Case Studies of System Identification Modeling for Flight Control Design

2013 ◽  
Vol 58 (1) ◽  
pp. 1-16 ◽  
Author(s):  
Christina M. Ivler ◽  
Mark B. Tischler
Keyword(s):  
System Identification ◽  
Flight Control ◽  
Control Design ◽  
Flight Test ◽  
Unmanned Aircraft ◽  
Integrated System ◽  
Control Law ◽  
Dynamics Model ◽  
Identification Methods ◽  
Flight Dynamics Model

Flight control design and analysis requires an accurate flight dynamics model of the bare airframe and its associated uncertainties, as well as the integrated system model (block diagrams), across the frequency range of interest. Frequency response system identification methods have proven to efficiently fulfill these modeling requirements in recent rotorcraft flight control applications. This paper presents integrated system identification methods for control law design with flight-test examples of the Fire Scout MQ-8B, S-76, and ARH-70A. The paper also looks toward how system identification could be used in new modeling challenges such as large tilt-rotors and uniquely configured unmanned aircraft.

scholarly journals Identification of Aeroelastic Models for the X-56A Longitudinal Dynamics Using Multisine Inputs and Output Error in the Frequency Domain

Aerospace ◽  
2019 ◽  
Vol 6 (2) ◽  
pp. 24 ◽  
Author(s):  
Jared Grauer ◽  
Matthew Boucher
Keyword(s):  
System Identification ◽  
Test Data ◽  
Flight Control ◽  
Fourier Transforms ◽  
Flight Dynamics ◽  
Flight Test ◽  
Multiple Control ◽  
Output Error ◽  
Short Period ◽  
Flight Dynamics Model

System identification from measured flight test data was conducted using the X-56A aeroelastic demonstrator to identify a longitudinal flight dynamics model that included the short period, first symmetric wing bending, and first symmetric wing torsion modes. Orthogonal phase-optimized multisines were used to simultaneously excite multiple control effectors while a flight control system was active. Non-dimensional stability and control derivatives parameterizing an aeroelastic model were estimated using the output-error approach to match Fourier transforms of measured output response data. The predictive capability of the identified model was demonstrated using other flight test data with different inputs and at a different flight conditions. Modal characteristics of the identified model were explored and compared with other predictions. Practical aspects of the experiment design and system identification analysis, specific to flexible aircraft, are also discussed. Overall, the approach used was successful for identifying aeroelastic flight dynamics models from flight test data.

System Identification Methods for Improving Flutter Flight Test Techniques

2004 ◽  
Author(s):  
David Klyde ◽  
Chuck Harris ◽  
Peter M. Thompson ◽  
Edward N. Bachelder
Keyword(s):  
System Identification ◽  
Flight Test ◽  
Identification Methods

Improved Architecture Designs for a Low Cost Personal Remote Sensing Platform: Flight Control and Safety

2011 ◽  
Author(s):  
Calvin Coopmans ◽  
Long Di ◽  
Austin Jensen ◽  
Aaron A. Dennis ◽  
YangQuan Chen
Keyword(s):  
Remote Sensing ◽  
Flight Control ◽  
Large Scale ◽  
Current System ◽  
Low Cost ◽  
Flight Test ◽  
Unmanned Aircraft ◽  
Personal Remote Sensing ◽  
Sensing Platform ◽  
Fail Safe

Remote sensing is a field traditionally dominated by expensive, large-scale operations. This paper presents our efforts to improve our unmanned aircraft (UA) platforms for low-cost personal remote sensing purposes. Safety concerns are first emphasized regarding the local airspace and multiple fail-safe features are shown in the current system. Then the AggieAir unmanned system architecture is briefly described including the Paparazzi UA autopilot, AggieAir JAUS implementation, AggieNav navigation unit and payload integration. Some preliminary flight test results and images acquired using an example thermal IR payload system are also shown. Finally Multi-UAV and heterogeneous platform capabilities are discussed with respect to their applications. Based on our approaches on the new architecture design, personal remote sensing on smaller-scale operations can be more beneficial and common.

scholarly journals GPC-Based Stable Reconfigurable Control

2003 ◽  
Author(s):  
Jianjun Shi ◽  
Atul G. Kelkar ◽  
Donald Soloway
Keyword(s):  
State Space ◽  
Predictive Control ◽  
Flight Control ◽  
Actuator Saturation ◽  
Control Design ◽  
Generalized Predictive Control ◽  
Control Law ◽  
Reconfigurable Control ◽  
Space Formulation ◽  
The Stability

This paper presents development of multi-input multi-output (MIMO) Generalized Predictive Control (GPC) law and its application to reconfigurable control design in the event of actuator saturation. The stability of the GPC control law without reconfiguration is first established using Riccati-based approach and state-space formulation. A novel reconfiguration strategy is developed for the systems which have actuator redundancy and are faced with actuator saturation type failure. An elegant reconfigurable control design is presented with stability proof. A numerical example with application to reconfigurable flight control is presented to demonstrate the results presented in the paper.

scholarly journals PERANCANGAN AWAL FLIGHT TEST INSTRUMENTATION (FTI) UNTUK PESAWAT TERBANG TANPA AWAK DI PUSTEKBANG LAPAN

Technologic ◽  
2020 ◽  
Vol 11 (2) ◽  
Author(s):  
Try K. W ◽  
Fuad S. P. ◽  
Gunta A.
Keyword(s):  
Flight Control ◽  
Flight Test ◽  
Control Law ◽  
Hardware In The Loop ◽  
Wiring Diagram ◽  
Test Instrumentation

Abstrak--Pesawat terbang tanpa awak (PTTA) yang dikembangkan oleh LAPAN memiliki maximum takeoff weight (MTOW) yang bervariasi. PTTA ini memiliki sistem kendali (SK) yang menjadikannya dapat terbang secara auotonomous. Salah satu sub sistem inti yang ada di dalam SK adalah flight control law (FCL), dimana pengembangannya dimulai dari tahap penentuan requirement dilanjutkan dengan tahap desain SK. Dalam desain SK, tahapan metode yang digunakan adalah software in the loop simulation, hardware in the loop simulation dan uji terbang. Untuk mengetahui apakah FCL yang dikembangkan telah memenuhi requirement awal yang didefinisikan, perlu sebuah alat yang mampu merekam parameter-parameter penting selama uji terbang, yang dinamakan dengan flight test instrumentation (FTI). Pada penelitian ini, akan dibahas mengenai requirement awal yang harus dipenuhi oleh FTI, mulai dari dimensi, berat, jumlah parameter yang direkam, serta kemampuan hardware & sensor. Tahapan selanjutnya adalah melakukan market study pemilihan hardware dengan metode pembobotan dan diakhiri dengan desain arsitektur serta wiring diagram FTI. Dari hasil penelitian yang dilakukan, diperoleh desain awal FTI yang memiliki berat total kurang dari 1.5Kg dan dimensi yang bisa dimasukkan ke dalam PTTA dengan MTOW 10Kg. FTI ini juga dilengkapi dengan baterai dan sensor yang independen, sehingga tidak tergantung dan membebani system elektronik yang terdapat pada PTTA Kata Kunci : FTI, Identifikasi Parameter, PTTA

Multiple Quadrotors Formation Flying Control Design and Experimental Verification

2019 ◽  
Vol 07 (01) ◽  
pp. 47-54 ◽  
Author(s):  
Jianan Wang ◽  
Zhengyang Zhou ◽  
Chunyan Wang ◽  
Jiayuan Shan
Keyword(s):  
Motion Capture ◽  
Formation Control ◽  
Formation Flying ◽  
Control Design ◽  
Euler Method ◽  
Control Law ◽  
Dynamics Model ◽  
Experimental Platform ◽  
Communication Constraint ◽  
The Stability

The formation control problem in multi-quadrotor systems is studied in this paper. Each quadrotor has limited access to its neighbors’ information due to communication constraint. First, the dynamics model of the quadrotor is linearized using Newton–Euler method. The distributed formation control law is then designed and the stability analysis is provided. An experimental platform is built with three Parrot Bebop drones and an indoor motion capture system. Numerical and experimental results are provided to show the effectiveness of the proposed algorithms.

Nonlinear model predictive controller robustness extension for unmanned aircraft

2015 ◽  
Vol 3 (2/3) ◽  
pp. 93-121 ◽  
Author(s):  
Gonzalo Garcia ◽  
Shahriar Keshmiri ◽  
Thomas Stastny
Keyword(s):  
Nonlinear Model ◽  
Flight Control ◽  
Unsteady Aerodynamics ◽  
Control Design ◽  
Unmanned Aircraft ◽  
Model Predictive Controller ◽  
Frequency Dependent ◽  
Content Type ◽  
Predictive Controller ◽  
Predictive Controllers

Purpose – Nonlinear model predictive control (NMPC) is emerging as a way to control unmanned aircraft with flight control constraints and nonlinear and unsteady aerodynamics. However, these predictive controllers do not perform robustly in the presence of physics-based model mismatches and uncertainties. Unmodeled dynamics and external disturbances are unpredictable and unsteady, which can dramatically degrade predictive controllers’ performance. To address this limitation, the purpose of this paper is to propose a new systematic approach using frequency-dependent weighting matrices. Design/methodology/approach – In this framework, frequency-dependent weighting matrices jointly minimize closed-loop sensitivity functions. This work presents the first practical implementation where the frequency content information of uncertainty and disturbances is used to provide a significant degree of robustness for a time-domain nonlinear predictive controller. The merit of the proposed method is successfully verified through the design, coding, and numerical implementation of a robust nonlinear model predictive controller. Findings – The proposed controller commanded and controlled a large unmanned aerial system (UAS) with unsteady and nonlinear dynamics in the presence of environmental disturbances, measurement bias or noise, and model uncertainties; the proposed controller robustly performed disturbance rejection and accurate trajectory tracking. Stability, performance, and robustness are attained in the NMPC framework for a complex system. Research limitations/implications – The theoretical results are supported by the numerical simulations that illustrate the success of the presented technique. It is expected to offer a feasible robust nonlinear control design technique for any type of systems, as long as computational power is available, allowing a much larger operational range while keeping a helpful level of robustness. Robust control design can be more easily expanded from the usual linear framework, allowing meaningful new experimentation with better control systems. Originality/value – Such algorithms allows unstable and unsteady UASs to perform reliably in the presence of disturbances and modeling mismatches.

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