Nonlinear simulation analysis of a tailless advanced fighter aircraft reconfigurable flight control law

1999 ◽  
Author(s):  
Joseph Brinker ◽  
Kevin Wise
Keyword(s):  
Flight Control ◽  
Simulation Analysis ◽  
Control Law ◽  
Fighter Aircraft ◽  
Nonlinear Simulation

The Research on Height Control of Airship with Constant Flying Speed

2014 ◽  
Vol 644-650 ◽  
pp. 875-878
Author(s):  
Xin Li Zhang ◽  
Yun An Hu ◽  
Di Liu
Keyword(s):  
Nonlinear Model ◽  
Flight Control ◽  
Pid Control ◽  
Simulation Analysis ◽  
Reference Value ◽  
Control Law ◽  
High Increase ◽  
Height Control ◽  
Control Scheme ◽  
Detailed Simulation

The PID control scheme of airship with fixed flying high is studied in allusion to pitch channel nonlinear model of a class of stratosphere airship in this paper. The traditional PID control law is designed aim at the fixed high flight control of airship. The detailed simulation analysis is presented. It indicates that the airship can realize the fixed high flight in the range of 1000 meters. When flying high increase further, PID control scheme is not reasonable because instruction is too large. At the same time, the speed of engine has large influence on PID control scheme. The research of paper has good technical reference value for design and experiments of stratosphere airship.

A continuation design framework for nonlinear flight control problems

2006 ◽  
Vol 110 (1104) ◽  
pp. 85-96 ◽  
Author(s):  
T. S. Richardson ◽  
M. H. Lowenberg
Keyword(s):  
Flight Control ◽  
Systematic Approach ◽  
Control Law ◽  
Control Problems ◽  
Eigenstructure Assignment ◽  
Design Framework ◽  
Aircraft Control ◽  
Fighter Aircraft ◽  
Highly Nonlinear ◽  
Fifth Order

Abstract A methodology referred to as the continuation design framework is developed for application to nonlinear flight control problems. This forms the basis of a systematic approach to control system design for aircraft operating in highly nonlinear regions of the flight envelope. The essence of the continuation design framework is to combine bifurcation analysis with modern control methods such as eigenstructure assignment. Theoretical and practical issues of the approach are discussed with particular reference to the problems posed by agile fighter aircraft. The proposed methodology is applied to a fifth order hypothetical aircraft model and is shown to provide a visible, flexible and logical approach to nonlinear aircraft control law design.

A non-iterative design for aileron to rudder interconnect gain

2020 ◽  
pp. 1-12
Author(s):  
J. Myala ◽  
V.V. Patel ◽  
G.K. Singh
Keyword(s):  
Flight Control ◽  
Design Procedure ◽  
Surface Damage ◽  
Mode Frequency ◽  
Control Law ◽  
Lateral Control ◽  
Damage Scenario ◽  
Fighter Aircraft ◽  
Iterative Design ◽  
Control Authority

Abstract Aileron to Rudder Interconnect (ARI) gain is implemented on most fighter aircraft, primarily to reduce the side slip produced due to adverse yaw from pilot lateral control stick input and to improve the turn rate response. A systematic and non-iterative design procedure for ARI gain is proposed herein based on the evaluation of a transfer function magnitude at the aircraft roll mode frequency. The simplicity of the proposed method makes it useful for real-time flight control law reconfiguration in situations where the aileron control authority is diminished due to damage. This is demonstrated by a simulation example considering an aileron surface damage scenario.

Development of a control law to improve the handling qualities for short-range air-to-air combat maneuvers

2020 ◽  
Vol 12 (7) ◽  
pp. 168781402093679
Author(s):  
Chong-Sup Kim ◽  
Chang-Ho Ji ◽  
Byoung Soo Kim
Keyword(s):  
Flight Control ◽  
Short Range ◽  
Control Method ◽  
Control Law ◽  
Fighter Aircraft ◽  
Handling Qualities ◽  
Flying Qualities ◽  
Air Combat ◽  
Handling Quality ◽  
The Mathematical Model

Modern fighter aircraft have been designed to have high maneuverability in order to preoccupy strategic superiority in short-range air-to-air combat between fighter aircraft in warfare. Digital fly-by-wire flight control system design is aimed at providing good handling qualities for all mission task elements over the entire flight envelope. To provide both excellent gross acquisition and fine tracking compatibility, simultaneously for air-to-air combat maneuvers, this article presents a common longitudinal control law design of a task-dependent self-adjusting command-path pilot prefilter gain scheduler within the same control law design architecture and response type based on nonlinear dynamic inversion control. We perform the frequency- and time-domain analyses based on the mathematical model of T-50 advanced trainer aircraft to evaluate the basic flying qualities of the proposed control method. Furthermore, the pilot evaluation is performed to evaluate the gross acquisition and fine tracking capability for air-to-air tracking maneuvers in a handling quality simulator. The evaluation results reveal that the proposed control method improves the fine tracking capability without the degradation of gross acquisition.

Rotor-state feedback control design to improve helicopter turbulence alleviation in hover

2017 ◽  
Vol 232 (1) ◽  
pp. 156-168 ◽  
Author(s):  
Honglei Ji ◽  
Renliang Chen ◽  
Pan Li
Keyword(s):  
Control System ◽  
Feedback Control ◽  
Flight Control ◽  
State Feedback ◽  
Integrated Control ◽  
State Feedback Control ◽  
Control Law ◽  
Frequency Range ◽  
Nonlinear Simulation ◽  
Stability Margins

A helicopter flight control system with rotor-state feedback to improve turbulence alleviation in hover is presented. First, a flight dynamic model coupled with turbulence model is developed and validated. Then, an integrated control strategy with a rotor-state feedback control law is proposed based on the baseline control system. The feedback gains of body and rotor states are designed in synergy to improve turbulence alleviation in the interested frequency range of handling qualities. Subsequently, the effects of the rotor-state feedback gains on both the stability of rotor dynamics and helicopter turbulence alleviation are analyzed in detail. Finally, the effectiveness of the integrated control system is evaluated with linear analysis in frequency domain and nonlinear simulation in time domain. The results indicate that with the rotor-state feedback control law integrated into the control system, the helicopter turbulence alleviation in the interested frequency range is improved with less degradation in helicopter stability margins, and the roll and pitch rate responses of helicopter to turbulence, measured with Root-Mean-Square (RMS) values, are reduced by more than 50% and 35% respectively.

Sign in / Sign up

Export Citation Format

Share Document