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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 ...
The fuselage is cigar-shaped, with an overall diameter of about 1.52 m (5 ft 0 in). The main structure is of a graphite/epoxy composite material. From front to back, it contains the crew cabin, oxidizer tank, fuel casing, and rocket nozzle. The craft has short, wide wings, with a span of 5 m (16 ft) and a chord of 3 m (9.8 ft). Large vertical ...
RocketMotorTwo is a hybrid rocket engine utilizing solid hydroxyl-terminated polybutadiene (HTPB) fuel and liquid nitrous oxide oxidizer – sometimes referred to as an N 2 O/HTPB motor [8] [9] – providing 70,000 pounds-force (310 kN) of thrust. [10] The design makes use of lessons learned during the development of the SpaceShipOne hybrid ...
The expanding nozzle addresses this to a degree by including two skirts on a single engine, one inside the other. The first skirt, attached directly to the combustion chamber, is designed for use at lower altitudes and is short and squat. The second, sitting outside the first, fits over the lower altitude bell to extend it into a longer and ...
[5]: 5 Vane length (whether it extends partially up the vessel or to the top) is partially determined by the shape of the tank. Cylindrical tanks require full-length vanes since a portion of the propellant could adhere to the forward tank head. Spherical tanks need full-length vanes in a case by case basis.
The core stage comprises five major sections: the engine section, the liquid hydrogen (LH 2) tank, the intertank, the liquid oxygen (LO x) tank, and the forward skirt.These elements can be further divided into ten barrel sections, four domes, and seven rings, together forming the structure of the rocket stage.
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Cutaway of Space Shuttle external tank. Autogenous pressurization is the use of self-generated gaseous propellant to pressurize liquid propellant in rockets.Traditional liquid-propellant rockets have been most often pressurized with other gases, such as helium, which necessitates carrying the pressurant tanks along with the plumbing and control system to use it.