Rapid Air System Concept Exploration - A Parametric Physics Based System Engineering Design Model

International Journal of Turbo &Amp; Jet-Engines

2016

In this study, a genuine code was developed for optimization of selected parameters of a turboprop engine for an unmanned aerial vehicle (UAV) by employing elitist genetic algorithm. First, preliminary sizing of a UAV and its turboprop engine was done, by the code in a given mission profile. Secondly, single and multi-objective optimization were done for selected engine parameters to maximize loiter duration of UAV or specific power of engine or both. In single objective optimization, as first case, UAV loiter time was improved with an increase of 17.5% from baseline in given boundaries or constraints of compressor pressure ratio and burner exit temperature. In second case, specific power was enhanced by 12.3% from baseline. In multi-objective optimization case, where previous two objectives are considered together, loiter time and specific power were increased by 14.2% and 9.7% from baseline respectively, for the same constraints.

Section: Introductionmentioning

confidence: 99%

“…Those parametric codes are typically used for concept exploration. Rapid Air System Concept Exploration (RASCE) is one example to parametric UAV conceptual design tools which was originally developed as an educational tool to support undergraduate student exploration [3].…”

Section: Introductionmentioning

confidence: 99%

Optimization of a Turboprop UAV for Maximum Loiter and Specific Power Using Genetic Algorithm

International Journal of Turbo &Amp; Jet-Engines

2016

“…Those tools have been modified for UAV specific needs from concept study to detail design. Rapid air system concept exploration (RASCE) is one sample to parametric UAV conceptual design tools, which was originally developed as an educational tool to support undergraduate student study (Chaput, 2010). Aircraft conceptual design tools need a propulsion model or data set.…”

Section: Introductionmentioning

confidence: 99%

“…That is to say, aircraft designers need a performance data set of an existing engine or a detailed generic engine model for propulsion calculations. For example in RASCE tool, some aircraft engine models are included (Chaput, 2010). Detailed propulsion models can increase the accuracy of these kinds of tools.…”

Section: Introductionmentioning

confidence: 99%

Optimization of turboprop ESFC and NOx emissions for UAV sizing

2017

AEAT

Purpose This paper aims to present a genuine code developed for multi-objective optimization of selected parameters of a turboprop unmanned air vehicle (UAV) for minimum landing-takeoff (LTO) nitrogen oxide (NOx) emissions and minimum equivalent power specific fuel consumption (ESFC) at loiter (aerial reconnaissance phase of flight) by using a genetic algorithm. Design/methodology/approach The genuine code developed in this study first makes computations on preliminary sizing of a UAV and its turboprop engine by analytical method for a given mission profile. Then, to minimize NOx emissions or ESFC or both of them, single and multi-objective optimization was done for the selected engine design parameters. Findings In single objective optimization, NOx emissions were reduced by 49 per cent from baseline in given boundaries or constraints of compressor pressure ratio and compressor polytropic efficiency in the first case. In second case, ESFC was improved by 25 per cent from baseline. In multi-objective optimization case, where previous two objectives were considered together, NOx emissions and ESFC decreased by 26.6 and 9.5 per cent from baseline, respectively. Practical implications Variation and trend in the NOx emission index and ESFC were investigated with respect to two engine design parameters, namely, compressor pressure ratio and compressor polytropic efficiency. Engine designers may take into account the findings of this study to reach a viable solution for the bargain between NOx emission and ESFC. Originality/value UAVs have different flight mission profiles or characteristics compared to manned aircraft. Therefore, they are designed in a different philosophy. As a number of UAV flights increase in time, fuel burn and LTO NOx emissions worth investigating due to operating costs and environmental reasons. The study includes both sizing and multi-objective optimization of an UAV and its turboprop engine in coupled form; compared to manned aircraft.

Preliminary Sizing and Performance Calculations of Unmanned Air Vehicles

Automated Systems in the Aviation and Aerospace Industries

2019

In this chapter, preliminary sizing and performance calculations of unmanned air vehicles (UAV), with relation to its propulsion system, are explained. Starting with the mission profile of the air vehicle, which is one of the important design drivers, the UAV is sized for the requirements. The requirements in design consist of a set of target values (e.g., payload amount to be carried, range, endurance time, cost, etc.). Additionally, the parameters within mission profile such as cruising altitude and speed of aircraft affect engine type, power level required, fuel quantity, and therefore general dimensions and the gross weight of the aircraft. It is often an iterative process to size the air vehicle and engine together. UAV is designed in a loop of calculations in which sizing, flight performance, and engine performance are done for each phase of the mission or flight profile to satisfy the overall design mission and requirements.