scispace - formally typeset
Search or ask a question
Topic

Burn rate (chemistry)

About: Burn rate (chemistry) is a research topic. Over the lifetime, 847 publications have been published within this topic receiving 8908 citations. The topic is also known as: Burning rate.


Papers
More filters
01 Nov 2006
TL;DR: In this paper, the detailed chemical kinetics and burn rate prediction of tri-aminoguanidinium azotetrazolate (TAGzT) and nitrocellulose (NC) were reported.
Abstract: : Advanced, burn-rate, propellant modeling is critical for developing new rocket missile and gun propellants for Future Combat Systems and for providing a fundamental screening tool that can result in substantial cost savings compared to missile and gun firings. In this paper, we report the detailed chemical kinetics and burn rate prediction of tri-aminoguanidinium azotetrazolate (TAGzT) and nitrocellulose (NC).

2 citations

Proceedings ArticleDOI
24 Jul 2013
TL;DR: In this paper, a polymer citrate precursor method (a combustion process) was developed (in this laboratory) for large scale synthesis of nano-Fe2O3 from starting material iron nitrate.
Abstract: Nano iron oxide (α-Fe2O3) exhibits better performance as a burn rate catalyst in composite rocket propellant. A polymer citrate precursor method (a combustion process) was developed (in this laboratory) for large scale synthesis of nanoα-Fe2O3 from starting material iron nitrate. The synthesized nanoα-Fe2O3 wascharacterized for bulk density, powder XRD, BET surface area and HRTEM. Two redox titration methods viz. permanganate and iodometricwere discussed for chemical analysis (assay) of samples. Preliminary study indicates that use of nanoFe2O3in composite propellant formulations resulted in ~ 50% improvement in burn rate.

2 citations

Proceedings ArticleDOI
15 May 2012
TL;DR: In this article, a numerical model of the radiation has been employed by a Monte Carlo method and statistical physics to simulate the process of a capillary plasma source for Electrothermal-Chemical (ETC) Launcher.
Abstract: A numerical model of the radiation has been employed by a Monte Carlo method and statistical physics to simulate the process of a capillary plasma source for Electrothermal-Chemical (ETC) Launcher. The effect on propellants with different physical parameters is discussed. The plasma-propellant interaction is also discussed when combined with a thermal model. Results show that radiant energy only causes a small field around the plasma injector in the propellant bed. The responses of energy flux and propellant particles on radiation are both in the order of picosecond. The strong instantaneous radiation is responsible for the transmission of energy to the propellant particles leading to ignition. Compared with conventional ignition, the energy absorbed by propellant particles is used to increase quickly the temperature in the surface layer of propellant particles. This energy skin effect in the propellant particle surface appears to be the main cause of plasma ignition.

2 citations

Patent
21 May 1987
TL;DR: In this article, a power unit for a vehicle using a solid propellant fuel material which is burned within a combustion chamber is provided with an outlet port, including an adjustable valve arranged for controlling the rate of gas flow through said port, in which the valve (4) is a fluid flow valve capable of effecting control of the gas flow in the abscence of a mechanically movable valve member.
Abstract: In a power unit for a vehicle using a solid propellant fuel material which is burned within a combustion chamber (1), the chamber is provided with an outlet port (3) including an adjustable valve (4) arranged for controlling the rate of gas flow through said port, in which the valve (4) is a fluid flow valve capable of effecting control of the gas flow in the abscence of a mechanically movable valve member. The valve (4) may be a fluidic vortex valve the flow through which is adjustable by controlling flow of a control fluid into the valve. This arrangement permits a build-up of gas pressure within the chamber (1) in order to increase the fuel burn rate at times when a high power output is demanded.

2 citations

01 Dec 1971
TL;DR: In this paper, a study was conducted to develop a solid-propellant rocket igniter system that would build up thrust at a controlled rate of less than 0.2 G/sec.
Abstract: A study was conducted to develop a solid-propellant rocket igniter system that would build up thrust at a controlled rate of less than 0.2 G/sec. The system consisted of a long burning, regressive burning, controlled flow igniter and an inhibited progressive burning surface in the main rocket motor. The igniter performed the dual role of igniting, under vacuum backpressure and low L* (motor free volume/nozzle throat area ratio) conditions, the nonrestricted portion of the propellant and providing the mass addition necessary to sustain combustion until the propellant burning area had increased sufficiently to provide a stable motor-chamber pressure. Two series of tests were conducted with existing small test motor hardware to: (1) demonstrate the feasibility of the concept, (2) determine the important parameters governing the system, and (3) obtain design guidelines for future scaled-up motor tests. A quasi-steady-state mass balance for the ignition system was written and programmed for use as a motor design tool.

2 citations


Network Information
Related Topics (5)
Combustion
172.3K papers, 1.9M citations
86% related
Internal combustion engine
130.5K papers, 1M citations
72% related
Heat transfer
181.7K papers, 2.9M citations
71% related
Reynolds number
68.4K papers, 1.6M citations
71% related
Laminar flow
56K papers, 1.2M citations
70% related
Performance
Metrics
No. of papers in the topic in previous years
YearPapers
202310
202220
202116
202015
201918
201811