| MAIN PROPULSION COMPONENTS | ||
Every second of a large liquid fueled rocket’s operation requires that hundreds of gallons of propellant be pumped into the combustion chamber. By controlling the rate of the liquid propellant flow into the chamber, thrust control is achieved. Once burned, the fuel’s exhaust gasses are directed outward by the nozzle. Just as in the solid rocket, the nozzle serves to further increase the efficiency of the engine. Terminating the thrust on a liquid rocket is also easily accomplished by simply shutting the propellant flow valves. This operation however, must be precisely timed and controlled. Any uneven or erratic fuel flow could quickly result in uncontrolled flight and loss of the vehicle. |
|
|
| 37 of 39 | ||