This paper focuses on the influence of ramp locations upstream of a strut-based scramjet combustor under reacting flow conditions that are numerically investigated. In contrast, a computational study is adopted using Reynolds Averaged Navier Stokes (RANS) equations with the Shear Stress Transport (SST) k-ω turbulence model. The numerical results of the Deutsches Zentrum für Luft- und Raumfahrt or German Aerospace Centre (DLR) scramjet model are validated with the reported experimental values that show compliance within the range, indicating that the adopted simulation method can be extended for other investigations as well. The performance of the ramps in the strut-based scramjet combustor is analyzed based on parameters such as wall pressures, combustion efficiency and total pressure loss at various axial locations of the combustor. From the numerical shadowgraph, more shock interactions are observed upstream of the strut injection region for the ramp cases, which decelerates the flow downstream, and additional shock reflections with less intensity are also noticed when compared with the DLR scramjet model. The shock reflection due to the ramps enhances the hydrogen distribution in the spatial direction. The ignition delay is noticed for ramp combustors due to the deceleration of flow compared to the baseline strut only scramjet combustor. However, a higher flame temperature is observed with the ramp combustor. Because more shock interactions arise from the ramps, a marginal increase in the total pressure loss is observed for ramp combustors when compared to the baseline model.

The present study focuses on the performance of dual ramps in a strut based scramjet combustor. The ramps are placed parallel to the strut on the top and bottom walls of the combustor. Air enters the combustor at a supersonic speed of Mach number 2.0, and the hydrogen jet injected from the strut, at sonic speed. The numerical investigations are performed using the commercial code ANSYS FLUENT software. The flow field is solved using a 2-D compressible Reynolds-Averaged Navier-Strokes equation (RANS) with the k-ω, SST turbulence model along with default constants and species transport equations are chosen for the computational study. The numerical results are validated with the experimental data that show compliance within the range, which has been extended for further investigation as well. The performance of the scramjet combustor with ramps is investigated under non-reacting and reacting flow conditions using, wall pressures, combustion efficiency, and total pressure loss of the combustor compared with the DLR scramjet model. In the case of the non-reacting flow field, the shock to shock, and shock to fuel stream shear layers, and shock to boundary layer interactions are observed. The reflected shock is observed downstream of the strut in the double ramp combustor resulting in the reduction of flow velocity downstream of the strut injector. In reacting flow studies, the fuel distribution in the spatial direction is enhanced towards the combustor walls with a double ramp than the DLR scramjet model. The higher temperature distribution is observed for double ramp combustors which reveal that an enhancement in heat release is perceived for double ramp combustor than the DLR combustor. The double ramp combustor provides complete combustion of the hydrogen-air mixture within the axial length with a marginal increase in the total pressure loss than the DLR combustor due to the shocks that emerge from the ramps.

Internet of things (IoT) has been implemented in aviation predictive maintenance in recent years for the enhancement of better maintenance prediction, to reduce downtime, unnecessary maintenance actions, increase safety, increase system readiness, and refine the management process and to improve component design. The IoT system in predictive maintenance is very optimistic in gathering and analysing, predicting the component failures and to determine the remaining useful life of a systems. Since Remaining useful life of an system is defines as the length from the current time to the end of its useful life. Due to its futuristic increasing demand of IoT in aviation maintenance, the biggest challenge is to ensuring the reliability and accuracy of any specific IoT system allotted for monitoring aircraft components in the near future. Hence, this review paper clearly explains the challenges associated with IoT systems on predicting Remaining useful life.

The mobile communication networks and towers go down or cease to exist leading to poor connectivity during disasters. When communication becomes paralyzed, it is vital to build a disaster relief solution with available resources. Without data connectivity, it is essential that an emergency protocol should be implemented by the government that uses the available paralyzed communication resources spread across various communication networks by pooling to form one single communication network backed by cloud facilities to restore connectivity. In this paper the authors introduce a new emergency protocol approach to design an unrestricted cloud-based mobile technology during disaster enabling instant communication services to the disaster zones that works best under the command of the government. This protocol can act faster than the existing communication network put in place for public communication, with the additional advantage of being more robust and capable of withstanding disaster conditions.