Development of control laws for a flight test maneuver autopilot foran F-15 aircraft

1985 ◽  
Author(s):  
G. ALAG ◽  
E. DUKE
Keyword(s):  
Flight Test ◽  
Control Laws

Adaptive control laws for F-8 flight test

1975 ◽  
Author(s):  
G. Stein ◽  
G. Hartmann ◽  
R. Hendrick
Keyword(s):  
Adaptive Control ◽  
Flight Test ◽  
Control Laws

Design of Dynamic Inversion and Explicit Model Following Flight Control Laws for Quadrotor UAS

2020 ◽  
Vol 65 (3) ◽  
pp. 1-16
Author(s):  
Umberto Saetti ◽  
Joseph F. Horn ◽  
Sagar Lakhmani ◽  
Constantino Lagoa ◽  
Tom F. Berger
Keyword(s):  
Flight Control ◽  
Flight Test ◽  
Parametric Model ◽  
Unmanned Aerial Systems ◽  
Model Parameters ◽  
Dynamic Inversion ◽  
Explicit Model ◽  
Control Laws ◽  
Model Following ◽  
Novel Approach

The objectives of this paper are to advance dynamic inversion (DI) and explicit model following (EMF) flight control laws for quadrotor unmanned aerial systems (UAS) and to develop an efficient strategy to compute the stability and performance robustness statistics of such control laws given parametric model uncertainty. For this purpose, a parametric model of a quadrotor is identified from flight-test data. The identified model is validated both in frequency and time domains. Next, DI and EMF flight control laws are designed for both inner attitude and outer velocity loops. Finally, a novel approach based on an unscented transform is used to evaluate the statistics of the controller's performance based on the statistics of the uncertain model parameters.

Business Jet Fly-by-Wire Control Laws Handling Qualities Flight Test Assessment

2021 ◽  
pp. 1-19
Author(s):  
Tom Berger ◽  
Mark B. Tischler ◽  
Steven G. Hagerott ◽  
M. Christopher Cotting ◽  
James L. Gresham ◽  
...  
Keyword(s):  
Flight Test ◽  
Control Laws ◽  
Handling Qualities ◽  
Business Jet ◽  
Test Assessment

Modernized Control Laws for UH-60 BLACK HAWK Optimization and Flight-Test Results

2005 ◽  
Vol 28 (5) ◽  
pp. 964-978 ◽  
Author(s):  
Mark B. Tischler ◽  
Christopher L. Blanken ◽  
Kenny K. Cheung ◽  
Sean S. M. Swei ◽  
Vineet Sahasrabudhe ◽  
...  
Keyword(s):  
Flight Test ◽  
Test Results ◽  
Control Laws

Stalling transport aircraft

2013 ◽  
Vol 117 (1198) ◽  
pp. 1183-1206 ◽  
Author(s):  
P. J. Bolds-Moorehead ◽  
V. G. Chaney ◽  
T. Lutz ◽  
S. Vaux
Keyword(s):  
Wind Tunnel ◽  
Flight Control ◽  
Flight Test ◽  
High Angle ◽  
Flight Testing ◽  
Control Laws ◽  
Transport Aircraft ◽  
Wind Tunnel Data ◽  
Predictive Validation ◽  
Flight Deck

Abstract Airbus and Boeing are cooperatively presenting this topic dealing with transport aircraft stalls. The paper will begin by defining a stall, followed by a review of requirements, predictive validation and flight testing. There are various ways of designing modern jet transports for the stall regime such as aerodynamic approaches, flight deck indications, and augmentation control laws to deal with the high angle-of-attack (α) arena. The goal of augmented control laws for high α is common – no full aerodynamic stall or loss of climb performance should occur in the operational flight envelope, in Normal flight control modes. The validation techniques employed in preparation for a flight test campaign will follow. These include flight characteristic predictions based on wind-tunnel data as well as pilot-in-the-loop simulation rehearsals. The preparation for flight testing will be reviewed from both the engineer and pilot viewpoints. This will be followed by a review of various flight testing that has been conducted. The paper will close with a brief foray into what the future of transport stalls could be – perhaps protection features in degraded flight control modes? What are the benefits as well as drawbacks to increased augmentation for high α?

scholarly journals Historical Overview of Research in Reconfigurable Flight Control

2005 ◽  
Vol 219 (4) ◽  
pp. 263-275 ◽  
Author(s):  
M Steinberg
Keyword(s):  
Intelligent Control ◽  
Flight Control ◽  
Flight Test ◽  
Historical Overview ◽  
Reconfigurable Control ◽  
Control Laws ◽  
Loop Control ◽  
Software Algorithms ◽  
Lifting Surfaces ◽  
Initial Research

This article presents a historical overview of research in reconfigurable flight control. For the purpose of this article, the term ‘reconfigurable flight control’ is used to refer to software algorithms designed specifically to compensate for failures or damage of flight control effectors or lifting surfaces, using the remaining effectors to generate compensating forces and moments. This article will discuss initial research and flight testing of approaches based on explicit fault detection, isolation, and estimation, as well as later approaches based on continuously adaptive and intelligent control algorithms. In addition, approaches for trajectory reshaping of an impaired aircraft with reconfigurable inner loop control laws will be briefly discussed. Finally, there will be some discussion on current implementations of reconfigurable control to improve safety on production and flight test aircraft and remaining challenges to enable broader use of the technology, such as the difficulties of flight certification of these types of approaches.

Adaptive control laws for F-8 flight test

1977 ◽  
Vol 22 (5) ◽  
pp. 758-767 ◽  
Author(s):  
G. Stein ◽  
G. Hartmann ◽  
R. Hendrick
Keyword(s):  
Adaptive Control ◽  
Flight Test ◽  
Control Laws

scholarly journals Inflight investigation of the effects of rotor state measurement and feedback on variable stability helicopters

2021 ◽  
Author(s):  
Marc David Alexander
Keyword(s):  
Flight Control ◽  
National Research Council ◽  
Likelihood Estimation ◽  
Flight Test ◽  
Flight Simulation ◽  
Tracking Accuracy ◽  
Response Dynamics ◽  
Control Laws ◽  
Systems Research ◽  
Model Following Control

This thesis describes a flight test evaluation of flight control laws applying rotor state measurements and feedback on the National Research Council Bell 412 Advanced Systems Research Aircraft (ASRA) and Bell 205A Airborne Simulator (AS). Parameter estimation of a higher-order mathematical model of the ASRA rotor dynamics was achieved by Maximum Likelihood Estimation (MLE) employing coupled rotor-body equations parameterized by explicit rotor and fuselage state measurements. Root Locus (RLM), Classical Multivariable (CMC), Eigenstructure Assignment (EAC), and Model Following control algorithms were implemented in Matlab/Simulink simulation for analysis of coupled rotor-body dynamics. Rotorcraft performance specifications were based on compliance with ADS-33E-PRF and Cooper Harper military handling qualities. Evaluated in desk-top and in-flight simulation, rotor state feedback of longitudinal and lateral disc tilt dynamics by modern multivariable control significantly improves inter-axis decoupling, disturbance rejection characteristics, rotor response dynamics, command tracking accuracy, and rigid-body bandwidth performance.

Multiplicative Error State Kalman Filter vs Nonlinear Complimentary Filter for a High Performance Aircraft Attitude Estimation

2016 ◽  
Vol 66 (6) ◽  
pp. 630 ◽  
Author(s):  
Kamali C. ◽  
Shikha Jain
Keyword(s):  
Kalman Filter ◽  
High Performance ◽  
Full Range ◽  
Flight Test ◽  
Control Laws ◽  
Multiplicative Error ◽  
Sensor Modelling ◽  
First Time ◽  
Error State ◽  
High Performance Aircraft

<p>Modern control law designs increasingly use aircraft attitude information to improve aircraft manoeuverability. Attitude information allows for gravity term compensations in the longitudinal as well as lateral directional control laws of a typical fighter aircraft. Methodologies and comparisons of multiplicative error state Kalman filter (MEKF) and nonlinear complimentary filter for estimation of attitudes of a high performance aircraft using its onboard autonomous sensors is presented. Shows a problem in pitch angle estimation beyond ± 80 deg in the MEKF and a solution is proposed for the same for the first time. Also presents novel aiding sensor modelling for the implementation of attitude heading reference system for this class of aircraft for the first time. The filter formulations are evaluated using full range manuoevering real flight test data.</p>

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