Journal of Propulsion Technology 

About: Journal of Propulsion Technology is an academic journal. The journal publishes majorly in the area(s): Combustion & Nozzle. Over the lifetime, 753 publications have been published receiving 1423 citations.

Analysis of thermophysical properties of Daqing RP-3 aviation kerosene

Abstract: To investigate the thermophysical properties of endothermic hydrocarbon fuels,the method of fuel surrogate and principle of the extended corresponding states(ECS) were reviewed brieflyA three-species surrogate consisting in mole of 49% n-decane,44% 1,3,5-trimethylcyclohexane,and 7% n-propyl-benzene was selected to simulate the thermophysical and transport properties of Daqing RP-3 aviation keroseneA new method has been proposed to predict the mass flow rates of a supercritical fluid through a sonic nozzleAgreement was obtained when comparing the calculated flow rates with measurements

Experimental investigation of kerosene fuel combustion in the supersonic flow

Abstract: For the dual-mode scramjet it is important to conduct experimental research for its combustor In order to get the performance parameters of the dual-mode combustor model at the different flight Mach, the investigation of liquid fuel kerosene was carried out in the combustor direct-connect wind tunnel In the non-cold state cases, fuel kerosene realized ignition and stable combustion, the normal shock wave series appeared in the isolator and these operating processes were the typical ramjet modes With one-dimensional analysis method, the flow field parameters, the total pressure loss coefficient and combustion efficiency were estimated in terms of the measured wall static pressure data At the combustor outlet, the total pressure loss coefficients of the non-cold state cases were 0565, 0696 and 0725, respectively and consistent with the experimental measurement values The combustion efficiencies were 082, 067 and 060, respectively With the data and parameters of the dual-mode combustor, its performance could be improved

Effect of nano metal powder on the thermal decomposition characteristics of HMX

Abstract: The thermal decomposition characteristics of HMX influenced by the addition of aluminum,nickel,copper with different particle size(general and nano)were studied by PDSC and TG The result shows that the nano copper have the greatest influence on the properties of condensed phase decomposition of HMX among the metal powders Such catalysis effect of nano copper will be weakened by the decrease of the content of naon copper or the increase of the system pressure Based on the kinetics result inferred from the isothermal DSC data,this catalysis mechanics are described to the efficacy of first catalysis,secondary catalysis and reaction site effect of nano copper on HMX

Numerical simulation of synthetic jet flow field and parameter analysis of actuator

Abstract: Modeling a computing model for synthetic jet actuator, X-L Model, it considers the actuator cavity, the exit throat, and the external flow field as a single computational region Numerical computations are performed for different cases With a view of providing references for designing a robust synthetic jet actuator, the effect of forcing factors and actuator geometric parameters on the synthetic jet is analyzed, using a priori given velocity profile at the actuator exit A parameter correlation function of the actuator is presented to express the correlation between the synthetic jet maximal velocity and the actuator parameters

Aeroengine direct thrust control based on neural network inverse control

Abstract: Dynamic neural network inverse control is applied to aeroengine direct thrust control for the first timeFor avoiding steady state error caused by construction error of neural network inverse model,which can not be exactly the same as inverse model of aeroengine,an integral compensator which parallelly connects with above neural network inverse model is designedDynamic neural network inverse controller is obtainedAn aeroengine thrust estimator is designed with neural network for overcoming a difficult problem that aeroengine thrust can not be measured accurately by sensorDigital simulation results show that this control scheme has good dynamic and steady state performance, high precision and fast tracking ability