Verification of Simulation Results Using Scale Model Flight Test Trajectories

2004 ◽  
Author(s):  
Jeff Obermark
Keyword(s):  
Flight Test ◽  
Scale Model ◽  
Simulation Results

scholarly journals UAS as flexible and innovative test platform for aircraft configuration and systems testing

2018 ◽  
Vol 233 ◽  
pp. 00001
Author(s):  
Dominique Paul Bergmann ◽  
Jan Denzel ◽  
Andreas Strohmayer
Keyword(s):  
Financial Risk ◽  
New Technologies ◽  
Aircraft Design ◽  
Flight Test ◽  
Scale Model ◽  
Efficient Test ◽  
Consumption Reduction ◽  
Test Platform ◽  
Cost Efficient ◽  
Configuration Changes

Today new technologies are available, which can be decisive for the success of future aircraft design. However, the gap between conventional designs and new visions often comes with a high financial risk. This complicates the integration of innovations significantly. The “Flightpath 2050 Europe’s Vision for Aviation” asks for new aircraft concepts and configurations to meet future requirements such as emission (CO2, NOx), noise and fuel consumption reduction. Scaled UAS are one way for getting new configurations and technologies into flight test while reducing the risk of exploding costs. UAS are cost-efficient test platform systems for two main tasks of future aircraft tests: Testing new configurations and advancing new aircraft systems and technologies from upstream research to TRL5-6. UAS can represent a connection between innovative research and flight demonstration. This paper focuses on the UAS as an innovative test platform and a tool for feasibility demonstration as well as its impact on new technologies and the implementation of innovative concepts. An example of a UAS test platform is given in the paper based on a 33,3% scale model of the e-Genius. It is developed as flying wind tunnel in order to better understand the effects of configuration changes on flight performance.

Roll aerodynamic characteristics study of an unmanned aerial vehicle based on circulation control technology

2017 ◽  
Vol 233 (3) ◽  
pp. 871-882
Author(s):  
Kun Chen ◽  
Zhiwei Shi ◽  
Jiachen Zhu ◽  
Haiyang Wang ◽  
Junquan Fu
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Flight Control ◽  
Attitude Control ◽  
Aerodynamic Force ◽  
Flight Test ◽  
Scale Model ◽  
Maximum Efficiency ◽  
Control Technology ◽  
Circulation Control ◽  
Aerial Vehicle

To explore the control efficiency of circulation flow control technology, a circulation control actuator with an independent gas source has been designed and applied in roll attitude control of a small unmanned aerial vehicle. The circulation control devices are arranged at the two ends of the wing on an unmanned aerial vehicle scale model, the changes in aerodynamic force and aerodynamic moment caused by turning on the actuator are measured in a wind tunnel, and the flow field characteristics are analysed using particle image velocimetry technology. The flight control effect of the roll attitude is verified via a flight test. Experimental and flight test results show that the control of roll attitude can be achieved by turning on the circulation control actuator on one side, and the maximum efficiency that the circulation control generates is equivalent to 8° aileron deflection with production of a favorable yaw moment to achieve a coordinated turn. The circulation control actuator can increase lift and reduce drag when opened on both sides simultaneously. The maximum lift-to-drag ratio of the UAV increased from 5 to 9, and this approach can also suppress flow separation and delay stall at high angles of attack. The aileron or trailing edge flaps can be replaced with circulation control actuators, and the circulation control technology can also be applied to aerodynamic performance improvement and flight control in other types of aircraft.

Study of Nanocutting Using Atomic Model

2008 ◽  
Vol 33-37 ◽  
pp. 963-968
Author(s):  
Chun Yi Chu ◽  
Chung Ming Tan ◽  
Yung Chuan Chiou
Keyword(s):  
Molecular Dynamics ◽  
Energy Minimization ◽  
Atomic Scale ◽  
Scale Model ◽  
Atomistic Simulations ◽  
Cutting Depth ◽  
Cutting Deformation ◽  
Simulation Results ◽  
Model Approach

The stress induced in a workpiece under nanocutting are analyzed by an atomic-scale model approach that is based on the energy minimization. Certain aspects of the deformation evolution during the process of nanocutting are addressed. This method needs less computational efforts than traditional molecular dynamics (MD) calculations. The simulation results demonstrate that the microscopic cutting deformation mechanism in the nanocutting process can be regarded as the instability of the crystalline structure in our atomistic simulations and the surface quality of the finished workpiece varies with the cutting depth.

Divergence Prediction for Practical Helicopter Slung Loads

2016 ◽  
Author(s):  
Nicholas Motahari ◽  
Thomas Kim ◽  
Dhwanil Shukla ◽  
Nandeesh Hiremath ◽  
Narayanan Komerath
Keyword(s):  
Bluff Body ◽  
General Pattern ◽  
Oscillation Amplitude ◽  
Flight Test ◽  
Scale Model ◽  
Aerodynamic Load ◽  
Stable Operation ◽  
Rotation Method ◽  
Angle Data ◽  
Continuous Rotation

Certifying the highest safe speed for an aircraft with a slung load, is life-critical yet daunting. Two flight cases are considered, to test an iterative procedure that predicts the divergence speed from experimental scale model data and simulations. The first is an empty engine canister. The second is a segment of a water-floatable military Ribbon Bridge. In each case, mass, geometry, tether length from a single rotation-bearing attachment, and moments of inertia, come from flight preparations. An initial aerodynamic load map is interpolated and synthesized from a growing library on bluff body aerodynamics. Dynamic simulation with these data predict maximum roll, pitch and yaw angles reached as functions of freestream speed. This yieldw a good initial estimate of critical speeds and dynamics. Model-scale wind tunnel data using our Continuous Rotation method about the required axes, refine simulation. For the engine canister, simulations matched detailed flight test data on maximum trailing and rolling amplitudes over the operational speed range. Trail angle data showed that Reynolds number errors are not significant. In this paper, model-based results explained the correct speed where the ribbobn bridge flight test was stopped. While flight test oscillation amplitude histories depend on initial perturbations of the load, a 15-degree initial amplitude gives conservative results. Ribbon bridge airloads resemble those on a long container but with asymmetries. Dynamic behavior follows the general pattern of an intermediate hump in roll amplitude followed by stable operation at higher speeds until divergence occurs.

A Comparative Study of Corrosion Related Electro-Magnetic Field Control Effect

2011 ◽  
Vol 239-242 ◽  
pp. 450-454
Author(s):  
Jian Hua Wu ◽  
Shao Hua Xing ◽  
Cheng Hao Liang ◽  
Yong Gui Yan
Keyword(s):  
Magnetic Field ◽  
Scale Model ◽  
Control Effect ◽  
Electro Magnetic Field ◽  
Physical Scale ◽  
Magnetic Signature ◽  
Field Control ◽  
Simulation Results ◽  
Electromagnetic Signature ◽  
Electro Magnetic

The corrosion related electro-magnetic signature is easily detected by modern sensor deployed in mine and other signal measurement system, so the importance of reducing is rapidly growing today. The eliminating effect of shaft frequency signature by shaft insulating technique, passive grounding technique and active grounding technique was comparatively studied by physical scale model (PSM), and their influence on static electromagnetic signature was also studied by boundary element method (BEM). Simulation results suggested that active shaft grounding technique was the best way for eliminating shaft frequency signature, but static electromagnetic signature was stronger than that when the shaft was insulated from hull.

scholarly journals ANALYSIS OF SAR MAIN PARAMETERS FOR SAR SENSOR DESIGN ON LSA

2017 ◽  
Vol 11 (2) ◽  
pp. 85
Author(s):  
Muchammad Soleh ◽  
Rahmat Arief
Keyword(s):  
Optical Sensors ◽  
Imaging System ◽  
Flight Test ◽  
Imaging Technology ◽  
Range Resolution ◽  
Fundamental Parameters ◽  
Slant Range ◽  
Sar Imaging ◽  
Simulation Results ◽  
Pseudo Data

LAPAN plans to conduct a flight test of LSA (LAPAN Surveillance Aircraft). LSA STEMME-S15 is capable of carrying sensor payloads up to 160 kg that are mounted on both sides of the wings with altitude between 400-2000 m. LSA can be designed to perform imaging by using optical sensors and SAR (Synthetic Aperture Radar). Compared to imaging using optical sensors, SAR sensor has advantages such as it can operate all day and night, able to penetrate clouds, and able to see objects from side looking, while optical sensors generally see the object perpendicular to the ground. Therefore the use of SAR imaging technology can complement optical imaging technology. To design SAR system imagers on LSA, it is necessary to simulate the primary parameters SAR i.e. altitude and look angle of sensor, speed of LSA, SAR frequency and signals power shot to object to calculate the resolution of azimuth and ground range values that can be obtained. This SAR parameters simulation used MATLAB which have been designed with two approaches; the first approach where the SAR sensor is ideal and in which all the fundamental parameters (such as polarization, frequency, etc.) are used to generate the desired sensitivity and resolution of azimuth and ground range, and the second approach is where SAR sensor is designed in a limited antenna size (constraint case), with the assumption that the dimensions of the antenna and the average available power are fixed. The data used in this simulation is a pseudo-data obtained from LSA technical spesification and SAR sensor. The simulation results with the first approach shows that if LSA is flying at an altitude of 1000 m, with speed of 36.11 m/s, and SAR frequency of 5.3 GHz, then to get resolution of azimuth, slant range and ground range of 1 m, 1.2 m and 3 m, it is necessary to design the length and width of SAR antenna at 2 m and 13.5 cm, with look angle of 23.5 degrees. While the result of second approach simulation is that if LSA is flying on the same altitude and speed, on the same look angle and SAR frequency, with a particular design of antenna length and width of 2 m and 13.5 cm, then azimuth, slant range and ground range resolution of 1 m, 1.87 and 4.79 m will be obtained. Form both simulations, it can be concluded that limited SAR system on LSA, especially on the technical aspects of mounting and space as in the simulation with the second approach, will produce slightly lower slant range and ground range resolution when compared with SAR system in the first simulation. This shows that space limitation on LSA will affect decrease the value of spatial ground range resolution. The simulation results are expected to be inputs on designing SAR imaging system on LSA.

scholarly journals Comparative Study on Computer Simulation of Solar Shading Performance with Heliodon and Artificial Sky

2021 ◽  
Vol 8 (1) ◽  
pp. 50-64
Author(s):  
David B. Dalumo ◽  
◽  
Yaik-Wah Lim ◽  
◽  
Keyword(s):  
Mechanical Design ◽  
Early Stage ◽  
Computational Simulation ◽  
Physical Experiment ◽  
Scale Model ◽  
Technological Advancement ◽  
Efficient Design ◽  
Evaluation Approach ◽  
Solar Shading ◽  
Simulation Results

Current technological advancement and the requirement for sustainability-driven practices has birthed increased demands for accuracy in performance and assessment of energy consumption in the built environment. Energy-efficient and sustainable building projects are to large extents dependent on achieving functional solar shading and sufficient daylighting in building interiors. Hence, the understanding and adequate evaluation of the sun and its dynamic influence on buildings right at the early stage of planning and design is essential for the development of performance-driven building designs. In this study, the performance simulation results of Integrated Environmental Solutions <Virtual Environment> software program modules are examined for accuracy in executing performance analysis of solar shading. This study assesses the shading prediction of Suncast; a virtual solar shading calculation tool, and RadianceIES for measuring daylight availability in a tropical climate region. The evaluation of shading performance with Suncast was validated through physical experiment by comparing the results obtained therein with shading analysis outcomes generated on a scale model with the aid of a heliodon. Likewise, RadianceIES daylighting simulations were compared with measurements realised from an artificial sky simulator. The results were further subjected to correlation tests to determine the relationship between simulation and physical experiment results. The computational evaluation approach presented more efficient means of conducting the performance simulations over the physical experiment methods which were limited by mechanical design of the components. Suncast and RadianceIES simulation results presented comparable equivalence with measurement output acquired from the heliodon and artificial sky respectively, with minimal variations in accuracy. Thus, demonstrating the ability of the computational simulation program in accurately predicting solar shading and daylight performance in buildings, this could benefit architects in the proper and efficient design of shading devices for building facades at early design stages.

scholarly journals Genome-scale model of Rhodotorula toruloides metabolism

2019 ◽  
Author(s):  
Ievgeniia A Tiukova ◽  
Sylvain Prigent ◽  
Jens Nielsen ◽  
Mats Sandgren ◽  
Eduard J Kerkhoven
Keyword(s):  
Lipid Production ◽  
Acyl Chain ◽  
Value Added ◽  
Scale Model ◽  
Distribution Data ◽  
Experimental Distribution ◽  
Future Studies ◽  
Simulation Results ◽  
Genome Scale ◽  
Genome Scale Model

AbstractThe basidiomycete red yeast Rhodotorula toruloides is a promising platform organism for production of biooils. We present rhto-GEM, the first genome-scale model of R. toruloides metabolism, that was largely reconstructed using RAVEN toolbox. The model includes 4869 genes, 897 reactions, and 3334 metabolites. Lipid metabolism was described using the SLIMEr formalism, which allows direct integration of lipid class and acyl chain experimental distribution data. The simulation results confirmed that the R. toruloides model provides valid growth predictions on glucose, xylose and glycerol, while prediction of genetic engineering targets to increase production of linolenic acid and triacylglycerols highlighted genes that have previously been successfully used to increase lipid production. This renders rtho-GEM useful for future studies to improve the production of other industrially important oleochemicals including both value-added fatty acids and carotenoids, while it will also be valuable tool for system-wide omics-data analysis in R. toruloides. Expanding the portfolio of GEMs for lipid accumulating fungi contributes to both understanding of metabolic mechanisms of the oleaginous phenotype but also uncover particularities of lipid production machinery in R. toruloides.

Sign in / Sign up

Export Citation Format

Share Document