Throughout the history of spaceflight many orbital launch systems have been proposed, designed and entered development, only to be cancelled before development was completed, without making any orbital launch attempts. Some launch systems were concept designs or studies, or proposals which were never taken further, whilst others such as the Ares I reached the stage of hardware construction and partial flight tests before cancellation.
This list contains orbital launch systems which were cancelled before making an orbital launch attempt. It includes rockets which made atmospheric and suborbital tests prior to cancellation, such as Ares I, however it does not include rockets cancelled after failed orbital launch attempts, such as the N1, Europa and Pilot.
United States. NASA design to launch Orion as part of Project Constellation, first stage to have been built by ATK, second by Boeing. Capable of placing 25.6 tonnes (25.2 long tons; 28.2 short tons) of payload into low Earth orbit. Designed by Exploration Systems Architecture Study in 2005, cancelled in 2010 along with Constellation programme United States. Proposed alternative to Ares I using the same first stage as Ares V. Capable of placing 40 tonnes (39 long tons; 44 short tons) to TLI.[1] United States. NASA design to launch Altair and Earth Departure Stage as part of Project Constellation, boosters to have been built by ATK. Capable of placing 160 to 188 tonnes (157 to 185 long tons; 176 to 207 short tons) into low Earth orbit and 63 to 71 tonnes (62 to 70 long tons; 69 to 78 short tons) to TLI. Designed by Exploration Systems Architecture Study in 2005, cancelled in 2010 along with Constellation programme United States. Proposed unified launch system for Project Constellation, combining the roles of the Ares I and Ares V into two launches of a single vehicle. Payload of 140 tonnes (140 long tons; 150 short tons) to Low Earth Orbit.[2] United States. SpaceX rocket with five first stage engines but otherwise identical to the Falcon 9. Cancelled in 2007 United States. SpaceX rocket consisting of a Falcon 9 with two Falcon 5 first stages being used as boosters. Cancelled along with Falcon 5 in 2007 United States. SpaceX concept design capable of delivering 38 tonnes (37 long tons; 42 short tons) into low Earth orbit. Heavy configuration capable of 125 tonnes (123 long tons; 138 short tons) to LEO. United States. SpaceX concept design capable of delivering 140 tonnes (140 long tons; 150 short tons) into low Earth orbit. United States. Designed in 2006 as part of the DIRECT programme, an unofficial NASA design study which proposed alternatives to the Ares family of rockets for Project Constellation (started in 2006) to replace Space Shuttle. Many variants were proposed, such as the Jupiter-130 and Jupiter-246, with claimed lift capacities exceeding 60 and 90 tonnes (59 and 89 long tons; 66 and 99 short tons) to LEO respectively; increasing to 100 tonnes (98 long tons; 110 short tons) with an upper stage, and 120 tonnes (120 long tons; 130 short tons) with five-segment solid rocket boosters as well.[2] United States. Designed by NASA between 1996 and 2004, Magnum was intended to launch a manned mission to Mars, with a payload capacity of 55 to 94 tonnes (54 to 93 long tons; 61 to 104 short tons) to Low Earth orbit, with 80 tonnes (79 long tons; 88 short tons). The rocket never made it past the preliminary design phase.
Soviet Union. Cryogenically-fuelled single-stage to orbit rocket based on the N1 first stage. Proposed in 1974, it would have had a payload capacity of 90 tonnes (89 long tons; 99 short tons) into a circular low Earth orbit at an altitude of 450 kilometres (280 mi) and an inclination of 97.5 degrees.[4] Soviet Union. A variant of the N1 studied by Sergei Korolev in 1963, the N1 Nuclear A would have used a third stage powered by a nuclear thermal engine, and been capable of placing 270 tonnes (270 long tons; 300 short tons) of payload into a circular low Earth orbit at an altitude of 220 kilometres (140 mi), and an inclination of 51.6 degrees.[5] Soviet Union. Derivative of the proposed N1 Nuclear A, which would have used less efficient engines delivering higher thrust, and could have placed 300 tonnes (300 long tons; 330 short tons) of payload into a circular low Earth orbit at an altitude of 220 kilometres (140 mi), and an inclination of 51.6 degrees.[6] Soviet Union. Derivative of the N1 rocket with nuclear-powered second and third stages, capable of placing 420 tonnes (410 long tons; 460 short tons) of payload into a circular low Earth orbit at an altitude of 220 kilometres (140 mi), and an inclination of 51.6 degrees.[7] Soviet Union. A variant of the N1 Nuclear V, the N1 Nuclear V-B would have had additional radiation shielding, allowing it to launch manned spacecraft. It could have placed 360 tonnes (350 long tons; 400 short tons) into a circular low Earth orbit at an altitude of 220 kilometres (140 mi), and an inclination of 51.6 degrees.[8] Soviet Union. An N1 derivative with upgraded engines, larger second and third stages, and incorporating changes made as a result of the four launch failures between 1969 and 1972. The 1965 design would have been capable of placing 100 tonnes (98 long tons; 110 short tons) of payload into a circular low Earth orbit at an altitude of 220 kilometres (140 mi) and an inclination of 51.6 degrees.[9] By the time development was cancelled in 1975, this had increased to 105 tonnes (103 long tons; 116 short tons).[10] Use of Blok S and Block R upper stages was also considered for launching L3M lunar missions.[11] Soviet Union. Designed in 1965 as the heaviest N1 derivative, with the payload capacity of the first stage doubled. It would have been capable of placing 155 tonnes (153 long tons; 171 short tons) into a circular low Earth orbit at an altitude of 220 kilometres (140 mi), and an inclination of 51.6 degrees,[15] subsequently redesigned a standard first stage and cryogenic upper stages to launch the LEK spacecraft on missions to the Moon. Development abandoned in 1971.[16] Soviet Union. Proposed production version of the N1 with improvements to increase reliability, particularly its engines. Capable of placing 95 tonnes (93 long tons; 105 short tons) into a circular low Earth orbit at an altitude of 220 kilometres (140 mi) and an inclination of 51.6 degrees.[19]
United States. Family of super-heavy launch systems studied by NASA for manned missions beyond Earth orbit. Some Nova-rockets, including the Nova C-8 and Nova 8L, were intended for direct ascent lunar missions, which were cancelled in favour of lunar orbit rendezvous with the Saturn V rocket. These rockets had a payload capacity of 24 to 75 tonnes (24 to 74 long tons; 26 to 83 short tons) tons to TLI, compared to the Saturn V's capacity of 45 tonnes (44 long tons; 50 short tons). Larger variants designed for missions to Mars could have placed up to 455 tonnes (448 long tons; 502 short tons) into Low Earth orbit.[21] United States. Late 1960s Saturn V derivative studied by Boeing; using four 6.6-metre (260 in) diameter solid rocket motors, which would also have incorporated liquid propellant tanks for the first stage. Capable of placing 362 tonnes (356 long tons; 399 short tons) of payload into a circular low Earth orbit at an altitude of 426 kilometres (265 mi) and an inclination of 28 degrees.[22] United States. Saturn V derivative studied in 1967 by Boeing, with stretched first and third stages, and four liquid fuelled boosters, each powered by two F-1 engines. Capable of placing 262.67 tonnes (258.52 long tons; 289.54 short tons) into a circular low Earth orbit at an altitude of 185 kilometres (115 mi) and an inclination of 28 degrees.[23] United States. Saturn V derivative studied in 1967 by Boeing, with all three stages stretched, first stage engines replaced with F-1As and second and third stage engines replaced with HG-3s. Augmented by four F-1A-powered liquid boosters. Capable of delivering 435.3 tonnes (428.4 long tons; 479.8 short tons) of payload into a circular low Earth orbit at an altitude of 185 kilometres (115 mi) and an inclination of 28 degrees.[24] United States. Saturn V derivative studied in 1967 by Boeing, with stretched first and third stages, and four 3.96-metre (156 in) solid rocket motors. Capable of placing 223.5 tonnes (220.0 long tons; 246.4 short tons) into a circular low Earth orbit at an altitude of 185 kilometres (115 mi) and an inclination of 28 degrees.[25] United States. A two-stage reusable sea-launched rocket studied in 1962, which would have been capable of placing 550 tonnes (540 long tons; 610 short tons) into LEO.[28] United States. Designed by Chrysler as their proposal for the Space Transportation System in the 1970s, SERV would have used the existing Saturn V launch complex, and could be used to launch the MURP spaceplane. It was capable of placing 11 to 57 tonnes (11 to 56 long tons; 12 to 63 short tons) into low Earth orbit, depending on the configuration, and whether MURP was being carried. United States. Proposed Shuttle-Derived Launch Vehicle which would have used then-existing Shuttle-components and infrastructure to place an unmanned payload of 60 to 80 tonnes (59 to 79 long tons; 66 to 88 short tons) into orbit. The configuration consisted of a Space Shuttle external tank and set of solid rocket boosters, but with an SSME-powered unmanned cargo vehicle in place of the orbiter. United States. Shuttle-Derived Launch Vehicle proposed as an alternative launch system for Project Constellation, capable of placing up to 104 tonnes (102 long tons; 115 short tons) of cargo into low Earth orbit. Other configurations would have been able to place 66 to 83 tonnes (65 to 82 long tons; 73 to 91 short tons) into LEO.[29][2] Soviet Union. 1950s study of a rocket incorporating a nuclear-powered second stage. Capable of placing 150 tonnes (150 long tons; 170 short tons) into low Earth orbit at an altitude of 185 kilometres (115 mi).[30] Soviet Union. Designed by Vladimir Chelomey in the 1960s, the UR-700 was based on the UR-500 rocket and designed for manned lunar missions using the direct ascent method. The N1 was developed instead, using the lunar orbit rendezvous method. UR-700 development continued until 1968 with different variants considered, with payloads between 70 and 175 tonnes (69 and 172 long tons; 77 and 193 short tons) to LEO (151 tonnes (149 long tons; 166 short tons) for the original design).[31] Using an 11D54 upper stage, it would have been able to deliver 185 tonnes (182 long tons; 204 short tons) to a circular low Earth orbit at 200 kilometres (120 mi) altitude and 51.5° inclination.[32] Using an upper stage powered by three RD-350 engines this could have been increased to 215 tonnes (212 long tons; 237 short tons) to an orbit at 200 kilometres (120 mi) and 51.0° inclination,[33] With an upper stage powered by seven RO-31 engines it could have placed 230 to 270 tonnes (230 to 270 long tons; 250 to 300 short tons) into low Earth orbit.[34] Soviet Union. Designed by Vladimir Chelomey in 1969 for Project Aelita, a Soviet programme to land a man on Mars in 1969. The design was based on the UR-700 rocket, and had a payload capacity of 750 tonnes (740 long tons; 830 short tons) to a circular low Earth orbit at 200 kilometres (120 mi) altitude and 51.0° inclination.[35] Soviet Union. Derivative of the UR-700 designed by Vladimir Chelomey, and proposed in 1969 for manned missions to Mars. Payload capacity of 240 tonnes (240 long tons; 260 short tons) to a circular low Earth orbit at 200 kilometres (120 mi) altitude and 51.0° inclination. Cancelled after a Proton launch failure raised concerns over the safety of its hypergolic propellants [36] Soviet Union. Energia derivative capable of placing 200 tonnes (200 long tons; 220 short tons) of payload into low Earth orbit.[37]
