Design and Manufacturing of an Inclinometer sensing element for launch vehicle applications Tony M Shaju, Nirmal Krishna, G Nagamalleswara Rao, Pradeep K Scientist/Engineer, ISRO Inertial Systems Unit, Vattiyoorkavu, Trivandrum, India - 695013 Indian Space Research Organisation (ISRO) uses indigenously developed launch vehicles like PSLV, GSLV, LVM3 and SSLV for placing remote sensing and communication satellites along with spacecrafts for other important scientific applications into earth bound orbits. Navigation systems present in the launch vehicle play a pivotal role in achieving the intended orbits for these spacecrafts. During the assembly of these navigation packages on the launch vehicle, it is required to measure the initial tilt of the navigation sensors for any misalignment corrections, which is given as input to the navigation software. A high precision inclinometer is required to measure these tilts with a resolution of 1 arc-second.
Metasurfaces, comprised of sub-wavelength structures, possess remarkable electromagnetic wave manipulation capabilities. Their application as radar absorbers has gained widespread recognition, particularly in modern stealth technology, where their role is to minimize the radar cross-section (RCS) of military assets. Conventional radar absorber design are tedious by their time-consuming, computationally intensive, iterative nature, and demand a high level of expertise. In contrast, the emergence of deep learning-based metasurface design for RCS reduction represents a rapidly evolving field. This approach offers automated and computationally efficient means to generate radar absorber designs. However, the practical implementation of radar-absorbing structures on complex aircraft bodies presents significant challenges.
The descent phase of GAGANYAAN (Indian Manned Space Mission) culminates with a crew module impacting at a predetermined site in Indian waters. During water impact, huge amount of loads are experienced by the astronauts. This demands an impact attenuation system which can attenuate the impact loads and reduce the acceleration experienced by astronauts to safe levels. Current state of the art impact attenuation systems use honeycomb core, which is passive, expendable, can only be used once (at touchdown impact) during the entire mission and does not account off-nominal impact loads. Active and reusable attenuation systems for crew module is still an unexplored territory. Three configurations of impact attenuators were selected for this study for the current GAGANYAAN crew module configuration, namely, hydraulic damper, hydro-pneumatic damper and airbag systems.
Effective contrail management while ensuring operational and economic efficiencies for flight services is essential for providing services with minimal adverse environmental impact. The paper explores various aspects of contrail management applicable to different platforms such as Unmanned vehicles, Commercial airliners and Business & regional jets. The aspects unique to each platform such as flight levels of operation, fuel types, flight endurance and radius of operation have been analyzed. Expanse of 5G network is resulting in increased flight activity at flight levels not envisaged hitherto. The paper also dwells on the ramifications of the increased proliferation of different platforms at newer flight levels from the perspective of contrail management.
Dimensional optimization has always been a time consuming process, especially for aerodynamic bodies, requiring much tuning of dimensions and testing for each sample. Aerodynamic auxiliaries, especially wings, are design dependent on the primary model attached, as they influence the amount of lift or reduction in drag which is beneficial to the model. In this study CFD analysis is performed to obtain pressure counter of wings. For a wing, the angle of attack is essential in creating proper splits to incoming winds, even under high velocities with larger distances from the separation point. In the case of a group of wings, each wing is then mentioned as a wing element, and each wing is strategically positioned behind the previous wing in terms of its vertical height and its self-angle of attack to create maximum lift. At the same time, its drag remains variable to its shape ultimately maximizing the C L /C D ratio.
This paper presents optimal control co-design of a parallel electric-hydraulic hybrid powertrain, to be specific, for heavy-duty vehicles. A pure electric powertrain that consists of a rechargeable lithium-ion battery, a high-efficient electric motor, and a single or double-speed gearbox has drawn a keen interest in the automotive sector because of a growing demand for clean and efficient mobility. However, the state-of-the-art has shown limited capability and has not been able to meet the design requirements for heavy-duty vehicles of high-power demand such as a class 8 semi-trailer truck in terms of a driving range on one battery charge, battery charging time, and load-carrying capacity primarily due to the low power density of lithium-ion batteries and low energy conversion efficiency of electric motors at low speed.
The rapid evolution of electric vehicle (EV) development has highlighted the need to develop EVs that meet customer demands for both high-performance and space-efficiency. This paper delves into the optimization opportunities available within the landscape of EV powertrains, focusing on the power-dense potential of single-axis powertrain systems. The need to adhere to power density requirements to accommodate performance aspirations while simultaneously yielding more cabin or storage space to the customer creates a challenging problem for designers. With this pursuit, these competing interests must strike a harmonious balance in order to create the best experience for the customer. The subject of this study is an investigation into a leading competitor's powertrain that explores the potential optimization opportunities available within its already compact single-axis electric transmission.
In recent years, the presence of electric buses within public transportation company fleets has significantly increased. To ensure optimal fleet management, it is necessary to analyze vehicle consumption in relation to their operational conditions. This study proposes an analysis of the energy consumption of a full-electric battery bus. Energy consumption was monitored using data made available on the vehicle's CAN network, including data from the main battery and major utilities such as the traction motor, the air conditioning system (both cooling and heating), power steering, main battery chiller, and low-voltage system utilities (lights, ventilation fans, doors opening, etc.). The parameters monitored during the experimentation included the vehicle's position and, consequently, the road gradient, instantaneous vehicle speed, internal and external temperature, vehicle load (to monitor consumption under various load conditions), and the involvement of different drivers.
Multi-motor powertrain topologies are playing an increasingly important role in the development of heavy duty battery electric trucks due to the changing driving requirements of these vehicles. The use of multiple motors and/or transmissions in a powertrain provides additional degrees of freedom for the energy management. The energy management system (EMS) consist of the gear selection strategy and torque split between the drive motors. The aim of the EMS is thereby to achieve high energy efficiency in motor and regenerative operation, while reducing the number of gear changes to ensure driving comfort. Ongoing research focuses on the energy management system of hybrid electric trucks, where the aim is to optimize the torque split between the combustion engine and the electric motor. In this paper, the EMS for an electric truck is described as a mixed-integer nonlinear control problem. This type of optimal control problem is notoriously difficult to solve.