Multi-objective stochastical revision of piston-prop MUAV for maximization of autonomous performance, range, endurance and ceiling altitude

In this research article the contribution of multi-objective stochastical revision of a mini unmanned aerial vehicle (i.e., MUAV) having liquid fuel piston-propeller powerplant system via redesigning its automatic flight control system (i.e., AFCS), “fuel weight/total weight” ratio, and propeller pitch for recovering both of autonomous flight performance and also general flight performance terms (i.e., maximum range, maximum endurance, and maximum ceiling altitude) is investigated. For this aim a piston-prop MUAV is manufactured in Ankara Yıldırım Bayezit University (i.e., AYBU) Drone Laboratory (i.e., DL) and named as piston-prop AYBU-MUAV. Some properties of this MUAV are as following: Its total mass is 2.2 kg, its wing span is 1.25 m, its wing aspect ratio is 6.25, and its powerplant is liquid-fuel powered two-stroke piston-prop engine. Its AFCS variables which are PID coefficients, its “fuel weight/total weight” ratio and its engine propeller pitch are simultaneously and stochastically revised with a multi-objective approach in order to maximize both autonomous flight performance and general flight performance via using a definite stochastic optimization methodology. Found revision fallouts are used meanwhile autonomous flight simulation of piston-prop MUAV. The first vital output of this research article is using simultaneous and stochastical revision approach during reaching optimum solutions of AFCS variables, “fuel weight/total weight” ratio, and engine propeller pitch. Another vital contribution of this research article is applying SPSA (i.e., simultaneous perturbation stochastical approximation) optimization policy for the previously stated aim. These significant contributions also reason much less fuel consumption and also green nature. Additionally, around %30 improvement in total cost index, %42 improvement in autonomous cost index and %12.6 improvement in general flight cost index (i.e., capturing terms relevant with range, endurance, and ceiling altitude) are found for this mentioned liquid fuel piston-prop MUAV with regard to the circumstance where simultaneous and stochastical revision idea is not benefitted.