scholarly journals Flight Test Results of an Angle of Attack and Angle of Sideslip Calibration Method Using Output-Error Optimization

2013 ◽  
Author(s):  
Marie-Michele Siu ◽  
Borja Martos ◽  
John Foster
Keyword(s):  
Angle Of Attack ◽  
Flight Test ◽  
Calibration Method ◽  
Test Results ◽  
Output Error ◽  
Error Optimization

Research on Improving Take-Off Characteristics of Fly Wing with a New Constitution

2012 ◽  
Vol 462 ◽  
pp. 265-270
Author(s):  
Song Mo ◽  
Jun Huang ◽  
Xue Chai ◽  
Quan Zhao
Keyword(s):  
Numerical Simulation ◽  
Angle Of Attack ◽  
Flight Test ◽  
The State ◽  
Test Results ◽  
Control Scheme ◽  
Pitch Moment

The take-off control of UAV with fly wing layout is limited by its relatively lower pitch moment. This paper gained the state parameters of a few groups of taking off model by means of numerical simulation. The influence of different models on take-off distance, take-off angle of attack (AOA), take-off safe speed and c.g. location was then analyzed. Based on the analysis, a new fly wing constitution was designed and the corresponding take-off control scheme was suggested as well. Finally, the flight test results shows that this fly wing constitution can gain better take-off control characteristics.

scholarly journals Development and Flight Test Results of a Small UAS Distributed Flush Airdata System

2018 ◽  
Vol 35 (5) ◽  
pp. 1127-1140 ◽  
Author(s):  
Roger J. Laurence ◽  
Brian M. Argrow
Keyword(s):  
Angle Of Attack ◽  
Feedforward Neural Networks ◽  
Flight Test ◽  
Unmanned Aircraft ◽  
Wind Instruments ◽  
Test Results ◽  
Alternative Approach ◽  
Computational Fluid Dynamics Simulations ◽  
Dynamics Simulations ◽  
Relative Wind

AbstractSmall unmanned aircraft systems (sUAS) have proven their effectiveness for measuring both the inertial and aircraft-relative wind. One of the more common aircraft-relative wind instruments is the multihole probe (MHP). While the MHP is accurate and simple to use, two main drawbacks exist: 1) the MHP airdata system can cost several times that of the sUAS and 2) the probe itself is often exposed to damage during routine operations. Flush airdata systems (FADS) are an alternative approach and utilize pressure ports flush with the aircraft surface. This removes any external components, thereby mitigating the risk of damage to the airdata system. The work presented details the implementation of a FADS for sUAS. Computational fluid dynamics simulations were used to determine the port locations of the FADS. Airframe locations were sorted based on the total sensitivity over a range of angles of attack and sideslip. The FADS was calibrated in flight using an onboard MHP. Multilayer feedforward neural networks were employed to produce estimates of the angle of attack and sideslip, while static and stagnation ports on the fuselage measured airspeed. Results from flight testing show errors in angle of attack and sideslip were unbiased. Additionally, 97.9% of the errors in airspeed were within 1 m s−1 of the MHP, while 93.8% and 87.3% of the angle of attack and sideslip errors, respectively, were within 1°. Flight tests show that a FADS can be calibrated in flight and that it is an effective method for measuring the aircraft-relative wind from small UAS.

Flight test results for a high-capacity single-groove heat pipe

1992 ◽  
Author(s):  
J. AMBROSE ◽  
H. HOLMES ◽  
R. CIMA ◽  
M. KAPOLNEK
Keyword(s):  
Heat Pipe ◽  
High Capacity ◽  
Flight Test ◽  
Test Results
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