Generic Design Methodology for Vertical Takeoff and Landing Aircraft with Hybrid-Electric Propulsion

2021 ◽  
pp. 1-15
Author(s):  
Donguk Lee ◽  
Daejin Lim ◽  
Kwanjung Yee
Keyword(s):  
Electric Propulsion ◽  
Design Methodology ◽  
Vertical Takeoff And Landing ◽  
Hybrid Electric ◽  
Generic Design ◽  
Vertical Takeoff

Development of a Fuel Cell Hybrid Electric Vertical Takeoff and Landing Aircraft Power Train

2021 ◽  
Author(s):  
Mengxuan Wei ◽  
Maohang Qiu ◽  
Shuai Yang ◽  
Xiaoyan Liu ◽  
Jeff Taylor ◽  
...  
Keyword(s):  
Fuel Cell ◽  
Cell Hybrid ◽  
Power Train ◽  
Vertical Takeoff And Landing ◽  
Hybrid Electric ◽  
Vertical Takeoff ◽  
Fuel Cell Hybrid

Interactions of Two UAV Rotors at Low Reynolds Number

2020 ◽  
Author(s):  
Yashvardhan Tomar ◽  
Dhwanil Shukla ◽  
Narayanan Komerath
Keyword(s):  
Reynolds Number ◽  
Electric Propulsion ◽  
Low Reynolds Number ◽  
Navier Stokes ◽  
Viscous Effects ◽  
Forward Flight ◽  
Spatial Spread ◽  
Vertical Takeoff And Landing ◽  
Low Reynolds ◽  
Vertical Takeoff

Abstract Vertical takeoff and landing vehicle platforms with many small rotors are becoming increasingly pertinent for small Unmanned Aerial Vehicles (UAVs) as well as distributed electric propulsion for larger vehicles. These rotors operate at low Reynolds number unlike large rotors for which the existing prediction methods were developed. Operating at very low Reynolds number essentially means that viscous effects are more dominant; and their spatial spread is significant with respect to the rotor dimensions. This impacts the nature of inter-rotor aerodynamic interactions which become more difficult to predict and characterize. In the present research, two nominally identical commercial UAV rotors are studied for a range of separations in hover and forward flight, both experimentally and computationally, in parallel with ongoing vehicle flight tests with 4 and 8 rotors. Bi-rotor tests in tandem in-plane configuration were performed in Georgia Tech’s 2.13m × 2.74m test section wind tunnel. Rotor simulations were done using the RotCFD Navier-Stokes solver. In hover, rotor performance is sensitive to the distance between rotors at low rotation speeds, indicating the presence of greater inter-rotor interactions at low Reynolds number. In forward flight, the performance of the downstream rotor gets negatively affected by the upstream rotor wake.

scholarly journals Design of Hybrid-Electric Megayachts: The Impact of Operative Profile and Smart Berthing Infrastructures

2021 ◽  
Vol 9 (2) ◽  
pp. 186
Author(s):  
Francesco Mauro ◽  
Elia Ghigliossi ◽  
Vittorio Bucci ◽  
Alberto Marinó
Keyword(s):  
Electric Propulsion ◽  
Propulsion System ◽  
Storage Devices ◽  
Electric Propulsion System ◽  
Hybrid Electric ◽  
The Impact

Nowadays, sustainable navigation is becoming a trending topic not only for merchant ships but also for pleasure vessels such as motoryachts. Therefore, the adoption of a hybrid-electric propulsion system and the installation of on-board storage devices could increase the greenness of a megayacht. This paper analyses the performance of three commercial propulsive solutions, using a dynamic operative profile and considering the influences of the smart berthing infrastructures. Results compare the yearly fuel consumptions of the analysed configurations for a reference megayacht.

scholarly journals Challenges and key requirements of batteries for electric vertical takeoff and landing aircraft

Joule ◽  
2021 ◽  
Author(s):  
Xiao-Guang Yang ◽  
Teng Liu ◽  
Shanhai Ge ◽  
Eric Rountree ◽  
Chao-Yang Wang
Keyword(s):  
Vertical Takeoff And Landing ◽  
Vertical Takeoff

Dynamics Simulation and Analysis of Transition Stage of Tilt-Rotor Aircraft

2016 ◽  
Vol 842 ◽  
pp. 251-258 ◽  
Author(s):  
Muhammad Rafi Hadytama ◽  
Rianto A. Sasongko
Keyword(s):  
Dynamic Response ◽  
Equations Of Motion ◽  
Flight Dynamics ◽  
Dynamics Simulation ◽  
Tilt Rotor ◽  
Vertical Takeoff And Landing ◽  
Improved Stability ◽  
Simulation Results ◽  
Vtol Aircraft ◽  
Vertical Takeoff

This paper presents the flight dynamics simulation and analysis of a tilt-rotor vertical takeoff and landing (VTOL) aircraft on transition phase, that is conversion from vertical or hover to horizontal or level flight and vice versa. The model of the aircraft is derived from simplified equations of motion comprising the forces and moments working on the aircraft in the airplane's longitudinal plane of motion. This study focuses on the problem of the airplane's dynamic response during conversion phase, which gives an understanding about the flight characteristics of the vehicle. The understanding about the flight dynamics characteristics is important for the control system design phase. Some simulation results are given to provide better visualization about the behaviour of the tilt-rotor. The simulation results show that both transition phases are quite stable, although an improved stability can give better manoeuver and attitude handling. Improvement on the simulation model is also required to provide more accurate and realistic dynamic response of the vehicle.

scholarly journals Power Line Charging Mechanism for Drones

Drones ◽  
2021 ◽  
Vol 5 (4) ◽  
pp. 108
Author(s):  
Boaz Ben-Moshe
Keyword(s):  
Homeland Security ◽  
Optimal Solution ◽  
Power Line ◽  
Flight Time ◽  
Security Applications ◽  
Long Duration ◽  
Vertical Takeoff And Landing ◽  
Charging Mechanism ◽  
Commercial Photography ◽  
Vertical Takeoff

The use of multirotor drones has increased dramatically in the last decade. These days, quadcopters and Vertical Takeoff and Landing (VTOL) drones can be found in many applications such as search and rescue, inspection, commercial photography, intelligence, sports, and recreation. One of the major drawbacks of electric multirotor drones is their limited flight time. Commercial drones commonly have about 20–40 min of flight time. The short flight time limits the overall usability of drones in homeland security applications where long-duration performance is required. In this paper, we present a new concept of a “power-line-charging drone”, the idea being to equip existing drones with a robotic mechanism and an onboard charger in order to allow them to land safely on power lines and then charge from the existing 100–250 V AC (50–60 Hz). This research presents several possible conceptual models for power line charging. All suggested solutions were constructed and submitted to a field experiment. Finally, the paper focuses on the optimal solution and presents the performance and possible future development of such power-line-charging drones.

scholarly journals Enabling the potential of hybrid electric propulsion through lean-burn-combustion turbofans

2021 ◽  
Vol 5 ◽  
pp. 164-176
Author(s):  
Stavros Vouros ◽  
Mavroudis Kavvalos ◽  
Smruti Sahoo ◽  
Konstantinos Kyprianidis
Keyword(s):  
Electric Propulsion ◽  
Direct Injection ◽  
Operating Cost ◽  
Pollutant Emissions ◽  
Civil Aviation ◽  
Lean Burn ◽  
Lean Direct Injection ◽  
Direct Operating Cost ◽  
Hybrid Electric ◽  
The Impact

Hybrid-electric propulsion has emerged as a promising technology to mitigate the adverse environmental impact of civil aviation. Boosting conventional gas turbines with electric power improves mission performance and operability. In this work the impact of electrification on pollutant emissions and direct operating cost of geared turbofan configurations is evaluated for an 150-passenger aircraft. A baseline two-and-a-half-shaft geared turbofan, representative of year 2035 entry-into-service technology, is employed. Parallel hybridization is implemented through coupling a battery-powered electric motor to the engine low-speed shaft. A multi-disciplinary design space exploration framework is employed comprising modelling methods for multi-point engine design, aircraft sizing, performance and pollutant emissions, mission and economic analysis. A probabilistic approach is developed considering uncertainties in the evaluation of direct operating cost. Sensitivities to electrical power system technology levels, as well as fuel price and emissions taxation are quantified at different time-frames. The benefits of lean direct injection are explored along short-, medium-, and long-range missions, demonstrating 32% NO<italic><sub>x</sub></italic> savings compared to traditional rich-burn, quick-mix, lean-burn technologies in short-range operations. The impact of electrification on the enhancement of lean direct injection benefits is investigated. For hybrid-electric powerplants, the take-off-to-cruise turbine entry temperature ratio is 2.5% lower than the baseline, extending the corresponding NO<italic><sub>x</sub></italic> reductions to the level of 46% in short-range missions. This work sheds light on the environmental and economic potential and limitations of a hybrid-electric propulsion concept towards a greener and sustainable civil aviation.

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