Size of Boost-Phase Region of Ballistic Missile Flight

Transcription

1 Size of Boost-Phase Region of Ballistic Missile Flight Location of Objects Shown Every 20 Seconds q =22.55 degrees 0 V 0=7.177, , and 7.21 km/s Altitude (Kilometers) Altitudes Where ICBM is in Powered Flight (200 to 300 seconds) Altitudes Where Reentry Effects May Be Observable (60 to 90 seconds) Range (Kilometers) Slide 39

2 Engagement Region of Trident II First-Stage + Kick-Stage Interceptor Against North Korean 250 Second Burn-Time ICBM Moscow Washington DC Chicago San Francisco Last Chance Intercept If GBI Launched 125 Seconds After ICBM Launch Range of GBI 100 Seconds After Launch Honolulu Honolulu Intercept Points If GBI is Launched 50 Seconds After ICBM is Launched Intercept Points If GBI is Launched 100 Seconds After ICBM is Launched Range of GBI 125 Seconds After Launch End of North Korean ICBM Powered Flight Interceptor Burnout Speed 6.2 km/sec Slide 40

3 First-Stage Trident II Plus Kick-Stage Interceptor Timelines Against Powered Flight Profiles of 250 and 320 Second Burn-Time ICBMs Location of Interceptor and ICBM Shown at 5 Second Intervals Al Altitude (km) Location of ICBM When Interceptor is Launched 120 Second After ICBM Liftoff 100 Location of ICBM When Interceptor is Launched 95 Second After ICBM Liftoff 145 seconds after launch 100 seconds after launch 50 seconds after launch 125 seconds after GBI launch Tangent to Earth Intercept Point If Interceptor is Launched 95 Seconds After ICBM Launch 2 Above Earth- 200 seconds after launch 150 seconds after launch 0 North Korea Vladivostok Earth Surface Intercept Point If Interceptor is Launched 120 Seconds After ICBM Launch Range (km) Titan II / SS-18 Class Liquid Propellant ICBM 250 seconds after launch North Korean 250 Second Burn Time ICBM 75 Second Burn-Time Trident II First-Stage Interceptor ( km/sec Burnout Speed) 50 seconds after launch 320 seconds after launch End of Powered Flight 64 seconds after launch Location of THAAD-GBR Slide 41

4 Boost-Phase Kill Vehicle Capable of 10 G Maximum Divert Acceleration and 2 km/sec Total Divert Velocity Telescope for Homing on Illuminated Targets Neodymium YAG Laser Total Propellant Weight = 230 lbs Propellant Density = 72 lb/ft3 Total Propellant Volume = 3.2 ft3 Motor Weight = 80 lbs Thrust = 4610 lbs Weight of Tanks and Structure = 46 lbs Overall Vehicle Weight = 460 lbs Payload Weight = 100 lbs Propellant=N2O4/MMH Vacuum Steady State Real Engine Performance Specific Impulse (lbf-s/lbms) = 295 Throat Diameter = 5.2 inches (.13 meters) Exit Diameter = 23.2 inches (.59 meters) Area Ratio=20 Chamber Pressure = 125 psia Motor Length = 50 inches (1.27 meters) Chamber Diameter = 13.5 inches (.35 meters) Spherical Fuel/Oxidizer Tank Diameters = 18 inches Barrel Tank Barrel Diameter = 10 inches (.26 meters) Overall Length = 38.5 inches (.98 meters) Barrel Lenght = 28.5 inches (.73 meters) Slide 42

5 Characteristics of the Navy Theater-Wide Interceptor that Make It Unsuitable for Anti-ICBM Boost-Phase Interceptor Navy interceptor Needs: To be much bigger and heavier to do the job A Much Higher booster burnout speed for Adequate Area Coverage Much more divert capability to deal with accelerating targets Much higher resolution sensors for homing on the target These requirements lead to a much bigger and heavier booster to do the Job Such a Bigger and Heavier Booster is NOT compatible with storage and launch systems on standard Navy combat ships. Navy Upper Tier Interceptor Weight = 3,100 lbs GBI Interceptor Weight = 30,000 40,000 lbs Slide 43

6 Size, Weight, Payload and Velocity Characteristics of Booster Variants Needed to Launch Kill Vehicles Slide 44

7 Mass Ratios for 70 Second Burn-Time Two and Three-Stage Boosters for Launch of Boost-Phase Kill Vehicles Mass Ratio (Total Wt) / (BPKV Weight) GBI Mass Ratios versus Burnout Speed Relative to BPKV Two Stage Point Design 400 lb BPKV 7.5 km/sec Burnout Speed Three Stage Point Design 400 lb BPKV 7.5 km/sec Burnout Speed Two Stage Point Design 400 lb BPKV 7.75 km/sec Burnout Speed Burnout Speed (km/sec) Slide 45

8 Basic Dimensions of Vertical Launch System Components Slide 46

9 Basic Dimensions of Vertical Launch System Components Slide 47

10 Vertical Launch System Compatible Variant of a Boost-Phase Two-Stage Navy Interceptor First Stage Minutman 51,000 lbs VLS "Compatible" Boost-Phase Interceptor 16,900 lbs BPKV Weight = 400 lbs V = 6.65 km/sec bo Shroud Weight = 75 lbs Stage Weight = 5,422 lbs Fuel Weight = 4,989 lbs I = 300 sec sp Stage Weight = 11,290 lbs Fuel Weight = 10,106 lbs I = 272 sec sp Slide 48

11 Vertical Launch System Compatible Variant of a Boost-Phase Two-Stage Navy Interceptor First Stage Minutman 51,000 lbs VLS "Compatible" Boost-Phase Interceptor 38,100 lbs BPKV Weight = 400 lbs, 300 lbs, 200 lbs V = 7.6 km/sec, 7.8 km/sec, 8 km/sec bo Shroud Weight = 100 lbs Stage Weight = 12,200 lbs Fuel Weight = 11,224 lbs I = 300 sec sp Stage Weight = 25,400 lbs Fuel Weight = 22,860 lbs I = 272 sec sp Slide 49

12 Notional Two-Stage Boost-Phase Interceptors Relative to the First Stage of the Minuteman ICBM Boost-Phase Interceptor 75,000 lbs Boost-Phase Interceptor 60,000 lbs First Stage Minutman 51,000 lbs VLS "Compatible" Boost-Phase Interceptor 38,100 lbs VLS "Compatible" Boost-Phase Interceptor 16,900 lbs BPKV Weight = 400 lbs, 300 lbs, 200 lbs V = 7.6 km/sec, 7.8 km/sec, 8 km/sec bo Shroud Weight = 100 lbs BPKV Weight = 400 lbs V = 6.65 km/sec bo Shroud Weight = 75 lbs Stage Weight = 12,200 lbs Fuel Weight = 11,224 lbs I = 300 sec sp Stage Weight = 5,422 lbs Fuel Weight = 4,989 lbs I = 300 sec sp Stage Weight = 25,400 lbs Fuel Weight = 22,860 lbs I = 272 sec sp Stage Weight = 11,290 lbs Fuel Weight = 10,106 lbs I = 272 sec sp Slide 50

13 Boost-Phase Interceptor Based on the Trident II First-Stage Rocket Motor Boost-Phase Interceptor Trident D5 Velocity of Homing Boost-Phase Kill Vehicle at Burnout km/sec (Kick-Stage) km/sec (No Kick-Stage) High-Divert and Acceleration Homing Boost-Phase Kill Vehicle ( lbs) Kick-Stage Motor (1, lbs, 10 Second Burn Time) Trident II First-Stage Rocket Motor (87,000 lbs, 64 Second Burn Time) Slide 51

14 Appendix Ballistic Missile Plumes Slide 52

15 Short and Medium Wavelength Missile Plume Characteristics Relevant to Hard-Body Homing Ballistic Missile Plume Radiance Characteristics at Intermediate Altitudes (50 to 90 Kilometers) Slide 53

16 Narrow Band Infrared Target Measurements Combined with Frame-to-Frame Subtraction Missile Hard-Body Plume Hot-Core Notes: Observation Bandwidth µm Laser Illuminator Bandwidth Could be <<.001 µm Frame-to-Frame Subtraction Should Give Edge Enhancement Effects Use of Shorter Wavelength Illuminators May Allow for Uncooled CCDs with Very Large Number of Elements > Slide 54

17 Shape and Radiance Characteristics of Ballistic Missile Exhaust Plumes at Different Altitudes Low Altitudes Intermediate Altitudes High Altitudes Slide 55

18 Variation of Apparent Ballistic Missile Exhaust Plume Intensities With Altitude Slide 56

19 Short and Medium Wavelength Radiance of the Titan IIIB at 18 and 118 Kilometers Altitude Slide 57

20 Short and Medium Wavelength Radiance Maps of the Titan IIIB at 18 and 118 Kilometers Altitude Slide 58

21 Flight Profile and Initial Plume Intensities of the Titan IIIB Slide 59

22 Short and Medium Wavelength Radiance of the Titan IIIB at 18 and 118 Kilometers Altitude ~ KW/sr = 500 W/sr ~1500 KW/sr ~ W/sr over distances of meters? ~.001µm 500 W/sr/µm =.5 W/sr? ~20 KW/sr Slide 60

23 Narrow Band Infrared Target Measurements Combined with Frame-to-Frame Subtraction Slide 61

24 Slide 62