Adaptable conceptual aircraft design model

Possible Hybrid Propulsion Configuration for Transport Jet Aircraft

“…"Matching chart" plot showing the benefit of the over boost at take-off. From (Fioriti 2014) motor-generators and energy storage system, taking into account the latest technologies which can be employed in the short term and estimating the possible operating cost reduction by considering the savings in terms of fuel and airport taxes. Acronyms β -propeller pitch angle; γ -ratio of aircraft speed to propeller tip speed; η CALCULATED -propeller efficiency calculated; η charge -battery charge efficiency; η discharge -battery discharge efficiency; ρ -air density; Ω -rotational propeller speed; AC -Alternate current; AEA -All electric aircraft; APU -Auxiliary power unit; ASTRID -Aircraft on board systems sizing and tradeoff analysis in initial design; BMS -Battery management system; C -Torque required by propeller; D r -Drag force during taxi; E -Energy required during taxi; ECS -Environment control system; F -Multiplying coefficient for braking actions and accelerations; f -Friction coefficient (wheels and runway): f = 0.024; HVDC -High voltage direct current; L ta -Distance from gate to runway threshold; OEW -Operating empty weight; P prop -Power required by propeller; R -Propeller radius; RAT -Ram air turbine; SFC -Specific fuel consumption; SRM -Switched reluctance machine; T -Propeller traction; t charge -battery charge time; TOGW -Take Off Gross Weight; V ta -Average speed during taxi; WF -Wild frequency.…”

“…This additional thrust could be particularly advantageous for hot and high take-off conditions. Moreover, as illustrated in Figure 12 (figure taken from the conceptual design methodology employed by the authors (Fioriti 2014)), since the take-off is usually the most stringent requirement, there is an opportunity to replace part of the internal combustion engine thrust with the one produced by the electric engine. This opportunity leads to two additional options:…”

Preliminary Sub-Systems Design Integrated in a Multidisciplinary Design Optimization Framework

“…Throughout the first phase of aircraft conceptual design (see Fig. 3 [15]), on-board systems are usually considered for their weight [15], [16], [17], [18]. This is due to the great importance of the convergence of aircraft weight during conceptual design.…”

“…high lift devices of a STOL (Short take-off and landing) aircraft is more complex than standard aircraft and usually weight more). An example of these fractions can be found in Table 1 [18]. Typically, the weight fractions are derived from statistical data.…”

“…Table 1. MTOM fractions for aircraft on-board systems [18] The systems volume could become a notable variable in conceptual design when large equipment and sensors is needed to carry out the mission of the aircraft. As previously said for C.G.…”