A guide to unmanned aerial vehicles performance analysis—the MQ‐9 unmanned air vehicle case study

• Published in: Journal of engineering (Stevenage, England) Vol. 2023; no. 6
• Main Authors: Zountouridou, Erietta, Kiokes, George, Dimeas, Aris, Prousalidis, John, Hatziargyriou, Nikos
• Format: Journal Article
• Language: English
• Published: London John Wiley & Sons, Inc 01.06.2023; Wiley
• Subjects: Aircraft; aircraft power systems; Alternative energy sources; Altitude; autonomous aerial vehicles; Efficiency; Energy management; Fatigue tests; Flight; Fuel cells; High altitude; Horsepower; Jet engines; Landing; Mathematical analysis; Parameter estimation; Parameter sensitivity; Propulsion system performance; Renewable energy sources; Surveillance; Systems analysis; Takeoff; Turboprop engines; Unmanned aerial vehicles; Velocity
• ISSN: 2051-3305; 2051-3305
• DOI: 10.1049/tje2.12270

Great efforts are devoted for integrating Renewable Energy Sources (RES) on the propulsion system of Unmanned Air Vehicles (UAVs). This is applicable to small UAVs, having a horizon to expand to large UAVs within the next decades. For the conventional propulsion systems to be replaced, the required power needs of the aircraft should first be examined. The required power depends on the UAV's flight stage from takeoff to landing, whereas its calculation varies with regard to the propulsion system type, which is separated into two main categories, the propelled‐driven engines and the jet engines. Two obstacles are arising. First, the parameters needed for the power estimation are commercially sensitive and second the analysis alters with respect to the engine's type. This paper focuses on the mathematical analysis of the required power for both the main propulsion systems, presented extensively for each flight phase, proposing, at the same time, a parameter estimation method which is applicable to any UAV type. The main purpose of this paper is to act as a guide for the calculation of any type UAV's required power at any flight stage. To validate the analysis, the MQ‐9 Reaper/Predator B, a High Altitude Long Endurance (HALE) turboprop UAV produced by General Atomics is analysed. Its unknown parameters are estimated and based on a selected flight profile, the required power in terms of horsepower from takeoff to landing is assessed, for two scenarios regarding the aircraft's initial weight. In the first scenario the UAV has the maximum gross takeoff weight, whereas in the second scenario it does not carry any payload. The estimated required shaft power per flight phase for each scenario is then marked into the TPE331‐10 turboprop engine characteristic curves. The conventional powered propulsion system of aircraft tends to be replaced partially or in total with an electric one. The appropriate electric power system should cover the aircraft's energy needs for propulsion per flight stage, which is rated in terms of shaft power for propelled driven‐reciprocating engines and in terms of thrust for jet engines, leading on different mathematical approach. The mathematical calculations are difficult, as they require detail knowledge of the aircraft's structure and parameters by the manufacturers, which are proprietary. The authors provide all the equations and diagrams needed for the mathematical analysis, applicable in all aircraft types. The authors propose a guide, rendering the necessary data for the commercially sensitive parameter estimation, applicable in all aircraft types. The authors use a case study, to perform the estimation of an unmanned aerial vehicle's shaft power needed per flight stage, having only its specification sheet. The authors compare the estimated power, with the actual power that the aircraft uses, validating the authors’ methodology.