Aircraft Performance

Keyword(s):  
Author(s):  
W. Austyn Mair ◽  
David L. Birdsall
Keyword(s):  

2019 ◽  
Vol 124 (1272) ◽  
pp. 170-188
Author(s):  
V. A. Deo ◽  
F. Silvestre ◽  
M. Morales

ABSTRACTThis work presents an alternative methodology for monitoring flight performance during airline operations using the available inboard instrumentation system. This method tries to reduce the disadvantages of the traditional specific range monitoring technique where instrumentation noise and cruise stabilisation conditions affect the quality of the performance monitoring results. The proposed method consists of using an unscented Kalman filter for aircraft performance identification using Newton’s flight dynamic equations in the body X, Y and Z axis. The use of the filtering technique reduces the effect of instrumentation and process noise, enhancing the reliability of the performance results. Besides the better quality of the monitoring process, using the proposed technique, additional results that are not possible to predict with the specific range method are identified during the filtering process. An example of these possible filtered results that show the advantages of this proposed methodology are the aircraft fuel flow offsets, as predicted in the specific range method, but also other important aircraft performance parameters as the aircraft lift and drag coefficients (CL and CD), sideslip angle (β) and wind speeds, giving the operator a deeper understanding of its aircraft operational status and the possibility to link the operational monitoring results to aircraft maintenance scheduling. This work brings a cruise stabilisation example where the selected performance monitoring parameters such as fuel flow factors, lift and drag bias, winds and sideslip angle are identified using only the inboard instrumentation such as the GPS/inertial sensors, a calibrated anemometric system and the angle-of-attack vanes relating each flight condition to a specific aircraft performance monitoring result. The results show that the proposed method captures the performance parameters by the use of the Kalman filter without the need of a strict stabilisation phase as it is recommended in the traditional specific range method, giving operators better flexibility when analysing and monitoring fleet performance.


2002 ◽  
Vol 39 (3) ◽  
pp. 427-433 ◽  
Author(s):  
Ashok Gopalarathnam ◽  
Christopher W. McAvoy
Keyword(s):  

1982 ◽  
Vol 26 (7) ◽  
pp. 605-609
Author(s):  
Thomas H. Killion

The use of surrogate aircraft for aircrew training involves two major issues. First, what effect does flying the secondary aircraft have on primary aircraft performance? This issue was addressed in the previous paper. Second, can the crew learn to safely operate the secondary aircraft while continuing to fly the primary aircraft? This paper addresses this second aspect of dual qualification. Of interest is the acquisition of skill in the secondary aircraft. For the purpose of testing the concept of a Companion Trainer Aircraft (CTA), eight B-52 pilot/copilot teams from the 2nd Bombardment Wing, Barksdale AFB, LA, were dual qualified in the T-39. Initial training in the T-39A occurred at Scott AFB, IL, followed by the flying of B-52 style training sorties in a specially modified T-39B at Barksdale AFB, LA. Pilot/copilot performance in the T-39A was evaluated by Military Airlift Command (MAC) instructor pilots (IPs), in the T-39B performance was monitored by a 4950 Test Wing IP. The results of these evaluations suggest that: 1, approach and landing is the most difficult part of the mission to learn; and 2, certain behaviors which are appropriate in the B-52 intrude on T-39 performance, where they are inappropriate. The data also suggest that in the early phase of skill acquisition, frequent sorties are necessary to avoid degradations in performance. In the T-39B training, the frequency required appeared to be about every two weeks. Although the short duration of this study prohibits conclusions concerning long term learning effects, the results do identify some areas for concern in any future CTA type program.


2020 ◽  
pp. 1-12
Author(s):  
Mostafa E. El-Salamony ◽  
Mohamed A. Aziz

Generally, unmanned aerial vehicles and micro aerial vehicles depend on batteries or conventional fuel as a source of energy. These sources of energy have limited flight time, relatively high cost, and also a certain level of pollutants. Solar energy applied to aerial vehicles is an excellent alternative way to overcome other sources of energy’s disadvantage. This study aimed to design a solar-powered aerial vehicle to achieve continuous flight on Earth. The efficiency of the solar system is related to the absorbed sun rays. The concept of an anti-symmetric N-shaped morphing wing is a good idea to increase the collected solar energy during the daily sun path. But this comes with the penalty of side forces and moments due to the anti-symmetry of the wing. This paper introduces a study for two parameters that strongly affect the aerodynamics of the N-shaped morphing wing; the dihedral part angle and the dihedral part length. The impact of the dihedral angle decreases the lift coefficient and increases the drag coefficient. The impact of the morphing wing on the aircraft performance is also considered.


2014 ◽  
Vol 1016 ◽  
pp. 365-369 ◽  
Author(s):  
Pedro Albuquerque ◽  
Pedro Gamboa ◽  
Miguel Silvestre

The present work describes an aircraft design methodology that uses the wingspan and its mean aerodynamic chord as main design parameters. In the implemented tool, low fidelity models have been developed for the aerodynamics, stability, propulsion, weight, balance and flight performance. A Fortran® routine that calculates the aircraft performance for the user defined mission and vehicle’s performance requirements has been developed. In order to demonstrate this methodology, the results for a case study using the design specifications of the Air Cargo Challenge 2013 are shown.


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