# **************************************************************************** # 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 ------ # BLUE_LR_SAM ############################################################################### # # ***** WARNING ***** WARNING ***** WARNING ***** WARNING ***** WARNING ***** # # This definition is intended to be EXPORTABLE. It is defined using publicly # available, attributable sources. DO NOT ADD ANYTHING BASED ON OTHER SOURCES! # # ***** WARNING ***** WARNING ***** WARNING ***** WARNING ***** WARNING ***** # ############################################################################### # # NOTE: If you modify any parameter in this file, you must rerun 'weapon_tools' # with 'blue_lr_sam_lcg.txt' as input to regenerate the launch computer data. # ############################################################################### # # References: (PDF files contained in the subdirectory blue_lr_sam_ref) # # 1) http://www.mda.mil/mdaLink/pdf/38112.pdf # User Operational Evaluation System (UOES) THAAD Missile Configuration # (NOTE: This document has vanished, but the captured wiki page in Ref 4 # has the same picture). # # 2) http://search.janes.com/Search/documentView.do?docId=/content1/janesdata/binder/jsws/jsws0203.htm@current&pageSelected=allJanes&keyword=THAAD&backPath=http://search.janes.com/Search&Prod_Name=JSWS& # Jane's (JSWS) THAAD # Launch weight: 630 kg # Length and diameter same as Ref 1 # Range: 300 km # Uses HTPB propellant # # There is some contradiction between the Jane's JSWS and JLAD documentation # with regards to launch weight (630 kg vs. 800 kg), . # # 3) http://www.army-technology.com/projects/thaad/specs.html # Launch weight: 900 kg # Velocity: 2,800 m/s # Range: > 200 km # Maximum altitude of intercept: 150 km # # 4) http://en.wikipedia.org/wiki/Terminal_High_Altitude_Area_Defense # # 5) http://en.wikipedia.org/wiki/Space_Shuttle_Solid_Rocket_Booster # Because there is no data that gives the mass of the propellant, it is # assumed that it will follow the ratio of the fuel mass/total mass for # the Space Shuttle solid rockets: # # Propellant Mass: 500,000 kg # Inert (empty) Mass: 91,000 kg # Fuel Mass / Total Mass = 500,000 / 591,000 = 0.846 # # 6) http://en.wikipedia.org/wiki/Solid-fuel_rocket # Indicates 'a typical solid fuel rocket motor may have a specific impulse # of 265 sec'. But we'll assume the use of 'High Energy Composite (HEC) # propellants, which is indicated a specific impulse of 275 sec. ############################################################################### ############################################################################### # Support for explicit representation of spent stages # # Platforms will be created for spent stages if one the global script variables # is defined as follows: # # script_variables # SHOW_SPENT_STAGES["ALL"] = true; # For any weapon # SHOW_SPENT_STAGES["BLUE_LR_SAM"] = true; # For just this weapon type # end_script_variables ############################################################################### include_once ../ssm/show_spent_stages.txt aero BLUE_LR_SAM_SPENT_BOOSTER_AERO WSF_AERO reference_area 0.09079 m^2 # Ref 1 aspect_ratio 1.0 cl_max 5.0 # zero_lift_cd 0.7 cd_zero_subsonic 1.5 # Extreme cd cd_zero_supersonic 3.0 # Extreme cd mach_begin_cd_rise 0.95 mach_end_cd_rise 1.30 mach_max_supersonic 6.00 end_aero infrared_signature BLUE_LR_SAM_SPENT_BOOSTER_INFRARED_SIGNATURE constant 1 watts/steradian end_infrared_signature optical_signature BLUE_LR_SAM_SPENT_BOOSTER_OPTICAL_SIGNATURE constant 1 m^2 end_optical_signature radar_signature BLUE_LR_SAM_SPENT_BOOSTER_RADAR_SIGNATURE constant 1 m^2 end_radar_signature platform_type BLUE_LR_SAM_SPENT_BOOSTER WSF_PLATFORM icon Scud_Missile infrared_signature BLUE_LR_SAM_SPENT_BOOSTER_INFRARED_SIGNATURE optical_signature BLUE_LR_SAM_SPENT_BOOSTER_OPTICAL_SIGNATURE radar_signature BLUE_LR_SAM_SPENT_BOOSTER_RADAR_SIGNATURE mover WSF_GUIDED_MOVER integration_timestep 0.01 secs stage 1 aero BLUE_LR_SAM_SPENT_BOOSTER_AERO total_mass 128.0 kg # Total - fuel end_stage end_mover processor fuse WSF_GROUND_TARGET_FUSE end_processor end_platform_type ############################################################################### # Signature data is unknown... infrared_signature BLUE_LR_SAM_INFRARED_SIGNATURE constant 1 watts/steradian end_infrared_signature optical_signature BLUE_LR_SAM_OPTICAL_SIGNATURE constant 1 m^2 end_optical_signature radar_signature BLUE_LR_SAM_RADAR_SIGNATURE constant 1 m^2 end_radar_signature # Nominal lethality data. weapon_effects BLUE_LR_SAM_EFFECT WSF_GRADUATED_LETHALITY radius_and_pk 100.0 m 0.9 # This script will reduce the effectiveness if the impact geometry is not desirable. script void on_weapon_target_engagement(WsfPlatform aTarget) WsfPlatform weapon = WeaponPlatform(); if (! (aTarget.IsValid() && weapon.IsValid())) return; // Compute the angle between the velocity vectors. A head-on hit would be 180 degrees. // (velocity vectors in opposite directions). Vec3 weaponVel = weapon.VelocityWCS(); Vec3 targetVel = aTarget.VelocityWCS(); double weaponVelMag = weaponVel.Magnitude(); double targetVelMag = targetVel.Magnitude(); if ((weaponVelMag > 1.0) && (targetVelMag > 1.0)) { double cosAngle = Vec3.Dot(weaponVel, targetVel) / (weaponVelMag * targetVelMag); if (cosAngle < -1.0) cosAngle = -1.0; if (cosAngle > 1.0) cosAngle = 1.0; double angle = Math.ACos(cosAngle); writeln("Angle=", angle); //TODO if (angle < xxx) SetPkDegrade(0.6); } end_script end_weapon_effects ############################################################################### aero BLUE_LR_SAM_BOOSTER_AERO WSF_AERO # Booster is actually 340 mm in diameter, but kill vehicle masks it. reference_area 0.10752 m^2 # Ref 1 - 370 mm diameter #aspect_ratio 2.0 #cl_max 6.0 # Values estimated from Hoerner's Drag book cd_zero_subsonic 0.10 cd_zero_supersonic 0.35 mach_begin_cd_rise 0.95 mach_end_cd_rise 1.30 mach_max_supersonic 6.00 end_aero aero BLUE_LR_SAM_KILL_VEHICLE_AERO WSF_AERO reference_area 0.10752 m^2 # Ref 1 - 370 mm diameter #aspect_ratio 2.0 #cl_max 6.0 # Values estimated from Hoerner's Drag book cd_zero_subsonic 0.10 cd_zero_supersonic 0.35 mach_begin_cd_rise 0.95 mach_end_cd_rise 1.30 mach_max_supersonic 6.00 end_aero mover BLUE_LR_SAM_MOVER WSF_GUIDED_MOVER integration_timestep 0.001 secs update_interval 0.01 secs # 20 sec of divert @ 1.5 G or 6 sec of divert @ 5.0 G # (assuming empty mass of 80kg) # # Thrust = 80 kg (empty mass) * 9.80665 m/s^2 (g) * 5 = 3922.66 Nt # Assume a specific impulse (I) of 267 sec # m(dot) = thrust / I / g = 1.4979 Kg/s # m = 5 sec * 1.4545 = 7.4894 kg divert_thrust 3922.66 Nt divert_fuel_mass 7.4894 kg divert_fuel_mass 10.0 kg # Gave it a little more for testing (bad initial conditions) divert_fuel_flow_rate 1.4979 kg/s divert_altitude_limits 80 km 500 km # The nozzle exit area and nozzle throat area were derived by ratios using the picture in Ref 1. # The measured diameters (NOT ACTUAL) from the picture were: # # Booster: 41.0 mm # Nozzle Throat: 7.2 mm # Nozzle Exit: 23.5 mm # # The derived values are then: # # Nozzle Throat: Diameter = 0.340 m * (7.2 / 41.0) = 0.0597 m, Area = 0.0938 m^2 # Nozzle Exit : Diameter = 0.340 m * (23.5 / 41.0) = 0.195 m, Area = 0.305 m^2 # # The volume of the fuel mass is also calculated from the drawing # # Inside length: 6.170 * (91 / 185) ~= 3.035 m # Inside diameter: = 0.340 * (39 / 41) ~= 0.3234 m # Inside volume = 3.168 * (pi * (0.3234/2)^2) ~= .2408 m^3 # # HTPB has a density of 0.92 g/ml, but is typically mixed with aluminum (2.7 g/ml) and # ammonium perchlorate (1.95 g/ml). An HTPB/AP/AL mixture of 12%/68%/20% resulted in a # density 1.98 g/ml which resulted in a fuel mass of 476 kg. The mass fraction will be # assumed to be 0.8 instead of the 0.85 of the Space Shuttle because of the increased # acceleration. This gives a mass of 595 kg. An addition 5 kg will be added for the # interstage and the shroud for a total of 600 kg. stage 1 aero BLUE_LR_SAM_BOOSTER_AERO nozzle_exit_area 0.305 m^2 # See calculations above total_mass 600 kg # See calculations above fuel_mass 485 kg # See calculations above #thrust_duration 11.0 sec #sea_level_specific_impulse 265 sec # Ref 6 thrust_duration 18 sec # Adjusted to get close to 2800 m/s sea_level_specific_impulse 250 sec # Adjusted to get close to 2800 m/s end_stage stage 2 aero BLUE_LR_SAM_KILL_VEHICLE_AERO total_mass 30 kg # Just the kill vehicle (630 - 600) end_stage end_mover ############################################################################### processor BLUE_LR_SAM_GUIDANCE WSF_GUIDANCE_COMPUTER # No datalink or seeker is being used, so we must guide to the true target guide_to_truth true phase LAUNCH commanded_flight_path_angle from_launch_computer proportional_navigation_gain 0.0 # Don't guide to target velocity_pursuit_gain 0.0 # Don't guide to target maximum_commanded_g 2.0 g next_phase MIDCOURSE when on_commanded_flight_path_angle end_phase phase MIDCOURSE # no guidance (just use gravity turn) guidance_delay 1000.0 sec next_phase TERMINAL when target_slant_range < 140.0 km end_phase phase TERMINAL proportional_navigation_gain 10.0 proportional_navigation_method augmented # Disable velocity pursuit. The angle which controls the switch between # velocity pursuit and pronav are too sensitive at short ranges. velocity_pursuit_gain 0.0 # Disable g-bias. The target is also falling, so we don't want to fight # against it! (this is assuming terminal intercept, not boost) g_bias 0.0 end_phase end_processor ############################################################################### platform_type BLUE_LR_SAM_BASE WSF_PLATFORM icon SA-10_Missile infrared_signature BLUE_LR_SAM_INFRARED_SIGNATURE optical_signature BLUE_LR_SAM_OPTICAL_SIGNATURE radar_signature BLUE_LR_SAM_RADAR_SIGNATURE weapon_effects BLUE_LR_SAM_EFFECT mover BLUE_LR_SAM_MOVER #show_status end_mover processor guidance BLUE_LR_SAM_GUIDANCE #show_status #show_graphics end_processor processor fuse WSF_AIR_TARGET_FUSE detonate_below_mach 1.0 end_processor weapon booster WSF_EXPLICIT_WEAPON launched_platform_type BLUE_LR_SAM_SPENT_BOOSTER launch_delta_v -50.0 0.0 0.0 m/s quantity 1 end_weapon script void on_stage_separation(int aStage) extern Map SHOW_SPENT_STAGES; if (SHOW_SPENT_STAGES["ALL"] || SHOW_SPENT_STAGES["BLUE_LR_SAM"]) { if (aStage == 1) Weapon("booster").Fire(WsfTrack()); } end_script end_platform_type ############################################################################### launch_computer BLUE_LR_SAM_LAUNCH_COMPUTER WSF_BALLISTIC_MISSILE_LAUNCH_COMPUTER surface_to_air_table weapons/sam/blue_lr_sam_launch_data.txt integration_time_step 0.05 sec # Disallow intercepts at unreasonable angles maximum_intercept_angle 60 deg end_launch_computer ############################################################################### weapon BLUE_LR_SAM 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 -2.085 m # Ref 1, length = 6170 mm launched_platform_type BLUE_LR_SAM launch_computer BLUE_LR_SAM_LAUNCH_COMPUTER end_launch_computer tilt 75 deg # This causes a call to the launch computer to compute the predicted intercept. # The launcher will then be cued to the proper angles (Subject to the slewing # limits defined below). This is a bit of a hack until the guidance computer # is changed... cue_to_predicted_intercept true slew_mode azimuth azimuth_slew_limits -180 deg 180 deg quantity 8 # Abort the launch if the launch computer didn't provide the required data require_loft_angle end_weapon