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This paper introduces the design, construction, and static testing of a solid rocket motor. The design was based on the solid rocket motor design methodology (SRM). The rocket motor included the igniter system, the combustion chamber, the solid propellant, and the nozzle. The internal diameter of the combustion chamber and the total length of the rocket motor were 27,67 mm and 230 mm, respectively. The rocket motor nozzle was of the convergent-divergent Laval type. The propellant was based on the mixture of potassium nitrate (KNO3) (oxidant) and high purity sugar (or sucrose: C12H22O11) (fuel), whose synthesis was achieved through a thermal fusion process (150-170 °C for 20-25 min). The performance of the rocket motor was evaluated using a static combustion test; resulting in a maximum thrust force (load) of 227 N, a total impulse of 98,69 Ns and a specific impulse of 65,8 s, thus allowing its classification as a class G rocket motor. The results obtained are considered of great importance in the development and characterization of solid rocket motors, necessary to promote the experimental rocketry in Colombia. [ABSTRACT FROM AUTHOR]

Rotating detonation engines (RDEs) are widely studied because of their compact configurations and high thermal cycle efficiency. In this paper, a series of numerical investigations of a non-premixed hollow RDE are performed. The transient explicit density-based solver in ANSYS Fluent is used to perform the simulations. For a hollow RDE without Laval nozzle, there is only one rotating detonation wave in the combustion chamber. Compared to the traditional annular RDE, the mixing quality is deteriorated, and the thrust of the engine decreases and becomes more unstable. When the hollow RDE is attached with a Laval nozzle, there are two rotating detonation waves in the combustion chamber. The pressure within the combustion chamber increases while the axial velocity decreases. The mixing quality is improved. The height of detonation waves decreases with larger contraction ratio of the nozzle. A Laval nozzle is beneficial for a hollow RDE to achieve steadier operation and higher thrust output. When the contraction ratio is 4, the propulsive performance of the engine is the highest. The maximum thrust achieved is 840 N. • The flowfield structure in a non-premixed hollow RDE is obtained. • The mixing quality is deteriorated in the hollow RDE. • The height of detonation waves decreases with larger CR of the nozzle. • A Laval nozzle is beneficial to achieve steadier and higher thrust output. [ABSTRACT FROM AUTHOR]