Online Dynamic Trim and Control Limit Estimation

Date

2012-9

Author

Yavrucuk, İlkay

Metadata

Show full item record

Item Usage Stats

259
views

0
downloads

The online estimation of a maneuvering steady-state condition of an aircraft, called the dynamic trim, is used to estimate the allowable control travel during flight, a key information in pilot cueing for envelope limit protection. In this paper a new methodology is presented where adaptive models are used to estimate online local dynamic trim conditions, while requiring very limited a priori vehicle information. Adaptive neural networks are employed to enable online learning. The models are used to estimate future aircraft responses and artificial margins on controls that would keep the aircraft response within its flight envelope limits. A linear helicopter model and the XV-15 tiltrotor model are used to demonstrate the method in simulation.

Subject Keywords

Output-feedback control, Tilt-rotor aircraft, Nonlinear-systems, Neural networks, Flight control, Avoidance

URI

https://hdl.handle.net/11511/28286

Journal

Journal of Guidance, Control, and Dynamics

DOI

https://doi.org/10.2514/1.53116

Collections

Department of Aerospace Engineering, Article

Suggestions

OpenMETU
Core

Concurrent Learning Enabled Adaptive Limit Detection for Active Pilot Cueing Yavrucuk, İlkay (2010-08-02) Adaptive dynamic models are commonly used to estimate allowable control travel and the proximity to a limiting flight condition in the design of advanced envelope protection algorithms for fly-by-wire aircraft. In this paper linear models are compensated with adaptive neural networks to build adaptive models of relevant aircraft dynamics. Neural networks are trained online not only using instantaneous sensor data, but also a stack of data collected during flight. The additional stack is made up of transient...
FREQUENCY-DOMAIN SYSTEM IDENTIFICATION OF F-16 LONGITUDINAL DYNAMICS Ergazi, Nazife Ege; Yavrucuk, İlkay; Gürsoy, Gönenç; Department of Aerospace Engineering (2022-3-10) The longitudinal dynamics of F-16 aircraft in a level trim, unaccelerated flight are identified using frequency-domain system identification techniques. The nonlinear system is excited by sine sweep elevator input, and angle of attack and pitch rate responses are collected. Detrending and windowing are applied to time-domain data and are converted to the frequency-domain by applying Fast Fourier Transform (FFT). The smooth spectral estimates are found from the transformed data, allowing frequency responses ...
Concurrent Learning Enabled Adaptive Limit Detection for Active Pilot Cueing Gursoy, Gonenc; Yavrucuk, İlkay (2014-09-01) Neural-network-based adaptive dynamic models are commonly used to estimate allowable control travel and the proximity to a limiting flight condition in the design of advanced envelope protection algorithms for fly-by-wire aircraft. In this paper, linear models are compensated with adaptive neural networks, which use instantaneous sensor data as well as past flight history information for concurrent learning. A law for collecting appropriate training data into the history stack is established. It is observed...
Structured H-Infinity controller design and analysis for highly maneuverable jet aircraft Özkan, Salih Volkan; Tekinalp, Ozan; Department of Aerospace Engineering (2022-2-10) Robust control technique is utilized to develop flight control laws for highly maneuverable aircraft. A structured H-Infinity controller is used to optimize the gains of the proposed control algorithm. For this purpose systune algorithm available in Matlab is employed to successfully obtain the controller gains satisfying selected design requirements. Designed control laws are evaluated according to these requirements and validation of the methodology is presented.
Flight flutter testing and aeroelastic stability of aircraft Kayran, Altan (2007-01-01) Purpose - To provide a general review of the flight flutter test techniques utilized in aeroelastic stability flight testing of aircraft, and to highlight the key items involved in flight flutter testing of aircraft, by emphasizing all the main information processed during the flutter stability verification based on flight test data.

Citation Formats

İ. Yavrucuk, “Online Dynamic Trim and Control Limit Estimation,” Journal of Guidance, Control, and Dynamics, pp. 1647–1656, 2012, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/28286.