A thrust converter for a pulse detonation engine

Abstract

The invention discloses a thrust conversion device of a pulse detonation engine, which includes an aircraft mount, a spring chamber, a linear viscous damper, an engine mount, parallel springs and series springs; The mounting seat is connected with the aircraft and the pulse detonation engine. The linear viscous damper is designed as a symmetrical double-rod gap damper, so that its damping property does not change as the direction of motion changes, which is convenient for control. The structural design of two springs installed side by side improves its ability to isolate the high-frequency, periodic, pulse-type, and peak-to-peak thrust of the pulse detonation engine, and reduces the axial displacement of the engine. When the pulse detonation engine is working, it generates periodic, pulsed, peak-to-peak thrust and transmits it to the engine mounting seat. The energy is stored by the spring, consumed by the damper, and finally converted into a quasi-steady-state force with small fluctuations, which is transmitted to the engine through the mounting seat. on the aircraft.

Description

technical field [0001] The invention belongs to the field of pulse detonation engines, in particular 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. The detonation wave can be approximated as consisting of a supersonic shock wave and a thin flame or reaction zone tightly coupled to it. Detonation waves are attractive to propulsion systems due to their extremely high gas pressure (greater than 15 to 55 atmospheres), gas temperature (greater than 2800K), and extremely fast propagation velocity (Mach number greater than 4). The detonation process is thermodynamically closer to an isovolumetric cycle than the isobaric combustion of ordinary detonation-based propulsion systems, and therefore has a higher thermodynamic efficiency. In addition, pulse detonation engines can operate...

AI Technical Summary

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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