 | This article needs additional citations for verification .(March 2009) |
This article contains the lift launch systems constructed by some solid fuel stages except the final stage.
| | This article needs additional citations for verification .(March 2009) |
This article contains the lift launch systems constructed by some solid fuel stages except the final stage.
| Vehicle | Stage number | Origin | Manufacturer | Height (meter) | Diameter (meter) | Weight (ton) | Mass to LEO (kg) | Mass to Other Orbit (kg) | Maiden flight | Retired | Record | Status |
|---|---|---|---|---|---|---|---|---|---|---|---|---|
| ASLV | 5 |  India | ISRO | 24 | 1 | 41 | 150 | 1987 | 1994 | 2/4 | Retired | |
| Epsilon (without PBS) | 3 |  Japan | IHI AeroSpace | 24.4 | 2.6 | 90.8 | 2016 | - | 1/1 | Active | ||
| J-I | 2(+1) | Japan | NASDA / ISAS | 33.1 | 1.8 | 88.5 | 1000 | 1996 | 1996 | 1/1* | Retired | |
| Kaituozhe-1 | 4 |  China | CASIC | 13.6 | 1.4 | SSO: 50 | 2002 | ? | 0/2 | ? | ||
| Kaituozhe-2 | China | CASIC | 2017 | 1/1 | Active | |||||||
| Kuaizhou-11 | 4 | China | CASIC | ? | 2.2 | 78 | 1500 | SSO: 1000@700 km | 2017 | - | - | Development |
| L-4S | 4 | Japan | Tokyo univ. | 16.5 | 0.735 | 9.4 | 26 | 1966 | 1970 [1] | 1/5 | Retired | |
| Minotaur I | 4 |  United States | Orbital Sciences | 19.2 | 1.67 | 36.2 | 580 | SSO: 331 | 2000 | - | 11/11 | Active |
| Minotaur IV Lite | 3 | United States | Orbital Sciences | 23.88[ citation needed ] | 2.34[ citation needed ] | 86.3[ citation needed ] | - | 2010 | - | 2/2* | Active | |
| Minotaur IV | 4 | United States | Orbital Sciences | 23.88 [2] | 2.34[ citation needed ] | 86.3[ citation needed ] | 1735[ citation needed ] | 2010 | - | 1/1 | Active | |
| Minotaur IV+ | 4 | United States | Orbital Sciences | 23.88 | 2.34 | 86.3 | 1985 | 2011 | 1/1 | Active | ||
| Minotaur IV/Orion 38 | 4 | United States | Orbital Sciences | 2017 | - | 1/1 | Active | |||||
| Minotaur V | 5 | United States | Orbital Sciences | 1.67 | GTO:640 TLI:447 | 2013 [3] | - | 1/1 | Active | |||
| M-3C | 3 | Japan | Tokyo univ. | 20.2 | 1.41 | 41.8 | 195 | 1974 | 1979 | 3/4 | Retired | |
| M-3H | 3 | Japan | Tokyo univ. | 23.8 | 1.41 | 48.7 | 300 | 1977 | 1978 | 3/3 | Retired | |
| M-3S | 3 | Japan | Tokyo univ. | 23.8 | 1.41 | 48.7 | 300 | 1980 | 1984 | 4/4 | Retired | |
| M-3SII | 3(+1) | Japan | ISAS | 27.8 | 1.41 | 61 | 770 | 1985 | 1995 | 7/8 | Retired | |
| M-4S | 4 | Japan | Tokyo univ. | 23.6 | 1.41 | 43.6 | 180 | 1970 | 1972 | 3/4 | Retired | |
| M-V | 3(+1) | Japan | ISAS | 30.8 | 2.5 | 140 | 1850 | Interplanetary: 500 | 1997 | 2006 | 6/7 | Retired |
| Pegasus | 3 | United States | Orbital Sciences | 16.9 | 1.27 | 18.5 | 375 | 1990 | 10/11 | ? | ||
| Pegasus XL | 3 | United States | Orbital Sciences | 17.6 | 1.27 | 23.13 | 443 | 1994 | - | 29/32 | Active | |
| Qaem 100 | 3 |  Iran | IRGC | 80 | 2022 | - | 2/3 | Active | ||||
| Scout | 4 [4] | United States | NACA | 23 | 1.01 | 21.5 | 1961 | 1994 | Retired | |||
| Scout-A | 4 | United States | NACA | 25 | 1.01 | 17.85 | 1965 | 1970 [5] | Retired | |||
| Shavit | 3 |  Israel | IAI | 15.3[ citation needed ] | 1.352[ citation needed ] | 23.2[ citation needed ] | 160[ citation needed ] | 1988 | 1990 | 2/2 | Retired | |
| Shavit1 (LK-A) | 3 | Israel | IAI | 17.2 | 1.352 | 27.3 | 240 | 1995 | 2004 | 2/4 | Retired | |
| Shavit2 (LK-1) | 3 | Israel | IAI | 19.5[ citation needed ] | 1.352[ citation needed ] | 31.2[ citation needed ] | 350[ citation needed ] | 2007 | - | 4/4 | Active | |
| SLV | 4 | India | ISRO | 22 | 1 | 17 | 40 | 1979 | 1983 | 3/4 | Retired | |
| RPS-420 | 4 |  Indonesia | LAPAN | 9.5 | 0.42 | 50 | (2014) | - | 0/0 | Development | ||
| SPARK (Super Strypi) | 3 | United States | Hawaii, Sandia, Aerojet Rocketdyne | SSO: 250 | 2015 | - | 0/1 | Active | ||||
| SS-520(3-stage) | 3 | Japan | ISAS/JAXA | 9.54 | 0.52 | 2.6 | 4 | - | 2017 | - | 1/2 | Active |
| Start-1 | 4 |  Russia | MIT | 22.7 | 1.61 | 47.2 | 532 | SSO: 167 | 1993 | - | 6/6 | Active |
| Taiwan SLV | 4 |  Republic of China | NSPO | 50 | - | - | 0/0 | Development | ||||
| Taurus | 3+1 | United States | Orbital Sciences | 27 | 2.35 | 69 | 1259 | SSO: 889 | 1994 | - | 5/6 | ? |
| Taurus XL Minotaur-C | 3+1 | United States | Orbital Sciences | 32 | 2.35 | 77 | 1458 | SSO: 1054 | 2004 | - | 2/4 | Active |
| VLS-1 | 4 |  Brazil | AEB, DCTA-IAE, Avibrás | 19.5[ citation needed ] | 1.01[ citation needed ] | 50.7[ citation needed ] | 380 [6] | 1997 | 2016 | 0/3 | Retired | |
| VLM-1 | 3 | Brazil/ Germany | AEB, DCTA-IAE, Avibrás, DLR | 19.6 | 1.45 | 28 | 30 | - | 2025 | - | 0/0 | Development |
| Vehicle | Main stages | Origin | Manufacturer | Height (meter) | Diameter (meter) | Weight (ton) | Mass to... (kg) | Maiden flight | Retired | Record | Status | ||
|---|---|---|---|---|---|---|---|---|---|---|---|---|---|
| Solid | Liquid | LEO | Other orbit | ||||||||||
| Ares I | 1 | 1 | United States | Alliant Techsystems / Boeing | 94 | 5.5 | 25000 | (2015) | 0/0 | Cancelled | |||
| Athena I | 2 | 1 | United States | Lockheed Martin | 1995 | 2001 | 3/4 | Retired | |||||
| Athena Ic | 2 | 1 | United States | Lockheed Martin Alliant Techsystems | (2012) | 0/0 | Development | ||||||
| Athena II [7] | 3 | 1 | United States | Lockheed Martin | 30.5 | 2.36 | 120.2 | 1896 | 1998 | 1999 | 2/3 | Retired | |
| Athena IIc | 3 | 1 | United States | Lockheed Martin Alliant Techsystems | (2012) | 0/0 | Development | ||||||
| Epsilon PBS | 3 | 1 | Japan | IHI AeroSpace | 24.4 | 2.6 | 90.8 | 2013 | - | 3/4 | Active | ||
| Hyperbola-1 | 3 | 1 | China | i-Space | 20 | 31 | 300 | 2019 | - | 1/1 | Active | ||
| Kuaizhou-1 | 3 | 1 | China | CASIC | 18 | 1.4 | 32 | ~300 | SSO: 430@500 km | 2013 | - | 1/1 | Active |
| Kuaizhou-1A | 3 | 1 | China | CASIC | 1.4 | 30 | ~300 | SSO: 200@700 km | 2014 | - | 2/2 | Active | |
| Long March 11 | 3 | 1 | China | 2015 | - | 7/7 | Active | ||||||
| Minotaur IV HAPS | United States | Orbital Sciences | 23.88 | 2.34 | 86.3 | 2010 | - | 1/1 | Active | ||||
| Vega | 3 | 1 |  European Union | ESA / ISA | 30 | 3 | 137 | 2000(?) | SSO: 1500 | 2012 | 2024 | 20/22 | Retired |
| Vega-C | 3 | 1 | European Union | ESA / ISA | 35 | 3.4 | 2022 | - | 1/2 | Active | |||
| Zuljanah | 2 | 1 | Iran | MODAFL | 25.5 | 1.5 | 52 | 220 | - | 0/0 | Development | ||
Human spaceflight programs have been conducted, started, or planned by multiple countries and companies. Until the 21st century, human spaceflight programs were sponsored exclusively by governments, through either the military or civilian space agencies. With the launch of the privately funded SpaceShipOne in 2004, a new category of human spaceflight programs – commercial human spaceflight – arrived. By the end of 2022, three countries and one private company (SpaceX) had successfully launched humans to Earth orbit, and two private companies had launched humans on a suborbital trajectory.
Pegasus is an air-launched multistage rocket developed by Orbital Sciences Corporation (OSC) and later built and launched by Northrop Grumman. Pegasus is the world's first privately developed orbital launch vehicle. Capable of carrying small payloads of up to 443 kg (977 lb) into low Earth orbit, Pegasus first flew in 1990 and remained active as of 2021. The vehicle consists of three solid propellant stages and an optional monopropellant fourth stage. Pegasus is released from its carrier aircraft at approximately 12,000 m (39,000 ft) using a first stage wing and a tail to provide lift and altitude control while in the atmosphere. The first stage does not have a thrust vector control (TVC) system.
Orbital Sciences Corporation was an American company specializing in the design, manufacture, and launch of small- and medium- class space and launch vehicle systems for commercial, military and other government customers. In 2014, Orbital merged with Alliant Techsystems (ATK) to create a new company called Orbital ATK, which in turn was purchased by Northrop Grumman in 2018.
A launch vehicle is typically a rocket-powered vehicle designed to carry a payload from Earth's surface or lower atmosphere to outer space. The most common form is the ballistic missile-shaped multistage rocket, but the term is more general and also encompasses vehicles like the Space Shuttle. Most launch vehicles operate from a launch pad, supported by a launch control center and systems such as vehicle assembly and fueling. Launch vehicles are engineered with advanced aerodynamics and technologies, which contribute to high operating costs.
Minotaur-C, formerly known as Taurus or Taurus XL, is a four stage solid fueled launch vehicle built in the United States by Orbital Sciences and launched from SLC-576E at California's Vandenberg Air Force Base. It is based on the air-launched Pegasus rocket from the same manufacturer, utilizing a "zeroth stage" in place of an airplane. The Minotaur-C is able to carry a maximum payload of around 1458 kg into a low Earth orbit (LEO).
The Minotaur is a family of United States solid-fuel launch vehicles repurposed from retired Minuteman and Peacekeeper model intercontinental ballistic missiles. Built by Northrop Grumman under the Space Force's Rocket Systems Launch Program, these vehicles are used for various space and test launch missions.
The following outline is provided as an overview of and topical guide to space exploration.
The Minotaur I, or just Minotaur is an American expendable launch system derived from the Minuteman II missile. It is used to launch small satellites for the US Government, and is a member of the Minotaur family of rockets produced by Orbital Sciences Corporation.
The Star 48 is the largest of a family of solid rocket motors used by many space propulsion and launch vehicle stages, almost exclusively as an upper stage. It was developed primarily by Thiokol Propulsion and after several mergers, is manufactured by Northrop Grumman’s Space Systems division. A Star 48B stage is also one of the few man-made items sent on escape trajectories out of the Solar System, although it is derelict since its use. The Star 48B variant was the PAM-D upper stage used on the retired Delta II rocket.
Antares, known during early development as Taurus II, is an American expendable medium-lift launch vehicle developed and built by Orbital Sciences Corporation with financial support from NASA under the Commercial Orbital Transportation Services (COTS) program awarded in February 2008, alongside the company's automated cargo spacecraft, Cygnus. Like other launch vehicles developed by Orbital, Antares leveraged lower-cost, off-the-shelf parts and designs.
This comparison of orbital launch systems lists the attributes of all current and future individual rocket configurations designed to reach orbit. A first list contains rockets that are operational or have attempted an orbital flight attempt as of 2024; a second list includes all upcoming rockets. For the simple list of all conventional launcher families, see: Comparison of orbital launchers families. For the list of predominantly solid-fueled orbital launch systems, see: Comparison of solid-fueled orbital launch systems.
Cygnus is an expendable American automated cargo spacecraft designed for International Space Station (ISS) resupply missions. Initially developed by Orbital Sciences Corporation with financial support from NASA under the Commercial Orbital Transportation Services (COTS) program. To create Cygnus, Orbital paired a pressurized cargo module, largely based on the Multi-Purpose Logistics Module, built by Thales Alenia Space and previously used by the Space Shuttle for ISS resupply, with a service module based on Orbital's GEOStar, a satellite bus. After a successful demonstration flight in 2013, Orbital was chosen to receive a Commercial Resupply Services (CRS) contract. A larger Enhanced Cygnus was introduced in 2015. Orbital Sciences was renamed Orbital ATK in 2015 and Northrop Grumman purchased Orbital in 2018 and has continued to operate Cygnus missions. A further enlarged Mission B Cygnus is expected to be introduced in 2025.
The Operationally Responsive Space Office is a joint initiative of the United States Department of Defense (DoD). The "stand up" of the office took place 21 May 2007 at Kirtland Air Force Base. The first director of the ORS Office was Col. Kevin McLaughlin, who was also the commander of the Space Development and Test Wing located at Kirtland. The ORS Office focuses on providing quick-response tactical space-based capabilities; utilizing smaller satellites, such as the Tactical Satellite Program and smaller launch vehicles.
Minotaur IV, also known as Peacekeeper SLV and OSP-2 PK is an active expendable launch system derived from the LGM-118 Peacekeeper ICBM. It is operated by Northrop Grumman Space Systems, and made its maiden flight on 22 April 2010, carrying the HTV-2a Hypersonic Test Vehicle. The first orbital launch occurred on 26 September 2010 with the SBSS satellite for the United States Air Force.
The Space Launch Complex 46 (SLC-46), previously Launch Complex 46 (LC-46), is a launch complex at Cape Canaveral Space Force Station operated under license by Space Florida previously used for Athena rocket launches. It has been used by Astra, which will continue the use with Rocket 4 and maybe 5 and will be used by ABL Space Systems for the near-term use by RS1.
Minotaur V is an American expendable launch system derived from the Minotaur IV, itself a derivative of the LGM-118 Peacekeeper, an intercontinental ballistic missile. It was developed by Orbital Sciences Corporation, and made its maiden, and to date, only flight on 7 September 2013 carrying the LADEE spacecraft for NASA. While Minotaur V is still likely active and available to fly, no further flights are scheduled as of May 2024.
Orbital ATK Inc. was an American aerospace manufacturer and defense industry company. It was formed in February 9, 2015 from the merger of Orbital Sciences Corporation and parts of Alliant Techsystems (ATK). Orbital ATK designed, built, and delivered rocket engines, military vehicles, firearms, autocannons, missiles, ammunition, precision-guided munitions, satellites, missile approach warning systems, launch vehicles and spacecraft. The company was acquired by Northrop Grumman on June 6, 2018. The former Orbital ATK operations were renamed Northrop Grumman Innovation Systems and operated as a division until January 1, 2020 when a reorganization merged the operations into the company's other divisions.
A small-lift launch vehicle is a rocket orbital launch vehicle that is capable of lifting 2,000 kilograms (4,400 lb) or less or under 5,000 kilograms (11,000 lb) of payload into low Earth orbit (LEO). The next larger category consists of medium-lift launch vehicles.
