 на сверхзвуке ( M >> 1)
    0.004,      -- Cx_k4 крутизна спада за волновым кризисом
    1.2,        -- коэффициент отвала поляры (пропорционально sqrt (M^2-1))

    -- параметры зависимости Cy
    1.3,        -- Cy_k0 планка Сy0 на дозвуке ( M << 1)
    1.2,        -- Cy_k1 планка Cy0 на сверхзвуке ( M >> 1)
    1.2,        -- Cy_k2 крутизна спада(фронта) за волновым кризисом

    0.4,        -- 7 Alfa_max Maximum balancing angle, radians (максимальный балансировочный угол, радианы)
    0,          -- angular velocity created by the moment of gas rudders (angular velocity created by thrust vectoring?)

    -- Engine data. Time, fuel flow, thrust.
    --  t_statr     t_b     t_accel     t_march     t_inertial      t_break     t_end           -- Stage
            -1,     -1,          5,         6.8,            0,            0,    1000000000,     -- time of stagem sec
             0,      0,      1.163,           0,            0,            0,             0,     -- fuel flow rate in kg/sec
             0,      0,       3100,           0,            0,            0,             0,     -- thrust, N

    11.8,   -- self-destruction timer, sec
    11.8,   -- power system operating time, sec
    0,      -- self-destruct altitude, m
    0.1,    -- control deplay time (launch maneuver safety delay), sec
    1000000000, -- range to the target at time of launch beyond which the rocket lofts, m
    1000000000, -- distance to target at which loft ends and missile switches to proportional navigation, m
    0,      -- синус угла возвышения траектории набора горки (sine of elevation?)
    30,     -- продольное ускорения взведения взрывателя (longitudinal acceleration arming (cocking?) fuse)
    0,      -- speed imparted by ejection device, expelling charge, etc
    1.19,   -- characteristic of the SAU-ROCKET system, second-order filter coefficient K0
    1,      -- характристика системы САУ-РАКЕТА,  second-order filter coefficient K1
    2,      -- характристика системы САУ-РАКЕТА,  полоса пропускания контура управления
    0,      -- дальность полета в горизонт с располагаемой перегрузкой Navail >= 1.0 на высоте H=2000 (Range to the horizon with disposable overload Naval >= 1.0 at a height of 200)
    0,      -- крутизна зависимости  дальность полета в горизонт с располагаемой перегрузкой Navail >= 1.0 от высоты H (slope of the dependence of the flight range to the horizon with a disposable overload Navail> = 1.0 on height H)
    0,      --  coefficient of corrections to the distance based on speed of shooter
    0,      -- dimensionless coefficient. SPG missile performance
    0,      -- Rocket flight time forecast
    -- DLZ. Data for calculating launch ranges (indication on the sight)
    11000,  -- range aspect 180 (hot), H = 10km, V=900kph
    7000,   -- range aspect 0 (cold), H=10km, V=900kph
    7000,   -- range aspect 180 (hot), Н=1000m, V=900kph
    0.2,    -- Decrease in launch range when target's velocity vector deviates from the line of sight of the target
    1,      -- Vertical plane. The slope of the curve of the permitted launch range in the lower hemisphere. Range reduction when shooting down.
    1.4,    -- Vertical plane. The slope of the curve allowed range launch in the upper hemisphere. Range increase when shooting up.
    -3,     -- Vertical plane. The inflection angle of the range curve, upper - lower hemisphere.
    0.5     -- Change of the slope coefficients of the curve in the upper and lower hemispheres depending on shooter's altitude.
  }
}