Mission-Based Multidisciplinary Aircraft Design Optimization Methodology Tailored for Adaptive Technologies

Albuquerque, Pedro F.; Gamboa, Pedro; Silvestre, Miguel

doi:10.2514/1.c034403

Cited by 10 publications

(6 citation statements)

References 24 publications

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“…In the above formula, f is the disturbance torque, U p is the pitch channel control signal, K and K sf are the control parameters. The research shows that the attitude stability control loop of pitch channel controlled by classical PID method cannot eliminate the attitude deviation caused by interference [16], [17].…”

Section: ) Control Scheme Of Swcmmentioning

confidence: 98%

An Integrated Scheme of a Smart Net Capturer for MUAVs

Dong

Liu

et al. 2020

IEEE Access

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Micro Unmanned Aerial Vehicles (MUAVs), including consumer-grade ones, have been frequently threatening urban low-altitude security in recent years. This article analyses the necessity to develop specialized technology of anti-MUAVs. Then the article proposes an engineering scheme of a Smart Weapon Capturing MUAVs (SWCM) in an automatic and soft-killing way. The scheme includes a ground subsystem and an aircraft subsystem. The ground subsystem mainly includes optical sighting equipment and handheld launch control device. The aircraft subsystem includes guidance, control, structure, aerodynamic, etc. The design principle of this scheme embodies the technical characteristics of autonomy, high efficiency, low cost and civil-military dual use. The validity of the smart weapon system design is proved by numerical simulations and experiments, and its application is also prospected.INDEX TERMS Anti-MUAVs, civil-military dual use, low altitude security, smart weapon, soft skill.

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Section: ) Control Scheme Of Swcmmentioning

confidence: 98%

An Integrated Scheme of a Smart Net Capturer for MUAVs

Dong

Liu

et al. 2020

IEEE Access

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“…In a review conducted by Papageorgiou et al on the advancements in MDO of aerial vehicles [6] it has been shown that the mass estimation discipline is the second most common discipline when it comes to aerial vehicles design. This is evident since vehicle mass is pivotal to the aerodynamic and performance calculations, which will ultimately be one of the most influential variables in the optimization [7].…”

Section: Mass and Balancementioning

confidence: 99%

Conceptual Design for Long-Endurance Convertible Unmanned Aerial System

Fayez

Leng

Jardin

et al. 2021

AIAA Scitech 2021 Forum

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This research is aimed at analysing the effect of design parameters on critical aerodynamic performance of convertible unmanned aerial vehicle (UAV) with vertical take-off and landing (VTOL) capabilities and providing a sizing tool for its conceptual design. The research was based on new aerodynamic models specifically developed and validated for convertible aircraft, performed using mission-based optimisation techniques.To accommodate a wide range of convertible aircraft configurations, a non-linear lifting-line method was used to efficiently analyse different combinations of lifting surface and propeller arrangements. Propeller loads were calculated using a blade element momentum approach and corrected for high incidence angle conditions according to numerical and experimental studies. Propeller-wing interactions were considered by modifying local boundary conditions at wing sections immersed in propeller slipstream.Previous studies have suggested that the design of convertible aircraft is sensitive to typical mission requirements, notably the endurance breakdown between near-hover flight and cruise flight. A clear sizing law for wing and propeller according to given mission specification could greatly improve the understanding of compromises between hover and high speed flight.

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“…The shape and size of the VSW reference design was obtained through an inhouse computational constrained aerodynamic shape optimization code, aimed at determining the wing mean chord and span values that minimize its drag for the specified mission profile. A detailed description of the aerodynamic optimization procedure is given in [12]. Along with the optimization procedure, two geometrically compatible aerofoils were provided in a way that the OMW slides inside the IFW.…”

Section: Wing Conceptmentioning

confidence: 99%