Launch Vehicles

Falcon 9

Falcon 9 is a two-stage rocket designed and manufactured by SpaceX for the reliable and safe transport of satellites and the Dragon spacecraft into orbit.

Fairing

Made of a carbon composite material, the fairing protects satellites on their way to orbit. The fairing is jettisoned approximately three minutes into flight, and SpaceX continues to recover fairings for reuse on future missions.

First Stage

Falcon 9’s first stage incorporates nine Merlin engines and aluminum-lithium alloy tanks containing liquid oxygen and rocketgrade kerosene (RP-1) propellant, generating more than 1.7 million pounds of thrust at sea level. After separation, the fist stage will return to Landing Zone 4.

Interstage

The interstage is a composite structure that connects the first and second stages, and houses the pneumatic pushers that allow the first and second stage to separate during flight.

Grid fins: Falcon 9 is equipped with four hypersonic grid fins positioned at the base of the interstage. They orient the rocket during reentry by moving the center of pressure.

Second Stage

Powered by a single Merlin Vacuum Engine, the second stage delivers Falcon 9’s payload to the desired orbit. The engine ignites a few seconds after stage separation, and can be restarted several times to place multiple payloads into different orbits.

Delta IV Heavy

United Launch Alliance’s Delta IV Heavy is a heavy-lift launch vehicle, the largest type of the Delta IV family and one of the world’s most powerful rockets. The Delta IV Heavy configuration is comprised of a common booster core (CBC), a cryogenic upper stage and a 5-meter diameter payload fairing (PLF). The Delta IV Heavy employs two additional CBCs as liquid rocket boosters to augment the first-stage CBC. The Delta IV Heavy can lift 28,370 kg (62,540 lbs) to low Earth orbit and 13,810 kg (30,440 lbs) to geostationary transfer orbit. It is an all liquid-fueled rocket, consisting of an upper stage, one main booster and two strap-on boosters.

Payload Fairing (PLF)

The PLF encapsulates the spacecraft to protect it from the launch environment on ascent. The 19.2-m (63-ft) long PLF makes the vehicle’s height approximately 71.0 m (233 ft).

Delta Cryogenic Second Stage (DCSS)

The DCSS is a cryogenic liquid hydrogen/liquid oxygen fueled vehicle, with a single RL10C-2-1 engine that produces 110.1 kilo-Newtons (24,750 lbs) of thrust.

Boosters

The Delta IV booster propulsion is provided by three liquid hydrogen and liquid oxygen-burning RS-68A engines. Each RS-68A engine produces 312.3 kilo-Newtons (705,250 lbs) of thrust for a combined total liftoff thrust of more than 2.1 million pounds.

Atlas V 500

United Launch Alliance’s Atlas V is a heavy-lift launch vehicle and is the latest evolution of this legendary family. Atlas V uses a standard common core booster, up to five solid rocket boosters (SRBs), a Centaur upper stage in a single- or dual-engine configuration, and one of several sizes of payload fairings. This launch vehicle, in an Atlas V 531 configuration, has a 5-meter (18 ft.) diameter payload fairing, three solid rocket boosters, and stands at 63 meters (206 ft.) tall. At liftoff, the launch vehicle will weigh 1.08 million lbs and the thrust will be 1.76 million lbs. The Atlas V 531 first launched on Aug. 14, 2010 and has launched three times to date.

Main Engine

Delivering more than 860,000 pounds of thrust at liftoff and an impressive range of continuous throttling capability, the RD-180 main engine uses liquid oxygen/ liquid kerosene, a two-thrust-chamber, hydraulics for control valve actuation and thrust vector gimbaling, pneumatics for valve actuation and system purging, and a thrust frame to distribute loads.

Upper Stage

RL10 engines harness the power of high-energy liquid hydrogen. The RL10 boasts a precision control system and restart capability to accurately place payloads into orbit. The Atlas V Centaur upper stage is powered by the RL10C and can be configured with either one or two engines.

Solid Rocket Boosters

When missions demand additional thrust at liftoff, Atlas integrates up to five SRBs on the Atlas V 500 series vehicles.

GEM 63

NROL-101 will be the first ULA launch vehicle flying the new Graphite Epoxy Motors (GEM) 63 that burn solid propellant and augment the lifting capacity of rocket’s first stage. ULA will be transitioning from Aerojet Rocketdyne AJ60-A Solid Rocket Boosters to the Northrop Grumman GEMs throughout 2021.

United Launch Alliance

With more than a century of combined heritage, ULA has successfully delivered 140 missions to orbit that aid meteorologists in tracking severe weather, unlock the mysteries of our solar system, provide critical capabilities for troops in the field, deliver cutting-edge commercial services and enable GPS navigation.

Atlas III B

Otherwise identical to the Atlas IIIA, the Atlas IIIB improved performance by employing a two-engine Centaur upper stage, as opposed to a one-engine Centaur upper stage employed on the Atlas IIIA. The two-engine Centaur, featuring two RL-10A engines, could produce a thrust of 41,592 pounds, roughly double the thrust of a single RL-10A engine. In the new configuration, the Atlas IIIB was capable of carrying a 23,630-pound payload to Low-Earth Orbit or a 9,900-pound payload to Geosynchronous Transfer Orbit.

Lockheed-Martin

Lockheed Martin's Space Division started in the production of missiles and later ICBM's in the 1950s. Their TITAN missile system was used for 12 Gemini spacecraft and the Voyager probes. They have worked largely in collaboration with NASA on many of their probes, landers, and spacecraft, and hope to play a key role in NASA's return to the moon in 2024.

Titan IV B

After 19 Titan IV launches from Cape Canaveral and 7 Titan IV launches from Vandenberg Air Force Base, California, an improved version called the Titan IVB was introduced in early 1997. The Titan IVB increased payload capability by 25 percent over previous Titan IV rockets, which were subsequently renamed Titan IVA. Although nearly identical to the Titan IVA in other respects, the Titan IVB introduced upgraded solid rocket motors manufactured by Alliant Techsystems, a company which had just recently purchased booster designer Hercules Aerospace Products. Each three-segment solid rocket motor upgrade (SRMU) was 112.4 feet tall by 10.5 feet wide. The solid rocket motors, which burned HTPB solid propellant, could each produce a thrust of 1,700,000 pounds. First stage thrust of the Titan IVB was improved to 547,100 pounds. Upgraded electronics and guidance, standard vehicle interfaces and new Programmable Aerospace Ground Equipment (PAGE) also enhanced Titan IVB performance over the Titan IVA.

Like the Titan IVA, the Titan IVB could employ a Centaur upper stage, an Inertial Upper Stage (IUS) or no upper stage. With the introduction of the SRMU, specific vehicle payload capacity was improved as follows:

• Version 401: Maximum 12,700 pounds
• Version 402: Maximum 47,000 pounds
• Version 403: Maximum 38,800 pounds
• Version 404: Maximum 36,700 pounds
• Version 405: Maximum 49,000 pounds

The first Titan IVB was launched from Cape Canaveral Launch Complex 40 on February 23, 1997 and carried a Defense Support Program (DSP) missile detection satellite for the Department of Defense. This maiden flight of the Titan IVB marked the first time a Cape-launched military Titan mission was declassified. In a change from previous policy, both the nature of the payload and the launch time were made public prior to launch.

Lockheed-Martin

Lockheed Martin's Space Division started in the production of missiles and later ICBM's in the 1950s. Their TITAN missile system was used for 12 Gemini spacecraft and the Voyager probes. They have worked largely in collaboration with NASA on many of their probes, landers, and spacecraft, and hope to play a key role in NASA's return to the moon in 2024.

Delta II 7920 10c

The Industry Workhorse

The Delta II program has a rich history. Over 29 years, the rocket launched 155 times with 100 consecutive successful missions, culminating in the final ICESat-2 flight for NASA.

Delta II has launched many memorable missions including NASA’s rovers Spirit and Opportunity, the Phoenix Mars Lander, all operational GPS missions through the constellation of 21 GPS II-R missions for the Air Force, and commercial missions for Iridium, Globalstar and three DigitalGlobe satellites. This tremendous achievement is a tribute to the dedicated ULA employees and supplier teammates that ensure mission success is the focus of each and every launch.

Payload Fairing

The Delta II launch vehicle offers the user a choice of three fairings: a 2.9-m (9.5-ft)-diameter skin-and-stringer center section fairing (bisector), and two versions of a 3-m (10-ft)-diameter (bisector) composite fairing with two different lengths. Each of these fairings can be used on either two-stage or three-stage missions. The stretched-length 3.0-m (10-ft) composite fairing, designated 10L, offers more payload volume. The stretched 3-m (10-ft)-diameter composite fairing has a reshaped nose cone and a cylindrical section 0.91 m (3 ft) longer than the standard 3-m (10-ft) version.

Main Engine

A pillar of the American aerospace industry for more than four decades, the RS-27A is second to none in its class featuring a mature engine design and demonstrated manufacturing processes. The RS-27A is a single-start, fixed thrust liquid bi-propellant gas generator cycle main engine and two vernier engines. In addition to providing vehicle roll control during flight, the vernier engines each contribute more than 1,000 pounds of thrust to the main engine.

Graphite Epoxy Motors (GEMs)

The Delta II 792X vehicle configuration includes nine Orbital ATK solid rocket GEMs to augment first-stage performance. Six GEMs are ignited at liftoff; the remaining three GEMs, with extended nozzles, are ignited in flight after burnout of the first six. Ordnance for the motor ignition and separation systems is fully redundant.

Upper Stages

The second stage is powered by the flight-proven Aerojet AJ10-118K engine. The simple, reliable start and restart operation requires only the actuation of a bipropellant valve to release the pressure-fed hypergolic propellants, with no need for a turbopump or an ignition system. Typical two- and three-stage missions use two second-stage starts, but the restart capability has been used as many as six times on a single mission, for a total of seven burns. During powered flight, the second-stage hydraulic system gimbals the engine for pitch and yaw control. A redundant attitude control system (RACS) using nitrogen gas provides roll control. The RACS also provides pitch, yaw and roll control during unpowered flight. The guidance system is installed in the forward section of the second stage.

Depending on payload requirements, the Delta II series of launch vehicles offers an optional spin-stabilized third-stage motor. The flight-proven long nozzle Star 48B motor is produced by Alliant Techsystems and uses a high-energy, solid propellant and high-strength titanium cases featuring forward and aft mounting flanges and multiple tabs for attaching external hardware. The submerged nozzle uses a carbon-phenolic exit cone and a 3D carbon-carbon throat. A spin table, containing small rockets, mounts the third stage to the second stage and is used to spin up the third stage prior to separation. The third-stage payload attach fitting mates the third stage with the spacecraft.

United Launch Alliance

With more than a century of combined heritage, ULA has successfully delivered 140 missions to orbit that aid meteorologists in tracking severe weather, unlock the mysteries of our solar system, provide critical capabilities for troops in the field, deliver cutting-edge commercial services and enable GPS navigation.

Minotaur IV

Minotaur IV has four stages; the first three stages utilize government-furnished solid rocket motors from decommissioned Peacekeeper ICBMs. The commercial solid rocket upper stage is an Orion 38. Minotaur IV is capable of launching payloads up to 1,730 kg (3,814 lb.) to low Earth orbit; Minotaur IV made its maiden flight on 22 April 2010.

Northrop Grumman

Northrop Grumman Minotaur rockets have completed missions out of every major U.S. spaceport. Under the U.S. Air Force Orbital/ Suborbital Program-3 (OSP-3) contract, Northrop Grumman integrates, tests and provides space launch services for the Minotaur family of rockets. The OSP-3 contract is managed by the Rocket Systems Launch Program, which is part of U.S. Space Force Space Systems Command (SSC). OSP-3 expands on OSP-2 by continuing to use excess ICBM motors, and includes potential Evolved Expendable Launch Vehicle new entrant launch vehicles. The OSP-3 contract is managed by the Rocket Systems Launch Program, which is part of U.S. Space Force and Missile Systems Center (SMC). OSP-3 expands on OSP-2 by continuing to use excess ICBM motors, and includes potential Evolved Expendable Launch Vehicle new entrant launch vehicles. The OSP-3 contract allows for an indefinite delivery, indefinite quantity with a $900M ceiling based on a firm fixed price service contract strategy.

Minotaur I

Minotaur I is a four-stage solid fuel space launch vehicle utilizing Minuteman rocket motors for its first and second stages, reusing motors that have been decommissioned as a result of arms reduction treaties. The Stage 3 and 4 motors are the Orion 50XL and Orion 38, respectively. Minotaur I is capable of launching payloads up to 580 kg (1,278 lbs) into low Earth Orbit. To date, Minotaur I has conducted 11 missions with a 100% success rate, delivering 62 satellites into orbit.

Northrop Grumman

Northrop Grumman Minotaur rockets have completed missions out of every major U.S. spaceport. Under the U.S. Space Force Orbital/Suborbital Program-3 (OSP-3) contract, Northrop Grumman integrates, tests and provides space launch services for the Minotaur I, IV, V, and VI family of rockets. The OSP-3 contract is managed by the Launch Enterprise Small Launch and Targets Division, which is part of U.S. Space Force’s Space and Missile Systems Center (SMC).

Electron

Electron is a two-stage rocket designed and manufactured by Rocket Lab for dedicated access to space of small satellites. The Electron has conducted nearly 40 launches, deploying more than 160 satellites into orbit.

Rutherford Engine(s)

Proven performance. The world’s first 3D-printed, electric-pump-fed rocket engine.

First Stage

• 9 Sea-level Rutherford Engines
• Lift-off Thrust: 190 kN (43,000 lbf)
• Peak Thrust: 224 kN (56,000 lbf)
• ISP: 311 seconds

Interstage

Pneumatic Pusher

Second Stage

• Single Vacuum Rutherford Engine
• Total Thrust: 25.8 kN (5,800 lbf)
• ISP: 343 seconds

Kick Stage

Electron’s unique Kick Stage is designed to deliver small satellites to precise and unique orbits, whether flying as dedicated or rideshare.

• Deployment of payloads at multiple planes/inclinations
• Higher altitude deployment
• Hosted payload support
• Multiple trajectory changes
• Sustained low altitude orbits
• Deorbiting payloads to eliminate space debris