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.

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.

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.

Conformal s-Shaped Inlet Design and Flow Field Characteristics of Flying Wing Unmanned Aerial Vehicle

2014 ◽  
Vol 940 ◽  
pp. 295-299
Author(s):  
Le Zhang ◽  
Zhou Zhou ◽  
Hong Bo Wang
Keyword(s):  
Power System ◽  
Unmanned Aerial Vehicle ◽  
Flow Characteristics ◽  
Aerodynamic Performance ◽  
Flow Distortion ◽  
Recovery Coefficient ◽  
Area Distribution ◽  
Flow Field Characteristics ◽  
Aerial Vehicle ◽  
The Moment

According to the stealth and conformal requirement of flying wing UAV(Unmanned Aerial Vehicle),an dorsal subsonic S-shaped inlet with long diffuser and large offset is designed. In the light of the characteristics of the inlet, new area distribution is created. In the study, the model with power system and the other model whose pipeline connected are established. The coupled numerical simulation is also carried out on the inflow/outflow integrated for flying wing UAV, and it is applied to study the longitudinal aerodynamic performance of UAV and the flow characteristics of inlet under different flight conditions. Results indicate: The longitudinal aerodynamic performance of the model with power system is close to the model with pipeline connected, but the moment characteristic of the former is better; The inlet characteristics are similar when Ma=0.5 and Ma=0.6; As the mach number increasing, the inlet performance decreases rapidly, Especially at the Ma = 0.7, there is a large low-pressure dominated region at the small angle of attack α = 2°, which leads to the total pressure recovery coefficient decreasing rapidly and the flow distortion increasing obviously.

icarusLabs: An Adventure in Crowdsourcing

2013 ◽  
Vol 01 (02) ◽  
pp. 199-209 ◽  
Author(s):  
Kimberly Jackson ◽  
Justine Li ◽  
Eric Timmons ◽  
Jason Wallace
Keyword(s):  
United States ◽  
Unmanned Aerial Vehicle ◽  
Design Process ◽  
Unique Feature ◽  
The United States ◽  
Lessons Learned ◽  
Unmanned Systems ◽  
Research Projects ◽  
Aerial Vehicle ◽  
Novel Approaches

From September 2011 through May 2012, icarusLabs competed in the UAVForge Competition, sponsored by the United States Defense Advanced Research Projects Agency (DARPA). The objective of the competition was to design and build a small unmanned aerial vehicle (UAV) that could complete a local surveillance mission. A unique feature of the competition was an experimental crowdsourcing model, in which competing teams were able to provide technical feedback to each other as part of the design process. The icarusLabs team's solution to the challenge combined a tricopter and blended wing body aircraft into a single hybrid airframe. This paper presents the rationale and theory behind the design as well as the lessons learned from the technical and logistical challenges faced. In addition, the authors reflect on the crowdsourcing aspect of the challenge from a competitor's perspective. Overall, incentives for individual teams' success directly conflicted with the essence of crowdsourcing, but the competition was successful at stimulating interest to fill a void in current UAV solutions, bringing together passionate individuals from the global unmanned systems community, and generating a broad range of novel approaches to address the presented challenges.

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.

scholarly journals Technical Note: Flow velocity and discharge measurement in rivers using terrestrial and unmanned-aerial-vehicle imagery

2020 ◽  
Vol 24 (3) ◽  
pp. 1429-1445 ◽  
Author(s):  
Anette Eltner ◽  
Hannes Sardemann ◽  
Jens Grundmann
Keyword(s):  
Flow Velocity ◽  
Unmanned Aerial Vehicle ◽  
Cross Section ◽  
Flow Characteristics ◽  
Technical Note ◽  
Surface Flow ◽  
Contactless Measurement ◽  
Aerial Vehicle ◽  
The Impact ◽  
Flow Velocities

Abstract. An automatic workflow to measure surface flow velocities in rivers is introduced, including a Python tool. The method is based on particle-tracking velocimetry (PTV) and comprises an automatic definition of the search area for particles to track. Tracking is performed in the original images. Only the final tracks are geo-referenced, intersecting the image observations with water surface in object space. Detected particles and corresponding feature tracks are filtered considering particle and flow characteristics to mitigate the impact of sun glare and outliers. The method can be applied to different perspectives, including terrestrial and aerial (i.e. unmanned-aerial-vehicle; UAV) imagery. To account for camera movements images can be co-registered in an automatic approach. In addition to velocity estimates, discharge is calculated using the surface velocities and wetted cross section derived from surface models computed with structure-from-motion (SfM) and multi-media photogrammetry. The workflow is tested at two river reaches (paved and natural) in Germany. Reference data are provided by acoustic Doppler current profiler (ADCP) measurements. At the paved river reach, the highest deviations of flow velocity and discharge reach 4 % and 5 %, respectively. At the natural river highest deviations are larger (up to 31 %) due to the irregular cross-section shapes hindering the accurate contrasting of ADCP- and image-based results. The provided tool enables the measurement of surface flow velocities independently of the perspective from which images are acquired. With the contactless measurement, spatially distributed velocity fields can be estimated and river discharge in previously ungauged and unmeasured regions can be calculated, solely requiring some scaling information.

scholarly journals Addressing Autonomy in Conceptual Design

AI Magazine ◽  
2019 ◽  
Vol 40 (2) ◽  
pp. 3-16 ◽  
Author(s):  
Robert Morris ◽  
Anjan Chakrabarty
Keyword(s):  
Conceptual Design ◽  
Unmanned Aerial Vehicle ◽  
Design Process ◽  
Iterative Process ◽  
Autonomous Systems ◽  
Aircraft Design ◽  
Robotic Systems ◽  
Aerial Vehicle ◽  
Initial Process ◽  
Mission Objective

Aircraft design is an iterative process of creating a design concept from a set of requirements. Conceptual design is an early phase in the process, during which preliminary decisions and trade studies are made from a set of requirements related to mission objective and costs. Although much attention has been paid to applying autonomy technologies to robotic systems, including air vehicles, there has been little attention paid to incorporating autonomy as part of the conceptual design process. Consequently, designing for autonomy tends to be retrofitted to a vehicle that has already gone through a complete design process rather than as part of the initial process. This derivative approach to designing autonomous systems is suboptimal, and there is evidence that this has hindered the acceptance of autonomy technologies. This article proposes an approach to conceptual design for aircraft that incorporates autonomy into the conceptual design process. To illustrate the principles introduced, we consider the example of configuring an autonomous small unmanned aerial vehicle for searching and tracking a target of interest.

Sign in / Sign up

Export Citation Format

Share Document