TY  - GEN
A1  - Eccleston, Paul
A1  - Drummond, Rachel
A1  - Middleton, Kevin
A1  - Bishop, Georgia
A1  - Caldwell, Andrew
A1  - Desjonqueres, Lucile
A1  - Tosh, Ian
A1  - Cann, Nick
A1  - Crook, Martin
A1  - Hills, Matthew
A1  - Pearson, Chris
A1  - Simpson, Caroline
A1  - Stamper, Richard
A1  - Tinetti, Giovanna
A1  - Pascale, Enzo
A1  - Swain, Mark
A1  - Holmes, Warren A.
A1  - Wong, Andre
A1  - Puig, Ludovic
A1  - Pilbratt, Göran
A1  - Linder, Martin
A1  - Boudin, Nathalie
A1  - Ertel, Hanno
A1  - Gambicorti, Lisa
A1  - Halain, Jean-Philippe
A1  - Pace, Emanuele
A1  - Vilardell, Francesc
A1  - Gómez, José M.
A1  - Colomé, Josep
A1  - Amiaux, Jérôme
A1  - Cara, Christophe
A1  - Berthe, Michel
A1  - Moreau, Vincent
A1  - Morgante, Gianluca
A1  - Malaguti, Giuseppe
A1  - Alonso, Gustavo
A1  - Álvarez, Javier P.
A1  - Ollivier, Marc
A1  - Philippon, Anne
A1  - Hellin, Marie-Laure
A1  - Roose, Steve
A1  - Frericks, Martin
A1  - Krijger, Matthijs
A1  - Rataj, Miroslaw
A1  - Wawer, Piotr
A1  - Skup, Konrad
A1  - Sobiecki, Mateusz
A1  - Christian Jessen, Niels
A1  - Møller Pedersen, Søren
A1  - Hargrave, Peter
A1  - Griffin, Matt
A1  - Ottensamer, Roland
A1  - Hunt, Thomas
A1  - Rust, Duncan
A1  - Saleh, Aymen
A1  - Winter, Berend
A1  - Focardi, Mauro
A1  - Da Deppo, Vania
A1  - Zuppella, Paola
A1  - Czupalla, Markus
ED  - Lystrup, Makenzie
ED  - Perrin, Marshall D.
ED  - Batalha, Natalie
ED  - Siegler, Nicholas
ED  - Tong, Edward C.
T1  - The ARIEL payload: A technical overview
T2  - Space Telescopes and Instrumentation 2020: Optical, Infrared, and Millimeter Wave
N2  - The Atmospheric Remote-Sensing Infrared Exoplanet Large-survey, ARIEL, has been selected to be the next (M4) medium class space mission in the ESA Cosmic Vision programme. From launch in 2028, and during the following 4 years of operation, ARIEL will perform precise spectroscopy of the atmospheres of ~1000 known transiting exoplanets using its metre-class telescope. A three-band photometer and three spectrometers cover the 0.5 µm to 7.8 µm region of the electromagnetic spectrum. This paper gives an overview of the mission payload, including the telescope assembly, the FGS (Fine Guidance System) - which provides both pointing information to the spacecraft and scientific photometry and low-resolution spectrometer data, the ARIEL InfraRed Spectrometer (AIRS), and other payload infrastructure such as the warm electronics, structures and cryogenic cooling systems.
KW  - Exoplanet
KW  - Spectroscopy
KW  - Transit
KW  - Atmospheres
KW  - Payload
Y1  - 2020
U6  - https://doi.org/10.1117/12.2561478
N1  - Space Telescopes and Instrumentation 2020: Optical, Infrared, and Millimeter Wave, 14–22 December 2020, Online Only, United States
VL  - 11443
SP  - 114430Z
PB  - SPIE
CY  - Washington
ER  - 
TY  - JOUR
A1  - Finger, Felix
A1  - Götten, Falk
A1  - Braun, Carsten
A1  - Bil, Cees
T1  - Mass, primary energy, and cost: the impact of optimization objectives on the initial sizing of hybrid-electric general aviation aircraft
JF  - CEAS Aeronautical Journal
N2  - For short take-off and landing (STOL) aircraft, a parallel hybrid-electric propulsion system potentially offers superior performance compared to a conventional propulsion system, because the short-take-off power requirement is much higher than the cruise power requirement. This power-matching problem can be solved with a balanced hybrid propulsion system. However, there is a trade-off between wing loading, power loading, the level of hybridization, as well as range and take-off distance. An optimization method can vary design variables in such a way that a minimum of a particular objective is attained. In this paper, a comparison between the optimization results for minimum mass, minimum consumed primary energy, and minimum cost is conducted. A new initial sizing algorithm for general aviation aircraft with hybrid-electric propulsion systems is applied. This initial sizing methodology covers point performance, mission performance analysis, the weight estimation process, and cost estimation. The methodology is applied to the design of a STOL general aviation aircraft, intended for on-demand air mobility operations. The aircraft is sized to carry eight passengers over a distance of 500 km, while able to take off and land from short airstrips. Results indicate that parallel hybrid-electric propulsion systems must be considered for future STOL aircraft.
Y1  - 2020
U6  - https://doi.org/10.1007/s13272-020-00449-8
SN  - 1869-5590
N1  - Corresponding author: Felix Finger
VL  - 2020
IS  - 11
SP  - 713
EP  - 730
PB  - Springer
CY  - Heidelberg
ER  - 
TY  - JOUR
A1  - Finger, Felix
A1  - Braun, Carsten
A1  - Bil, Cees
T1  - Impact of Battery Performance on the Initial Sizing of Hybrid-Electric General Aviation Aircraft
JF  - Journal of Aerospace Engineering
N2  - Studies suggest that hybrid-electric aircraft have the potential to generate fewer emissions and be inherently quieter when compared to conventional aircraft. By operating combustion engines together with an electric propulsion system, synergistic benefits can be obtained. However, the performance of hybrid-electric aircraft is still constrained by a battery’s energy density and discharge rate. In this paper, the influence of battery performance on the gross mass for a four-seat general aviation aircraft with a hybrid-electric propulsion system is analyzed. For this design study, a high-level approach is chosen, using an innovative initial sizing methodology to determine the minimum required aircraft mass for a specific set of requirements and constraints. Only the peak-load shaving operational strategy is analyzed. Both parallel- and serial-hybrid propulsion configurations are considered for two different missions. The specific energy of the battery pack is varied from 200 to 1,000 W⋅h/kg, while the discharge time, and thus the normalized discharge rating (C-rating), is varied between 30 min (2C discharge rate) and 2 min (30C discharge rate). With the peak-load shaving operating strategy, it is desirable for hybrid-electric aircraft to use a light, low capacity battery system to boost performance. For this case, the battery’s specific power rating proved to be of much higher importance than for full electric designs, which have high capacity batteries. Discharge ratings of 20C allow a significant take-off mass reduction aircraft. The design point moves to higher wing loadings and higher levels of hybridization if batteries with advanced technology are used.
Y1  - 2020
U6  - https://doi.org/10.1061/(ASCE)AS.1943-5525.0001113
SN  - 1943-5525
VL  - 33
IS  - 3
PB  - ASCE
CY  - Reston, Va.
ER  -