1 edition of An experimental investigation of fuel regression rate control in solid fuel ramjets found in the catalog.
An experimental investigation of fuel regression rate control in solid fuel ramjets
Bog Nam Ko
Written in English
tion)SFRJandb)solid fuel scramjet. Fig. 3 Geometry and nomenclature for the differential control volume. 1)In solid fuel scramjets as well as in SFRJs, the overall fuel-to-air ratio cannot be controlled directly because of the dependence of the fuel regression rate on the port ‘ ow char-acteristics(with major effects ofG,T,andd). A hybrid rocket is so named because one of the propellant components is liquid and the other solid. Normally the oxidizer is liquid and the fuel is solid. In a typical design (Fig. ), the oxidizer is sprayed in at the head end of a solid cylindrical fuel by: 5.
regression rate and performance as compared to conventional hybrid motor (pure PE+GO 2). Regression rate of hybrid fuel grain was enhanced by addition of Al powder. Adding up to % gives the best performance as regression rate increases by 90% and chamber pressure increases by 40% compared to basic configuration (0% Al).File Size: KB. solid fuel ramjets, was adjusted and used for the test campaigns . A side view of the whole combustion chamber set-up is shown in Fig. 4. The oxidizer main flow is entering the combustion chamber from the left, after having passed two flow straighteners. The mass flow rate is adjusted by a flow control valve and it is measured with a Coriolis.
The well-known theory developed by Marxman and colleagues [15–17] set the basis for understanding and describing fuel regression assumed that the fuel regression rate is controlled by heat transfer to the grain and applied a flux balance at the fuel surface, finding where is the fuel regression rate, is the fuel density, is the total heat flux received by the fuel grain, and is the Cited by: International Journal of Energetic Materials and Chemical Propulsion. Buy Issue $ Volume 5, Issue EXPERIMENTAL INVESTIGATION OF EROSIVE BURNING OF COMPOSITE PROPELLANTS UNDER SUPERSONIC CROSSFLOWS ANALYSIS AND TESTING OF FUEL REGRESSION RATE CONTROL IN SOLID FUEL RAMJETS Deborah Pelosi-Pinhas, Alon .
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'An experimental investigation was conducted to examine fuel regression rate control methods other than variable bypass air flow rates in the solid fuel ramjet. Air and oxygen injection at various axial locations within the fuel grain were examined as well as air.
An experimental investigation of fuel regression rate control in solid fuel ramjets. An experimental investigation of fuel regression rate control in solid fuel ramjets. by Ko, Bog Nam. Publication date TZ Topics National Security Internet Archive (NSIA).
Approved for public release; distribution is unlimitedAn experimental investigation was conducted to examine fuel regression rate control methods other than variable bypass air flow rates Author: Bog Nam Ko. Solid paraffin was patented as a high regression rate fuel for hybrid rocket and ramjet applications in the late ´s.
Since then, many research work has been conducted investigating the use of. Additives in the solid fuel may have influences on the fuel regression rate, which will affect the internal ballistics of the motor.
A series of firing experiments have been conducted on lab-scale hybrid rocket motors with 98% hydrogen peroxide (H 2 O 2) oxidizer and hydroxyl terminated polybutadiene (HTPB) based fuels in this by: Most of the experimental researches of the fuel regression rate were based on this formula. George et al.
conducted experimental investigation on the methods of enhancing the fuel regression rate in hydroxyl terminated polybutadiene (HTPB) fuel and gas- eous oxygen hybrid rocket motor .
Since the regression rate obtained by this model is only related to the properties of the local fluid near the wall, it can be applied not only to obtain the regression rate of SF-Scramjet, but also to obtain the regression rate of the hybrid rocket and the solid fuel : Hao Zhang, Ningfei Wang, Zhiwen Wu, Wanzhi Han, Rui Du.
Thedistinguishingfeaturesofthesolidfuelramjetaretheabsence offuel tankage, fuel delivery,and fuel control l is packagedentirely inthe combustor,contributingtowardssimplicity and. AD-A AN EXPERIMENTAL ON OF THE COMBUSTION I BEHAVIOR OF SOLID FUEL (U) NAVAL POSTGRADUATE SCHOOL MONTEREY CA G A BEGLET DEC 82 UNCLASSIFIEDF/U 21/2.
AIAA 2 American Institute of Aeronautics and Astronautics #ˆ = Averaged spatially and temporally s R u = Universal gas constant r = Radial coordinate (see fig. 1) r& = Instantaneous local fuel regression rate T = Temperature t b = Time (burn duration) u,v = Axial and normal velocity, respectively x, y f= Coordinate system (see fig.
1) a = Thermal diffusivityFile Size: 1MB. Experimental investigation on the effect of swirling flow on combustion characteristics and performance of solid fuel ramjet Acta Astronautica, Vol.
Investigations on the influence of swirl intensity on solid-fuel ramjet engineCited by: A comprehensive experimental investigation aimed at the examination of a solid fuel ramjet (SFRJ) regulation concept using an air-division valve was conducted.
By controlling the ratio between port and bypass flows, it is possible to maintain a desirable working state over a wide range of flight conditions. A fuel regression rate correlation versus the oxidizer mass flux is derived, presenting a major advantage for the fuel flow rate management in comparison to control of the solid propellant gas.
Experimental and computational flammability limits in a solid fuel ramjet. ELANDS, F. DIJKSTRA and B. ZANDBERGEN. Flow field characteristics of and regression rate distribution for the solid-fuel ramjet (SFRJ) with star solid fuel were investigated by numerical and experimental methods.
The experimental data were obtained by burning polyethylene using a connected-pipe facility. Experimental study of fuel regression rate in an HTPB/N2O hybrid rocket motor the solid fuel is embedded in the combustion chamber while the oxidizer, stored in a separate tank in gas or in both the fuel regression rate and the e ciency of the motor's performance.
combustion chamber of a ramjet. In this case, the evolution of the local regression rate along the wall is in good qualitative agreement with the data, but quantitative disagreement was found, mainly due to the shortcomings of the turbulence model employed.
0 Elsevier, Paris Keywords: Solid Fuel Combustion -Ramjets Multi-block. Experimental investigation and modeling of solid fuel regression rate for hybrid propulsion Italian abstract: Il lavoro qui presentato ha lo scopo di investigare la balistica di formulazioni combustibili per endoreattori ibridi a base di HTPB reagenti in ossigeno gassoso.
In this study, a series of experiments was designed to investigate the enhancement of regression rate of solid fuel by embedded metal wires and by fuel port grain.
And fuel port was designed with a helical configuration to attempt to induce swirl flow. PMMA with gaseous oxygen is the solid fuel used for by: 5.
A preliminary-sizing procedure for solid fuel ramjet powered gun launched projectile is presented. Also, presented are the ramjet-control requirements for a typical mm gun launched projectile.
The control requirements are minimal, demonstrating the "self throttling characteristics" of solid fuel ramjets. A time-resolved technique for regression rate measurement developed at SPLab was used to determine solid fuel regression rate and other ballistic parameters.
Reference solid parafﬁn wax-based tested fuel formulation (SW) was a mixture of parafﬁn with 10% (by mass) of stearic acid and 2% (by mass) of graphite.
SW fuel ballistics was compared.Regression Rate Study of PVC/HTPB Hybrid Rocket Fuels International Journal of Mechanical & Industrial Engineering, Volume-1 Issue-1, 65 isothermal pyrolysis kinetic parameter of polymeric fuels and compared to the observed rates.
The fuel regression rate in the most of hybrid rocket system is approximately mm/sec or less underFile Size: KB. Regression and combustion characteristics of boron containing fuels for solid fuel ramjets D. NETZER, A. GANY, A. KARADIMITRIS, and C. SCOTT, II Journal of Propulsion and Power,Volume 7, Number 3, Page Cited by: