An expendable launch system (or expendable launch vehicle/ELV ) is a launch vehicle that can be launched only once, after which its components are either destroyed during reentry or discarded in space. ELVs typically consist of several rocket stages that are discarded sequentially as their fuel is exhausted and the vehicle gains altitude and speed. As of 2024, fewer and fewer satellites and human spacecraft are launched on ELVs in favor of reusable launch vehicles . However, there are many instances where a ELV may still have a compelling use case over a reusable vehicle. ELVs are simpler in design than reusable launch systems and therefore may have a lower production cost. Furthermore, an ELV can use its entire fuel supply to accelerate its payload, offering greater payloads. ELVs are proven technology in widespread use for many decades.
35-748: 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 Minotaur IV vehicle consists of four stages and
70-522: A core diameter of 1.25 m, with two liquid propellant stages, a single thrust chambered first stage and a two-thrust chambered, step-throttled second stage, the SLV has a lift off mass exceeding 26 tons. The first stage consists of a lengthened up-rated Shahab-3C . According to the technical documentation presented in the annual meeting of the United Nations Office for Outer Space Affairs , it is
105-462: A two-stage rocket with all liquid propellant engines. The first stage is capable of carrying the payload to the maximum altitude of 68 kilometres. The Israel Space Agency is one of only seven countries that both build their own satellites and launch their own launchers. The Shavit is a space launch vehicle capable of sending payload into low Earth orbit . The Shavit launcher has been used to send every Ofeq satellite to date. The development of
140-507: Is a French company founded in March 1980 as the world's first commercial launch service provider . It operates two launch vehicles : Vega C , a small-lift rocket , and Ariane 6 , a medium -to- heavy-lift rocket. Arianespace is a subsidiary of ArianeGroup , a joint venture between Airbus and Safran . European space launches are carried out as a collaborative effort between private companies and government agencies. The role of Arianespace
175-663: Is a launch vehicle that improved reliability while reducing costs by making significant improvements to the H-II, and the M-V was the world's largest solid-fuel launch vehicle at the time. In November 2003, JAXA's first launch after its inauguration, H-IIA No. 6, failed, but all other H-IIA launches were successful, and as of February 2024, the H-IIA had successfully launched 47 of its 48 launches. JAXA plans to end H-IIA operations with H-IIA Flight No. 50 and retire it by March 2025. JAXA operated
210-632: Is also an ELV customer, having designed the Titan, Atlas, and Delta families. The Atlas V from the 1994 Evolved ELV (EELV) program remains in active service, operated by the United Launch Alliance . The National Security Space Launch (NSSL) competition has selected two EELV successors, the expendable Vulcan Centaur and partially reusable Falcon 9 , to provide assured access to space. Iran has developed an expendable satellite launch vehicle named Safir SLV . Measuring 22 m in height with
245-568: Is available for suborbital trajectories. The Minotaur IV has also been flown with multiple upper stages. A five-stage derivative, the Minotaur V , made its maiden flight on 7 September 2013. Minotaur IV launches are conducted from SLC-8 at Vandenberg Space Force Base , LP-0B at the Mid-Atlantic Regional Spaceport , SLC-46 at Cape Canaveral Space Force Station and Pacific Spaceport Complex – Alaska Pad 1 of
280-545: Is capable of placing 1,591 kilograms (3,508 lb) of payload into a low Earth orbit (LEO). It uses the first three stages of the Peacekeeper missile, combined with a new upper stage. On the baseline version, the fourth stage is an Orion 38 . However a higher performance variant, designated Minotaur IV+ , uses a Star 48BV instead. A three-stage configuration (no Orion 38), designated the Minotaur IV Lite ,
315-550: Is composed of four stages. The first stage SR118 motor provides 2,224 kilonewtons (500,000 lb f ) of thrust during its 56.6-second burn, followed immediately after by stage separation and second-stage ignition. The second stage, powered by an SR119 motor, burns for 61 seconds and provides an average thrust of 1,223 kilonewtons (275,000 lb f ). The third stage then burns for 72 seconds, with an average thrust of 289 kilonewtons (65,000 lb f ). The initial three stages all have thrust vector control , allowing them to steer
350-585: Is intended for suborbital launches, such as testing prototype hypersonic vehicles. The separate Minotaur V is also available, consisting of a Minotaur IV+ with an added fifth stage for high-energy trajectories such as geostationary transfer orbit or trans-lunar injection . The Minotaur IV family is derived from the LGM-118 Peacekeeper intercontinental ballistic missile (ICBM), deployed from 1985 until 2005. The Minotaur IV family utilizes decommissioned Peacekeeper solid rocket motors, which compose
385-547: Is intended for suborbital missions, allowing government customers to test new technologies like hypersonic aircraft or missile interception. As of May 2024, the Minotaur IV Lite has only flown twice, both times in support of the HTV-2 program. This variant is almost identical to the unflown Minotaur III rocket, which was also intended to perform suborbital missions. LEO LEO The third Minotaur IV launch, which
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#1732793330994420-487: Is needed, or the rocket needs to be able to manoeuvre to deploy multiple payloads. It can place up to 580 kilograms (1,280 lb) of payload into a 185-kilometer (115 mi) low Earth orbit at 28.5 degrees of inclination . The Minotaur I is 69 feet tall and 5 feet wide. Initially Minotaur I launches are conducted from Space Launch Complex 8 at the Vandenberg Air Force Base . Starting with
455-684: Is the follow-on to the Orbital Sciences' Taurus (later renamed the "Minotaur-C" ) launch vehicle, combining the original Taurus's booster stage with a second stage from a Minuteman missile . Minotaur I rockets consist of the M55A1 first stage and SR19 second stage of a decommissioned Minuteman missile. The Orion 50XL and Orion 38 , from the Pegasus rocket, are used as third and fourth stages. A HAPS (Hydrazine Auxiliary Propulsion System) upper stage can also be flown if greater precision
490-694: Is to market Ariane 6 launch services, prepare missions, and manage customer relations. At the Guiana Space Centre (CSG) in French Guiana , the company oversees the team responsible for integrating and preparing launch vehicles. The rockets themselves are designed and manufactured by other companies: ArianeGroup for the Ariane 6 and Avio for the Vega. The launch infrastructure at the CSG is owned by
525-539: Is uncommon for Star 48 motors. The Star 48 motor has also seen use on the Atlas V , Delta IV , and Space Shuttle , alongside over 70 missions on the Delta II . Minotaur IV+ was further evolved to create the Minotaur V rocket, which adds an extra Star 37FM stage to the vehicle for improved high-energy performance. This configuration has only flown once as of 2024 and is not scheduled for any further launches. In addition,
560-563: Is very experienced in development, assembling, testing and operating system for use in space. Minotaur I 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 (now Northrop Grumman ). The Minotaur I
595-631: The European Space Agency , while the land itself belongs to and is managed by CNES , the French national space agency. During the 1960s and 1970s, India initiated its own launch vehicle program in alignment with its geopolitical and economic considerations. In the 1960s–1970s, the country India started with a sounding rocket in the 1960s and 1970s and advanced its research to deliver the Satellite Launch Vehicle-3 and
630-813: The H-IIB , an upgraded version of the H-IIA, from September 2009 to May 2020 and successfully launched the H-II Transfer Vehicle six times. This cargo spacecraft was responsible for resupplying the Kibo Japanese Experiment Module on the International Space Station . To be able to launch smaller mission on JAXA developed a new solid-fueled rocket, the Epsilon as a replacement to the retired M-V . The maiden flight successfully happened in 2013. So far,
665-587: The Kodiak Launch Complex . The launch facility contractor was Alaska Aerospace Corporation (AAC). The payloads were released in a 650 kilometres (400 mi) orbit, before the HAPS upper stage was demonstrated by deploying two ballast payloads into a 1,200 kilometres (750 mi) orbit. The primary objective of the STP-S26 launch was to deploy STPSAT-2 (USA-287), whilst demonstrating the ability of
700-477: The Pacific Spaceport Complex – Alaska (PSCA). The Minotaur IV (and the overall Minotaur rocket family) was developed by Orbital Sciences (now owned by Northrop Grumman ) as part of the United States Air Force 's Orbital Suborbital Program. There are three variants available: Minotaur IV, IV+, and IV Lite. Minotaur IV and IV+ are used for low Earth orbit missions, while Minotaur IV Lite
735-665: The Redstone missile to the Delta , Atlas , Titan and Saturn rocket families, have been expendable. As its flagship crewed exploration replacement for the partially reusable Space Shuttle , NASA's newest ELV, the Space Launch System flew successfully in November 2022 after delays of more than six years. It is planned to serve in a major role on crewed exploration programs going forward. The United States Air Force
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#1732793330994770-535: The Minotaur IV to carry additional payloads, by deploying FASTSAT , FASTRAC , RAX , O/OREOS and FalconSat-5 . A Hydrazine Auxiliary Propulsion System upper stage was flown aboard the Minotaur to demonstrate its ability to deploy payloads to multiple orbits, however only mass simulators were deployed after the HAPS burn. The launch marked the first flight of an STP-SIV (Standard Interface Vehicle) satellite,
805-584: The Shavit began in 1983 and its operational capabilities were proven on three successful launches of the Ofek satellites on September 19, 1988; April 3, 1990; and April 5, 1995. The Shavit launchers allows low-cost and high-reliability launch of micro/mini satellites to a low Earth orbit . The Shavit launcher is developed by Malam factory, one of four factories in the IAI Electronics Group. The factory
840-575: The final orbital insertion burn for the payload. Like the first three stages, the Orion 38 also features thrust vectoring, with a 5-degree range of motion. On one occasion, for the ORS-5 mission, Minotaur IV was outfitted with a second Orion 38 motor to allow the payload to be inserted into an equatorial orbit. In addition, another Minotaur IV mission featured a Hydrazine Auxiliary Propulsion System (HAPS) for additional orbital maneuvering capability. The HAPS
875-462: The first three stages in all Minotaur IV rockets and derivatives. This relatively simple architecture allows Minotaur to be launched from essentially anywhere in the US through the use of mobile launch facilities - although this capability has never been needed. Because of its use of decommissioned ICBM components, Minotaur IV can only be used to launch US government missions. The standard Minotaur IV rocket
910-603: The first use of the Multi Mission Satellite Operations Center Ground System Architecture (MMSOC GSA), the first flight of the Minotaur IV's Multi-payload Adapter (MPA), the first use of a HAPS to obtain multiple orbits on a Minotaur IV flight, the first Minotaur launch from Kodiak Launch Complex (KLC), and the first deployment of CubeSats from a Minotaur IV via Poly-PicoSatellite Orbital Deployers (P-Pods). Expendable launch system Arianespace SA
945-546: The more advanced Augmented Satellite Launch Vehicle (ASLV), complete with operational supporting infrastructure by the 1990s. Japan launched its first satellite, Ohsumi , in 1970, using ISAS' L-4S rocket. Prior to the merger, ISAS used small Mu rocket family of solid-fueled launch vehicles, while NASDA developed larger liquid-fueled launchers. In the beginning, NASDA used licensed American models. The first model of liquid-fueled launch vehicle developed domestically in Japan
980-486: The more powerful Minotaur VI and Minotaur VI+ concepts were based on the Minotaur IV+, featuring an additional SR118 motor as the first stage to improve vehicle performance. However, neither Minotaur VI variant has flown and no flights are scheduled. The Minotaur IV Lite is a suborbital configuration of Minotaur IV. It features the same first three stages as the standard variant but lacks a fourth stage. The IV Lite
1015-809: The most famous of them being the R-7 , commonly known as the Soyuz rocket that is capable of launching about 7.5 tons into low Earth orbit (LEO). The Proton rocket (or UR-500K) has a lift capacity of over 20 tons to LEO. Smaller rockets include Rokot and other Stations. Several governmental agencies of the United States purchase ELV launches. NASA is a major customer with the Commercial Resupply Services and Commercial Crew Development programs, also launching scientific spacecraft. The vast majority of launch vehicles for its missions, from
1050-468: The rocket downrange by gimballing the motor nozzles. The second and third stages also feature extendable nozzles, allowing for improved performance in the upper portions of Earth's atmosphere as well as the vacuum of space. The fourth stage of the Minotaur IV is the Orion 38 motor, which is also used in the Minotaur-C , Minotaur I , Pegasus , and Ground-Based Interceptor rockets. This motor performs
1085-468: The rocket has flown six times with one launch failure. In January 2017, JAXA attempted and failed to put a miniature satellite into orbit atop one of its SS520 series rockets. A second attempt on 2 February 2018 was successful, putting a four kilogram CubeSat into Earth orbit. The rocket, known as the SS-520-5, is the world's smallest orbital launcher. Roscosmos uses a family of several launch rockets,
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1120-469: Was also known as STP-S26, deployed eight payloads. It was the 29th small launch vehicle mission in STP's 49-year history of flying DoD space experiments, STP-S26 was intended to extend previous standard interface development efforts, implementing a number of capabilities aimed at enabling responsive access to space for small experimental satellites and payloads. STP-S96 launched at 01:25 UTC on 20 November 2019 from
1155-537: Was carried over to its successor, the H-IIA and H-IIB and became the basic configuration of Japan's liquid fuel launch vehicles for 30 years, from 1994 to 2024. In 2003, JAXA was formed by merging Japan's three space agencies to streamline Japan's space program, and JAXA took over operations of the H-IIA liquid-fueled launch vehicle, the M-V solid-fuel launch vehicle, and several observation rockets from each agency. The H-IIA
1190-721: Was developed for the Pegasus rocket to fine-tune the payload's orbit since solid motors are not capable of fine adjustments. The Minotaur IV+ is a higher-performance variant of the Minotaur IV. The first three stages are identical, but the Orion 38 fourth stage is replaced with a Star 48BV motor. The Star motor features more propellant than the Orion motor, allowing the rocket to carry roughly 200 kg (440 lb) of extra payload to low-Earth orbit, or can allow for payloads to be sent to elliptical orbits. The Star 48BV burns for 85.2 seconds with an average thrust of 68.63 kilonewtons (15,430 lb f ) and also features thrust vectoring, which
1225-619: Was the H-II , introduced in 1994. NASDA developed the H-II with two goals in mind: to be able to launch satellites using only its own technology, such as the ISAS, and to dramatically improve its launch capability over previous licensed models. To achieve these two goals, a staged combustion cycle was adopted for the first stage engine, the LE-7 . The combination of the liquid hydrogen two-stage combustion cycle first stage engine and solid rocket boosters
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