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One of the distinguishing characteristics of an HCCI engine is that the ignition is controlled by the chemical kinetics, unlike the diesel or spark ignition engines, for which ignition time can be controlled externally by the fuel injection or spark time.
In this paper, based on the periodic up and down cruising mode a controller design method for a hypersonic aircraft is addressed to achieve further voyage with fixed fuel by solving for ignition time of combined engine, throttle opening and the elevator deflection angle.
The Mach 3.0 APT spaceplane has a T/W of 0.8 at rocket engine ignition.
The Mach 5.5 APT has a T/W of 0.6 at rocket engine ignition.
Keyless entry and keyless engine ignition are also included.
Ignition timing, in a spark ignition engine, is the process of setting the time that an ignition will occur in the combustion chamber (during the compression stroke) relative to piston position and crankshaft angular velocity.
The aim of this paper was effects of ignition timing of a spark- ignition engine using different initial timing and engine speeds on engine performance by experimental.
For example, electronic circuits determine the optimum fuel/air mixture, ignition sequence and valve timing on a modern engine 6,000 times a minute.
Also, temperature pressure trajectories and ignition delay time maps are used to explore relationships between engine operational parameters and HCCI.
There was also significant difference between the ignition delay times from open cup tests and those from rocket engine static firings.
The use of plant oils as fuels in the compression ignition engine is as old as the engine itself (Knothe 2001).
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