DC Roundtable June 13, 2001 Slide 39 Size of Boost-Phase Region of Ballistic Missile Flight Location of Objects Shown Every 20 Seconds =22.55 degrees 0 V =7.177, 7.1935, and 7.21 km/s 0 q Altitude (Kilometers) Altitudes Where Reentry Effects May Be Observable (60 to 90 seconds) Altitudes Where ICBM is in Powered Flight (200 to 300 seconds) Range (Kilometers)
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Size of Boost-Phase Region of Ballistic Missile Flight · Size of Boost-Phase Region of Ballistic Missile Flight Location of Objects Shown Every 20 Seconds =22.55 degrees 0 V =7.177,
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DC RoundtableJune 13, 2001Slide 39
Size of Boost-Phase Region of Ballistic Missile Flight
Location of ObjectsShown Every 20 Seconds
=22.55 degrees0
V =7.177, 7.1935, and 7.21 km/s0
q
Altitu
de (K
ilome
ters)
Altitudes Where Reentry Effects May Be Observable(60 to 90 seconds)
Altitudes Where ICBMis in Powered Flight(200 to 300 seconds)
Range (Kilometers)
DC RoundtableJune 13, 2001Slide 40
Engagement Region of Trident II First-Stage + Kick-Stage Interceptor Against North Korean 250 Second Burn-Time ICBM
Honolulu
Washington DC Chicago San Francisco
Honolulu
End of North Korean ICBM Powered Flight
Intercept Points If GBI is Launched 50 Seconds After ICBM is Launched
Moscow
Last Chance Intercept If GBI Launched 125 Seconds After ICBM Launch
Intercept Points If GBI is Launched 100 Seconds After ICBM is Launched
Range of GBI 125 Seconds After Launch
Range of GBI 100 Seconds After Launch
Interceptor Burnout Speed ≈ 6.2 km/sec
DC RoundtableJune 13, 2001Slide 41
First-Stage Trident II Plus Kick-Stage Interceptor Timelines Against Powered Flight Profiles of 250 and 320 Second Burn-Time ICBMs
0 100 200 300 400 500 600 7000
100
200
300
400
500
600
700
Range (km)
Altit
ude
(km
)A
l
250 seconds after launch
50 seconds after launch
100 seconds after launch
200 seconds after launch
150 seconds after launch
50 seconds after launch
End of Powered Flight 64 seconds after launch
North Korean 250 Second Burn Time ICBM
75 Second Burn-Time Trident II First-Stage Interceptor (8.1-8.3 km/sec Burnout Speed)
North Korea Vladivostok
125 seconds after GBI launch
Location of Interceptor and ICBM
Shown at 5 Second Intervals
Earth Surface
2° Above Earth-
Location of THAAD-GBR
Tangent to Earth
Intercept Point If Interceptor is Launched 95 Seconds After ICBM Launch
Location of ICBM When Interceptor is Launched 95 Second After ICBM Liftoff
320 secondsafter launch
145 seconds after launch
Titan II / SS-18 Class Liquid Propellant ICBM
Location of ICBM When Interceptor is Launched 120 Second After ICBM Liftoff
Intercept Point If Interceptor is Launched 120 Seconds After ICBM Launch
DC RoundtableJune 13, 2001Slide 42
Boost-Phase Kill Vehicle Capable of 10 G Maximum Divert Acceleration and 2 km/sec Total Divert Velocity
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.
Boost-Phase Interceptor Based on the Trident II First-Stage Rocket Motor
Trident D5Boost-Phase Interceptor
Trident II First-Stage Rocket Motor (87,000 lbs, 64 Second Burn Time)
High-Divert and Acceleration Homing Boost-Phase Kill Vehicle
(250-500 lbs)
Kick-Stage Motor (1,000-1500 lbs, 10 Second Burn Time)
Velocity of Homing Boost-Phase Kill Vehicle at Burnout ≥ 8.1-8.5 km/sec (Kick-Stage)
≥ 6.1-6.5 km/sec (No Kick-Stage)
DC RoundtableJune 13, 2001Slide 52
Appendix Ballistic Missile Plumes
DC RoundtableJune 13, 2001Slide 53
Short and Medium Wavelength Missile Plume Characteristics Relevant to Hard-Body Homing
Ballistic Missile Plume Radiance Characteristics
at Intermediate Altitudes (50 to 90 Kilometers)
DC RoundtableJune 13, 2001Slide 54
Narrow Band Infrared Target Measurements Combined with Frame-to-Frame Subtraction
Missile Hard-Body
Plume Hot-Core
Notes: Observation Bandwidth 3.4 – 3.7 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 > 1000×1000
DC RoundtableJune 13, 2001Slide 55
Shape and Radiance Characteristics of Ballistic Missile Exhaust Plumes at Different Altitudes
Low Altitudes Intermediate Altitudes High Altitudes
DC RoundtableJune 13, 2001Slide 56
Variation of Apparent Ballistic Missile Exhaust Plume Intensities With Altitude
DC RoundtableJune 13, 2001Slide 57
Short and Medium Wavelength Radiance of the Titan IIIB at 18 and 118 Kilometers Altitude
DC RoundtableJune 13, 2001Slide 58
Short and Medium Wavelength Radiance Maps of the Titan IIIB at 18 and 118 Kilometers Altitude
DC RoundtableJune 13, 2001Slide 59
Flight Profile and Initial Plume Intensities of the Titan IIIB
DC RoundtableJune 13, 2001Slide 60
Short and Medium Wavelength Radiance of the Titan IIIB at 18 and 118 Kilometers Altitude
~1500 KW/sr
~20 KW/sr
~.005×100 KW/sr = 500 W/sr
~.001µm×500 W/sr/µm = .5 W/sr? ~200 – 500 W/sr over distances of meters?
DC RoundtableJune 13, 2001Slide 61
Narrow Band Infrared Target Measurements Combined with Frame-to-Frame Subtraction