![]() The deposited coating layer was analyzed by electron dispersive x-ray analysis (EDX) and scanning electron microscopy (SEM). It has been found the formation of a deposited thin layer of burned material after the test. Analysis of the materials from the subsonic and supersonic nozzle insert parts was performed after the end of burning tests. This paper presents an investigation of the ablation phenomena in the nozzle throat region during firing tests using graphite inserts. The thermal protections and the nozzle throat are adapted in order to test the material of the nozzle throat insert systems and allow definite burning times, from 10 up to 70 s, using a propellant grain size having appropriate end-burning configuration. ![]() The burning rate determination method consists of burning a set of motors under different chamber pressures, which is accomplished basically by using different nozzle throat diameters.Īnother important evaluation that can be done, besides burning time and ablation, which are related to the small amount of propellant burning characteristics, is the evaluation of the thermal protection materials, the behavior of the thermal protection materials and nozzle insert material. Since the late 1960s, when the Instituto de Aeronáutica e Espaço (IAE) started the development of SRM for the Brazilian Space Program, subscale rocket motors have been used to perform testimony tests aiming the quality control of burning rate parameters and energetic characteristics for solid propellants. (2005) used a similar model of a SRM in their study. Thus, subscale rocket motors are those in a lab scale and a benchmark for real-size rocket launchers. The subscale SRM is also a useful tool to study problems related to the effect of multiple chamber lengths, submergence nozzle, end burners, nozzle inserts, insulation capability and ablation rate ( Wermimont 1993 Cortopassi et al. Also, subscale motors are a classroom lesson for understanding the performance of solid rockets, since in general the delivered specific impulse is the main target ( Geisler and Beckman 1998). Because of this, a reduced amount of propellant is needed, and reliable results related to the burning test can be achieved. These subscale motor provide an estimation of full-scale motor performance at as small as possible motor size. Subscales of solid rocket motors (SRM) are devices used for propellant development and for propellant ballistic parameters control. KEYWORDS: Propulsion, Subscale motor, Nozzle inserts, Graphite, Firing test. It was also noticed that, because of the unexpected coating deposition forming material in exit conical and throat of the insert that the effect of ablation was not observed. Finally, the material was analyzed by x-ray diffraction, and the results showed the presence of aluminum oxide. The results analyzed by these methods showed that there were aluminum and carbon in the coating. The deposited coating layer was analyzed by electron dispersive x-ray analysis and scanning electron microscopy. It was found the formation of a thin layer of material deposited after the test. Analysis of the materials of the subsonic and supersonic nozzle insert parts was performed after the burning tests. The critical section to evaluate the test device is rocket nozzle throat region. The objective was to correlate the mass flow between subscale solid rocket motors and full scale using insert data materials such as graphite and carbon fiber-reinforced carbon composites, which have ablative characteristics determined in subscale solid rocket motors used at the Instituto de Aeronáutica e Espaço. These subscale solid rocket motors, simulating full scale motor operating time, but with mass flow far below, aim to determine the ablative characteristics of composite materials as a function of operating time. The motivation for the development of a subscale solid rocket motor with end burning propellant grain geometry arose from the need to evaluate the nozzle inserts of graphite for the possible replacement with the carbon fiber-reinforced carbon composite. This paper presents the study and development of a firing test used to evaluate the behavior of a solid rocket motor.
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