Designing Unmanned Aircraft Systems: A Comprehensive Approach, Second Edition

Gundlach, Jay

doi:10.2514/4.102615

Cited by 115 publications

(137 citation statements)

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“…There are two aspects of survivability, susceptibility, related to the probability of the aircraft being detected and hit by the enemy and vulnerability, related to the probability of the aircraft withstanding the battle damage. As described by Gundlach [76], there is a kill chain, associated with potential battle damage, first the aircraft must be detected, then once detected, to be targeted and hit and finally once hit, to be destroyed.…”

Section: Survivability Assessmentmentioning

confidence: 99%

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Development and application of a value driven design assessment framework to an unmanned air system design

Papageorgiou

2018

2018 Advances in Science and Engineering Technology International Conferences (ASET)

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The work presented in this thesis concerns the development of a value driven engineering design assessment framework and its application to the conceptual design of an Unmanned Air System (UAS) to be utilised in a defence application. This research demonstrates the implementation of the value driven design philosophy in this framework, identifying value enhancing designs, with value not converted to monetary worth and as perceived by all stakeholders involved. A multi-criteria and multi-stakeholder decision making analysis is adopted to address their preferences as well as to study their interacting strategic choices. The ultimate objective of this framework is to convert engineering design to a decision making analysis with multiple conflicting objectives of multiple stakeholders considered.This framework is capable of providing a product definition and estimation of all performance and cost related attributes for the conceptual phase. However, instead of pertaining to a single aircraft concept, a broad range of combinations of UAS configurations and geometries is generated by systematically searching alternative concepts and design configurations through a novel parameterization of the aircraft geometric topologies.Value, related to the designed system's capabilities or performance and lifecycle cost, is used to compare different alternatives in the decision making of engineering design through the appropriate value model. Following a valuefocused approach, a novel multi-attribute value model is introduced for objectively capturing the stakeholder's preferences and expectations. Furthermore, a more sophisticated multi-attribute utility model, based on standard Multi-attribute Utility Theory, is employed in the evaluation.Game Theory as an optimization tool is used to develop a novel hybrid cooperative/non-cooperative non-zero sum, complete information game among all involved stakeholders as players. This game successfully addresses the stakeholders' preferences in a functional outcome-focused way, resolving the high indeterminacy of the alternative designs through a cooperative game. At the same time, their strategic interactions are captured in a process-focused non-cooperative game. Hence, the optimal design is identified through the simultaneous employment of the Nash bargaining solution and the Nash equilibrium.i

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Section: Survivability Assessmentmentioning

confidence: 99%

“… Visual detection of reconnaissance aircraft from ground observers was studied by Dugas [90], and it is the design parameters of aircraft effective size, such as wing span, overall length, total area that greatly affect visual detection, [76].…”

Section: Survivability Assessmentmentioning

confidence: 99%

Development and application of a value driven design assessment framework to an unmanned air system design

Papageorgiou

2018

2018 Advances in Science and Engineering Technology International Conferences (ASET)

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“…Fuel and fuel system: According to Kundu [20] fuel can be accounted as 20% of the TOGW . Whilst, Gundlach [21] mentions that fuel system can be estimated as 10% of the fuel weight.…”

Section: 24mentioning

confidence: 99%

Weight assessment for a blended wing Body-Unmanned aerial vehicle implementing boundary layer ingestion

Valencia

Alulema

Hidalgo

2018

IOP Conf. Ser.: Mater. Sci. Eng.

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Abstract. Boundary Layer Ingestion (BLI) has been studied extensively for implementation in Blended Wing Body (BWB) transport aircrafts, and it has been reported that BLI offers potential benefits mainly in terms of energy, improving the propulsive efficiency of a propulsion system and reducing the fuel consumption. This paper examines potential benefits of BLI related with a reduction on the Take-Off Gross Weight (TOGW) for a BWB-Unmanned Aerial Vehicle (UAV). It is discussed the methodology for weight estimation of a BWB-UAV through parametric models. To evaluate the benefits of BLI in terms of weight reduction, it has been taken into account the removal of pylons and the nacelle weight reduction when embedding nacelles into the airframe. The validation of the parametric models, and the case of study have been carried out for the aircraft NASA X-48B. The results show a reduction in TOGW between 8% and 19% when removing pylons and embedding nacelles into the airframe. IntroductionThe benefits of boundary layer ingestion (BLI) have been evaluated extensively with a special focus on Blended Wing Body (BWB) transport aircrafts. Most of previous studies about BLI for transport aircrafts have focussed mainly on design of inlets, reduction on fuel consumption, improvement of propulsive efficiency, ram and viscous drag reduction, aeroacoustics effects, and flow control at duct inlet. In 1998, Liebeck [1] introduces BLI in the design of a subsonic BWB transport aircraft, and the results show a reduction of 13% on thrust to weight ratio, and a reduction of 27% on fuel burned, compared to a conventional aircraft operating at the same conditions. Rodriguez [2] performed a multidisciplinary design optimization (MDO) of BLI inlets, and estimated a reduction of 3.7% in fuel burn rate, and 2.3% in total drag coefficient. In 2004, a design optimization of a BWB subsonic transport was developed by Liebeck [3]; in his work, BLI was evaluated experimentally, simulating the boundary layer over a flat plate and testing different duct geometries. A. Plas [4] assessed the performance of a BLI propulsion system; to evaluate the benefits of BLI in terms of energy, Plas considered power saving coefficient as figure of merit. For the "Silent aircraft", Plas estimated a power saving between 3% and 4% when embedding nacelles into the BWB airframe [4].Campbell [5] and Carter [6] designed and tested 2 scale models of a BWB aircraft: a clean wing BWB, and a BWB with BLI nacelles. These studies determined aerodynamic coefficients for both configurations and evaluated the Propulsor-Airframe Integration (PAI) through computational fluid dynamics (CFD) and wind tunnel experiments at high Reynolds numbers about 75 million and a Mach number of 0.85 [6].

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“…The parameter n(j) = 2 j -1 and the indices i and j go from 1 to N. Solving equation (5), the section lift coefficient at station i can be calculate by (12) Finally, the total lift coefficient of the wing and the induced drag are: …”

Section: (8)mentioning

confidence: 99%

“…As derivation of the numerical lifting-line theory suitable for nonlinear lift-curve slopes [11], which is useful for analyzing wings near and beyond stall angle of attack, the present code is based on a matrix form was developed for subsonic applications [12].…”

Section: Mathematical Modelmentioning

confidence: 99%