1. Lesson 10: Solid Propulsion Systems Dr. Andrew Ketsdever

2. 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

3. Titan IV 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.Titan UA1207 SolidUA1207 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.IUS-1 SolidSRM-1 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.IUS-2 SolidSRM-2

4. 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 (Lockheed- Martin Launch Vehicle); LLV (Lockheed Launch Vehicle).

5. 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.Castor 120SolidCastor 120 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.ESBMSolidSRM-1 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. Pressure- fed, indefinite number of restarts.OAMHydrazineMR-107

6. Space Shuttle Solid Rocket Boosters 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).propellantSRB 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.propellant aft 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. propellant

7. Space Shuttle Solid Rocket Boosters The nozzle expansion ratio of each booster beginning with the STS-8 mission is 11.286nozzle STS-8 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.nozzle SRB auxiliary power units Each nozzle has a carbon cloth liner that erodes and chars during firing. The nozzle is a convergent- divergent, movable design in which an aft pivot- point flexible bearing is the gimbal mechanism.nozzle aft

8. 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.Solid 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.Shuttle ASRMSolid Hercules

9. 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.

10. Pegasus Stage Data - Pegasus XL 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: Belly-mounted, 36,800 kg, 17.1 m length x 7.9 m span at 925 kph at 11,890 m altitude.L-1011Air/KeroseneRB-211-22B 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.Pegasus XL-1 SolidPegasus XL-1 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.Pegasus XL-2 SolidPegasus XL-2 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-3SolidPegasus-3

11. Pegasus

13. Pegasus Capabilities

14. H2 (Japan) 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.H-2-0SolidH-2-0 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.H-2-1 Lox/LH2LE-7 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. LE- 5A Other designations: LE-5EC. Status: In Production.H-2-2Lox/LH2LE- 5A

15. 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.SolidAerojet SRB

16. 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-AJ- 1. 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

17. Minuteman 3 LGM-30ALGM-30BLGM-30FLGM-30G Length16.4 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) Diameter1.7 m (5 ft 6 in) (1st stage) Weight29400 kg (65000 lb) 33100 kg (73000 lb) 35300 kg (78000 lb) Speed24100 km/h (15000 mph) Ceiling1100 km (700 miles) Range 10100 km (6300 miles) 9600 km (6000 miles) 11300 km (7000 miles) 13000 km (8100 miles) Propulsion 1st stage:Thiokol M55 solid-fuel rocket; 933 kN (210000 lb) 2nd stage: 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) 3rd stage: 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) Post-boost: LGM-30G only: Rocketdyne RS-14 liquid-fueled rocket; 1.40 kN (315 lb)

18. 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.

19. Peacekeeper Length 21.6 m (71 ft) Diameter2.34 m (7 ft 8 in) Weight88,300 kg (195,000 lb) Speed24,100 km/h (15,000 mph) Ceiling800 km (500 miles) Range10,900+ 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 Warhead10x W-87 thermonuclear (300 kT) in 10x Mk.21 MIRV

20. Peacekeeper A view you don’t want to see

21. 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.

22. Minotaur 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.Minuteman-1SolidM55/TX-55/Tu-122 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. SR- 19 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.Minuteman 2-2SolidSR- 19 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.Pegasus XL-2SolidPegasus XL-2 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.Pegasus-3SolidPegasus-3

23. Missile Defense

24. 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

25. Missile Defense Plume signatures Hard body recognition Wavelength bands

26. 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