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Due to limited electric power the thrust is much weaker compared to chemical rockets, but electric propulsion can provide thrust for a longer time. [2] Electric propulsion was first demonstrated in the 1960s and is now a mature and widely used technology on spacecraft. American and Russian satellites have used electric propulsion for decades. [3]
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.
The Distributed Space Systems Laboratory (DSSL) is focused on dynamics and control of multiple spacecraft formation flying. The experimental facility is designed and equipped to test methods and machinery under circumstances as close to actual operating conditions as possible, including cooperative control, relative position and attitude sensing and space-borne sparse-aperture imaging.
On Tuesday, Nov. 5, Rocket Lab (NASDAQ: RKLB) launched its 12th rocket of the year, using a two-stage Electron launch vehicle to put a mysterious payload for a secret (commercial) customer into ...
In chronological order, spacecraft are listed equipped with electric space propulsion. This includes both cruise engines and/or thrusters for attitude and orbit control. It is not specified whether the given engine is the sole means of propulsion or whether other types of engine are also used on a spacecraft.
It was Rocket Lab's first mission failure in over two years. Rocket Lab on Friday said it had launched its Electron rocket into space from a facility in New Zealand, the SpaceX rival's first ...
Meanwhile, Rocket Lab, which has already established itself as a thriving launch company with its Electron rocket, has signed its first customer for its larger Neutron launch vehicle. The customer ...
The electric-pump-fed engine is a bipropellant rocket engine in which the fuel pumps are electrically powered, and so all of the input propellant is directly burned in the main combustion chamber, and none is diverted to drive the pumps. This differs from traditional rocket engine designs, in which the pumps are driven by a portion of the input ...