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The company stated in 2019 that the planned full operational payload capacity of the two-stage version of New Glenn would be 13,000 kg (29,000 lb) to GTO and 45,000 kg (99,000 lb) to a 51.6° inclined LEO, [5] though the initial operating capability could be somewhat lower. [61]
Payload Payload Mass Orbit Customer Launch outcome Booster landing 1 16 January 2025 07:03 [1] GS1-SN001 So You're Telling Me There's a Chance [2] Cape Canaveral, LC-36: Blue Ring: Unknown MEO: Blue Origin: Success Failure Maiden/demonstration flight of New Glenn, carrying a prototype Blue Ring spacecraft.
New Glenn is roughly twice as powerful as Falcon 9, the world's most active rocket, with a payload bay diameter two times larger to fit bigger batches of satellites. Blue Origin has not disclosed ...
A heavy-lift launch vehicle (HLV) is an orbital launch vehicle capable of lifting payloads between 20,000 to 50,000 kg (44,000 to 110,000 lb) (by NASA classification) or between 20,000 to 100,000 kilograms (44,000 to 220,000 lb) (by Russian classification) [1] into low Earth orbit (LEO). [2]
Blue Origin is to lead the development of the lander, which is designed to fit in the 7 m (23 ft) payload fairing of the New Glenn launch vehicle in order to launch aboard the rocket. [8] [19] Astrobotic is to provide a cargo accommodation system for Blue Moon, to be used for large payloads such as surface habitats or lunar rovers. [20]
Maximum payload mass (kg) Reusable / Expendable Orbital launches including failures [a] Suborbital test flights Launch site(s) Dates of flight LEO GTO Other First Latest Starship Block 1 [140] United States: SpaceX: 121 m 40,000 – 50,000 [141] N/A N/A Reusable: 0 6 Starbase: 2023 2024 Angara A5 / Orion Russia: Khrunichev: 54.9 m N/A 6,500 ...
Category A payloads fit within a 4 m diameter payload envelope, category B payloads fit within a 5 m diameter payload envelope, and category C payloads require an extended 5 m diameter envelope. The USAF and United States Space Force (USSF) plan to use the next generation NSSL launch vehicles until at least 2030.
Engine Origin Designer Vehicle Status Use Propellant Power cycle Specific impulse (s) [a] Thrust (N) [a] Chamber pressure (bar) Mass (kg) Thrust: weight ratio [b] Oxidiser: fuel ratio