Design and Human-in-the-loop Simulation of Radio Controlled Fixed Wing Aircraft

Vrdoljak, Milan; Prebeg, Pero; Barać, Mirna Inge; Andrić, Marijan

doi:10.23919/splitech49282.2020.9243722

Cited by 1 publication

(2 citation statements)

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“…Afterwards, the maximum power P max for the given speed is determined using the power-speed curve (Figure 6a), and the full throttle thrust is obtained using the thrust-speed curve (Figure 6b). The output thrust given the actual throttle setting (and battery state) is finally obtained using Equation (6).…”

Section: Propulsionmentioning

confidence: 99%

“…Since ACC is a demanding multidisciplinary design problem, no single work has been published covering all relevant coupled disciplines. Among the few published works, excluding academic bachelor and master theses, the most significant scientific documents reveal emphasis on singular disciplines, such as aerodynamic design [2,3], mass prediction models [4], parametric geometric definition [5] or flight dynamics and control [6].…”

Section: Introductionmentioning

confidence: 99%

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Concurrent Trajectory Optimization and Aircraft Design for the Air Cargo Challenge Competition

Matos

Marta

2022

Aerospace

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A coupled aerostructural aircraft design and trajectory optimization framework is developed for the Air Cargo Challenge competition to maximize the expected score based on cargo carried, altitude achieved and distance traveled. Its modular architecture makes it easily adaptable to any problem where the performance depends not only on the design of the aircraft but also on its flight trajectory. It is based on OpenAeroStruct, an aerostructural solver that uses analytic derivatives for efficient gradient-based optimization. A trajectory optimization module using a collocation method is coupled with the option of using b-splines to increase computational efficiency together with an experimentally-based power decay model that accurately determines the aircraft propulsive response to control input depending on the battery discharge level. The optimization problem totaled 206 variables and 283 constraints and was solved in less than 7 h on a standard computer with 12% reduction when using b-splines for trajectory control variables. The results revealed the need to consider the multi-objective total score to account for the different score components and highlighted the importance of the payload level and chosen trajectory. The wing area should be increased within allowable limits to maximize payload capacity, climb to maximum target height should be the focus of the first 60 s of flight and full throttle should be avoided in cruise to reduce losses and extend flight distance. The framework proved to be a valuable tool for students to easily obtain guidelines for both the model aircraft design and control to maximize the competition score.

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Section: Propulsionmentioning

confidence: 99%