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, 2011.

• 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 IIPrimary Function: Space lift vehicleBuilder: Boeing Company, Expendable Launch SystemsPower 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 poundsPayload assist module: If used, Star-48B Solid-fuel Rocket: 14,920 pounds.Thrust (at liftoff): 699,250 poundsHeight: 125 feet, 9 inches (38.32 meters)Diameter: Fairing -- 9.5 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 1996 • Mars Pathfinder in 1996 • Mars Climate Orbiter in 1998 • Mars Polar Lander in 1999 • Mars Odyssey in 2001 • Mars Exploration Rovers (MER-A, Spirit and MER-B, Opportunity) in 2003 • Mars Phoenix lander in 2007

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): 492.931 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: 12.96 m (42.51 ft). Propellants: Solid. No Engines: 1. Engine: GEM 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): 1,054.195 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: 26.05 m (85.46 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RS-27C. Other designations: Extra ELT Thor+.

• 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): 43.630 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.

• Stage Number: 3. 1 x Stage: PAM-D2. Gross Mass: 3,697 kg (8,150 lb). Empty Mass: 431 kg (950 lb). Thrust (vac): 107.196 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.

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.