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The closer the position is to the top of the fuel grain, the higher the O/F ratio.
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In addition to the O/F varying as a function of time, it also varies based on the position down the fuel grain. The increased fuel mass flow rate can be compensated for by also increasing the oxidizer mass flow rate. This phenomenon makes the oxidizer to fuel ratio (O/F) shift during the burn. Īs the motor burns, the increase in diameter of the fuel port results in an increased fuel mass flow rate. The theoretical specific impulse ( I s p is the regression rate, a o is the regression rate coefficient (incorporating the grain length), G o is the oxidizer mass flux rate, and n is the regression rate exponent. Like liquid rocket engines, hybrid rocket motors can be shut down easily and the thrust is throttleable. The Titan, Delta, and Space Shuttle launch vehicles use strap-on solid propellant rockets to provide added thrust at liftoff. Because it is difficult for the fuel and oxidizer to be mixed intimately (being different states of matter), hybrid rockets tend to fail more benignly than liquids or solids. Hybrid rockets avoid some of the disadvantages of solid rockets like the dangers of propellant handling, while also avoiding some disadvantages of liquid rockets like their mechanical complexity.
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The hybrid rocket concept can be traced back to the early 1930s. Hybrid rocket motor detail of SpaceShipOneĪ hybrid-propellant rocket is a rocket with a rocket motor that uses rocket propellants in two different phases: one solid and the other either gas or liquid.