Showing papers on "Rocket published in 2019"
TL;DR: An overview of the research done worldwide to address some of the challenges and questions pertaining to the physics of rotating detonation combustors operation is provided in this paper, where notable parallels are drawn to the phenomena of low and high frequency instabilities in solid and liquid rockets that have been recognized as the most severe hindrance to their operation.
204 citations
TL;DR: In this article, the aerodynamic control and propulsion should be coordinated to realize fuel-optimal precise landing for a reusable rocket returning back to Earth, where aerodynamic forces are not negligible.
Abstract: Aerodynamic forces are not negligible for a reusable rocket returning back to Earth. How the aerodynamic controls and propulsion should be coordinated to realize fuel-optimal precise landing is add...
91 citations
TL;DR: A novel guidance algorithm based on convex optimization, pseudospectral discretization, and a model predictive control (MPC) framework is proposed to solve the highly nonlinear and c-linear guidance problems.
Abstract: In this paper, a novel guidance algorithm based on convex optimization, pseudospectral discretization, and a model predictive control (MPC) framework is proposed to solve the highly nonlinear and c...
75 citations
TL;DR: In this article, numerical simulations of three-dimensional flow of a gas mixture with chemical reactions over a flat thermally destructing material surface are presented, and two ways of determining the heat removal are considered, and a comparison with the analytical solution obtained within the frame of the boundary layer approximation is represented.
62 citations
TL;DR: In this paper, the authors present the results from thrust measurements of an ethylene/gas-oxygen rotating deformation for a rocket combustor with a geometrical throat.
Abstract: Geometric throats are commonly applied to rocket combustors to increase pressure and specific impulse. This paper presents the results from thrust measurements of an ethylene/gas-oxygen rotating de...
58 citations
07 Jan 2019
54 citations
TL;DR: In this paper, a 3D printing of the large-diameter gas-discharge chambers of electric rocket engines was developed for the first time, using a ceramic composite based on silicon nitride.
Abstract: A technology is developed for 3D printing of the large-diameter gas-discharge chambers of electric rocket engines. The material employed is a ceramic composite based on silicon nitride.
45 citations
TL;DR: In this article, an efficient method for estimating the time and spatially resolved heat flux distribution at the hot gas wall of a single-element rocket engine using the information provided by temperature measurements in the material is presented.
45 citations
TL;DR: A simplified theoretical treatment of rotating detonation engine (RDE) performance is developed for rocket applications with traceability to current combustion technology.
Abstract: A simplified theoretical treatment of rotating detonation engine (RDE) performance is developed for rocket applications with traceability to current combustion technology. In particular, the influe...
38 citations
TL;DR: This study aims to provide a summary report on the recent research progress on the RBCC engine in ejector mode from four aspects, namely the combustion organization, the mixing enhancement, the resistance to backpressure and the ejector/ramjet mode transition.
37 citations
TL;DR: The concept of the HyImpulse mini-launcher includes eleven engines of this type, which will result in large scale serial production for the foreseen launch rate of twelve launches per year, which further reduces production costs of the hybrid rocket engine.
TL;DR: The turbulence network, which consists of nodes and vertexes in weighted networks between vortices, can characterize the complex spatiotemporal structure of a flow field during thermoacoustic combustion instability.
Abstract: We numerically study the spatiotemporal dynamics and early detection of thermoacoustic combustion instability in a model rocket combustor using the theories of complex networks and synchronization. The turbulence network, which consists of nodes and vertexes in weighted networks between vortices, can characterize the complex spatiotemporal structure of a flow field during thermoacoustic combustion instability. The transfer entropy allows us to identify the driving region of thermoacoustic combustion instability. In addition to the order parameter, a phase parameter newly proposed in this study is useful for capturing the precursor of thermoacoustic combustion instability.
TL;DR: In this article, the authors present an overview on progress and perspectives of the jet impingement research for rocket launching and discuss the interaction of impinging jets with multiphase flows.
TL;DR: In this paper, the influence of the injector design on the main performance parameters, such as fuel regression rate, specific impulse and combustion efficiency, of a hybrid rocket motors was analyzed.
TL;DR: A series of firing tests have been performed on a laboratory-scale hybrid rocket engine of 200 N class, fed with gaseous oxygen through a converging nozzle injector, to assess the mechanical feasib... as mentioned in this paper.
Abstract: A series of firing tests have been performed on a laboratory-scale hybrid rocket engine of 200 N class, fed with gaseous oxygen through a converging nozzle injector, to assess the mechanical feasib...
TL;DR: In this article, the authors address the nature of supercritical hydrogen-oxygen flame coupling to acoustics through visualization under conditions representative of upper-stage rocket engines, and present a research thrust analysis of the supercritical HOOG flame.
Abstract: This work addresses the nature of supercritical hydrogen-oxygen flame coupling to acoustics through visualization under conditions representative of upper-stage rocket engines. A research thrust ch...
TL;DR: In this article, a computational thermo-fluid-dynamic model of the internal ballistics of hybrid rockets burning gaseous oxygen and paraffin-based fuel is presented for predicting the local fuel regression rate.
TL;DR: A number of relevant key technologies regarding the study of the ejector mode are proposed, including efficient ejection, efficient mixing and combustion, widely adjustable rocket, widely applicable variable geometry inlet/nozzle design and control, multi-mode flow passage design, and robust mode transition.
TL;DR: In this paper, the simulation of the flow inside an experimental GOX/GCH4 rocket thrust chamber is undertaken, where the combustor's injector consists of seven individual coaxial injector elements.
Abstract: In the present Paper, the simulation of the flow inside an experimental GOX/GCH4 rocket thrust chamber is undertaken. The combustor’s injector consists of seven individual coaxial injector elements...
TL;DR: In this paper, an experimental study aimed at combustion characteristics and the affection mechanism of powder magnesium and carbon dioxide combustion in a rocket engine was conducted, and a new configuration of powder rocket system was established.
TL;DR: In this paper, an axisymmetric computational fluid dynamics (CFD) solver was used to calculate the reaction time of plume flows in the view of the phenomenon.
TL;DR: In this paper, a review of the effects observed during injections of powerful electron beams from sounding rockets into the upper atmosphere is given, where data come from in situ particle and wave measurements near a beam emitting rocket and ground-based optical, wideband radiowave, and radar observations.
Abstract: A review is given of the effects observed during injections of powerful electron beams from sounding rockets into the upper atmosphere. Data come from in situ particle and wave measurements near a beam emitting rocket and ground-based optical, wideband radiowave, and radar observations. The overall data cannot be explained solely by collisional degradation of energetic electrons but require collisionless beam plasma interactions (BPI) be taken into account. The beam-plasma discharge theory describes the features of the region near a beam-emitting rocket, where the beam-excited plasma waves energize plasma electrons, which then ignite the discharge. The observations far beneath the rocket reveal a double-peak structure of artificial auroral rays, which can be understood in terms of the beam-excited strong Langmuir turbulence being affected by collisions of ionospheric electrons. This leads to the enhanced energization of ionospheric electrons in a narrow layer termed the plasma turbulence layer (PTL), which explains the upper peak. Similar double-peak structures or a sharp upper boundary in rayed auroral arcs have been observed in the auroral ionosphere by optical, radar, and rocket observations, and called Enhanced Aurora. A striking resemblance between Enhanced and Artificial Aurora altitude profiles indicates that they are created by the above BPI process which results in the PTL.
TL;DR: In this article, a robust and efficient flamelet model accounting for heat losses is applied to represent the hydrocarbon combustion process at affordable computational effort, and three different near-wall treatments are used: wall-resolved LES, wall-modeled LES and a hybrid RANS/LES approach.
TL;DR: In this article, both experimental and numerical approaches for estimating the heat exchange through thermal radiation towards the walls of a lab-scale paraffin-based thrust chambers were presented, and two firing tests of a gaseous-oxygen/paraffinwax hybrid rocket engine were performed to apply such methods.
TL;DR: In this paper, a seven-element gaseous methane/oxygen subscale rocket combustion chamber is analyzed for two no-no-state simulations with different fidelity and the covered region of thermo-chemical states is analyzed.
Abstract: Combustion models of different fidelity are applied to a seven-element gaseous methane/oxygen subscale rocket combustion chamber. The covered region of thermo-chemical states is analyzed for two no...
TL;DR: In this article, a single element GCH4/GOx rocket combustion chamber developed at the Technische Universitat Munchen has been computed using Large Eddy Simulation, with a particular focus on the prediction of wall heat flux.
Abstract: The single element GCH4/GOx rocket combustion chamber developed at the Technische Universitat Munchen has been computed using Large Eddy Simulation. The aim of this work is to analyze the flow and combustion features at high pressure, with a particular focus on the prediction of wall heat flux, a key point for the development of reusable engines. The impact of the flow and flame, as well as of the model used, on thermal loads is investigated. Longitudinal distribution of wall heat flux, as well as chamber pressure, have been plotted against experimental data, showing a good agreement. The link between the heat released by the flame, the heat losses and the chamber pressure has been explained by performing an energetic balance of the combustion chamber. A thermally chained numerical simulation of the combustor structure has been used to validate the hypothesis used in the LES.
TL;DR: In this article, an efficient inverse method for estimating the spatially resolved heat flux distribution at the hot gas wall of multi-element, actively cooled engines using the information provided by temperature measurements in the material is presented.
TL;DR: Numerous real-time implementations such as a robust balancing process, segway and hover board riding, and rocket propeller operation are done with the control principle of Inverted Pendulum (IP).
Abstract: Numerous real-time implementations such as a robust balancing process, segway and hover board riding, and rocket propeller operation are done with the control principle of Inverted Pendulum (IP). D...
TL;DR: The sea-level startup of rocket engines is characterized by the nozzle experiencing a high degree of overexpansion and consequent internal flow separation with a strong unsteady shock-wave/boundary as discussed by the authors.
Abstract: The sea-level startup of rocket engines is characterized by the nozzle experiencing a high degree of overexpansion and consequent internal flow separation with a strong unsteady shock-wave/boundary...