On-Line Robust Aeroservoelastic Stability Margin Analysis from Wavelet-Processed Flight Testing Data

2006 ◽  
Author(s):  
Hongchao Li ◽  
Zhongke Shi ◽  
Wei Tang
Keyword(s):  
Stability Margin ◽  
Flight Testing ◽  
Testing Data ◽  
On Line ◽  
Margin Analysis

scholarly journals Prototype Mesin Pengantar Barang Otomatis Menggunakan Load Cell Berbasis Robot Line Follower

2018 ◽  
Vol 10 (1) ◽  
pp. 23-29
Author(s):  
Dwi Budi Susilo ◽  
Hari Wibawanto ◽  
Anggraini Mulwinda
Keyword(s):  
Load Cell ◽  
Load Testing ◽  
White Line ◽  
Photo Diode ◽  
Testing Data ◽  
Data Output ◽  
On Line ◽  
The Difference ◽  
Development Methods ◽  
Prototype Design

Overloaded condition in the product porter like hand pallet, hand stacker, forclift, and etc, can causes damage and terrible accident in the machine operator. This research aim to build a prototype of porter machine that can prevent overloaded condition through the reading of load cell and photo diode sensor to guide the line follower direction. Research and development methods are used with the systematic writing are background of study and problems, prototype design and validation, testing, taking and analysis of the data. Output of the research is a prototype of porter machine using load cell sensor based on line follower robot. The Result of the load cell reading is compared to SF-400 weigher, and found the difference amount 0.117%. The load testing data of automatic moving trigger is 1 gram until 2999 gram. The Overload condition warning is active while the load is more than 3000 gram. The data reading of the photo diode on the black line is running succesfully, however on the white line with orange color is found some error.

Deadbands Tell No Tails: X-56A Dynamic Actuation Requirements

2020 ◽  
Author(s):  
Alexander M. Pankonien ◽  
Peter M. Suh ◽  
Jacob R. Schaefer ◽  
Robert M. Mitchell
Keyword(s):  
State Of The Art ◽  
Ride Quality ◽  
Flight Testing ◽  
Nonlinear Simulation ◽  
The Past ◽  
Actuation System ◽  
Testing Data ◽  
Aircraft Performance ◽  
Number Of Cycles ◽  
Significant Effort

Abstract Following significant effort over the past several years by AFRL and NASA, the X-56A flight vehicle has proven to be a useful platform for exploring controllers and distributed actuation on a flexible, swept flying-wing. The program sought to advance the state of the art in airworthiness for vehicles encountering flutter, leading to relaxed design constraints that could drastically decrease structural weight and improve aircraft performance. Specifically, the vehicle was designed to encounter different forms of flutter: body-freedom flutter, and wing-bending torsion flutter, making it an ideal candidate for identifying dynamic actuation challenges. Flight testing led to fundamental observations by controller designers about the actuation needs for such a vehicle. Namely, the small inherent actuator deadband led to significant constant-amplitude limit cycle oscillations of the system during post-flutter controlled flight. This work captures these observations by exploring theoretical changes in the actuators via a nonlinear simulation tuned with flight testing data and shows that a 60% reduction in actuator deadband can improve ride quality by nearly 50%. The results are combined into a set of actuation challenges for the adaptive structures community at large, including precise actuation for a large number of cycles over multiple timescales, with a relevant baseline described by original actuation system.

Automation for Safety and Precision in Flight Testing

2020 ◽  
Vol 10 (1) ◽  
pp. 29-34
Author(s):  
Diogo Castilho
Keyword(s):  
Remote Control ◽  
Flight Testing ◽  
Autonomous Flight ◽  
Handling Qualities ◽  
Testing Data ◽  
Safety Constraints ◽  
Autonomous Aircraft ◽  
First Time ◽  
Airborne Sensors

Abstract. The first flight of any new aircraft remains a potentially dangerous event. Test pilots face many unknowns when a prototype leaves the ground for the first time. In a time when remotely piloted and autonomous aircraft fly every day, the question about using their technologies to avoid losing a test pilot arises. This study investigates the advantages of using a machine to test another machine. It also discusses the disadvantages of relying on airborne sensors instead of using the test pilot’s cognitive capabilities and judgment. The analysis of collected flight testing data suggests that aircraft handling qualities may be more precisely tested adding specific automation. However, remote control and autonomous flight testing bring new safety constraints that cannot be ignored.

Response of a Rotating Shaft to Uniaxial Random Excitation

2012 ◽  
Vol 79 (4) ◽  
Author(s):  
M. F. Dimentberg ◽  
A. Naess ◽  
L. Sperling
Keyword(s):  
Exact Analytical Solution ◽  
Quantitative Description ◽  
Stability Margin ◽  
Lateral Force ◽  
Random Excitation ◽  
Mean Square ◽  
Rotating Shaft ◽  
Simple Processing ◽  
Mean Square Response ◽  
On Line

Random vibrations are considered for a Jeffcott rotor subject to uniaxial broadband random excitation by a lateral force along one of its transverse axes. Exact analytical solution for mean square responses is obtained which provide quantitative description of two effects: the magnification of mean square whirl radius due to rotation; and the increasing mean square response along the nonexcited direction with increasing rotation speed, that is, the spread of vibration to all directions around the shaft. The latter effect clearly corresponds to the approaching forward whirl of the shaft approaching its instability threshold; it can be used for the on-line evaluation of the rotor’s stability margin from the simple processing of its measured response signals as demonstrated by direct numerical simulation.

STABILITY MARGIN ANALYSIS IN MULTIOBJECTIVE DESIGN: APPLICATION TO AN AEROSPACE LAUNCHER

2005 ◽  
Vol 38 (1) ◽  
pp. 61-66
Author(s):  
Mohamed ABBAS-TURKI ◽  
Gilles DUC ◽  
Benoît CLEMENT
Keyword(s):  
Stability Margin ◽  
Multiobjective Design ◽  
Margin Analysis
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