Publications

Conceptual Design of a Hybrid Hydrogen Fuel Cell/Battery Blended-Wing-Body Unmanned Aerial Vehicle—An Overview

Abstract: The manuscript presents the conceptual design phase of an unmanned aerial vehicle, with the objective of a systems approach towards the integration of a hydrogen fuel-cell system and Li-ion batteries into an aerodynamically efficient platform representative of future aircraft configurations. Using a classical approach to aircraft design and a combination of low- and high-resolution computational simulations, a final blended wing body UAV was designed with a maximum take-off weight of 25 kg and 4 m wingspan. Preliminary aerodynamic and propulsion sizing demonstrated that the aircraft is capable of completing a 2 h long mission powered by a 650 W fuel cell, hybridized with a 100 Wh battery pack, and with a fuel quantity of 80 g of compressed hydrogen..

Journal: Aerospace 2022, 9(5), 275; https://doi.org/10.3390/aerospace9050275

Authors: Siwat Suewatanakul, Alessandro Porcarelli, Adam Olsson, Henrik Grimler, Ariel Chiche, Raffaello Mariani, and Göran Lindbergh

Design of a structural composite hydrogen tank

Abstract: Hydrogen could be the new, clean fuel for aviation to reduce emissions. However, storing hydrogen is complicated and the high pressure tanks needed add weight to the airframe. Structural hydrogen tanks are one solution and reduce weight by structural integration. The work addresses the topic of integraton of composite hydrogen storage tanks in the structure of the wing.

Journal: KunststoffXtra, 05/2021

Authors: Urs Zimmermann, Prof. Dr. Gion A. Barandun, IWK Institut für Werkstofftechnik und Kunststoffverarbeitung, OST Ostschweizer Fachhochschule Eichwiesstrasse 18b CH-8645 Rapperswil-Jona, www.ost.ch/iwk

Wind tunnel testing of a blended wing body unmanned aerial Vehicle

Abstract: This paper discusses the wind tunnel test of a 37.5% scale model of a blended wing body unmanned aerial vehicle. The model was mounted on a fixed belly-fairing sting, and the pitch variation was facilitated via a linear actuator. The model and set-up were directly mounted on a force plate placed underneath the tunnel floor. Aerodynamic loads were acquired at a range of wind tunnel velocities between 10m/s and 30m/s, corresponding to a Reynolds number range between ∼246 000 and ∼760 000, and results show good repeatability throughout the experimental campaign. A virtual wing tunnel was set up using computational fluid dynamics representative of the real-life facility, and the model was simulated inside the tunnel for a range of angles of attack between -4deg and 10deg without support, and at a reduced range between 0deg and 6deg with the support “installed.” Classical analytical methods for boundary and support interference corrections were implemented, and corrections factors were estimated by numerical simulation of the model with and without the support installed. Preliminary comparison between experimental measurements from force balance and numerical data show satisfactory agreement in the prediction of the lift curve slope, with some disagreement in the prediction of the stall condition. Prediction of drag and pitching moment are significantly impacted by the presence of the support and show poor agreement with numerical data.

Conference: 33rd Congress of the International Council of the Aeronautical Science, Stockholm, 4-9 September, 2022. Paer ID 0215

Authors: Raffaello Mariani, Siwat Suewatanakul, Sara Ghika, Luis Alfonso Penela, Per Wennhage, Bin Zang

Development of a CFD model and methodology for the internal flow simulaton in a hydrogen powered UAV

Abstract: The onboard carrying of a hydrogen fuel cell leads to unexplored internal flow characteristics, including the introduction of water vapour. Given the strict environmental operational requirements of PEM fuel cells, a Runge-Kutta-based solver is developed and tested to effectively and efficiently assess the evolution of the UAV internal bay flow temperature and humidity fields.

Conference: 33rd Congress of the International Council of the Aeronautical Science, Stockholm, 4-9 September, 2022. Paer ID 0051

Authors: Alessandro Porcarelli