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Hybrid rocket propulsion system conceptual overview. In its simplest form, a hybrid rocket consists of a pressure vessel (tank) containing the liquid oxidizer, the combustion chamber containing the solid propellant, and a mechanical device separating the two. When thrust is desired, a suitable ignition source is introduced in the combustion ...
A 1963 paper by Myron Levoy proposed a hybrid nuclear-electric engine design, which would have been able to work both in open-cycle mode as a nuclear thermal engine during mission phases requiring high thrust, as well as in closed-cycle mode as a nuclear-electric engine with low thrust, but high efficiency during remaining mission phases.
Electric thrusters typically use much less propellant than chemical rockets because they have a higher exhaust speed (operate at a higher specific impulse) than chemical rockets. [1] 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]
All launch vehicle propulsion systems employed to date have been chemical rockets falling into one of three main categories: Solid-propellant rockets or solid-fuel rockets have a motor that uses solid propellants, typically a mix of powdered fuel and oxidizer held together by a polymer binder and molded into the shape of a hollow cylinder. The ...
Solid rockets use propellant in the solid phase, liquid fuel rockets use propellant in the liquid phase, gas fuel rockets use propellant in the gas phase, and hybrid rockets use a combination of solid and liquid or gaseous propellants. In the case of solid rocket motors, the fuel and oxidizer are combined when the motor is cast.
If all goes to plan, Virginia will be the site of the world’s first grid-scale nuclear fusion power plant, able to harness this futuristic clean power and generate electricity from it by the ...
This page is an incomplete list of orbital rocket engine data and ... Propellant Power cycle Specific impulse (s) [a] Thrust (N ... ABL Space Systems: RS1: Active
For instance, if limited onboard power fed to its engine was the dominant limitation on how much payload a hypothetical spacecraft could shuttle (such as if intrinsic propellant economic cost was minor from usage of extraterrestrial soil or ice), ideal exhaust velocity would rather be around 62.75% of total mission delta v if operating at ...