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Fuel and oxidizer are injected into the channel, normally through small holes or slits. A detonation is initiated in the fuel/oxidizer mixture by some form of igniter. After the engine is started, the detonations are self-sustaining. One detonation ignites the fuel/oxidizer mixture, which releases the energy necessary to sustain the detonation.
Above this speed, given sufficient initial flight velocity, a ramjet is self-sustaining. Unless the vehicle drag is extremely high, the engine/airframe combination tends to accelerate to higher and higher flight speeds, substantially increasing the air intake temperature. As this could damage the engine and/or airframe integrity, the fuel ...
As the piston approaches the TDC the combustible mixture is self-ignited due to the compression of it. Then, the deflagration to the detonation transition occurs in the detonation tube 9. The output of detonation products from the tube 9 happens in a short period of time, when the piston is near the TDC. Then, the process is repeated.
The Humphrey cycle is the thermodynamic cycle occurring detonation engines such as rotating detonation engines, the pulse detonation engines, and pulse compression detonation systems. It may be considered to be a modification of the Brayton cycle in which the constant-pressure heat addition process of the Brayton cycle is replaced by a constant ...
A pulse detonation engine (PDE) is a type of propulsion system that uses detonation waves to combust the fuel and oxidizer mixture. [ 1 ] [ 2 ] The engine is pulsed because the mixture must be renewed in the combustion chamber between each detonation wave and the next.
The Fickett–Jacobs (FJ) cycle is based on Chapman–Jouguet (CJ) theory, an approximation for the detonation wave's velocity during a detonation. [ 1 ] [ 2 ] This cycle is researched for rotating detonation engines (RDE), considered to be more efficient than the classical combustion engines that are based on the Brayton or Humphrey cycles .
The engine has three intake stages, which are sized according to the sound created by the combustion process when running. This has exactly the same effect as the turbine and compressor in a turbojet, creating a vacuum that sucks in air. The intakes, along with the exhaust, are sonically tuned so that the locations of the pressure antinodes of ...
David Chapman [3] and Émile Jouguet [4] originally (c. 1900) stated the condition for an infinitesimally thin detonation. A physical interpretation of the condition is usually based on the later modelling (c. 1943) by Yakov Borisovich Zel'dovich, [5] John von Neumann, [6] and Werner Döring [7] (the so-called ZND detonation model).
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