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Rutherford is a liquid-propellant rocket engine designed by aerospace company Rocket Lab [8] and manufactured in Long Beach, California. [9] The engine is used on the company's own rocket, Electron. It uses LOX (liquid oxygen) and RP-1 (refined kerosene) as its propellants and is the first flight-ready engine to use the electric-pump-fed cycle.
This page is an incomplete list of orbital rocket engine data and specifications. Current, upcoming, and in-development rocket engines. Engine ... Rutherford New ...
Its Rutherford engines are the first electric-pump-fed engine to power an orbital-class rocket. [17] Electron is often flown with a kickstage or Rocket Lab's Photon spacecraft. Although the rocket was designed to be expendable, Rocket Lab has recovered the first stage twice and is working towards the capability of reusing the booster. [18]
The F-1 engine is the most powerful single-nozzle liquid-fueled rocket engine ever flown. The M-1 rocket engine was designed to have more thrust, but it was only tested at the component level. The later developed RD-170 is much more stable, technologically more advanced , more efficient and produces more thrust, but uses four nozzles fed by a ...
The largest vendors of high-power rocket motors in the world are Cesaroni Technology Inc. and RCS Rocket Motor Components, Inc. The very first model rocket motor certified was by Model Missiles Inc. (Orville Carslile). Circa 1958. The very first high-power rocket motor certified was by U.S. Rockets (Jerry Irvine). Circa 1985.
The TR-201 or TR201 is a hypergolic pressure-fed rocket engine used to propel the upper stage of the Delta rocket, referred to as Delta-P, from 1972 to 1988. The rocket engine uses Aerozine 50 as fuel, and N 2 O 4 as oxidizer. It was developed in the early 1970s by TRW as a derivative of the lunar module descent engine (LMDE).
It would use practically every single component of the RD-8, but arranged without the big hollow section in the middle. It was a proposed engine for a proposed liquid upper stage of the Antares rocket, then named Taurus II. [3] It would be capable of five engine burns in a single mission. [11] RD-809K: A proposed single nozzle version of the RD-8.
The RD-0162 rocket engine was developed at the Voronezh KBKhA after 2006, initially with an engine version aimed at 2,000 kN (200 tf) thrust, and later, after 2012, a smaller version with a thrust of 416 kN (42.4 tf) in the RD-0162SD version. Engine development funding was included in the Russian Federal Space Program for 2016–2025.