Abstract
A rocket uses fuel and oxidizers to generate propulsion by combustion and ejection, and is used for space exploration aircrafts, weapons, and satellite launches. In particular, the nozzle generating thrust of solid-propellant rockets is exposed to a high-temperature and high-pressure environment with erosion occurring from the combustion gas. When erosion occurs on the nozzle throat of such a rocket, it has a great impact on the flight performance such as reaching distance and flight speed. Many studies have been conducted to characterize erosion based on the thermochemical erosion model, since it has become important to choose nozzle materials suitable for such environments having robustness against combustion gasses of high temperature and high pressure. However, there is a limit to fully analyze the erosion characteristics only by the thermochemical erosion model. In this paper, we thus consider the mechanical erosion model with the thermochemical model for better understanding of erosion characteristics and investigate the thermochemical and mechanical erosion characteristics of nozzle throat heat-resistant materials made of graphite and carbon–carbon composites; the main factors affecting erosion are discussed by comparing the results of the experimental and theoretical models.
Highlights
A rocket is a device that generates thrust through action and reaction forces
In the C–C composite material, the surface groove was that of graphite as the matrix was burned and absent, and the fiber-reinforced composite material larger than that of graphite as the matrix was burned and absent, and the fiber-reinforced composite under the laminate was exposed due to erosion, appearing as a circular pattern
It was five fibers were exposed by each 90◦ downward directions, but they were resistant to surface erosion confirmed that five fibers were exposed by each 90° downward directions, but they were resistant to while the matrix was removed
Summary
A rocket is a device that generates thrust through action and reaction forces. It uses fuel and oxidants to generate propulsion by combustion and emissions, and is mainly used for space exploration aircrafts, weapons and satellite launches. Examples include liquid-propellant, solid-propellant, nuclear propulsion, and laser propulsion rockets. Solid-propellant rockets consist of a motor case, igniter, propellant, nozzle, insulator, and control and drive device. The nozzle is a very important component that generates thrust. Since the nozzle is burnt in a high-temperature/high-pressure environment, it cannot be cooled, unlike the liquid-propellant rocket that circulates fuel around the nozzle. Solid-propellant rockets experience erosion due to combustion gas [1]
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