Uncertainty based aircraft derivative design for requirement changes

Park, Hyeong-Uk; Chung, Joon; Neufeld, Daniel

doi:10.1017/aer.2015.17

Cited by 4 publications

(5 citation statements)

References 30 publications

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“…Figure 6 and Table I show its dimensions and specifications (Park et al , 2016; Found Aircraft). The main objective of the UAV derivative is payload delivery.…”

Section: Unmanned Aerial Vehicle Derivative Design and Virtual Flight Test – Case Studymentioning

confidence: 99%

“…The interior was horizontally split where the upper section was used for fuselage fuel tank and the lower section was used for payload bay, as seen in Figure 8. The fuel tank volume in the wing, fuselage geometry and the location of the wings were fixed (Park et al , 2016).…”

Section: Unmanned Aerial Vehicle Derivative Design and Virtual Flight Test – Case Studymentioning

confidence: 99%

“…The framework covers the selection of the aircraft, the conceptual design of its derivative by using the multidisciplinary design optimization (MDO) technique and a virtual flight test of the optimized model to verify the performance of the aircraft. The baseline aircraft was optimized into a conceptual unmanned aerial vehicle (UAV) derivative, and the design optimization results were implemented in the simulation software for the flight test (Park et al , 2016). X-Plane was selected as the main simulation software because past research has used it for aircraft design and flight tests (Garcia and Barnes, 2010; Kaviyarasu and Kumar, 2014; Lu et al , 2014; Bittar et al , 2014; Coombes et al , 2014; Bittar and De Oliveria, 2013).…”

Section: Introductionmentioning

confidence: 99%

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Application of virtual flight test framework with derivative design optimization

Park

Chung

Kwon

2018

AEAT

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Purpose The purpose of this paper is a development of a virtual flight test framework with derivative design optimization. Aircraft manufactures and engineers have been putting significant effort into the design process to lower the cost of development and time to a minimum. In terms of flight tests and aircraft certification, implementing simulation and virtual test techniques may be a sufficient method in achieving these goals. In addition to simulation and virtual test, a derivative design can be implemented to satisfy different market demands and technical changes while reducing development cost and time. Design/methodology/approach In this paper, a derivative design optimization was applied to Expedition 350, a small piston engine powered aircraft developed by Found Aircraft in Canada. A derivative that changes the manned aircraft to an Unmanned Aerial Vehicle for payload delivery was considered. An optimum configuration was obtained while enhancing the endurance of the UAV. The multidisciplinary design optimization module of the framework represents the optimized configuration and additional parameters for the simulator. These values were implemented in the simulator and generated the aircraft model for simulation. Two aircraft models were generated for the flight test. Findings The optimization process delivered the UAV derivative of Expedition E350, and it had increased endurance up to 21.7 hours. The original and optimized models were implemented into virtual flight test. The cruise performance exhibited less than 10 per cent error on cruise performance between the original model and Pilots Operating Handbook (POH). The dynamic stability of original and optimized models was tested by checking Phugoid, short period, Dutch roll and spiral roll modes. Both models exhibited stable dynamic stability characteristics. Practical implications The original Expedition 350 was generated to verify the accuracy of the simulation data by comparing its result with actual flight test data. The optimized model was generated to evaluate the optimization results. Ultimately, the virtual flight test framework with an aircraft derivative design was proposed in this research. The additional module for derivative design optimization was developed and its results were implemented to commercial off-the-shelf simulators. Originality/value This paper proposed the application of UAV derivative design optimization for the virtual flight test framework. The methodology included the optimization of UAV derivative utilizing MDO and virtual flight testing of an optimized result with a flight simulator.

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“…Figure 6 and Table I show its dimensions and specifications (Park et al , 2016; Found Aircraft). The main objective of the UAV derivative is payload delivery.…”

Section: Unmanned Aerial Vehicle Derivative Design and Virtual Flight Test – Case Studymentioning

confidence: 99%

Section: Unmanned Aerial Vehicle Derivative Design and Virtual Flight Test – Case Studymentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Application of virtual flight test framework with derivative design optimization

Park

Chung

Kwon

2018

AEAT

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“…The analysis tools were evaluated in the previous research of general aircraft design optimization. 20,46…”

Section: Uav Derivative Designmentioning

confidence: 99%

“…In this research, the requirements of flying and handling qualities for small aircraft from the military specification (MIL-F-8785 C) were applied. 33,46…”

Section: Uav Derivative Designmentioning

confidence: 99%

Unmanned aerial vehicle derivative design optimization based on light sport aircraft

Park

Chung

Lee

et al. 2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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Manufacturers often develop new products by modifying and extending existing products in order to achieve new market demands while minimizing development time and manufacturing costs. In this research, an efficient derivative design process was developed to efficiently adapt existing aircraft designs according to new requirements. The proposed design process was evaluated using a case study that derives an unmanned aerial vehicle design from a baseline manned 2-seatlight sport aircraft. Multiple unmanned aerial vehicle operational scenarios were analysed to define the requirements of the derivative aircraft. These included patrol, environmental monitoring, and communications relay missions. Each mission has different requirements and therefore each resulting derivative unmanned aerial vehicle design has different geometry, devices, and performance. The derivative design process involved redefining the design requirements and identifying the minimum design variable set that needed to be considered in order to efficiently adapt the baseline design. Uncertainty was considered as well to enhance the reliability of the optimized result when it considered different conditions for each mission. An optimization method based on the possibility based design optimization was proposed to handle uncertainty that arises in the design requirements for the multi-role nature of unmanned aerial vehicles. In this paper, the possibility based design optimization method was implemented with multidisciplinary design optimization technique to derive the derivative unmanned designs based on originally manned aircraft. This approach prevented constraint violation via uncertainty variations in the operating altitude and payload weight for each. The unmanned aerial vehicle derivative designs satisfying the requirements of three different missions were derived from the proposed design process.

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Designer Systems of Systems: A Rational Integrated Approach of System Engineering to Tailored Aerodynamics, Aeroelasticity, Aero-viscoelasticity, Stability, Control, Geometry, Materials, Structures, Propulsion, Performance, Sizing, Weight, Cost

Hilton

D'Urso

Wiener

2016

Transdisciplinary Perspectives on Complex Systems

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Uncertainty based aircraft derivative design for requirement changes

Cited by 4 publications

References 30 publications

Application of virtual flight test framework with derivative design optimization

Application of virtual flight test framework with derivative design optimization

Unmanned aerial vehicle derivative design optimization based on light sport aircraft

Designer Systems of Systems: A Rational Integrated Approach of System Engineering to Tailored Aerodynamics, Aeroelasticity, Aero-viscoelasticity, Stability, Control, Geometry, Materials, Structures, Propulsion, Performance, Sizing, Weight, Cost

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