295 lines
11 KiB
Plaintext
295 lines
11 KiB
Plaintext
# ****************************************************************************
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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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# UNCLASSIFIED
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# This missile model created from internet sources as listed.
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# Although sources have range listed from 8,000km to 14,000km,
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# this model achieves 1,140 km max range with a 1,050kg RV (payload).
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# In the "Annual Report to Congress Military Power of the People's Republic
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# of China Military Report 2008", it lists the range as 11,200km.
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# http://www.sinodefence.com/strategic/missile/df31.asp
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#Contractor: CASIC 4th Academy
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#Service status: In service
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#Configuration: Three-stage, solid propellant
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#Deployment: Road mobile, 8X8 tractor truck + 8-wheel trailer; or silo
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#Length: 13m
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#Body diameter: 2.25m
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#Launch weight: 42,000kg
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#Range: 10,700~11,200km
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#Re-entry vehicle mass: 700kg (or 1,050~1,750kg)
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#Warhead: One single 1,000kT yield
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#Guidance: Inertial + stellar update
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#Accuracy: 100~300m CEP
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#Launch preparation time: 15~30 min
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#
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#http://www.janes.com (subscription required)
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#Length: 13.0 m (31), 18.7 m (31A)
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#Body diameter: 2.0 m (1st and 2nd stages) and 1.5 m (3rd stage)
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#Launch weight: 42,000 kg (31), 63,000 kg (31A)
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#Payload: Single warhead or 3-5 MIRV, 1,050-1,750 kg
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#Warhead: Nuclear 1 MT or 3-5 MIRV with selectable 20, 90 or 150 kT each
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#Guidance: Inertial with stellar updates
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#Propulsion: 3-stage solid propellant
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#Range: 8,000 km (31), or 10,000 and 14,000 km (31A)
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#Accuracy: 300 m CEP
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#http://www.astronautix.com/lvs/df31.htm
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#* Stage1: 1 x JL-2-1. Motor: 1 x red_icbm_1-1. Length: 8.00 m (26.20 ft). Diameter:
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#* 2.00 m (6.50 ft). Propellants:
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#Solid.
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#* Stage2: 1 x KT-1-2. Motor: 1 x red_icbm_1-2. Length: 4.00 m (13.10 ft). Diameter:
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#* 2.00 m (6.50 ft). Propellants:
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#Solid.
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#* Stage3: 1 x JL-2-3. Motor: 1 x red_icbm_1-3. Length: 2.00 m (6.50 ft). Diameter:
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#* 2.00 m (6.50 ft). Propellants: S
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#Solid.
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infrared_signature RED_ICBM_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_ICBM_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_ICBM_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_ICBM_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_ICBM_1_STAGE_1_AERO WSF_AERO
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reference_area 3.141 m^2 # 2.0 m diameter
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aspect_ratio 4.0 # 8 meters length
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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 0.25
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mach_begin_cd_rise 0.95
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mach_end_cd_rise 1.20
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mach_max_supersonic 6.00
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end_aero
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aero RED_ICBM_1_STAGE_2_AERO WSF_AERO
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reference_area 3.141 m^2 # 2.0 m diameter
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aspect_ratio 2.0 # 4 meters length
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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 0.25
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mach_begin_cd_rise 0.95
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mach_end_cd_rise 1.20
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mach_max_supersonic 6.00
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end_aero
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aero RED_ICBM_1_STAGE_3_AERO WSF_AERO
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# According to pictures, about 65% of diameter
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reference_area 1.767 m^2 # 1.5 m diameter
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aspect_ratio 1.0 # 2 meters length
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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 0.25
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mach_begin_cd_rise 0.95
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mach_end_cd_rise 1.20
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mach_max_supersonic 6.00
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end_aero
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aero RED_ICBM_1_RV_AERO WSF_AERO
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reference_area 1.767 m^2 # 1.5 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 0.25
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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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mover RED_ICBM_1_MOVER WSF_GUIDED_MOVER
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integration_timestep 0.01 secs
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update_interval 0.01 secs
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# Length: 18.7 m (31A)
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#Body diameter: 2.0 m (1st and 2nd stages) and 1.5 m (3rd stage)
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#Launch weight: 63,000 kg (31A)
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#Payload: Single warhead or 3-5 MIRV, 1,050-1,750 kg
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#Warhead: Nuclear 1 MT or 3-5 MIRV with selectable 20, 90 or 150 kT each
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#Guidance: Inertial with stellar updates
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#Propulsion: 3-stage solid propellant
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#Range: 14,000 km (31A) / 11,200 km wiki
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#Stage1:Motor: 1 x red_icbm_1-1. Length: 8.00 m (26.20 ft). Diameter: 2.00 m (6.50 ft). Propellants: Solid.
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#Stage2:Motor: 1 x red_icbm_1-2. Length: 4.00 m (13.10 ft). Diameter: 2.00 m (6.50 ft). Propellants: Solid.
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#Stage3:Motor: 1 x red_icbm_1-3. Length: 2.00 m (6.50 ft). Diameter: 2.00 m (6.50 ft). Propellants: Solid.
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#Appr:Taking 63,000 kg - 1,050kg for RV
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#Appr:61,950 kg total x 22% for empty weight leaves
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#Appr:13,629 kg structure weight and 48321 fuel weight
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#Appr:Motor Total weight (lbs) is function of diameter and length:
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#Appr:Rule of thumb: W = length(in) x diam^2(in) x 0.04
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#Appr:First stage total mass 314.4 x 6084 x 0.04 = 76512.384 lbs = 34705 kg
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#Appr:Second stage total mass 157.2 x 6084 x 0.04 = 38256.192 lbs = 17352 kg
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#Appr:Third stage total mass 78.0 x 6084 x 0.04 = 18982.080 lbs = 8610 kg
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#Appr:Total Weight of stages = 60667 kg - close to published weight
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#Appr:Use 90% of total weight for fuel. Rule of thumb is 75-90%.
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#Appr:Burn time = (total impulse)/(average thrust)
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#Appr:Burn time = (motor impulse in newton seconds / (motor thrust in Newtons )
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#Appr:Burn time = (Fuel Mass) / (Mass Flow Rate)
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stage 1
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aero RED_ICBM_1_STAGE_1_AERO
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total_mass 34750 kg # rounded
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fuel_mass 31275 kg # 90% of stage weight
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specific_impulse 270 sec # typical
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thrust_duration 70 sec # adjust for max g's
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# COMPUTED FROM WSF RUN
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#Empty Mass : 3475 kg; 7661.06 lbm
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#Fuel Mass : 31275 kg; 68949.6 lbm
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#Total Mass : 34750 kg; 76610.6 lbm
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#Thrust : 1.183e+06 N; 265948 lbf; 120632 kgf
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#Specific Impulse: 270 sec
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#Burn Rate : 446.786 kg/sec; 984.994 lbm/sec
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#Thrust Duration : 70 sec
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#Fuel Used : 31275 kg; 68949.6 lbm
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#Total Starting Mass: 61800 kg; 136246 lbm
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#Total Ending Mass: 30525 kg; 67296.1 lbm
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#Acceleration at stage 1 separation: 3.26g
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end_stage
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stage 2
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aero RED_ICBM_1_STAGE_2_AERO
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total_mass 17400 kg # rounded
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fuel_mass 15660 kg # 90% of stage weight
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specific_impulse 270 sec # typical
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thrust_duration 80 sec # adjust for max g's
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#Empty Mass : 1740 kg; 3836.04 lbm
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#Fuel Mass : 15660 kg; 34524.4 lbm
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#Total Mass : 17400 kg; 38360.4 lbm
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#Thrust : 518306 N; 116520 lbf; 52852.5 kgf
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#Specific Impulse: 270 sec
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#Burn Rate : 195.75 kg/sec; 431.555 lbm/sec
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#Thrust Duration : 80 sec
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#Fuel Used : 15660 kg; 34524.4 lbm
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#Total Starting Mass: 27050 kg; 59635 lbm
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#Total Ending Mass: 11390 kg; 25110.7 lbm
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#Acceleration at stage 2 separation: 4.30g
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end_stage
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stage 3
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aero RED_ICBM_1_STAGE_3_AERO
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total_mass 8600 kg # rounded
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fuel_mass 7740 kg # 90% of stage weight
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specific_impulse 270 sec # typical
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thrust_duration 100 sec # adjust for max g's
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#Empty Mass : 860 kg; 1895.98 lbm
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#Fuel Mass : 7740 kg; 17063.8 lbm
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#Total Mass : 8600 kg; 18959.8 lbm
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#Thrust : 204939 N; 46072.2 lbf; 20898 kgf
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#Specific Impulse: 270 sec
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#Burn Rate : 77.4 kg/sec; 170.638 lbm/sec
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#Thrust Duration : 100 sec
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#Fuel Used : 7740 kg; 17063.8 lbm
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#Total Starting Mass: 9650 kg; 21274.6 lbm
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#Total Ending Mass: 1910 kg; 4210.83 lbm
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#Acceleration at stage 3 separation: 9.9g (a little high)
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end_stage
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stage 4
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aero RED_ICBM_1_RV_AERO
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total_mass 1050 kg
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end_stage
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end_mover
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processor RED_ICBM_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 5.0 sec
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commanded_flight_path_angle 89.9 deg
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next_phase PITCH_OVER when phase_time >= 5.0 sec
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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 89 deg
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commanded_flight_path_angle from_launch_computer
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proportional_navigation_gain 0.0
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velocity_pursuit_gain 0.0
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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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guidance_delay 5000.0 sec
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end_phase
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end_processor
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###############################################################################
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platform_type RED_ICBM_1 WSF_PLATFORM
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icon Scud_Missile
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infrared_signature RED_ICBM_1_INFRARED_SIG
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optical_signature RED_ICBM_1_OPTICAL_SIG
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radar_signature RED_ICBM_1_RADAR_SIG
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weapon_effects RED_ICBM_1_EFFECT
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mover RED_ICBM_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_ICBM_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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end_platform_type
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###############################################################################
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launch_computer RED_ICBM_1_LAUNCH_COMPUTER WSF_BALLISTIC_MISSILE_LAUNCH_COMPUTER
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surface_to_surface_table red_icbm_1_launch_data.txt
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end_launch_computer
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###############################################################################
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weapon RED_ICBM_1 WSF_EXPLICIT_WEAPON
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# The location offset puts the weapon center at half the length - 1 m.
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# This assumes the scenario creator puts the launching platform at 1 m agl.
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location 0.0 0.0 -9.0 m # 1/2 distance of length of missile
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launched_platform_type RED_ICBM_1
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launch_computer RED_ICBM_1_LAUNCH_COMPUTER
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end_launch_computer
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tilt 89.9 degrees
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cue_to_predicted_intercept true
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slew_mode azimuth
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azimuth_slew_limits -180 deg 180 deg
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# Default to a single weapon on the vehicle
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quantity 1
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end_weapon
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