Flight Mission and Performance Simulator for Hybrid Propulsion Aircraft

Result code in IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F68407700%3A21220%2F25%3A00383795" target="_blank" >RIV/68407700:21220/25:00383795 - isvavai.cz</a>

Result on the web

<a href="https://www.fs.cvut.cz/ustavy/sekce-centrum-leteckeho-a-kosmickeho-vyzkumu/centrum-leteckeho-a-kosmickeho-vyzkumu-12203/centrum-12203/" target="_blank" >https://www.fs.cvut.cz/ustavy/sekce-centrum-leteckeho-a-kosmickeho-vyzkumu/centrum-leteckeho-a-kosmickeho-vyzkumu-12203/centrum-12203/</a>

DOI - Digital Object Identifier

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Result language

angličtina

Original language name

Flight Mission and Performance Simulator for Hybrid Propulsion Aircraft

Original language description

The Flight Mission and Performance Simulator for Hybrid Propulsion Aircraft is a computational tool developed for simulating, analyzing, and optimizing the performance of aircraft equipped with hybrid propulsion systems. The simulator is designed to model complete flight missions while accounting for the dynamic interactions between gas turbines, electric motors, fuel cells, and energy storage systems. Its primary purpose is to support early-stage design, mission planning, and performance trade-off evaluations for regional and medium-range aircraft operating under various hybridization strategies. The tool is intended for use by researchers, engineers, and educators in the field of sustainable aviation propulsion technologies.

Czech name

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Czech description

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Type

R - Software

CEP classification

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OECD FORD branch

20304 - Aerospace engineering

Project

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Continuities

R - Projekt Ramcoveho programu EK

Publication year

2025

Confidentiality

S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

Internal product ID

12203-0004-FlightPerformance

Technical parameters

The simulator is implemented in MATLAB with a modular, object-oriented architecture. Each propulsion component—internal combustion engine, electric motor, fuel cell, gearbox, hydrogen tank, and power electronics—is modeled as a replaceable class with adjustable inputs. The aircraft model includes aerodynamic, structural, and mission-specific definitions for flexible configuration of range, altitude, payload, and speed. Key flight phases—taxi, take-off, climb, cruise, descent, approach, go-around, loiter, and alternate—are modeled explicitly. Flight dynamics use Euler integration with configurable time steps. Performance is interpolated from multidimensional tables reflecting altitude, speed, and engine settings. Outputs include fuel consumption, hybrid power split, propulsion mass, energy balance, payload-range diagrams, and emissions. Hybridization is continuous (0.0–1.0), from conventional to fully electric. The validated model simulates a 68-seat regional turboprop (MTOM 22,500 kg). Typical runtime is under 30 seconds per mission.

Economical parameters

From an economic standpoint, the Flight Mission and Performance Simulator for Hybrid Propulsion Aircraft has been developed as a research-oriented academic tool, primarily intended for use in universities, research centers, and collaborative development environments. Its implementation leverages widely available computational environments and institutional software licenses, which keeps operational costs manageable. The simulator is distributed under a non-commercial academic license, with the possibility of tailored agreements for collaborative or extended use. In the event of commercial interest, licensing terms can be adapted based on the desired scope, technical support, and level of integration into industrial workflows. Maintenance, updates, and technical assistance can be arranged through periodic service agreements. Optional services such as user training, methodological support, or curriculum integration are available to academic institutions and project partners.

Owner IČO

68407700

Owner name

České vysoké učení technické v Praze / FS / centrum leteckého a kosmického výzkumu