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The P-800 Oniks (Russian: П-800 Оникс; English: Onyx), marketed in export as the Yakhont (Russian: Яхонт; English: ruby), is a Soviet/Russian supersonic anti-ship cruise missile developed by NPO Mashinostroyeniya as a ramjet version of P-80 Zubr.
In 2014, NASA announced that it would proceed with development of Block 1B with the EUS [12] and would use it on Exploration Mission 2, now referred to as Artemis II. [13] In April 2016, it was reported that NASA has chosen to use a design based on four RL10 -C3 engines for the EUS, [ 6 ] and in October 2016 NASA confirmed they had ordered 10 ...
The Inertial Upper Stage (IUS), originally designated the Interim Upper Stage, was a two-stage, solid-fueled space launch system developed by Boeing for the United States Air Force beginning in 1976 [4] for raising payloads from low Earth orbit to higher orbits or interplanetary trajectories following launch aboard a Titan 34D or Titan IV rocket as its upper stage, or from the payload bay of ...
A variety of other rocket propulsion methods, such as ion thrusters, give much higher specific impulse but with much lower thrust; for example the Hall-effect thruster on the SMART-1 satellite has a specific impulse of 1,640 s (16.1 km/s) but a maximum thrust of only 68 mN (0.015 lbf). [45]
Several on-orbit demonstrations were conducted over 2.4 hours, concluding with a deorbit burn. [61] The initial demonstration was intended to prepare for more-advanced cryogenic fluid management experiments planned under the Centaur-based CRYOTE technology development program in 2012–2014, [ 62 ] and will increase the TRL of the Advanced ...
Delta II A Delta II launch vehicle launches from Cape Canaveral carrying the Dawn spacecraft. Function Launch vehicle Manufacturer United Launch Alliance Country of origin United States Cost per launch US$51 million in 1987 (7920-10 model) US$137 million in 2018 before retirement Size Height 38.9 m (128 ft) Diameter 2.44 m (8 ft 0 in) Mass 152,000–286,000 kg (335,000–631,000 lb) Stages 2 ...
The standard payload fairing of the Tianlong-3 has a diameter of 4.2 m, a height of 12 m, and can accommodate payloads with a diameter of up to 3.8 m and a height of up to 10 m. An enhanced version of the fairing, with a diameter of 5.2 m and a height of 14 m, is also available.
The operational Angara 1.2 will also use a modified Block I powered by the RD-0124A as a second stage, though this stage will have a diameter of no more than 2.9 meters. [ 3 ] The Naro-1 launch vehicle was based on the URM-1 with a reduced thrust RD-191 , called RD-151, combined with a solid-fueled second stage built by Republic of Korea KARI .