INCAS BULLETIN, Volume 11, Issue 2/ 2019, pp. 69 – 83 (P) ISSN 2066-8201, (E) ISSN 2247-4528 A Characterized Status Report on Pulse Detonation Engine Bharat Ankur DOGRA* , 1 , Mehakveer SINGH 1 , T. K. JINDAL 1 *Corresponding author 1 Aerospace Engineering Department, Punjab Engineering College, (Deemed to be University), Sector-12, Chandigarh, 160012- India, mechanicalerankur906@gmail.com*, mehakveersingh11@gmail.com, tkjindal@pec.ac.in DOI: 10.13111/2066-8201.2019.11.2.6 Received: 28 January 2019/ Accepted: 19 May 2019/ Published: June 2019 Copyright © 2019. Published by INCAS. This is an “open access” article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/) Abstract: Pulse Detonation Engine (PDE), is an exciting propulsion technology for the future and has been able to seek considerable attention over the last era. It has the potential to work efficiently in the modern cosmos. It works on a Humphrey cycle offering a great opportunity, which outweighs the conventional Brayton cycle. The operating cycle of PDE starts with the fuel-oxidizer mixture, combustion and DDT followed by purging. The PDE combustion process, which is a unique process, leads to consistent and repeatable detonation waves. This pulsed detonation combustion process causes rapid burning of the fuel-oxidizer mixture, which cannot be seen in any other combustion process as it is a thousand times faster than any other mode of combustion. PDE not only holds the capability of running effectively up to Mach 5 but it also changes the technicalities in space propulsion. The present study deals with the categorization of design approach, thermal analysis, performance analysis, fuel- based analysis, PDE combustors, detonation propagation, experimentation analysis, valving techniques, ignition studies, parameters & specification optimization, instrumentation, thrusters, parameters affecting specific impulse & thrust, hybrid PDE’s & turbine integration. Key Words: Pulse Detonation Engine (PDE), Deflagration to Detonation Transition (DDT), Rotating Detonation Engine (RDE), specific impulse, Shchelkin spiral, Rotating Detonation Wave Engine (RDWE). 1. INTRODUCTION With the advent of propulsion technology, a name that came into the picture was- an Air- breathing engine. These engines were sub-categorized according to the type of combustion process engaged. Now, the propulsion systems may be further indexed based on the deflagrative or detonative mode of the combustion utilized. As we go in the past, we find that the first powered flight was accomplished by Wright Brothers in late 1903, on an aircraft driven by a reciprocating internal combustion engine in the field of propulsion; the first turbojet-powered aircraft, HE178, was flown by German Hienkel Company in 1939. Since then the gas turbine engines have become the workhorse of the aircraft industries, ships, tanks & electric power plants [1]. After that, piston engines were used to power small propelled aircraft. However, helicopters and other large propeller aircraft are powered by turboshaft & turboprop engines but these two engines are limited to subsonic speed range as propeller gets