Delta IV Heavy Launch Vehicle

Delta IV Heavy Launch Vehicle Delta IV Heavy Delta IV Heavy Upgrade Select Image Delta IV Heavy History Delta IV Heritage Reference Information

Delta IV Heavy Model Configuration Payload Fairing Starboard Strap-on Common Booster Core Center Common Booster Core Port Strap-on Common Booster Core

Delta IV Heavy Model Configuration Starboard Strap-on Common Booster Core Center Common Booster Core Payload Fairing Port Strap-on Common Booster Core

Delta IV Heavy Configuration 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 1 2 3 4 5 6 7 Credit: United Launch Alliance The Delta 4 Heavy launch vehicle configuration consists of one center common booster core (CBC) and two strap-on CBCs powered by Rocketdyne RS-68A engines that burn liquid hydrogen and liquid oxygen, and a payload fairing. The approximately 232 ft in height rocket is launched from Space Launch Complex-37 at Cape Canaveral Air Force Station in Florida and Space Launch Complex-6 at Vandenberg Air Force Base in California. The major components of the vehicle are: 1. Payload Fairing 2. Acoustic Blankets 3. Spacecraft 4. Payload Attach Fitting 5. Second-Stage Fuel (H) Tank 6. Second-Stage Intertank Truss Assembly 7. High Pressure Helium Bottle 8. Second-Stage Oxidizer (L02) Tank 9. Strap-on Nosecone 10. Second-Stage Equipment Shelf 11. Hydrazine Bottle 12. Interstage Adapter 13. Second-Stage Engine (RL10) 14. Strap-on Strut Assembly 15. First-Stage Oxidizer (L02) Tank 16. Anti-slosh Baffle 17. Centerbody 18. First-Stage Fuel (LH2) Tank 19. First-Stage Oxidizer (L02) Feedline 20. Port Strap-on Common Booster Core 21. Center Common Booster Core 22. Starboard Strap-on Common Booster Core 23. Isogrid Structure 24. First-Stage Fuel (LH2) Feedline 25. Thermal Shield 26. First-Stage Engine (RS-68)

First Delta IV Heavy Launch The Boeing Delta IV Heavy was first launched on December 21, 2004 from Space Launch Complex 37B, Cape Canaveral Air Force Station, FL. The inaugural flight payload included a demonstration DemoSat and two low Earth orbit Microsats. However, the center common booster core (CBC) shut down 9 seconds early and the two strap-on CBCs shut down 8 seconds early. - The second stage compensated for the early shutdowns. - The DemoSat payload achieved the correct geosynchronous transfer orbit but the two Microsats failed to orbit. - The Delta IV CBCs were retrofitted with new pressure valves to alleviate cavitation in the liquid oxygen fuel lines that possibly occurred in the during the flight. -- The cavitation, or bubbling, is a localized condition where the super-cold oxidizer changed from liquid to vapor within the feed lines running from the rocket's tanks to the engines causing the them to shutdown early. Credit: The Boeing Company

First Successful Operational Delta IV Heavy Launch The first operational flight of the United Launch Alliance Delta IV Heavy successfully launched the Defense Support Program flight 23 satellite (DSP-23). The rocket is shown launching the early warning satellite from Space Launch Complex 37B at Cape Canaveral Air Force Station, FL on November 11, 2011. - DSP-23 marked the end of a 36 year era of DSP satellites. United Launch Alliance (ULA) was formed in December 2006 bringing together two launch industry teams to provide space launch services for the United States government. ULA is a 50-50 joint venture between Lockheed Martin and The Boeing Company. - U.S. government launch customers include: the Department of Defense, NASA, the National Reconnaissance Office and other organizations. Credit: U.S. Air Force

First Delta IV Heavy Launch from Vandenberg Credit: United Launch Alliance The first launch of the United Launch Alliance Delta IV Heavy from Space Launch Complex- 6 from Vandenberg Air Force Base, CA was on January 20, 2011. The rocket successfully orbited a National Reconnaissance Office payload (NROL-49). The rocket was the largest to ever launch from the West Coast of the United States. During the launch, a large fireball of unburnt hydrogen emerged from the launch table engulfing the center common booster core (CBC) and the two strap-on CBCs in flames. - The hydrogen burn-off caused the foam insulation on the CBCs to catch fire. -- The flames were extinguished during vertical ascent. - A staggered ignition was implemented to reduce the flame. -- As the starboard engine runs, it aspirates the gaseous hydrogen coming from the port and center engines, directing the H 2 down the launch table into the flame deflector where the H 2 can burn instead of rising and creating the large fireball.

First Delta IV Heavy Upgrade Launch An upgrade of the Delta IV Heavy was first successfully flight tested during a launch on June 29, 2012 from Space Launch Complex 37B, Cape Canaveral Air Force Station, FL. The upgraded rocket lifted the National Reconnaissance Office NROL-15 payload (NROL-15). The center and two strap-on common booster cores were powered by the higher performance RS-68A engine. - The three engines produced a combined liftoff thrust of nearly 2.1 million lbs, approximately a 6 percent increase from the previous RS-68 engine thrust. -- Pratt & Whitney Rocketdyne developed the RS-68A specifically to be able to lift the NROL-15 payload. Credit: U.S. Air Force

Launch Orion Exploration Flight Test-1 Orion Crew Vehicle 2nd Stage Center Common Booster Core Strap-on Common Booster Core Credit: U.S. Air Force and Lockheed Martin A United Launch Alliance Delta IV Heavy Upgrade is scheduled to launch an un-crewed Orion Multi-Purpose Crew Vehicle from Cape Canaveral Air Force Station (CCAFS), FL on December 4, 2014. The Orion spacecraft will take astronauts beyond low Earth orbit to deep space. - It will provide emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space. The Exploration Flight Test-1 will test the Orion Crew Module s orbital ability and re-entry capabilities. - The capsule will dive into Earth's atmosphere giving engineers key data on how the spacecraft responds to a re-entry at speeds closely replicating what the vehicle will see when returning from deep space missions. The Delta IV Heavy launch vehicle has a center common booster core (CBC) and two strap-on CBCs powered by RS-68A cryogenic engines. - The second stage is also cryogenic powered by a Pratt and Whitney RL-10B2 engine. This Delta IV Heavy, shown with Orion, was originally photographed launching a National Reconnaissance Office classified payload in November 2010 from CCAFS, FL.

Orion Exploration Flight Test-1 Vehicle Service Module (SM) Crew Module (CM) Delta IV Second Stage Select Image for Animation Credit: NASA Exploration Flight Test-1 or EFT-1 is the first planned un-crewed test flight of the Orion Multi- Purpose Crew Vehicle. The EFT-1 Delta IV Heavy rocket and the SM with the Delta IV second stage will take Orion to an altitude of approximately 3,600 miles above the Earth. - By flying Orion out to that distance, NASA will be able to see how Orion performs in and returns from deep space journeys. After the test flight, the Orion CM will separate from the SM and re-enter the atmosphere at a speed of over 20,000 miles per hour, faster than any current human spacecraft. - As Orion reenters the atmosphere, it will endure temperatures up to 4,000º F, higher than any human spacecraft since astronauts returned from the Moon. - Orion will land in the water and be recovered. The EFT-1 flight will play an important role in the finalization of Orion s design and will increase efficiencies and reduce risk. - It is equivalent to the 1967 Apollo 4 mission which validated the Apollo flight control system and the heat shield at re-entry conditions planned for the return from lunar missions.

Orion EFT-1 Delta IV Heavy Assembly The Horizontal Integration Facility (HIF) near Space Launch Complex 37 at Cape Canaveral Air Force Station, FL is used to process the Delta launch vehicles. Work areas are used for assembly and checkout to provide fully integrated launch vehicles ready for transfer to the launch pad. Inside the HIF (left), United Launch Alliance technicians prepare the second stage of the Delta IV Heavy rocket for mating to the center common core booster for the Exploration Flight Test-1 (EFT-1). Credit: NASA The Mobile Service Tower (MST), shown on the right, provides Credit: NASA environmental protection and access to the launch vehicle prior to and after mating it to the Launch Table (LT) in the vertical position. The MST includes an overhead bridge crane with a 300 ft hook height capacity. The LT supports the vehicle on the pad. The Fixed Pad Erector uses two long-stroke hydraulic pistons to raise the vehicle to the vertical position after being rolled to the pad from the HIF. The EFT-1 Delta IV Heavy rocket is shown, after it was raised to the vertical position in the MST, on the pad at Space Launch Complex 37 on October 1, 2014. Credit: Aerojet The MST moves on rails to a parked position during final launch Rocketdyne countdown.

Delta IV Heavy Launch History No. Date Type Type of Payload 1 December 21, 2004 2 November 11, 2007 3 January 18, 2009 4 November 21, 2010 5 January 20, 2011 6 June 29, 2012 7 August 28, 2013 8 December 4, 2014 Heavy Heavy Heavy Heavy Heavy Upgrade Upgrade Upgrade Demonstration payload Missile warning satellite Reconnaissance satellite Reconnaissance satellite Reconnaissance satellite Reconnaissance satellite Reconnaissance satellite NASA Orion EFT-1 Legend: CCAFS Cape Canaveral Air Force Station, FL CM Crew Module EFT-1 Exploration Flight Test-1 VAFB Vandenberg Air Force Base, CA Launch Site Outcome Remarks CCAFS Success First launch CCAFS Success First operational launch CCAFS CCAFS Success Success VAFB Success First launch from VAFB CCAFS Success First upgrade launch VAFB CCAFS Success First flight test of Orion CM (no crew)

Delta IV Heavy Heritage Credit: U.S. Federal Aviation Administration The Delta launch vehicle program was initiated in the late 1950s by NASA. The Delta vehicle was developed as an interim space launch vehicle using a modified Thor missile as the first stage and Vanguard components as the second and third stages capable of delivering payloads of 120 lbs to Geosynchronous Transfer Orbit and 400 lbs to Low Earth Orbit. The Delta program has culminated in the current Delta family of launch vehicles, with a wide range of increasing capabilities.

Reference Information Text and Images: http://www.afspc.af.mil/ http://upload.wikimedia.org/ www.ulalaunch.com/ http://www.boeing.com/ http://www.spacelaunchreport.com/ http://www.spaceflightnow.com/ http://en.wikipedia.org/ http://www.spaceflight101.com/ www.nasa.gov/ http://www.nasa.gov/ Propulsion for the 21st Century - RS-68, AIAA 2002-4324, B. K. Wood, The Boeing Company, Rocketdyne Propulsion - American Institute of Aeronautics and Astronautics paper summarizes the development of the RS-68 engine & End Orion Exploration Flight Test-1 Animation: http://youtu.be/lmq8g2fnhos?list=uuq7fcasmpevrfv5-e5nwvaa

Delta IV Heavy Major Components Sheet 1 The Delta IV Heavy launch vehicle major components include: The Delta IV common booster core (CBC) is 16.7 ft in diameter and 133.9 ft long. - The CBC is constructed of isogrid aluminum barrels, spun-formed aluminum domes, machined aluminum tank skirts, and a composite centerbody. Delta IV first-stage propulsion is provided by the RS-68 engine system. - The RS-68 burns cryogenic liquid hydrogen and liquid oxygen and delivers 663,000 Ibf of thrust at sea level. - The booster's cryogenic tanks are insulated with a combination of spray-on and bond-on insulation and helium-purged insulation blankets. - The Delta IV vehicle is controlled by an avionics system, which provides guidance, flight control, and vehicle sequencing functions during CBC and second-stage phases of flight. The Delta IV Heavy configuration employs two additional CBCs as strap-on liquid rocket boosters to augment the first-stage CBC. The spacecraft is encapsulated inside the 16.8 ft payload fairing, consisting of a composite bisector (two-piece shell) or optional trisector (three-piece shell) fairing. The second-stage is 16.7 ft in diameter and 42.8 ft long. - The propellant tanks are constructed of isogrid aluminum ring forgings, spun-formed aluminum domes, machined aluminum tank skirts and a composite intertank truss. - The second-stage is also a cryogenic liquid hydrogen/liquid oxygen-fueled vehicle. - It uses a single RL10 engine that produces 24,750 Ibf of thrust. - An equipment shelf attached to the aft dome of the second-stage liquid oxygen tank provides the structural mountings for vehicle electronics. The structural and electronic interfaces with the satellite are provided via the payload attach fitting.

Delta IV Heavy RS-68 Engine Sheet 2 Credit: NASA The RS-68 engine schematic is shown on the right. High-pressure hot gases from the gas generator power, in parallel, the two turbines. - The turbopumps are single-shaft with direct drive turbines. High-pressure ducting delivers pumped fuel and LO 2 (LOX) to the injector/thrust chamber assembly. The thrust chamber/nozzle assembly consists of a combustion chamber and an ablative nozzle. - The expansion of the gases through the chamber and the nozzle produce thrust. The RS-68 engine (left) is undergoing hot-fire testing on July 6, 2000 at Stennis Space Center during its developmental phase. The nearly transparent exhaust is due to the engine's exhaust being mostly superheated steam (water vapor from its propellants, hydrogen and oxygen). The RS-68 is capable of operating in and transitioning between full power and minimum power upon command from the vehicle. The engine also supplies pressurization gasses to thrust vector and roll control by gimbaling the thrust chamber assembly and the fuel turbine exhaust roll control nozzle, respectively. The engine is designed and built by Aerojet Rocketdyne, Canoga Park, CA. Credit: Aerojet Rocketdyne

Delta IV Heavy Heritage Sheet 1 Thor and Vanguard Launch Vehicles: Thor was the first operational ballistic missile deployed by the U.S. Air Force. - Named after the Norse god of thunder, it was deployed in the United Kingdom between 1959 and September 1963 as an intermediate range ballistic missile with thermonuclear warheads. Vanguard rockets were used by Project Vanguard from 1957 to 1959. - Vanguard was intended to be the first launch vehicle the U.S. would use to place a satellite into orbit. -- Instead, the surprise launch of the Soviet Union s Sputnik 1 led the U.S., after the failure of Vanguard TV3, to quickly orbit the Explorer 1 satellite using a Juno I rocket, making Vanguard I the second successful U.S. orbital launch. -- Three successful launches of eleven placed satellites into orbit. Delta Launch Vehicles: Delta is an American space launch system, originally designed and built by McDonnell Douglas and continued by Boeing and United Launch Alliance. - A four-digit system is used to identify the specific Delta configurations. -- The numbers and letters indicate the major configuration elements. The Delta II entered service in 1989 and delivers a capacity of 5,960-13,440 lbs to low Earth orbit (LEO). - Delta II is available in a number of configurations within the following series: 7300, 7400, and 7900. The first Delta III launch was on August 26, 1998 and had the capability to deliver a capacity of 18,280 lbs to LEO. - The Delta III is referred to as the Delta 8930.

Delta IV Heavy Heritage Sheet 2 Delta Launch Vehicles (Continued): The Delta IV entered service in 1989 and delivers a capacity of 20,750-63,470 lbs to LEO. The newest member of the Delta family is the Delta IV launch system which comes in five vehicle configurations. - Each has a first-stage, called the Common Booster Core (CBC), using cryogenic propellants. The Delta IV Medium employs a first-stage CBC, a cryogenic second stage, and a 13.4 ft diameter composite Payload Fairing (PLF). The Delta IV M+ vehicle comes in three different configurations. - The Delta IV M+(4,2) configuration uses two strap-on Solid Rocket Motors (SRMs) to augment the first-stage CBC, a cryogenic second stage, and a 13.4 ft diameter composite PLF. - The other two configurations are the Delta IV M+(5,2) and Delta IV M+(5,4) that have two and four SRMs, respectively, to augment the first-stage CBC. -- Both of these configurations employ a cryogenic second stage, and a 16.8 ft diameter composite PLF. The Delta IV Heavy employs two additional CBCs as strap-on Liquid Rocket Boosters to augment the first-stage CBC, a cryogenic second stage, and either a 16.8 ft diameter composite or metallic PLF.