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A nuclear thermal rocket (NTR) is a type of thermal rocket where the heat from a nuclear reaction replaces the chemical energy of the propellants in a chemical rocket. In an NTR, a working fluid , usually liquid hydrogen , is heated to a high temperature in a nuclear reactor and then expands through a rocket nozzle to create thrust .
Nuclear thermal rockets can provide great performance advantages compared to chemical propulsion systems. Nuclear power sources could also be used to provide the spacecraft with electrical power for operations and scientific instrumentation. [12] Examples: NERVA (Nuclear Energy for Rocket Vehicle Applications), a US nuclear thermal rocket program
A pulsed nuclear thermal rocket is a type of nuclear thermal rocket (NTR) concept developed at the Polytechnic University of Catalonia, Spain, and presented at the 2016 AIAA/SAE/ASEE Propulsion Conference for thrust and specific impulse (I sp) amplification in a conventional nuclear thermal rocket. [1] The pulsed nuclear thermal rocket is a ...
The thermal energy source is a laser, which heats a working fluid in a heat exchanger. The working fluid is then expanded through a nozzle to produce thrust. Depending on the laser power, a laser thermal rocket can have a thrust-to-weight ratio similar to chemical rockets, while achieving a specific impulse similar to nuclear thermal rockets. [7]
The fission-fragment rocket is a rocket engine design that directly harnesses hot nuclear fission products for thrust, as opposed to using a separate fluid as working mass. The design can, in theory, produce very high specific impulse while still being well within the abilities of current technologies.
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Examples of concepts that use nuclear power for space propulsion systems include the nuclear electric rocket (nuclear powered ion thruster(s)), the radioisotope rocket, and radioisotope electric propulsion (REP). [6] One of the more explored concepts is the nuclear thermal rocket, which was ground tested in the NERVA program.
RD-0410 (РД-0410, GRAU index: 11B91) was a Soviet nuclear thermal rocket engine developed by the Chemical Automatics Design Bureau [1] in Voronezh from 1965 through the 1980s using liquid hydrogen propellant. [2] The engine was ground-tested at the Semipalatinsk Test Site, [3] and its use was incorporated in the Kurchatov Mars 1994 crewed ...