Morphing Unmanned Air Vehicle Intelligent Shape and Flight Control

Valasek, John; Lampton, Amanda; Marwaha, Monika

doi:10.2514/6.2009-1827

Cited by 12 publications

(4 citation statements)

References 9 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In practice, this is an integral feature of the CAS to be implementable on the control system for morphing aircraft, where the moment of inertia may have a wide variation. Then, the commanded moment coefficients can be recovered from the commanded moments through equations (18) to (20). Finally, the commanded moment coefficients can be expressed in terms of the control surface deflections by using equations (37) to (39) as follows where…”

Section: Model Inversionmentioning

confidence: 99%

“…On the other hand, a gain scheduling (conventional and linear-parameter varying) approach, model-reference adaptive control scheme, and various nonlinear control techniques such as feedback linearization, sliding mode, and back-stepping control methods have been studied. Consequently, the problem of morphing aircraft flight controller design has been addressed via various approaches that can capture the parameter-varying nature of the system, such as linear parameter-varying control, [12][13][14][15][16][17] adaptive control, [18][19][20][21][22] and sliding mode control. 16,17 However, no previous study has considered handling qualities criteria.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Neural network-based nonlinear dynamic inversion control of variable-span morphing aircraft

Lee

Kim

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

A nonlinear command and stability augmentation system is designed based on feedback linearization for a morphing aircraft in the presence of different variable-span configurations. A variable-span morphing aircraft model is obtained by modifying a conventional aircraft model. Feed-forward neural networks are trained to learn the inverse dynamics in various morphing configurations and flight conditions. An attitude orientation system is designed to stabilize the airframe and track the commanded angular rates. Finally, an online adaptive mechanism is employed to compensate for inversion error. Even when the aircraft is changing the morphing configuration while maneuvering, the proposed design satisfies the desired handling quality specifications. Consequentially, the proposed design provides another degree of freedom to manipulate the morphing configuration, and therefore agility or fuel efficiency can be improved. Numerical simulation is performed to demonstrate the effectiveness of the proposed scheme.

show abstract

Section: Model Inversionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Neural network-based nonlinear dynamic inversion control of variable-span morphing aircraft

Lee

Kim

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

show abstract

“…Remark 6. There exists an RBFNN in the form of (21) and an optimal parameter vector * such that | ( in ) − * Φ( in )| = | * | < re . re denotes the supremum of the reconstruction error that is inevitably generated.…”

Section: Neural Networkmentioning

confidence: 99%

“…In [20], a single network adaptive critic tracking controller design for a morphing aircraft is studied, wherein the set of initial weights of the neural network is determined by using a linear system model, which requires offline pretraining. Based on the concepts of feedback linearization, in [21], a combination of dynamic inversion and structured model reference adaptive control is used for the control of a morphing air vehicle. Typically a morphing aircraft exhibits highly nonlinear dynamics characteristics.…”

Section: Introductionmentioning

confidence: 99%

Adaptive Neural Control Based on High Order Integral Chained Differentiator for Morphing Aircraft

Rajput

et al. 2015

Mathematical Problems in Engineering

View full text Add to dashboard Cite

This paper presents an adaptive neural control for the longitudinal dynamics of a morphing aircraft. Based on the functional decomposition, it is reasonable to decompose the longitudinal dynamics into velocity and altitude subsystems. As for the velocity subsystem, the adaptive control is proposed via dynamic inversion method using neural network. To deal with input constraints, the additional compensation system is employed to help engine recover from input saturation rapidly. The highlight is that high order integral chained differentiator is used to estimate the newly defined variables and an adaptive neural controller is designed for the altitude subsystem where only one neural network is employed to approximate the lumped uncertain nonlinearity. The altitude subsystem controller is considerably simpler than the ones based on backstepping. It is proved using Lyapunov stability theory that the proposed control law can ensure that all the tracking error converges to an arbitrarily small neighborhood around zero. Numerical simulation study demonstrates the effectiveness of the proposed strategy, during the morphing process, in spite of some uncertain system nonlinearity.

show abstract

Modeling and Simulation of Morphing Wing Aircraft

Obradovic

Subbarao

2012

Morphing Aerospace Vehicles and Structures

View full text Add to dashboard Cite

Morphing Unmanned Air Vehicle Intelligent Shape and Flight Control

Cited by 12 publications

References 9 publications

Neural network-based nonlinear dynamic inversion control of variable-span morphing aircraft

Neural network-based nonlinear dynamic inversion control of variable-span morphing aircraft

Adaptive Neural Control Based on High Order Integral Chained Differentiator for Morphing Aircraft

Modeling and Simulation of Morphing Wing Aircraft

Contact Info

Product

Resources

About