scholarly journals ALGORITHM DEVELOPMENT FOR BREAK-EVEN ANALYSIS OF UNMANNED AERIAL VEHICLE

2019 ◽  
Vol 11 (2) ◽  
Author(s):  
Muhammad Ridlo Erdata Nasution ◽  
Dhaesa Pramana
Keyword(s):  
Cost Analysis ◽  
Unmanned Aerial Vehicle ◽  
Design Process ◽  
Cost Model ◽  
Unit Price ◽  
Vehicle Design ◽  
Aerial Vehicle ◽  
Break Even Point ◽  
The Cost ◽  
Cost Components

Break-Even Analysis is an important step to be considered in the design process of a product. In order to facilitate this cost analysis in the framework of unmanned aerial vehicle design, a numerical algorithm is proposed and implemented on an in-house software. The developed algorithm adopts the cost components of Modified DAPCA IV Cost Model. It aims to calculate the number of units to achieve Break-Even Point and its corresponding unit price, as well as the obtained profit margin. Three example cases are employed in the assessment of the outcomes of the proposed algorithm, whereby reasonable results and good agreements with theoretical trends are concluded.

Unmanned aerial vehicle derivative design optimization based on light sport aircraft

2016 ◽  
Vol 231 (3) ◽  
pp. 485-496 ◽  
Author(s):  
Hyeong-Uk Park ◽  
Joon Chung ◽  
Jae-Woo Lee ◽  
Daniel Neufeld
Keyword(s):  
Design Optimization ◽  
Unmanned Aerial Vehicle ◽  
Design Process ◽  
Optimization Technique ◽  
Optimization Method ◽  
Vehicle Design ◽  
Baseline Design ◽  
Aerial Vehicle ◽  
Design Requirements ◽  
And Performance

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.

Development of Autonomous Quad-Tilt-Wing (QTW) Unmanned Aerial Vehicle: Design, Modeling, and Control

2010 ◽  
pp. 77-93 ◽  
Author(s):  
Kenzo Nonami ◽  
Farid Kendoul ◽  
Satoshi Suzuki ◽  
Wei Wang ◽  
Daisuke Nakazawa
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Vehicle Design ◽  
Modeling And Control ◽  
Aerial Vehicle ◽  
And Control

Optimisation Studies for an Efficient Aerodynamic Configuration of a Blended Wing Unmanned Aerial Vehicle

2021 ◽  
Vol 13 (2) ◽  
Author(s):  
M.K. Padmanabhan ◽  
G. Santhoshkumar ◽  
Praveen Narayan ◽  
N. Jeevaraj ◽  
M. Dinesh ◽  
...  
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Focal Point ◽  
Lift Coefficient ◽  
Innovative Design ◽  
Aerodynamic Efficiency ◽  
Payload Capacity ◽  
Aerial Vehicle ◽  
Computational Fluid Dynamics Cfd ◽  
The Cost ◽  
Long Endurance

There are various configurations and parameters that contribute to the Design of Unmanned Aerial Vehicles for specific applications. This paper deals with an innovative design of an unmanned aerial vehicle for a specified class of UAVs that require demands such as long endurance, minimized landing space with vertical take-off and landing (VTOL) capabilities. The focal point of this design is superimposing the high endurance blended wing design into tri-copter to address these parameters. The preliminary calculations are initially performed for the blended wing VTOL vehicle based on the required payload capacity and endurance. Superimposing the tri-copter will decrease the aerodynamic efficiency of the vehicle. Computational fluid dynamics (CFD) is a branch of fluid mechanics that uses numerical methods and algorithms to solve complex problems involving fluid flow which will effectively employed to reduce the cost and time during the conceptual and preliminary design stages. CFD analysis was carried out to estimate the major parameters like lift, drag, lift coefficient (CL) and drag coefficient (CD) for various Angle of Attack (AoA) for configurations of blended wing vehicle with and without tri-copter system in the cruise condition. Thus, the vehicle design and propulsion system is effectively optimized using this drag estimation.

scholarly journals Electric Aircraft: Exploiting the Synergy between Powertrain, Energy Management and Structure

2018 ◽  
Vol 233 ◽  
pp. 00026
Author(s):  
Teresa Donateo ◽  
Claudia Lucia De Pascalis ◽  
Antonio Ficarella
Keyword(s):  
Power System ◽  
Evolutionary Algorithm ◽  
Electric Power ◽  
Energy Management ◽  
Unmanned Aerial Vehicle ◽  
Design Process ◽  
Electric Power System ◽  
Multi Objective ◽  
Electric Aircraft ◽  
Aerial Vehicle

This study aims at investigating the synergy between powertrain and structure within the design process of a fixed-wing tail-sitter unmanned aerial vehicle (UAV). The UAV is equipped with a pure-electric power system and has vertical take-off and landing capabilities (VTOL). The problem is addressed by running a contemporary optimization of the parameters of both the powertrain and the UAV’s structure, in order to maximize electric endurance and payload weight through the usage of a performant multi-objective evolutionary algorithm named SMS-EMOA. Three different designs are selected, discussed and compared with literature results on the same UAV to quantify the increase of payload and cruise time that can be obtained by exploiting the synergy between structure and powertrain. The potentiality of furtherly improving payload through the usage of multi-functional panels, while keeping the same endurance, is also quantified and compared with the technologies proposed in literature.

scholarly journals Control and flight test of a tilt-rotor unmanned aerial vehicle

2017 ◽  
Vol 14 (1) ◽  
pp. 172988141667814 ◽  
Author(s):  
Chao Chen ◽  
Jiyang Zhang ◽  
Daibing Zhang ◽  
Lincheng Shen
Keyword(s):  
Unmanned Aerial Vehicle ◽  
High Speed ◽  
Cross Coupling ◽  
Flight Test ◽  
Control Allocation ◽  
Tilt Rotor ◽  
Satisfactory Performance ◽  
Allocation Method ◽  
Aerial Vehicle ◽  
The Cost

Tilt-rotor unmanned aerial vehicles have attracted increasing attention due to their ability to perform vertical take-off and landing and their high-speed cruising abilities, thereby presenting broad application prospects. Considering portability and applications in tasks characterized by constrained or small scope areas, this article presents a compact tricopter configuration tilt-rotor unmanned aerial vehicle with full modes of flight from the rotor mode to the fixed-wing mode and vice versa. The unique multiple modes make the tilt-rotor unmanned aerial vehicle a multi-input multi-output, non-affine, multi-channel cross coupling, and nonlinear system. Considering these characteristics, a control allocation method is designed to make the controller adaptive to the full modes of flight. To reduce the cost, the accurate dynamic model of the tilt-rotor unmanned aerial vehicle is not obtained, so a full-mode flight strategy is designed in view of this situation. An autonomous flight test was conducted, and the results indicate the satisfactory performance of the control allocation method and flight strategy.

scholarly journals Research of Pneumatic Distributors for Launcher of Unmanned Aerial Vehicle (UAV)

2017 ◽  
Vol 43 (1) ◽  
pp. 249-276
Author(s):  
Paweł Szczepaniak ◽  
Michał Jóźko
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Design Process ◽  
Flow Characteristic ◽  
Flow Characteristics ◽  
Flow Simulation ◽  
Test Stand ◽  
Simulation Research ◽  
Aerial Vehicle

Abstract The test stand for investigations of flow characteristics of pneumatic distributor has been presented in this paper. This test stand has been composed as requirements include in standard PN-92/M-73763. The results of experimental and simulation investigations for standard five ways and two position pneumatic distributor have been presented. In simulations have been used CFD of SolidWorks Flow Simulation application. Flow characteristic of pneumatic distributor is necessary for design process of special pneumatic circuits of UAV launchers. CFD methods allow specify flow characteristics. Simulation research allow effective pneumatic components modification, whose used of special pneumatic circuits of UAV launchers. Results of experimental and simulation investigations were analyzed and compared.

Life-cycle cost analysis of a short-haul underground freight transportation system for the DFW Airport

2019 ◽  
Vol 9 (3) ◽  
pp. 440-456
Author(s):  
Seyed Ehsan Zahed ◽  
Sirwan Shahooei ◽  
Ferika Farooghi ◽  
Mohsen Shahandashti ◽  
Siamak Ardekani
Keyword(s):  
Life Cycle ◽  
Cost Analysis ◽  
Life Cycle Cost ◽  
Freight Transportation ◽  
Cash Flows ◽  
Research Approach ◽  
Life Cycle Cost Analysis ◽  
Content Type ◽  
The Cost ◽  
Cost Components

Purpose The purpose of this paper is to conduct life-cycle cost analysis of a short-haul underground freight transportation (UFT) system for the Dallas Fort Worth international airport. Design/methodology/approach The research approach includes: identifying the cost components of the proposed airport UFT system; estimating life-cycle cost (LCC) of system components using various methods; determining life-cycle cash flows; evaluating the reliability of the results using sensitivity analysis; and assessing the validity of the results using analogues cases. Findings Although the capital cost of constructing an airport UFT system seems to be the largest cost of such innovative projects, annual costs for running the system are more significant, taking a life-cycle perspective. System administrative cost, tunnel operation and maintenance, and tunnel construction cost are the principle cost components of the UFT system representing approximately 46, 24 and 19 percent of the total LCC, respectively. The shipping cost is estimated to be $4.14 per ton-mile. Although this cost is more than the cost of transporting cargos by trucks, the implementation of UFT systems could be financially justified considering their numerous benefits. Originality/value This paper, for the first time, helps capital planners understand the LCC of an airport UFT system with no or limited past experience, and to consider such innovative solutions to address airport congestion issues.

Predicated Partial Redundancy Elimination using a Cost Analysis

2003 ◽  
Vol 13 (04) ◽  
pp. 525-536
Author(s):  
Bernhard Scholz ◽  
Eduard Mehofer ◽  
Nigel Horspool
Keyword(s):  
Cost Analysis ◽  
Cost Model ◽  
Code Size ◽  
Redundancy Elimination ◽  
Key Technology ◽  
Flow Information ◽  
Partial Redundancy Elimination ◽  
The Cost ◽  
Traditional Approaches ◽  
Partial Redundancy

Partial redundancy elimination (PRE) is a key technology for modern compilers. However traditional approaches are conservative and fail to exploit many opportunities for optimization. New PRE approaches which greatly increase the number of eliminated redundancies have been developed. However, they either cause the code size to explode or they cannot handle statements with side-effects. In this paper we describe a predicated partial redundancy elimination (PPRE) approach which can potentially remove all partial redundancies. To avoid performance overheads caused by predication, PPRE is applied selectively based on a cost model. The cost analysis presented in the paper utilizes probabilistic data-flow information to decide whether PPRE is profitable for each instance of a partially redundant computation. Refinements of the basic PPRE transformation are described in detail. In contrast to some other approaches our transformation is strictly semantics preserving.

CU-24: Unmanned Aerial Vehicle Design for Long Endurance

2009 ◽  
Author(s):  
Andrew Lind ◽  
Eric Liu ◽  
Roland Florenz ◽  
Honghao (Long-Long) Tien ◽  
C Avedisian ◽  
...  
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Vehicle Design ◽  
Aerial Vehicle ◽  
Long Endurance
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