# **************************************************************************** # CUI # # The Advanced Framework for Simulation, Integration, and Modeling (AFSIM) # # The use, dissemination or disclosure of data in this file is subject to # limitation or restriction. See accompanying README and LICENSE for details. # **************************************************************************** # UNCLASSIFIED # This missile model created from internet sources as listed. # Although sources have range listed from 8,000km to 14,000km, # this model achieves 1,140 km max range with a 1,050kg RV (payload). # In the "Annual Report to Congress Military Power of the People's Republic # of China Military Report 2008", it lists the range as 11,200km. # http://www.sinodefence.com/strategic/missile/df31.asp #Contractor: CASIC 4th Academy #Service status: In service #Configuration: Three-stage, solid propellant #Deployment: Road mobile, 8X8 tractor truck + 8-wheel trailer; or silo #Length: 13m #Body diameter: 2.25m #Launch weight: 42,000kg #Range: 10,700~11,200km #Re-entry vehicle mass: 700kg (or 1,050~1,750kg) #Warhead: One single 1,000kT yield #Guidance: Inertial + stellar update #Accuracy: 100~300m CEP #Launch preparation time: 15~30 min # #http://www.janes.com (subscription required) #Length: 13.0 m (31), 18.7 m (31A) #Body diameter: 2.0 m (1st and 2nd stages) and 1.5 m (3rd stage) #Launch weight: 42,000 kg (31), 63,000 kg (31A) #Payload: Single warhead or 3-5 MIRV, 1,050-1,750 kg #Warhead: Nuclear 1 MT or 3-5 MIRV with selectable 20, 90 or 150 kT each #Guidance: Inertial with stellar updates #Propulsion: 3-stage solid propellant #Range: 8,000 km (31), or 10,000 and 14,000 km (31A) #Accuracy: 300 m CEP #http://www.astronautix.com/lvs/df31.htm #* Stage1: 1 x JL-2-1. Motor: 1 x red_icbm_1-1. Length: 8.00 m (26.20 ft). Diameter: #* 2.00 m (6.50 ft). Propellants: #Solid. #* Stage2: 1 x KT-1-2. Motor: 1 x red_icbm_1-2. Length: 4.00 m (13.10 ft). Diameter: #* 2.00 m (6.50 ft). Propellants: #Solid. #* Stage3: 1 x JL-2-3. Motor: 1 x red_icbm_1-3. Length: 2.00 m (6.50 ft). Diameter: #* 2.00 m (6.50 ft). Propellants: S #Solid. infrared_signature RED_ICBM_1_INFRARED_SIG constant 1 watts/steradian end_infrared_signature optical_signature RED_ICBM_1_OPTICAL_SIG constant 1 m^2 end_optical_signature radar_signature RED_ICBM_1_RADAR_SIG constant 1 m^2 end_radar_signature # Nominal lethality data. weapon_effects RED_ICBM_1_EFFECT WSF_GRADUATED_LETHALITY radius_and_pk 1000.0 m 1.0 end_weapon_effects ############################################################################### aero RED_ICBM_1_STAGE_1_AERO WSF_AERO reference_area 3.141 m^2 # 2.0 m diameter aspect_ratio 4.0 # 8 meters length cl_max 4.5 # Values estimated from Hoerner's Drag book cd_zero_subsonic 0.10 cd_zero_supersonic 0.25 mach_begin_cd_rise 0.95 mach_end_cd_rise 1.20 mach_max_supersonic 6.00 end_aero aero RED_ICBM_1_STAGE_2_AERO WSF_AERO reference_area 3.141 m^2 # 2.0 m diameter aspect_ratio 2.0 # 4 meters length cl_max 4.5 # Values estimated from Hoerner's Drag book cd_zero_subsonic 0.10 cd_zero_supersonic 0.25 mach_begin_cd_rise 0.95 mach_end_cd_rise 1.20 mach_max_supersonic 6.00 end_aero aero RED_ICBM_1_STAGE_3_AERO WSF_AERO # According to pictures, about 65% of diameter reference_area 1.767 m^2 # 1.5 m diameter aspect_ratio 1.0 # 2 meters length cl_max 4.5 # Values estimated from Hoerner's Drag book cd_zero_subsonic 0.10 cd_zero_supersonic 0.25 mach_begin_cd_rise 0.95 mach_end_cd_rise 1.20 mach_max_supersonic 6.00 end_aero aero RED_ICBM_1_RV_AERO WSF_AERO reference_area 1.767 m^2 # 1.5 m diameter aspect_ratio 2.0 cl_max 4.5 # Values estimated from Hoerner's Drag book cd_zero_subsonic 0.10 cd_zero_supersonic 0.25 mach_begin_cd_rise 0.95 mach_end_cd_rise 1.30 mach_max_supersonic 6.00 end_aero mover RED_ICBM_1_MOVER WSF_GUIDED_MOVER integration_timestep 0.01 secs update_interval 0.01 secs # Length: 18.7 m (31A) #Body diameter: 2.0 m (1st and 2nd stages) and 1.5 m (3rd stage) #Launch weight: 63,000 kg (31A) #Payload: Single warhead or 3-5 MIRV, 1,050-1,750 kg #Warhead: Nuclear 1 MT or 3-5 MIRV with selectable 20, 90 or 150 kT each #Guidance: Inertial with stellar updates #Propulsion: 3-stage solid propellant #Range: 14,000 km (31A) / 11,200 km wiki #Stage1:Motor: 1 x red_icbm_1-1. Length: 8.00 m (26.20 ft). Diameter: 2.00 m (6.50 ft). Propellants: Solid. #Stage2:Motor: 1 x red_icbm_1-2. Length: 4.00 m (13.10 ft). Diameter: 2.00 m (6.50 ft). Propellants: Solid. #Stage3:Motor: 1 x red_icbm_1-3. Length: 2.00 m (6.50 ft). Diameter: 2.00 m (6.50 ft). Propellants: Solid. #Appr:Taking 63,000 kg - 1,050kg for RV #Appr:61,950 kg total x 22% for empty weight leaves #Appr:13,629 kg structure weight and 48321 fuel weight #Appr:Motor Total weight (lbs) is function of diameter and length: #Appr:Rule of thumb: W = length(in) x diam^2(in) x 0.04 #Appr:First stage total mass 314.4 x 6084 x 0.04 = 76512.384 lbs = 34705 kg #Appr:Second stage total mass 157.2 x 6084 x 0.04 = 38256.192 lbs = 17352 kg #Appr:Third stage total mass 78.0 x 6084 x 0.04 = 18982.080 lbs = 8610 kg #Appr:Total Weight of stages = 60667 kg - close to published weight #Appr:Use 90% of total weight for fuel. Rule of thumb is 75-90%. #Appr:Burn time = (total impulse)/(average thrust) #Appr:Burn time = (motor impulse in newton seconds / (motor thrust in Newtons ) #Appr:Burn time = (Fuel Mass) / (Mass Flow Rate) stage 1 aero RED_ICBM_1_STAGE_1_AERO total_mass 34750 kg # rounded fuel_mass 31275 kg # 90% of stage weight specific_impulse 270 sec # typical thrust_duration 70 sec # adjust for max g's # COMPUTED FROM WSF RUN #Empty Mass : 3475 kg; 7661.06 lbm #Fuel Mass : 31275 kg; 68949.6 lbm #Total Mass : 34750 kg; 76610.6 lbm #Thrust : 1.183e+06 N; 265948 lbf; 120632 kgf #Specific Impulse: 270 sec #Burn Rate : 446.786 kg/sec; 984.994 lbm/sec #Thrust Duration : 70 sec #Fuel Used : 31275 kg; 68949.6 lbm #Total Starting Mass: 61800 kg; 136246 lbm #Total Ending Mass: 30525 kg; 67296.1 lbm #Acceleration at stage 1 separation: 3.26g end_stage stage 2 aero RED_ICBM_1_STAGE_2_AERO total_mass 17400 kg # rounded fuel_mass 15660 kg # 90% of stage weight specific_impulse 270 sec # typical thrust_duration 80 sec # adjust for max g's #Empty Mass : 1740 kg; 3836.04 lbm #Fuel Mass : 15660 kg; 34524.4 lbm #Total Mass : 17400 kg; 38360.4 lbm #Thrust : 518306 N; 116520 lbf; 52852.5 kgf #Specific Impulse: 270 sec #Burn Rate : 195.75 kg/sec; 431.555 lbm/sec #Thrust Duration : 80 sec #Fuel Used : 15660 kg; 34524.4 lbm #Total Starting Mass: 27050 kg; 59635 lbm #Total Ending Mass: 11390 kg; 25110.7 lbm #Acceleration at stage 2 separation: 4.30g end_stage stage 3 aero RED_ICBM_1_STAGE_3_AERO total_mass 8600 kg # rounded fuel_mass 7740 kg # 90% of stage weight specific_impulse 270 sec # typical thrust_duration 100 sec # adjust for max g's #Empty Mass : 860 kg; 1895.98 lbm #Fuel Mass : 7740 kg; 17063.8 lbm #Total Mass : 8600 kg; 18959.8 lbm #Thrust : 204939 N; 46072.2 lbf; 20898 kgf #Specific Impulse: 270 sec #Burn Rate : 77.4 kg/sec; 170.638 lbm/sec #Thrust Duration : 100 sec #Fuel Used : 7740 kg; 17063.8 lbm #Total Starting Mass: 9650 kg; 21274.6 lbm #Total Ending Mass: 1910 kg; 4210.83 lbm #Acceleration at stage 3 separation: 9.9g (a little high) end_stage stage 4 aero RED_ICBM_1_RV_AERO total_mass 1050 kg end_stage end_mover processor RED_ICBM_1_GUIDANCE WSF_GUIDANCE_COMPUTER # Go vertical for a short time. phase LIFTOFF guidance_delay 5.0 sec commanded_flight_path_angle 89.9 deg next_phase PITCH_OVER when phase_time >= 5.0 sec end_phase # Pitch over to the desired flight path angle from the launch computer. phase PITCH_OVER #commanded_flight_path_angle 89 deg commanded_flight_path_angle from_launch_computer proportional_navigation_gain 0.0 velocity_pursuit_gain 0.0 maximum_commanded_g 1.0 g next_phase BALLISTIC when on_commanded_flight_path_angle end_phase # Continue flight without guidance (gravity turn). phase BALLISTIC guidance_delay 5000.0 sec end_phase end_processor ############################################################################### platform_type RED_ICBM_1 WSF_PLATFORM icon Scud_Missile infrared_signature RED_ICBM_1_INFRARED_SIG optical_signature RED_ICBM_1_OPTICAL_SIG radar_signature RED_ICBM_1_RADAR_SIG weapon_effects RED_ICBM_1_EFFECT mover RED_ICBM_1_MOVER show_status #debug end_mover processor guidance RED_ICBM_1_GUIDANCE #show_status #show_graphics end_processor processor fuse WSF_GROUND_TARGET_FUSE # If the target is killed by another weapon we want to still keep going. coast_time_on_loss_of_target 10000.0 secs end_processor end_platform_type ############################################################################### launch_computer RED_ICBM_1_LAUNCH_COMPUTER WSF_BALLISTIC_MISSILE_LAUNCH_COMPUTER surface_to_surface_table red_icbm_1_launch_data.txt end_launch_computer ############################################################################### weapon RED_ICBM_1 WSF_EXPLICIT_WEAPON # The location offset puts the weapon center at half the length - 1 m. # This assumes the scenario creator puts the launching platform at 1 m agl. location 0.0 0.0 -9.0 m # 1/2 distance of length of missile launched_platform_type RED_ICBM_1 launch_computer RED_ICBM_1_LAUNCH_COMPUTER end_launch_computer tilt 89.9 degrees cue_to_predicted_intercept true slew_mode azimuth azimuth_slew_limits -180 deg 180 deg # Default to a single weapon on the vehicle quantity 1 end_weapon