A thrust transducer for a pulse detonation engine

Abstract

The invention discloses a thrust converting device of a pulse detonation engine, comprising an aircraft mount, a spring cavity, a linear viscous damper, an engine mount, a parallel spring and a seriesspring; the thrust converting device comprises an aircraft mount, a spring cavity, a linear viscous damper, an engine mount, a parallel spring and a series spring. The thrust conversion device is connected with the aircraft and the pulse detonation engine through an aircraft mount and an engine mount. The linear viscous damper is designed as a symmetrical double-output rod clearance damper, so that the damping property thereof does not change with the change of the motion direction, and is convenient to control. Adopting the structure design of two springs mounted side by side not only improves its ability to isolate high frequency, periodic, pulse-type and large peak-to-peak thrust, but also reduces the axial displacement of the engine. Pulse detonation engine produces periodic, pulsed,large peak-to-peak thrust transfer to the engine mount, through the spring storage energy, damper energy consumption, and ultimately converted into a small fluctuation of the quasi-steady force, through the mount transfer to the aircraft.

Description

Technical field [0001] The invention belongs to the field of pulse detonation engines, and specifically relates to a thrust converter of a pulse detonation engine. Background technique [0002] Pulse detonation engine is a new concept aircraft engine that uses high temperature and high pressure gas generated by intermittent detonation waves to generate thrust. Detonation waves can be roughly considered to be composed of supersonic shock waves and tightly coupled thin flames or reaction zones. Due to the extremely high gas pressure (greater than 15 to 55 atmospheres), the gas temperature (greater than 2800K) and the extremely fast propagation speed (Mach number greater than 4) of the detonation wave, it is very attractive to the propulsion system. The detonation process is thermodynamically closer to the constant volume cycle than the isobaric combustion of the ordinary deflagration-based propulsion system, so it has a higher thermodynamic efficiency. In addition, pulse detonati...

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Problems solved by technology

But this can bring new problem again: 1. the upper limit of frequency is limited by factors such as detonation tube actual size, valve switch, reactant supply speed, control program reaction time and reactant detonation rate, can not improve without limit; 2. .Increasing the knocking frequency will reduce the stable working range of the engine; 3. High-frequency and large-scale impact will make the material very easy to fatigue, greatly reduce the working life, and increase the probability of accidents

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