# **************************************************************************** # 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 ------ # RED_MRBM_1 ############################################################################### # # ***** 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 'red_mrbm_1_lcg.txt' as input to regenerate the launch computer data. # ############################################################################### # # This model is built using data from unclassified sources as follows: # # 1) Jane's DF-21 (CSS-5) # RED_MRBM parameters # Length: 10.7 m # Body Diameter: 1.4 m # Launch weight: 14,700 kg # Payload: Single warhead, 600 kg # Minimum range 500 km, Maximum range 2500 km # # RED_MRBM_4/RED_MRBM_1 parameters # Length: 12.3 m # Body Diameter: 1.4 m # Launch weight: 15,200 kg # Payload: Single warhead, 500 kg # Minimum range 600 km, Maximum range 2150 km # # RED_MRBM_1 RV is believed to have pop-out fins and an active radar seeker. # # 2) http://www.astronautix.com/lvs/df21.htm # Length: 10.43 m # Diameter: 1.4 m # Total Mass: 14,664 kg # Stage 1 gross mass: 10,000 kg # Stage 2 gross mass: 4,000 kg # Warhead mass: 600 kg # # 3) 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 # # As a point of reference, it also quotes the specific impulse as 242 secs. # # 4) http://en.wikipedia.org/wiki/Solid-fuel_rocket # Indicates 'a typical solid fuel rocket motor may have a specific impulse # of 265 sec'. # # 5) http://en.wikipedia.org/wiki/Specific_impulse # Indicates specific impulse of 250 sec for 'solid rocket technologies'. # ############################################################################### ############################################################################### # 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["RED_MRBM_1"] = true; # For just this weapon type # end_script_variables ############################################################################### include_once show_spent_stages.txt ##### Stage 1 aero RED_MRBM_1_SPENT_STAGE_1_AERO WSF_AERO # TODO reference_area 16.62 ft^2 aspect_ratio 1.0 cl_max 5.0 zero_lift_cd 0.7 end_aero infrared_signature RED_MRBM_1_SPENT_STAGE_1_INFRARED_SIG constant 1 watts/steradian end_infrared_signature optical_signature RED_MRBM_1_SPENT_STAGE_1_OPTICAL_SIG constant 1 m^2 end_optical_signature radar_signature RED_MRBM_1_SPENT_STAGE_1_RADAR_SIG constant 1 m^2 end_radar_signature platform_type RED_MRBM_1_SPENT_STAGE_1 WSF_PLATFORM icon Scud_Missile infrared_signature RED_MRBM_1_SPENT_STAGE_1_INFRARED_SIG optical_signature RED_MRBM_1_SPENT_STAGE_1_OPTICAL_SIG radar_signature RED_MRBM_1_SPENT_STAGE_1_RADAR_SIG mover WSF_GUIDED_MOVER integration_timestep 0.01 secs stage 1 aero RED_MRBM_1_SPENT_STAGE_1_AERO total_mass 1618.0 kg end_stage end_mover processor fuse WSF_GROUND_TARGET_FUSE end_processor end_platform_type ##### Stage 2 aero RED_MRBM_1_SPENT_STAGE_2_AERO WSF_AERO # TODO reference_area 16.62 ft^2 aspect_ratio 1.0 cl_max 5.0 zero_lift_cd 0.7 end_aero infrared_signature RED_MRBM_1_SPENT_STAGE_2_INFRARED_SIG constant 1 watts/steradian end_infrared_signature optical_signature RED_MRBM_1_SPENT_STAGE_2_OPTICAL_SIG constant 1 m^2 end_optical_signature radar_signature RED_MRBM_1_SPENT_STAGE_2_RADAR_SIG constant 1 m^2 end_radar_signature platform_type RED_MRBM_1_SPENT_STAGE_2 WSF_PLATFORM icon Scud_Missile infrared_signature RED_MRBM_1_SPENT_STAGE_2_INFRARED_SIG optical_signature RED_MRBM_1_SPENT_STAGE_2_OPTICAL_SIG radar_signature RED_MRBM_1_SPENT_STAGE_2_RADAR_SIG mover WSF_GUIDED_MOVER integration_timestep 0.01 secs stage 1 aero RED_MRBM_1_SPENT_STAGE_2_AERO total_mass 708.0 kg end_stage end_mover processor fuse WSF_GROUND_TARGET_FUSE end_processor end_platform_type ############################################################################### # Signature data is unknown... infrared_signature RED_MRBM_1_INFRARED_SIG constant 1 watts/steradian end_infrared_signature optical_signature RED_MRBM_1_OPTICAL_SIG constant 1 m^2 end_optical_signature radar_signature RED_MRBM_1_RADAR_SIG constant 1 m^2 end_radar_signature # Nominal lethality data. weapon_effects RED_MRBM_1_EFFECT WSF_GRADUATED_LETHALITY radius_and_pk 1000.0 m 1.0 end_weapon_effects ############################################################################### aero RED_MRBM_1_STAGE_1_AERO WSF_AERO reference_area 1.539 m^2 # 1.4 m diameter (Ref 1) aspect_ratio 2.0 cl_max 4.5 # 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 RED_MRBM_1_STAGE_2_AERO WSF_AERO reference_area 1.539 m^2 # 1.4 m diameter (Ref 1) aspect_ratio 2.0 cl_max 4.5 # 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 RED_MRBM_1_RV_AERO WSF_AERO # Based on the line drawing from Janes, it appears the RV is about 60% of the # stage 1/2 diameter. So, 1.4 * 0.6 = 0.84m reference_area 0.554 m^2 # 0.84 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 0.35 mach_begin_cd_rise 0.95 mach_end_cd_rise 1.30 mach_max_supersonic 6.00 end_aero ############################################################################### mover RED_MRBM_1_MOVER WSF_GUIDED_MOVER integration_timestep 0.005 secs update_interval 0.05 secs # Total mass for RED_MRBM_1 is 15,200 kg (Ref 1). Ref 2 is the only thing that # states the mass of the stages and that is for the orignal RED_MRBM. # # For original RED_MRBM (Ref 2) # Total = 14,664 kg # Stage 1 = 10,000 kg # Stage 2 = 4,000 kg # Payload = 600 kg # Assume the shroud is the remaining 64 kg # # For the RED_MRBM_1, we'll assume the shroud is the same 64 kg and the payload # is 500 kg (Ref 1). We'll ratio the stage 1 and stage 2 masses. # # Total - Shroud - Payload = 15,200 - 64 - 500 = 14,636 # Stage 1 = 14,636 * (10,000 / 14,000) = 10,454 # Stage 2 = 14,636 * (4,000 / 14,000) = 4,182 # The burn times were set so as to match the ratio of the fuel masses. # The specific impulse was tuned to get a match on maximium range. stage 1 aero RED_MRBM_1_STAGE_1_AERO total_mass 10454 kg fuel_mass 8844 kg # 10,454 * 0.846 (using Ref 3) specific_impulse 260 sec # Ref 4/5 thrust_duration 90 sec end_stage stage 2 aero RED_MRBM_1_STAGE_2_AERO total_mass 4246 kg # Stage + shroud = 4182 + 64 fuel_mass 3538 kg # 4182 * 0.846 (using Ref 3) specific_impulse 260 sec # Ref 4/5 thrust_duration 36 sec end_stage stage 3 aero RED_MRBM_1_RV_AERO total_mass 500 kg # Ref 1 end_stage end_mover ############################################################################### processor RED_MRBM_1_GUIDANCE WSF_GUIDANCE_COMPUTER # Go vertical for a short time. phase LIFTOFF guidance_delay 100.0 sec # NOTE: Do not use altitude for the criteria for starting pitch over as # trajectory is VERY sensitive to the TIME when pitch over starts. If it # were to be used, a minor changes in the launcher altitude would cause # pitch over to start at a different time! next_phase PITCH_OVER when phase_time >= 2.0 sec # About 100 ft end_phase # Pitch over to the desired flight path angle from the launch computer. phase PITCH_OVER 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 1.0 g next_phase BALLISTIC when on_commanded_flight_path_angle end_phase # Continue flight without guidance (gravity turn). phase BALLISTIC # Turn the guidance processor off once pure ballistic mode is started. # This shaves several percent off the processor time. on_entry TurnOff(); end_on_entry guidance_delay 2000.0 sec end_phase end_processor ############################################################################### platform_type RED_MRBM_1 WSF_PLATFORM icon Scud_Missile infrared_signature RED_MRBM_1_INFRARED_SIG optical_signature RED_MRBM_1_OPTICAL_SIG radar_signature RED_MRBM_1_RADAR_SIG weapon_effects RED_MRBM_1_EFFECT mover RED_MRBM_1_MOVER #show_status #debug end_mover processor guidance RED_MRBM_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 weapon stage_1 WSF_EXPLICIT_WEAPON launched_platform_type RED_MRBM_1_SPENT_STAGE_1 launch_delta_v -100.0 0.0 0.0 m/s quantity 1 end_weapon weapon stage_2 WSF_EXPLICIT_WEAPON launched_platform_type RED_MRBM_1_SPENT_STAGE_2 launch_delta_v -100.0 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["RED_MRBM_1"]) { if (aStage == 1) Weapon("stage_1").Fire(WsfTrack()); if (aStage == 2) Weapon("stage_2").Fire(WsfTrack()); } end_script end_platform_type ############################################################################### launch_computer RED_MRBM_1_LAUNCH_COMPUTER WSF_BALLISTIC_MISSILE_LAUNCH_COMPUTER surface_to_surface_table weapons/ssm/red_mrbm_1_launch_data.txt end_launch_computer ############################################################################### # Provide the aero and mass data to WSF_BALLISTIC_MISSILE_LAUNCH_COMPUTER. This # is 'truth data' used by the launch computer for 'trajectory estimation'. ballistic_missile_launch_computer target_data RED_MRBM_1 aero RED_MRBM_1_RV_AERO # Aero type of final stage mass 500 kg # Mass of final stage end_target_data end_ballistic_missile_launch_computer ############################################################################### weapon RED_MRBM_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 -5.15 m # Ref 1, length = 12.3 m launched_platform_type RED_MRBM_1 launch_computer RED_MRBM_1_LAUNCH_COMPUTER end_launch_computer # The missiles are launched vertically. # We can't specify 90 degrees because of a singularity tilt 89.9 degrees # 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 # Default to a single weapon on the vehicle quantity 1 # Abort the launch if the launch computer didn't provide the required data require_loft_angle end_weapon