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The Sea Dragon was a 1962 conceptualized design study for a two-stage sea-launched orbital super heavy-lift launch vehicle. The project was led by Robert Truax while working at Aerojet , one of a number of designs he created that were to be launched by floating the rocket in the ocean.
Download as PDF; Printable version; ... Engine: Solid-fuel rocket engine: Operational range. R-73A, ... Sea Dragon − Ukrainian modification for use in unmanned ...
Pressure-fed rocket cycle. Propellant tanks are pressurized to directly supply fuel and oxidizer to the engine, eliminating the need for turbopumps. The pressure-fed engine is a class of rocket engine designs. A separate gas supply, usually helium, pressurizes the propellant tanks to force fuel and oxidizer to the combustion chamber. To ...
In 1966 Robert Truax founded Truax Engineering, which studied sea launch concepts similar to the earlier Sea Dragon—the Excalibur, the SEALAR, and the Excalibur S. [10] Truax also designed the Skycycle X-2 , which he unsuccessfully tested on April 15, 1972 and June 24, 1973, and which Evel Knievel unsuccessfully used at the Snake River Canyon ...
The General Dynamics Nexus was proposed in the 1960s as a fully reusable successor to the Saturn V rocket, having the capacity of transporting up to 450–910 t (990,000–2,000,000 lb) to orbit. [24] [25] See also Sea Dragon, and Douglas SASSTO. The BAC Mustard was studied starting in 1964. It would have comprised three identical spaceplanes ...
The Crew Dragon employs eight side-mounted SuperDraco engines for its emergency escape system, eliminating the need for a traditional, disposable escape tower. Furthermore, instead of housing the critical and expensive life support , thruster , and propellant storage systems in a disposable service module , Dragon 2 integrates them within the ...
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The LR87 was an American liquid-propellant rocket engine used on the first stages of Titan intercontinental ballistic missiles and launch vehicles. [1] Composed of twin motors with separate combustion chambers and turbopump machinery, [2] it is considered a single unit and was never flown as a single combustion chamber engine or designed for this.