MAE 5495: Launch Vehicle Analysis LECTURE 1 Dr. Andrew Ketsdever Spring 2008

Messenger Spacecraft at Mercury Messenger flew within 124 miles of Mercury's singed surface at 2:04 p.m. EST Monday Complex course through the inner solar system to set up for the craft's permanent arrival at Mercury. Messenger already completed swings past Earth and Venus since its 2004 launch. Two more close approaches to Mercury are planned in October and September 2009 to slow the spacecraft before it maneuvers into orbit around the planet on March 18, Scientists plan to operate Messenger for at least a year after its 2011 arrival Plan to answer key questions about the planet's history and the formation of the inner solar system

Messenger

Messenger Launch Launched: 03 AUG 2004 Boeing Delta II Rocket

The Delta Family of Launch Vehicles

Delta II Primary Function: Space lift vehicle Builder: Boeing Company, Expendable Launch Systems Power Plant, first stage: one Rocketdyne RS-27 and two LR-101-NA-11 vernier engines; both use refined kerosene and liquid oxygen as its propellants. Nine Alliant Techsystems strap-on graphite-epoxy motors surround the first stage for augmented lift-off. Power Plant, second stage: restartable Aerojet AJ10-110K motor; uses nitrogen tetroxide and Aerozine 50 propellants; thrust, 9,750 pounds Payload assist module: If used, Star-48B Solid-fuel Rocket: 14,920 pounds. Thrust (at liftoff): 699,250 pounds Height: 125 feet, 9 inches (38.32 meters) Diameter: Fairing feet (2.87 meters), core -- 8 feet (2.4 meters) Weight: 511,190 pounds (231,870 kilograms) Lift Capability: The Delta II can carry payloads into near-earth orbits, approximately 100 nautical miles (160 kilometers) in space. It can lift up to 11,100 pounds (4,995 kilograms) into low earth orbit, 28-degree circular near-earth orbit and up to 8,420 pounds (3,789 kilograms) into a 90-degree polar orbit. The Delta II also can carry up to 4,010 pounds (1,804.5 kilograms) into geo-transfer orbit, approximately 12,000 miles (19,200 kilometers) and up to 2,000 pounds (909 kilograms) into geosynchronous orbit, approximately 22,000 miles (35,200 kilometers). Launch Sites: Space Launch Complex 17 Pads A and B, Cape Canaveral AFS, Fla.; Space Launch Complex 2 West, Vandenberg AFB, Calif.

Delta II History Mars Global Surveyor in 1996Mars Global Surveyor1996 Mars Pathfinder in 1996Mars Pathfinder Mars Climate Orbiter in 1998Mars Climate Orbiter1998 Mars Polar Lander in 1999Mars Polar Lander1999 Mars Odyssey in 2001Mars Odyssey2001 Mars Exploration Rovers (MER-A, Spirit and MER-B, Opportunity) in 2003Mars Exploration RoversMER-AMER-B2003 Mars Phoenix lander in 2007Mars Phoenix

Atlas V Staging Data Stage Data - Delta II Stage Number: 0. 9 x Stage: GEM 40. Gross Mass: 13,064 kg (28,801 lb). Empty Mass: 1,361 kg (3,000 lb). Thrust (vac): kN (110,815 lbf). Isp: 274 sec. Burn time: 64 sec. Isp(sl): 244 sec. Diameter: 1.02 m (3.34 ft). Span: 1.02 m (3.34 ft). Length: m (42.51 ft). Propellants: Solid. No Engines: 1. Engine: GEM 40.GEM 40SolidGEM 40 Stage Number: 1. 1 x Stage: Delta Thor XLT-C. Gross Mass: 101,900 kg (224,600 lb). Empty Mass: 5,900 kg (13,000 lb). Thrust (vac): 1, kN (236,992 lbf). Isp: 302 sec. Burn time: 265 sec. Isp(sl): 255 sec. Diameter: 2.44 m (8.00 ft). Span: 2.44 m (8.00 ft). Length: m (85.46 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RS-27C. Other designations: Extra ELT Thor+.Delta Thor XLT-CLox/KeroseneRS-27C Stage Number: 2. 1 x Stage: Delta K. Gross Mass: 6,954 kg (15,330 lb). Empty Mass: 950 kg (2,090 lb). Thrust (vac): kN (9,808 lbf). Isp: 319 sec. Burn time: 431 sec. Diameter: 1.70 m (5.50 ft). Span: 2.40 m (7.80 ft). Length: 5.89 m (19.32 ft). Propellants: N2O4/Aerozine-50. No Engines: 1. Engine: AJ10-118K.Delta KN2O4/Aerozine-50AJ10-118K Stage Number: 3. 1 x Stage: PAM-D2. Gross Mass: 3,697 kg (8,150 lb). Empty Mass: 431 kg (950 lb). Thrust (vac): kN (24,099 lbf). Isp: 282 sec. Burn time: 120 sec. Isp(sl): 0 sec. Diameter: 1.60 m (5.20 ft). Span: 1.60 m (5.20 ft). Length: 1.83 m (6.00 ft). Propellants: Solid. No Engines: 1. Engine: Star 63.PAM-D2SolidStar 63

The Point By the end of this course, you will be able to analyze the performance of the launch vehicle that sent Messenger to Mercury. You will notice that a mix of solid and liquid propulsion systems were used within the context of a single mission. –By the end of this course, you will be able to recognize the advantages and disadvantages of these systems Lets get started.