Analysis of Laser-Generated Impulse In An Airbreathing Pulsed Detonation Engine: Part 1

Richard, Jacques; Myrabo, Leik N.

doi:10.1063/1.1925149

Cited by 3 publications

(1 citation statement)

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“…The parabolic afterbody acts as both a primary receptive optic for the incident laser beam, and an expansion nozzle for the heated exhaust flow. Current research into lightcraft inlet designs is somewhat limited, with the typical configurations being similar to that of the Lightcraft Technology Demonstrator concept [3]. This research aims to investigate and extend the work on hypersonic lightcraft inlets to provide a stable and efficient platform for the pulsed laser detonation engine.…”

Section: Introductionmentioning

confidence: 99%

Hypersonic Inlet for a Laser Powered Propulsion System

Harrland¹,

Doolan²,

Wheatley³

et al. 2011

AIP Conference Proceedings

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Abstract. Propulsion within the lightcraft concept is produced via laser induced detonation of an incoming hypersonic air stream. This process requires suitable engine configurations that offer good performance over all flight speeds and angles of attack to ensure the required thrust is maintained. Stream traced hypersonic inlets have demonstrated the required performance in conventional hydrocarbon fuelled scramjet engines, and has been applied to the laser powered lightcraft vehicle. This paper will outline the current methodology employed in the inlet design, with a particular focus on the performance of the lightcraft inlet at angles of attack. Fully threedimensional turbulent computational fluid dynamics simulations have been performed on a variety of inlet configurations. The performance of the lightcraft inlets have been evaluated at differing angles of attack. An idealized laser detonation simulation has also been performed to validate that the lightcraft inlet does not unstart during the laser powered propulsion cycle.

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Section: Introductionmentioning

confidence: 99%