422 lines
14 KiB
Plaintext
422 lines
14 KiB
Plaintext
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# ****************************************************************************
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# CUI
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#
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# The Advanced Framework for Simulation, Integration, and Modeling (AFSIM)
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#
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# The use, dissemination or disclosure of data in this file is subject to
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# limitation or restriction. See accompanying README and LICENSE for details.
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# ****************************************************************************
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###############################################################################
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# ------ UNCLASSIFIED ------
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# RED_MRBM_1
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###############################################################################
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#
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# ***** WARNING ***** WARNING ***** WARNING ***** WARNING ***** WARNING *****
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#
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# This definition is intended to be EXPORTABLE. It is defined using publicly
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# available, attributable sources. DO NOT ADD ANYTHING BASED ON OTHER SOURCES!
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#
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# ***** WARNING ***** WARNING ***** WARNING ***** WARNING ***** WARNING *****
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#
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###############################################################################
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#
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# NOTE: If you modify any parameter in this file, you must rerun 'weapon_tools'
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# with 'red_mrbm_1_lcg.txt' as input to regenerate the launch computer data.
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#
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###############################################################################
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#
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# This model is built using data from unclassified sources as follows:
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#
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# 1) Jane's DF-21 (CSS-5)
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# RED_MRBM parameters
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# Length: 10.7 m
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# Body Diameter: 1.4 m
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# Launch weight: 14,700 kg
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# Payload: Single warhead, 600 kg
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# Minimum range 500 km, Maximum range 2500 km
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#
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# RED_MRBM_4/RED_MRBM_1 parameters
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# Length: 12.3 m
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# Body Diameter: 1.4 m
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# Launch weight: 15,200 kg
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# Payload: Single warhead, 500 kg
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# Minimum range 600 km, Maximum range 2150 km
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#
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# RED_MRBM_1 RV is believed to have pop-out fins and an active radar seeker.
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#
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# 2) http://www.astronautix.com/lvs/df21.htm
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# Length: 10.43 m
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# Diameter: 1.4 m
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# Total Mass: 14,664 kg
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# Stage 1 gross mass: 10,000 kg
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# Stage 2 gross mass: 4,000 kg
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# Warhead mass: 600 kg
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#
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# 3) http://en.wikipedia.org/wiki/Space_Shuttle_Solid_Rocket_Booster
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# Because there is no data that gives the mass of the propellant, it is
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# assumed that it will follow the ratio of the fuel mass/total mass for
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# the Space Shuttle solid rockets:
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#
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# Propellant Mass: 500,000 kg
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# Inert (empty) Mass: 91,000 kg
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# Fuel Mass / Total Mass = 500,000 / 591,000 = 0.846
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#
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# As a point of reference, it also quotes the specific impulse as 242 secs.
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#
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# 4) http://en.wikipedia.org/wiki/Solid-fuel_rocket
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# Indicates 'a typical solid fuel rocket motor may have a specific impulse
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# of 265 sec'.
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#
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# 5) http://en.wikipedia.org/wiki/Specific_impulse
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# Indicates specific impulse of 250 sec for 'solid rocket technologies'.
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#
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###############################################################################
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###############################################################################
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# Support for explicit representation of spent stages
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#
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# Platforms will be created for spent stages if one the global script variables
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# is defined as follows:
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#
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# script_variables
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# SHOW_SPENT_STAGES["ALL"] = true; # For any weapon
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# SHOW_SPENT_STAGES["RED_MRBM_1"] = true; # For just this weapon type
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# end_script_variables
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###############################################################################
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include_once show_spent_stages.txt
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##### Stage 1
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aero RED_MRBM_1_SPENT_STAGE_1_AERO WSF_AERO # TODO
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reference_area 16.62 ft^2
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aspect_ratio 1.0
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cl_max 5.0
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zero_lift_cd 0.7
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end_aero
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infrared_signature RED_MRBM_1_SPENT_STAGE_1_INFRARED_SIG
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constant 1 watts/steradian
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end_infrared_signature
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optical_signature RED_MRBM_1_SPENT_STAGE_1_OPTICAL_SIG
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constant 1 m^2
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end_optical_signature
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radar_signature RED_MRBM_1_SPENT_STAGE_1_RADAR_SIG
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constant 1 m^2
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end_radar_signature
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platform_type RED_MRBM_1_SPENT_STAGE_1 WSF_PLATFORM
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icon Scud_Missile
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infrared_signature RED_MRBM_1_SPENT_STAGE_1_INFRARED_SIG
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optical_signature RED_MRBM_1_SPENT_STAGE_1_OPTICAL_SIG
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radar_signature RED_MRBM_1_SPENT_STAGE_1_RADAR_SIG
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mover WSF_GUIDED_MOVER
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integration_timestep 0.01 secs
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stage 1
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aero RED_MRBM_1_SPENT_STAGE_1_AERO
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total_mass 1618.0 kg
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end_stage
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end_mover
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processor fuse WSF_GROUND_TARGET_FUSE
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end_processor
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end_platform_type
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##### Stage 2
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aero RED_MRBM_1_SPENT_STAGE_2_AERO WSF_AERO # TODO
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reference_area 16.62 ft^2
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aspect_ratio 1.0
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cl_max 5.0
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zero_lift_cd 0.7
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end_aero
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infrared_signature RED_MRBM_1_SPENT_STAGE_2_INFRARED_SIG
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constant 1 watts/steradian
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end_infrared_signature
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optical_signature RED_MRBM_1_SPENT_STAGE_2_OPTICAL_SIG
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constant 1 m^2
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end_optical_signature
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radar_signature RED_MRBM_1_SPENT_STAGE_2_RADAR_SIG
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constant 1 m^2
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end_radar_signature
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platform_type RED_MRBM_1_SPENT_STAGE_2 WSF_PLATFORM
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icon Scud_Missile
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infrared_signature RED_MRBM_1_SPENT_STAGE_2_INFRARED_SIG
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optical_signature RED_MRBM_1_SPENT_STAGE_2_OPTICAL_SIG
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radar_signature RED_MRBM_1_SPENT_STAGE_2_RADAR_SIG
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mover WSF_GUIDED_MOVER
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integration_timestep 0.01 secs
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stage 1
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aero RED_MRBM_1_SPENT_STAGE_2_AERO
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total_mass 708.0 kg
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end_stage
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end_mover
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processor fuse WSF_GROUND_TARGET_FUSE
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end_processor
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end_platform_type
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###############################################################################
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# Signature data is unknown...
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infrared_signature RED_MRBM_1_INFRARED_SIG
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constant 1 watts/steradian
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end_infrared_signature
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optical_signature RED_MRBM_1_OPTICAL_SIG
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constant 1 m^2
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end_optical_signature
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radar_signature RED_MRBM_1_RADAR_SIG
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constant 1 m^2
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end_radar_signature
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# Nominal lethality data.
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weapon_effects RED_MRBM_1_EFFECT WSF_GRADUATED_LETHALITY
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radius_and_pk 1000.0 m 1.0
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end_weapon_effects
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###############################################################################
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aero RED_MRBM_1_STAGE_1_AERO WSF_AERO
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reference_area 1.539 m^2 # 1.4 m diameter (Ref 1)
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aspect_ratio 2.0
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cl_max 4.5
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# Values estimated from Hoerner's Drag book
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cd_zero_subsonic 0.10
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cd_zero_supersonic 0.35
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mach_begin_cd_rise 0.95
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mach_end_cd_rise 1.30
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mach_max_supersonic 6.00
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end_aero
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aero RED_MRBM_1_STAGE_2_AERO WSF_AERO
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reference_area 1.539 m^2 # 1.4 m diameter (Ref 1)
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aspect_ratio 2.0
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cl_max 4.5
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# Values estimated from Hoerner's Drag book
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cd_zero_subsonic 0.10
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cd_zero_supersonic 0.35
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mach_begin_cd_rise 0.95
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mach_end_cd_rise 1.30
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mach_max_supersonic 6.00
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end_aero
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aero RED_MRBM_1_RV_AERO WSF_AERO
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# Based on the line drawing from Janes, it appears the RV is about 60% of the
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# stage 1/2 diameter. So, 1.4 * 0.6 = 0.84m
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reference_area 0.554 m^2 # 0.84 m diameter
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aspect_ratio 2.0
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cl_max 4.5
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# Values estimated from Hoerner's Drag book
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cd_zero_subsonic 0.10
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cd_zero_supersonic 0.35
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mach_begin_cd_rise 0.95
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mach_end_cd_rise 1.30
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mach_max_supersonic 6.00
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end_aero
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###############################################################################
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mover RED_MRBM_1_MOVER WSF_GUIDED_MOVER
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integration_timestep 0.005 secs
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update_interval 0.05 secs
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# Total mass for RED_MRBM_1 is 15,200 kg (Ref 1). Ref 2 is the only thing that
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# states the mass of the stages and that is for the orignal RED_MRBM.
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#
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# For original RED_MRBM (Ref 2)
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# Total = 14,664 kg
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# Stage 1 = 10,000 kg
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# Stage 2 = 4,000 kg
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# Payload = 600 kg
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# Assume the shroud is the remaining 64 kg
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#
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# For the RED_MRBM_1, we'll assume the shroud is the same 64 kg and the payload
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# is 500 kg (Ref 1). We'll ratio the stage 1 and stage 2 masses.
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#
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# Total - Shroud - Payload = 15,200 - 64 - 500 = 14,636
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# Stage 1 = 14,636 * (10,000 / 14,000) = 10,454
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# Stage 2 = 14,636 * (4,000 / 14,000) = 4,182
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# The burn times were set so as to match the ratio of the fuel masses.
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# The specific impulse was tuned to get a match on maximium range.
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stage 1
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aero RED_MRBM_1_STAGE_1_AERO
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total_mass 10454 kg
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fuel_mass 8844 kg # 10,454 * 0.846 (using Ref 3)
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specific_impulse 260 sec # Ref 4/5
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thrust_duration 90 sec
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end_stage
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stage 2
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aero RED_MRBM_1_STAGE_2_AERO
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total_mass 4246 kg # Stage + shroud = 4182 + 64
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fuel_mass 3538 kg # 4182 * 0.846 (using Ref 3)
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specific_impulse 260 sec # Ref 4/5
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thrust_duration 36 sec
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end_stage
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stage 3
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aero RED_MRBM_1_RV_AERO
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total_mass 500 kg # Ref 1
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end_stage
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end_mover
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###############################################################################
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processor RED_MRBM_1_GUIDANCE WSF_GUIDANCE_COMPUTER
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# Go vertical for a short time.
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phase LIFTOFF
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guidance_delay 100.0 sec
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# NOTE: Do not use altitude for the criteria for starting pitch over as
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# trajectory is VERY sensitive to the TIME when pitch over starts. If it
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# were to be used, a minor changes in the launcher altitude would cause
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# pitch over to start at a different time!
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next_phase PITCH_OVER when phase_time >= 2.0 sec # About 100 ft
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end_phase
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# Pitch over to the desired flight path angle from the launch computer.
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phase PITCH_OVER
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commanded_flight_path_angle from_launch_computer
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proportional_navigation_gain 0.0 # Don't guide to target
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velocity_pursuit_gain 0.0 # Don't guide to target
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maximum_commanded_g 1.0 g
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next_phase BALLISTIC when on_commanded_flight_path_angle
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end_phase
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# Continue flight without guidance (gravity turn).
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phase BALLISTIC
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# Turn the guidance processor off once pure ballistic mode is started.
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# This shaves several percent off the processor time.
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on_entry
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TurnOff();
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end_on_entry
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guidance_delay 2000.0 sec
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end_phase
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end_processor
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###############################################################################
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platform_type RED_MRBM_1 WSF_PLATFORM
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icon Scud_Missile
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infrared_signature RED_MRBM_1_INFRARED_SIG
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optical_signature RED_MRBM_1_OPTICAL_SIG
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radar_signature RED_MRBM_1_RADAR_SIG
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weapon_effects RED_MRBM_1_EFFECT
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mover RED_MRBM_1_MOVER
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#show_status
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#debug
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end_mover
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processor guidance RED_MRBM_1_GUIDANCE
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#show_status
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#show_graphics
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end_processor
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processor fuse WSF_GROUND_TARGET_FUSE
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# If the target is killed by another weapon we want to still keep going.
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coast_time_on_loss_of_target 10000.0 secs
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end_processor
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weapon stage_1 WSF_EXPLICIT_WEAPON
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launched_platform_type RED_MRBM_1_SPENT_STAGE_1
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launch_delta_v -100.0 0.0 0.0 m/s
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quantity 1
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end_weapon
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weapon stage_2 WSF_EXPLICIT_WEAPON
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launched_platform_type RED_MRBM_1_SPENT_STAGE_2
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launch_delta_v -100.0 0.0 0.0 m/s
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quantity 1
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end_weapon
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script void on_stage_separation(int aStage)
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extern Map<string, bool> SHOW_SPENT_STAGES;
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if (SHOW_SPENT_STAGES["ALL"] ||
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SHOW_SPENT_STAGES["RED_MRBM_1"])
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{
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if (aStage == 1) Weapon("stage_1").Fire(WsfTrack());
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if (aStage == 2) Weapon("stage_2").Fire(WsfTrack());
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}
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end_script
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end_platform_type
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||
|
|
|
||
|
|
###############################################################################
|
||
|
|
|
||
|
|
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
|