Lesson 10:
Solid Propulsion Systems
Dr. Andrew Ketsdever
Titan
• The Titan series started out as
a back-up ICBM to the Atlas
• Early versions used
Lox/Kerosene propellants,
later versions used nitrogen
tetroxide/UDMH
• Solid boosters added to later
launch vehicle versions
Titan IV
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Manufacturer: Martin. Launches: 22. Failures: 2. Success Rate: 90.91% pct.
First Launch Date: 14 June 1989. Last Launch Date: 12 August 1998.
Launch data is: continuing. LEO Payload: 17,700 kg. to: 185 km Orbit.
Payload: 6,350 kg. to a: Geosynchronous transfer trajectory. Liftoff Thrust:
1,307,380 kgf. Liftoff Thrust: 12,821.00 kN. Total Mass: 886,420 kg. Core
Diameter: 4.33 m. Total Length: 51.00 m. Launch Price $: 400.00 million. in
1997 price dollars. Flyaway Unit Cost $: 89.36 million. in 1985 unit dollars.
Cost comments: Titan IV development contract was $ 15.8 billion, including
40 launch vehicles and 39 launches.
Stage Number: 0. 2 x Titan UA1207 Gross Mass: 319,330 kg. Empty Mass:
51,230 kg. Thrust (vac): 725,732 kgf. Isp: 272 sec. Burn time: 120 sec.
Isp(sl): 245 sec. Diameter: 3.05 m. Span: 3.05 m. Length: 34.14 m.
Propellants: Solid No Engines: 1. UA1207 Status: In Production.
Stage Number: 3. 1 x IUS-1 Gross Mass: 10,841 kg. Empty Mass: 1,134 kg.
Thrust (vac): 18,508 kgf. Isp: 296 sec. Burn time: 152 sec. Isp(sl): 220 sec.
Diameter: 2.34 m. Span: 2.34 m. Length: 3.52 m. Propellants: Solid No
Engines: 1. SRM-1 Other designations: Orbus 21D. Status: In Production.
Stage Number: 4. 1 x IUS-2 Gross Mass: 3,919 kg. Empty Mass: 1,170 kg.
Thrust (vac): 7,996 kgf. Isp: 304 sec. Burn time: 103 sec. Isp(sl): 200 sec.
Diameter: 1.61 m. Span: 1.61 m. Length: 2.08 m. Propellants: Solid No
Engines: 1. SRM-2 Other designations: TOS. Status: In Production.
Athena I and II
• All-solid orbital launch vehicle.
• Privately funded solid
propellant satellite launch
vehicle. Basic version with
Castor 120 first stage, Orbus
second stage, and OAM
Orbital Adjustment Module.
Formerly LMLV (LockheedMartin Launch Vehicle); LLV
(Lockheed Launch Vehicle) .
Athena
•
Manufacturer: Lockheed. Launches: 4. Failures: 1. Success Rate: 75.00% pct. First
Launch Date: 15 August 1995. Last Launch Date: 30 September 2001. Launch data
is: complete. LEO Payload: 820 kg. to: 185 km Orbit. at: 28.5 degrees. Payload: 360
kg. to a: Sun synchronouts, 800 km, 98.6 deg orbit trajectory. Liftoff Thrust: 147,800
kgf. Liftoff Thrust: 1,449.00 kN. Total Mass: 66,300 kg. Core Diameter: 2.36 m. Total
Length: 18.90 m. Launch Price $: 17.00 million. in 2000 price dollars.
Stage Data - Athena-1
• Stage Number: 1. 1 x Castor 120 Gross Mass: 53,020 kg. Empty Mass: 4,211 kg.
Thrust (vac): 163,827 kgf. Isp: 286 sec. Burn time: 83 sec. Isp(sl): 229 sec. Diameter:
2.36 m. Span: 2.36 m. Length: 10.70 m. Propellants: Solid No Engines: 1. Castor 120
Status: In Production. Comments: Modification of Peackeeper ICBM first stage.
• Stage Number: 2. 1 x ESBM Gross Mass: 10,810 kg. Empty Mass: 1,030 kg. Thrust
(vac): 19,300 kgf. Isp: 293 sec. Burn time: 150 sec. Diameter: 2.30 m. Span: 2.30 m.
Length: 3.00 m. Propellants: Solid No Engines: 1. SRM-1 Status: In Production.
• Stage Number: 3. 1 x OAM Gross Mass: 714 kg. Empty Mass: 360 kg. Thrust (vac):
90 kgf. Isp: 222 sec. Burn time: 1,500 sec. Diameter: 2.30 m. Span: 2.30 m. Length:
1.00 m. Propellants: Hydrazine No Engines: 4. MR-107 Status: In Production.
Comments: Monopropellant final stage providing precise orbital injection. Pressurefed, indefinite number of restarts.
Space Shuttle
Solid Rocket Boosters
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The propellant mixture in each SRB motor consists
of an ammonium perchlorate (oxidizer, 69.6 percent
by weight), aluminum (fuel, 16 percent), iron oxide
(a catalyst, 0.4 percent), a polymer binder (PBAN 12.04 percent), and an epoxy curing agent (1.96
percent).
The propellant is an 11-point star- shaped
perforation in the forward motor segment and a
double- truncated- cone perforation in each of the
aft segments and aft closure. This configuration
provides high thrust at ignition and then reduces the
thrust by approximately one third at 50 seconds
after lift-off to prevent overstressing the vehicle
during maximum dynamic pressure.
The SRBs are used as matched pairs and each is
made up of four solid rocket motor segments. The
pairs are matched by loading each of the four motor
segments in pairs from the same batches of
propellant ingredients to minimize any thrust
imbalance. The segmented-casing design assures
maximum flexibility in fabrication and ease of
transportation and handling – BUT is more likely to
have failure modes. Each segment is shipped to the
launch site on a heavy- duty rail car with a specially
built cover.
Space Shuttle
Solid Rocket Boosters
• The nozzle expansion ratio of
each booster beginning with the
STS-8 mission is 11.286
• The nozzle is gimbaled for thrust
vector (direction) control. Each
SRB has its own redundant
auxiliary power units and
hydraulic pumps. The all-axis
gimbaling capability is 8 degrees.
• Each nozzle has a carbon cloth
liner that erodes and chars during
firing. The nozzle is a convergentdivergent, movable design in
which an aft pivot- point flexible
bearing is the gimbal mechanism.
Space Shuttle
Solid Rocket Motors
• Designer: Thiokol. Gross Mass: 589,670 kg. Empty
Mass: 86,183 kg. Propellants: Solid Thrust(vac):
1,174,713 kgf. Thrust(vac): 11,519.80 kN. Isp: 269 sec.
Isp (sea level): 237 sec. Burn time: 124 sec. Diameter:
3.71 m. Length: 38.47 m. Chambers: 1. Country: USA.
Status: In Production. First Flight: 1981. Last Flight:
1998. Flown: 186.
• ADVANCED DESIGN: Stage Number: 0. 2 x Shuttle
ASRM Gross Mass: 625,000 kg. Empty Mass: 75,000
kg. Thrust (vac): 1,587,302 kgf. Isp: 286 sec. Burn time:
133 sec. Isp(sl): 259 sec. Diameter: 3.81 m. Span: 3.81
m. Length: 38.41 m. Propellants: Solid No Engines: 1.
Hercules Other designations: Advanced Solid Rocket
Motor. Status: Development 1990.
Pegasus
• Manufacturer: OSC. Launches: 27. Failures: 3. Success Rate:
88.89% pct. First Launch Date: 27 June 1994. Last Launch Date: 15
April 2005. Launch data is: continuing. LEO Payload: 443 kg. to: 185
km Orbit. at: 28.5 degrees. Payload: 190 kg. to a: Sun synchronous,
800 km, 98.5 deg orbital trajectory. Liftoff Thrust: 49,623 kgf. Liftoff
Thrust: 486.64 kN. Total Mass: 24,000 kg. Core Diameter: 1.27 m.
Total Length: 17.60 m. Launch Price $: 12.00 million. in 1994 price
dollars.
Pegasus
Stage Data - Pegasus XL
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Stage Number: 0. 1 x L-1011 Gross Mass: 156,000 kg. Empty Mass:
109,629 kg. Thrust (vac): 57,300 kgf. Isp: 9,900 sec. Burn time: 4,590 sec.
Isp(sl): 9,000 sec. Diameter: 16.86 m. Span: 47.00 m. Length: 54.00 m.
Propellants: Air/Kerosene No Engines: 3. RB-211-22B Status: In Production.
Comments: Lockheed airliner swept wing. Release conditions: Bellymounted, 36,800 kg, 17.1 m length x 7.9 m span at 925 kph at 11,890 m
altitude.
Stage Number: 1. 1 x Pegasus XL-1 Gross Mass: 17,934 kg. Empty Mass:
2,886 kg. Thrust (vac): 60,062 kgf. Isp: 293 sec. Burn time: 73 sec. Isp(sl):
180 sec. Diameter: 1.27 m. Span: 6.71 m. Length: 8.88 m. Propellants:
Solid No Engines: 1. Pegasus XL-1 Status: In Production.
Stage Number: 2. 1 x Pegasus XL-2 Gross Mass: 4,331 kg. Empty Mass:
416 kg. Thrust (vac): 15,653 kgf. Isp: 290 sec. Burn time: 73 sec. Isp(sl):
240 sec. Diameter: 1.27 m. Span: 1.27 m. Length: 3.58 m. Propellants:
Solid No Engines: 1. Pegasus XL-2 Status: In Production.
Stage Number: 3. 1 x Pegasus-3 Gross Mass: 985 kg. Empty Mass: 203 kg.
Thrust (vac): 3,525 kgf. Isp: 293 sec. Burn time: 65 sec. Isp(sl): 240 sec.
Diameter: 0.97 m. Span: 0.97 m. Length: 2.08 m. Propellants: Solid No
Engines: 1. Pegasus-3 Status: In Production.
Pegasus
Pegasus
Pegasus Capabilities
H2 (Japan)
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Manufacturer: Mitsubishi. Launches: 7. Failures: 2. Success Rate: 71.43%
pct. First Launch Date: 3 February 1994. Last Launch Date: 15 November
1999. Launch data is: complete. LEO Payload: 10,060 kg. to: 200 km Orbit.
at: 30.4 degrees. Payload: 3,930 kg. to a: Geosynchronous transfer
trajectory. Liftoff Thrust: 405,000 kgf. Liftoff Thrust: 3,970.00 kN. Total Mass:
260,000 kg. Core Diameter: 4.00 m. Total Length: 49.00 m. Development
Cost $: 2,300.00 million. in 1998 average dollars. Launch Price $: 190.00
million. in 1994 price dollars. Cost comments: Development cost includes $
800 million spent on LE-7 engine development.
•
Stage Number: 0. 2 x H-2-0 Gross Mass: 70,400 kg. Empty Mass: 11,250
kg. Thrust (vac): 157,036 kgf. Isp: 273 sec. Burn time: 94 sec. Isp(sl): 237
sec. Diameter: 1.81 m. Span: 1.81 m. Length: 23.36 m. Propellants: Solid
No Engines: 1. H-2-0 Status: In Production.
Stage Number: 1. 1 x H-2-1 Gross Mass: 98,100 kg. Empty Mass: 11,900
kg. Thrust (vac): 109,925 kgf. Isp: 446 sec. Burn time: 346 sec. Isp(sl): 349
sec. Diameter: 4.00 m. Span: 4.00 m. Length: 28.00 m. Propellants:
Lox/LH2 No Engines: 1. LE-7 Other designations: LE-7. Status: In
Production.
Stage Number: 2. 1 x H-2-2 Gross Mass: 16,700 kg. Empty Mass: 2,700 kg.
Thrust (vac): 12,390 kgf. Isp: 452 sec. Burn time: 600 sec. Diameter: 4.00
m. Span: 4.00 m. Length: 10.60 m. Propellants: Lox/LH2 No Engines: 1. LE5A Other designations: LE-5EC. Status: In Production.
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Atlas V
• Gross Mass: 40,824 kg. Empty Mass:
4,000 kg. Thrust (vac): 130,000 kgf.
Isp: 275 sec. Burn time: 94 sec.
Propellants: Solid Isp(sl): 245 sec.
Diameter: 1.55 m. Span: 1.00 m.
Length: 17.70 m. Country: USA. No
Engines: 1. Aerojet SRB Status: In
production. Comments: New SRB
boosters in development for Atlas V.
Empty mass, vacuum thrust, sea
level Isp estimated.
Minuteman 3
• Manufacturer: Boeing. Launches: 267. Failures:
5. Success Rate: 98.13% pct. First Launch
Date: 16 August 1968. Last Launch Date: 14
September 2005. Launch data is: continuing.
Apogee: 1,600 km. Liftoff Thrust: 81,600 kgf.
Liftoff Thrust: 935.00 kN. Total Mass: 35,400 kg.
Core Diameter: 1.68 m. Total Length: 18.23 m.
Span: 1.89 m. Standard warhead mass: 1,000
kg. Maximum range: 12,900 km. Number
Standard Warheads: 3. Standard RV: Mk. 12A.
Standard warhead: W78. Standard warhead
yield: 335 KT. Standard warhead CEP: 0 km.
Boost Propulsion: Solid rocket. Boost engine:
M55A-1. Cruise Propulsion: Solid rocket. Cruise
engine: SR19-AJ-1. Stage 3 Engine: SR73-AJ1. Stage 3 Propellants: Solid rocket. Guidance:
Inertial. Maximum speed: 29,030 kph. Ceiling:
1,287,800 m. Development Cost $: 2,694.60
million. in 1971 average dollars. Recurring Price
$: 4.91 million. Total Number Built: 830. Total
Development Built: 46. Total Production Built:
794. Flyaway Unit Cost $: 2.90 million. in 1971
unit dollars
Minuteman 3
LGM-30A
LGM-30B
LGM-30F
LGM-30G
Length
16.4 m (53 ft 8 in)
17.0 m (55 ft 11
in)
17.6 m (57 ft 7
in)
18.2 m (59 ft 9.5 in)
Diameter
1.7 m (5 ft 6 in) (1st stage)
Weight
29400 kg (65000 lb)
33100 kg (73000
lb)
35300 kg (78000 lb)
Speed
24100 km/h (15000 mph)
Ceiling
1100 km (700 miles)
Range
10100 km (6300
miles)
11300 km (7000
miles)
13000 km (8100 miles)
1st stage:
2nd stage:
Propulsion
3rd stage:
Post-boost:
9600 km (6000
miles)
Thiokol M55 solid-fuel rocket; 933 kN (210000 lb)
LGM-30A/B: Aerojet General M56 solid-fuel rocket; 267 kN (60000 lb)
LGM-30F/G: Aerojet General SR19-AJ-1 solid-fuel rocket; 268 kN (60300 lb)
LGM-30A/B/F: Hercules M57 solid-fuel rocket; 156 kN (35000 lb)
LGM-30G: Aerojet/Thiokol SR73-AJ/TC-1 solid-fuel rocket; 153 kN (34400 lb)
LGM-30G only: Rocketdyne RS-14 liquid-fueled rocket; 1.40 kN (315 lb)
Peacekeeper
• Manufacturer: Martin Marietta. Guidance
contractor: Boeing. Launches: 51. Failures: 1.
Success Rate: 98.04% pct. First Launch Date:
17 June 1983. Last Launch Date: 21 July 2004.
Launch data is: continuing. Apogee: 1,000 km.
Liftoff Thrust: 1,711.00 kN. Total Mass: 88,430
kg. Core Diameter: 2.34 m. Total Length: 21.60
m. Span: 2.34 m. Standard warhead mass:
3,600 kg. Maximum range: 13,000 km. Number
Standard Warheads: 10. Standard RV: Mk.
12A. Standard warhead: W87. Standard
warhead yield: 300 KT. Boost Propulsion: Solid
rocket. Cruise Propulsion: Solid rocket.
Guidance: Inertial. Development Cost $:
10,926.80 million. Recurring Price $: 77.88
million. Total Number Built: 226. Flyaway Unit
Cost $: 77.40 million.
Peacekeeper
Length
21.6 m (71 ft)
Diameter
2.34 m (7 ft 8 in)
Weight
88,300 kg (195,000 lb)
Speed
24,100 km/h (15,000 mph)
Ceiling
800 km (500 miles)
Range
10,900+ km (6,800+ miles)
Propulsion
1st stage: Thiokol solid-fuel rocket; 2200 kN (500,000 lb)
2nd stage: Aerojet solid-fuel rocket
3rd stage: Hercules solid-fuel rocket
4th stage (post-boost): Rocketdyne restartable liquid-fuel
rocket
Warhead
10x W-87 thermonuclear (300 kT) in 10x Mk.21 MIRV
Peacekeeper
A view you don’t want to see
Minotaur – Minotaur IV
• Decommissioned Minuteman (Minotaur)
or Peacekeeper (Minotaur IV) boosters
• Manufacturer: OSC. Launches: 4
(Minotaur). Success Rate: 100.00% pct.
First Launch Date: 27 January 2000. Last
Launch Date: 23 September 2005.
Launch data is: continuing. LEO Payload:
640 kg. to: 185 km Orbit. at: 28.5 degrees.
Payload: 335 kg. to a: Sun synchronous,
741 km, 98.6 deg inclination trajectory.
Apogee: 1,000 km. Liftoff Thrust: 73,000
kgf. Liftoff Thrust: 720.00 kN. Total Mass:
36,200 kg. Core Diameter: 1.67 m. Total
Length: 19.21 m. Recurring Price $: 12.50
million. in 1999 price dollars.
Minotaur
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Stage Number: 1. 1 x Minuteman-1 Gross Mass: 23,077 kg. Empty Mass:
2,292 kg. Thrust (vac): 80,700 kgf. Isp: 262 sec. Burn time: 60 sec. Isp(sl):
237 sec. Diameter: 1.67 m. Span: 1.67 m. Length: 7.49 m. Propellants: Solid
No Engines: 1. M55/TX-55/Tu-122 Status: Out of Production. Comments:
First stage of Minuteman I. Proposed as zero stage for various Saturn
variants in 1960's. Surplus motors used in ABM SDI tests in 1980's and
1990's.
Stage Number: 2. 1 x Minuteman 2-2 Gross Mass: 7,032 kg. Empty Mass:
795 kg. Thrust (vac): 27,300 kgf. Isp: 288 sec. Burn time: 66 sec. Diameter:
1.33 m. Span: 1.33 m. Length: 4.12 m. Propellants: Solid No Engines: 1. SR19 Status: Out of production. Comments: Second stage of Minuteman 2.
Used as second stage of Minotaur launch vehicle and various SDI targets in
1980's.
Stage Number: 3. 1 x Pegasus XL-2 Gross Mass: 4,331 kg. Empty Mass:
416 kg. Thrust (vac): 15,653 kgf. Isp: 290 sec. Burn time: 73 sec. Isp(sl): 240
sec. Diameter: 1.27 m. Span: 1.27 m. Length: 3.58 m. Propellants: Solid No
Engines: 1. Pegasus XL-2 Status: In Production.
Stage Number: 4. 1 x Pegasus-3 Gross Mass: 985 kg. Empty Mass: 203 kg.
Thrust (vac): 3,525 kgf. Isp: 293 sec. Burn time: 65 sec. Isp(sl): 240 sec.
Diameter: 0.97 m. Span: 0.97 m. Length: 2.08 m. Propellants: Solid No
Engines: 1. Pegasus-3 Status: In Production.
Missile Defense
Sensor Difficulties
• Where should the sensor be located?
– Air (Airborne Laser)
– Sea (Aegis)
– Space (SBIRs, DSP)
• What wavelength should the sensor be tuned
to?
– Plume signature
• IR, Visible, UV
– Hard body heating
• IR, Visible
– Atmospheric windows (boost phase)
• Broad band wavelength or discrete capability?
– Blackbody radiator
– Atomic/Molecular radiator
– Sensor resolution is key
Missile Defense
• Plume
signatures
• Hard body
recognition
• Wavelength
bands
Plume Signatures
• Boost Phase
– Huge IR signature from plume
– Differentiation with the hard body
• Where is the needle in the haystack?
• Don’t want to shoot down the plume
• Midcourse Phase
– Plume expansion
– Evasion (liquid systems for maneuvers)
– Decoys
– Excitation due to AO and Solar UV