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Since at least in the early 20th century, single-stage-to-orbit reusable launch vehicles have existed in science fiction. In the 1970s, the first reusable launch vehicle, the Space Shuttle, was developed. However, in the 1990s, due to the program's failure to meet expectations, reusable launch vehicle concepts were reduced to prototype testing.
The Reusable Launch Vehicle Landing Experiment or RLV-LEX was the second test flight in the RLV Technology Demonstration Programme following the Hypersonic Flight Experiment. The demonstration trials will pave the way for the two-stage-to-orbit (TSTO) fully reusable launch vehicle.
Reusable launch vehicle, the general concept of Reusable launch vehicles (to space) Reusable Launch Vehicle program (NASA), a cancelled NASA program that included the X33 experimental craft; RLV-TD, India's Reusable Launch Vehicle - Technology Demonstrator project; Relevium Technologies Inc, Stock Symbol: RLV; Restrained Life Viewer for Second Life
RLV TD: GSLV derived ascent vehicle for RLV ORE campaign. [5] [6] [7] Launch Vehicle Mark III (LVM-3) LVM 3 – Operational; Human-rated LVM 3 – Under development; LVM 3 with semi-cryogenic engine – Under development; Small Satellite Launch Vehicle (SSLV) – Operational; Nano Satellite Launch Vehicle (NSLV) – Under development
The Next Generation Launch Vehicle (NGLV) is a three-stage partially reusable Heavy-lift launch vehicle, currently under development by the Indian Space Research Organisation (ISRO). This vehicle is designed to replace currently operational systems like PSLV, GSLV and LVM3. The project was previously referred to as Unified Launch Vehicle (ULV ...
The proposed reusable launch vehicles were to be used for the inexpensive delivery of satellite payloads into orbit as early as 2015. [2] A prototype of Hopper, known as ( EADS ) Phoenix , was a German-led European project which involved the construction and testing of a one-seventh scale model of the proposed Hopper.
The RS-83 was developed by Rocketdyne Propulsion and Power in Canoga Park, California to power the launch vehicle as part of the Space Launch Initiative program. This engine was designed to produce a thrust of 664,000 lbf (2,950 kN) at sea level and 750,000 lbf (3,300 kN) in a vacuum with an I sp of 395 and 446 seconds (3.87 and 4.37 kN·s/kg ...
Reusable launch systems (3 C, 27 P) Reusable spacecraft (7 C, 26 P) ... Reusable launch vehicle; RLV Technology Demonstration Programme; S. Space Shuttle;