Abstract In order to broaden the stable working range of air-breathing continuous rotating detonation engine and explore influence combustor configuration on propagation characteristics wave, cavity-based annular is introduced. Air-breathing experiments are conducted with non-premixed ethylene air. A tri-propellant air-heater used imitate outlet parameters intake Ma4/20km. The designed mass flo...

This study conducts experimental research on the liquid sloshing performance of a vane-type tank used in high orbit satellites. The tests without propellant management device (PMD) were developed under different liquid-filling ratios. Liquid with PMD performed directions and test results agree considerably theoretical results, indicating system’s reliability. A linear relationship was observed ...

A numerical framework based on the generalized finite element method (GFEM) is developed to capture the coupled effects of thermomechanical deformations and thermal gradients on the regression rate of a heterogeneous solid propellant. The thermomechanical formulation is based on a multiplicative split of the deformation gradient and regression of the heterogeneous solid propellant is simulated ...

Reusable liquid-propellant rocket engines (LPREs) imply more demanding robustness requirements than expendable ones due to their extended capabilities. Therefore, the goal of this article was develop a control loop adapted all operating phases LPRE, including transients, and robust internal parametric variations. First, thermo-fluid-dynamic simulators representative gas-generator-cycle were bui...

Neural networks (NN) are implemented as sub-grid flame models in a large-eddy simulation of single-injector liquid-propellant rocket engine with the aim to replace look-up table approach. The NN training process presents an extraordinary challenge. multi-dimensional combustion instability problem involves multi-scale lengths and characteristic times unsteady flow nonlinear acoustics, addressing...

This paper presents a model based experimental investigation to demonstrate the usefulness of an active damping strategy to manage fluid sloshing motion in spacecraft tanks. The active damping strategy is designed to reduce the degrading impact on maneuvering and pointing performance via a force feedback strategy. Many problems have been encountered until now, such as instability of the closed ...

High thrust-to-power ratio on Hall-effect thrusters allows for more efficient thrust generation and better overall performance. It allows Hall-effect thrusters to perform more thrust-intensive maneuvers such as orbit raising, thus saving the mass of a second engine purely for those maneuvers. This paper presents the initial performance measurements of aHall-effect thruster using in-channel elec...

A low-power microwave arjet thruster was studied using ammonia gas as propellant. The purpose of the project was to generate ammonia plasma using a 7.5 GHz magnetron and a cylindrical cavity thruster, which is resonant in the TM001 mode [1]. The desired pressure was atmospheric or above while generating a thrust of roughly 20mN and an Isp of about 500s operating at low power (<100 kW). Introduc...