Publication

Ignition and Combustion Behavior in Solid Propellant Microsystems Using Joule-Effect Igniters

Nico de Rooij
2011
Journal Articles

Abstract

A study of solid propellant ignition and combustion of potassium dinitrobenzofuroxanate in Joule-heating pyrotechnical microelectromechanical systems igniters is carried out using a high-speed framing camera. The effect of igniter geometry, propellant formulation (binder content), fuel mass, and input power level on ignition delay time variability is investigated. Analytical heat transfer models of the ignition process were constructed based on the geometry of the igniters and successfully fitted to experimental ignition delay times. Complete combustion of the propellant drops was observed for fuel masses greater than 100 mu g. Flame speeds on the order of tens of centimeters per second were obtained. Two different ignition regimes were observed: a thermal ignition and a "direct ignition" regime.

Official source

https://infoscience.epfl.ch/entities/publication/f8dff745-a5b2-4dc9-aebb-64637dba1ce5

About this result

This page is automatically generated and may contain information that is not correct, complete, up-to-date, or relevant to your search query. The same applies to every other page on this website. Please make sure to verify the information with EPFL's official sources.

Graph Chat

Chat with Graph Search

Ask any question about EPFL courses, lectures, exercises, research, news, etc. or try the example questions below.

DISCLAIMER: The Graph Chatbot is not programmed to provide explicit or categorical answers to your questions. Rather, it transforms your questions into API requests that are distributed across the various IT services officially administered by EPFL. Its purpose is solely to collect and recommend relevant references to content that you can explore to help you answer your questions.

Nico de Rooij
2011
Journal Articles

Abstract

Official source

https://infoscience.epfl.ch/entities/publication/f8dff745-a5b2-4dc9-aebb-64637dba1ce5

About this result

Related concepts (32)

Rocket propellant

Rocket propellant is the reaction mass of a rocket. This reaction mass is ejected at the highest achievable velocity from a rocket engine to produce thrust. The energy required can either come from the propellants themselves, as with a chemical rocket, or from an external source, as with ion engines. Rockets create thrust by expelling mass rear-ward, at high velocity. The thrust produced can be calculated by multiplying the mass flow rate of the propellants by their exhaust velocity relative to the rocket (specific impulse).

Rocket engine

A rocket engine uses stored rocket propellants as the reaction mass for forming a high-speed propulsive jet of fluid, usually high-temperature gas. Rocket engines are reaction engines, producing thrust by ejecting mass rearward, in accordance with Newton's third law. Most rocket engines use the combustion of reactive chemicals to supply the necessary energy, but non-combusting forms such as cold gas thrusters and nuclear thermal rockets also exist. Vehicles propelled by rocket engines are commonly called rockets.

National Ignition Facility

The National Ignition Facility (NIF) is a laser-based inertial confinement fusion (ICF) research device, located at Lawrence Livermore National Laboratory in Livermore, California, United States. NIF's mission is to achieve fusion ignition with high energy gain. It achieved the first instance of scientific breakeven controlled fusion in an experiment on December 5, 2022, with an energy gain factor of 1.5. It supports nuclear weapon maintenance and design by studying the behavior of matter under the conditions found within nuclear explosions.

Related publications (1)

Ignition and Combustion Behavior in Solid Propellant Microsystems Using Joule-Effect Igniters

Chat with Graph Search

Active Model Rocket Stabilization via Cold Gas Thrusters