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The Journal of Propulsion and Power is a bimonthly peer-reviewed scientific journal covering research on aerospace propulsion and power. The editor-in-chief is Joseph M. Powers (University of Notre Dame). It is published by the American Institute of Aeronautics and Astronautics and was established in 1985.
By 2005 progress at ASPL included full and efficient plasma production and acceleration of the plasma ions with the 50 kW, 0.5 newtons (0.1 lbf) thrust VX-50. [4] Published data on the 50 kW VX-50 showed the electrical efficiency to be 59% based on a 90% coupling efficiency and a 65% ion speed boosting efficiency.
An arcjet rocket or arcjet thruster is a form of electrically powered spacecraft propulsion, in which an electrical discharge is created in a flow of propellant [1] [2] (typically hydrazine or ammonia). This imparts additional energy to the propellant, so that one can extract more work out of each kilogram of propellant, at the expense of ...
The rapid technological advances of the U.S. rocket industry during World War II, accomplished primarily through the wartime Office of Scientific Research and Development (OSRD) and its cadre of leading scientists, produced a substantial foundation of technical reports and data on solid rockets, propellants, and ballistics.
During its six years of operational funding, this program received a total investment of $1.2 million. The Breakthrough Propulsion Physics project addressed a selection of "incremental and affordable" research questions towards the overall goal of propellantless propulsion, hyperfast travel, and breakthrough propulsion methods. [3]
The exhaust velocity of a PPT is of the order of tens of km/s while conventional chemical propulsion generates thermal velocities in the range of 2–4.5 km/s. Due to this lower thermal velocity, chemical propulsion units become exponentially less effective at higher vehicle velocities, necessitating the use of electric spacecraft propulsion ...
Deep Space 1 had 178 pounds (81 kilograms) of xenon propellant, with a total impulse capability of 2.65 x10 6 Ns [5] and was capable of increasing the speed of DS1 by 7900 miles per hour (12,700 kilometers per hour, 3.58 km/s) over the course of the mission. [3] It used 2.3 kW of electrical power and was the primary propulsion for the probe. [4]
is the standard gravity (in m/s 2 or ft/s 2). In rockets, due to atmospheric effects, the specific impulse varies with altitude, reaching a maximum in a vacuum. This is because the exhaust velocity is not simply a function of the chamber pressure, but is a function of the difference between the interior and exterior of the combustion chamber .