Ignition Characteristics of GH2/GOx Mixture Using Laser Ablation Ignition
Copyright policy )Ignition Characteristics of GH2/GOx Mixture Using Laser Ablation Ignition
The characteristics of a laser ablation igniter were investigated systematically. This kind of igniter is expected to realize a lightweight rocket engine system that consists of many combustion chambers, such as the Reaction Control System (RCS), without having heavy spark igniters. In this igniter, ignition is accomplished utilizing a high-temperature metal vapor produced by focusing a high-intensity laser pulse transmitted through an optical fiber. The laser ablation igniter was tested in a GH2/GOx thruster (dia. 1 cm). As a result, the minimum ignition energy was found to be lower than 2 mJ, and the required ignition energy decreased with increasing pressure in the combustion chamber.
- University of Tokyo Japan
- National Aerospace Laboratories India
- Netherlands Aerospace Centre Netherlands
- National Institute for Aerospace Technology Spain
- Mitsubishi Heavy Industries (Germany) Germany
Laser, Propulsion, Ablation, Ignition, Ignition, Laser
Laser, Propulsion, Ablation, Ignition, Ignition, Laser
selected citations These citations are derived from selected sources.This is an alternative to the "Influence" indicator, which also reflects the overall/total impact of an article in the research community at large, based on the underlying citation network (diachronically).8 popularity This indicator reflects the "current" impact/attention (the "hype") of an article in the research community at large, based on the underlying citation network.Average influence This indicator reflects the overall/total impact of an article in the research community at large, based on the underlying citation network (diachronically).Top 10% impulse This indicator reflects the initial momentum of an article directly after its publication, based on the underlying citation network.Average
Citations provided by BIP!Popularity provided by BIP!