Research On The Way Of Solid-propellant Ducted Rocket Performance Estimate And Simulation Of Missile Trajectory

The solid-propellant ducted rocket (SDR) work with high specific impulse and Mach number can improve performance and capacity of battle as the engine divice of new missiles. On this background, the research of performance estimate of ramjet and missile-ramjet intergrativation comes to be very important. At the same time, in the data processing of ramjet tests, there is always a problem about data conversion from ground to space, that is how to esitimate the flight performance based on the ground tests data along with the test condition and flight parameters, consequently, the emendation relationship of test data and flight performance need to be established.In order to obtain the flight performance by applying the test data processing results effectively and achieve the preliminary design results of missile driven by the ramjet rapidly and exactly. The thesis disscused the thermodynamic calculation model and the characteristics with the change of air-fuel ration and expansion ration of ramjet. Then, based on the current test data of ramjets, the thesis put forward methods which have been validated to process the ground test data of SDR. With the way of"subsection", which calculates the combustion effciency of chamber and mass flow coefficient of nozzle partly, the nozzle loss is abtained by the combination results of therotical calculation and test data processing. Hence, nozzle loss model was established, and the model could do the data conversion work from ground to space very well. These conclusions could give direction to the component selection and modification in the preliminary design of ramjets and missiles.The engineering method of aerodynamic estimate has been researched and the interface of the work has been realized. Meanwhile, the thesis builds a platform of the estimation of ramjet performance. In the end, the thesis validated the platform by the ideal ballistic trajetory of a cruise missile and discussed the affect of range by the combustion effciency and angle-of-attack emphasizely. The result showed that the engineering estimate could meet the demand and the previous methods could apply in the preliminary design of missile with routine figuration.