Design of a nonlinear dynamic inversion controller for trajectory following and maneuvering for fixed wing aircraft

Pashilkar, AA; Ismail, Shaik; Ayyagari, Ramakalyan; Sundararajan, N.

doi:10.1109/cisda.2013.6595429

Cited by 10 publications

(5 citation statements)

References 9 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The linear model at this flight condition has been used in the design of the NDI based flight controller (FC). The design process is described in detail in [22].…”

Section: Aircraft Modelmentioning

confidence: 99%

“…The classical feedback controller (FC) is designed for nominal plant, separately for the longitudinal and lateraldirectional axes [22]. The feedback gains are chosen such that when there are no failures or winds the innermost feedback loops do not cause rate or position limiting of the actuators.…”

Section: Feedback Controller (Fc)mentioning

confidence: 99%

“…The design begins by considering the three rotational axes for feedback control. As described in [22], the dependent variables of the aircraft chosen for control law design are [ ]…”

Section: Feedback Controller (Fc)mentioning

confidence: 99%

“…The objective of the present work is not only to expand the fault tolerance envelope of the controller without gaps, but also to enable the controller to handle more types of actuator failures. As a first step in achieving this objective, a basic controller based on the principles of time-scale separation and Nonlinear Dynamic Inversion (NDI) is designed [22]. This fault tolerance baseline controller was augmented with a combination of an EMRAN neural controller and an SMC controller [23][24].…”

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Improved neural-aided sliding mode controller for autolanding under actuator failures and severe winds

Ismail

Pashilkar

Ayyagari

et al. 2014

Aerospace Science and Technology

Self Cite

View full text Add to dashboard Cite

In this paper, the fault tolerant capabilities of the neural aided sliding mode controller for autolanding under actuator failures and severe winds developed earlier are improved significantly by incorporating a novel anti-windup strategy and a phase compensation scheme. This controller further increases the size of the fault tolerance envelope for various types of control surface stuck faults and provides complete coverage at every point within the envelope boundaries. Earlier work by the authors showed the existence of a neural-aided sliding mode controller which could handle a wide range of actuator stuck faults. One of the major drawbacks of this earlier controller is that it does not ensure that all points within the range of minimum and maximum bounds of the fault tolerance envelope are covered. The anti-windup proposed in this paper is a generalization of the scheme used for proportionalderivative-integral controllers to the cascaded trajectory following controllers designed by the authors. This scheme can handle requirements of state limiting as well as multiple redundant control surface saturation. The proposed anti-wind up design is a simplification over the command filter approach used for adaptive backstepping. The approach is demonstrated for a fixed-wing aircraft undergoing unknown actuator stuck failures and subject to severe wind disturbances during autolanding. An example of three control surface failures (both ailerons and rudder) handled by this controller is also presented.

show abstract

“…The linear model at this flight condition has been used in the design of the NDI based flight controller (FC). The design process is described in detail in [22].…”

Section: Aircraft Modelmentioning

confidence: 99%

Section: Feedback Controller (Fc)mentioning

confidence: 99%

“…The design begins by considering the three rotational axes for feedback control. As described in [22], the dependent variables of the aircraft chosen for control law design are [ ]…”

Section: Feedback Controller (Fc)mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Improved neural-aided sliding mode controller for autolanding under actuator failures and severe winds

Ismail

Pashilkar

Ayyagari

et al. 2014

Aerospace Science and Technology

Self Cite

View full text Add to dashboard Cite

show abstract

“…The control effect and has the advantage of the universality of the control law and no requirement for adjusting the gain parameter. The application of the DI control is not only mature in SUAVs' attitude control but also successful in SUAVs' navigation and velocity control [1,[5][6][7][8][9].However, if the DI method is directly used to realize the navigation, attitude and velocity control in SUAVs, the unstable zero dynamics exists in the system [10]. The perturbation theory of time-scale separation is applied to solve that problem.…”

Section: Introductionmentioning

confidence: 99%

The flight control design for the SUAVs based on hierarchy-structured incremental dynamic inversion

Zheng

Jiang

Chen

2014

Proceedings of 2014 IEEE Chinese Guidance, Navigation and Control Conference

View full text Add to dashboard Cite

In this paper, the Small Unmanned Aerial Vehicles (SUAVs)' navigation, attitude and velocity control are integrated into a simple, unified Hierarchy-Structured Incremental Dynamic Inversion (HSIDI) control system. Firstly, based on singular perturbation theory, all the variables of the SUAVs' dynamics are divided into four groups according to time-scale, and four Dynamic Inversion (DI) subsystems are designed. Secondly, to increase the robust performance of the system, the method of the Incremental Dynamic Inversion (IDI) is applied. The IDI attitude control subsystem and the IDI velocity control subsystem are designed. This approach reduces the controller's sensitivity to the model mismatch and increases the robustness of the control system. The SUAVs' landing simulation program designed in this paper verifies the effectiveness of the method. 978-1-4799-4699-0/14/$31.

show abstract

Nonlinear Modular 3D Trajectory Control of a General Aviation Aircraft

Schatz

Holzapfel

2017

Advances in Aerospace Guidance, Navigation and Control

View full text Add to dashboard Cite

Design of a nonlinear dynamic inversion controller for trajectory following and maneuvering for fixed wing aircraft

Cited by 10 publications

References 9 publications

Improved neural-aided sliding mode controller for autolanding under actuator failures and severe winds

Improved neural-aided sliding mode controller for autolanding under actuator failures and severe winds

The flight control design for the SUAVs based on hierarchy-structured incremental dynamic inversion

Nonlinear Modular 3D Trajectory Control of a General Aviation Aircraft

Contact Info

Product

Resources

About