Robust Landing Guidance Law for Impaired Aircraft

Menon, P. K.; Vaddi, Sai; Sengupta, Prasenjit

doi:10.2514/1.54213

Cited by 26 publications

(3 citation statements)

References 26 publications

(35 reference statements)

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“…The basic concept is the same as that for the vertical plane. Let us consider the aircraft as a point mass; then, we can derive the five degrees-of-freedom (DOF) equations of motion as follows 15,18…”

Section: Terminal Velocity Estimation and Trajectory Generationmentioning

confidence: 99%

Auto-landing guidance for unmanned aerial vehicle with engine flame-out

Kim

Tahk

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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Landing is the most dangerous phase of the entire flight phases. If the total loss of thrust occurs during flight, a powered aircraft converts to a glider, which can use kinetic and potential energy only. For this reason, a proper scheme is needed for safe landing in cases of the total loss of thrust. This paper presents three-dimensional unpowered auto-landing guidance based on trajectory generation, expanding the concept of the energy-to-range ratio. We develop the terminal velocity estimation method for a horizontal plane applied to three-dimensional space; this method is based on the previously suggested terminal velocity estimation method for a vertical plane. Then, we show trajectory generation for landing guidance combining vertical with horizontal waypoints. The proposed auto-landing guidance with trajectory generation is evaluated by numerical simulation.

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Section: Terminal Velocity Estimation and Trajectory Generationmentioning

confidence: 99%

Auto-landing guidance for unmanned aerial vehicle with engine flame-out

Kim

Tahk

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Bouadi et al proposed a new ACLS control strategy based on NDI to deal with different kinds of air wake perturbance [25]. Menon et al utilized the feedback linearization method to design the control law to guide the impaired aircraft [26]. Chen et al introduced a state observer into the NDI controller and the performance was described in time and frequency domains [27].…”

Section: Introductionmentioning

confidence: 99%

Bulletin of the Polish Academy of Sciences: Technical Sciences

Wang,

Zhang,

Zhu

et al. 2021

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The longitudinal automatic carrier landing system (ACLS) control law is designed based on nonlinear dynamic inversion (NDI), which can reject air wake, decouple lateral states, and track the dynamic desired touchdown point (DTP). First of all, the nonlinear landing model of F/A−18 aircraft in the final approach is established, in which the parameters of the aerodynamic, control surfaces, and limited states are acquired. Second, the strategy of tracking the desired longitudinal trajectory through pitch angle control is adopted. The automatic power compensation system (APCS), pitch angle rate, pitch angle, and vertical position control loops are developed based on the adaptive NDI. The stable analysis and the principal description are derived in detail. Deck motion compensation (DMC) algorithm is designed by frequency response method. Third, the control parameters are optimized through the genetic algorithm. A fitness function integrated with velocity, angle of attack (AOA), pitch rate, pitch angle, and vertical position of the aircraft are proposed. Finally, integrated simulations are conducted on a semi-physical simulation platform. The results indicate that the adopted automatic landing control law can achieve both excellent performance and the ability to reject the air wake and lateral coupling.

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“…Reference [25] establishes an innovative motion model for the aircraft based on NDI, which could reduce different kinds of wind turbulence. Reference [26] designs an automatic landing control law for the impaired aircraft based on feedback linearization. However, the most affecting parameter, such as the wind disturbance, is not considered.…”

Section: Introductionmentioning

confidence: 99%

Design of Automatic Carrier-Landing Controller Based on Compensating States and Dynamic Inversion

et al. 2019

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In this paper, a design scheme of automatic carrier landing system (ACLS) control law based on compensating states and dynamic inversion is proposed, in order to eliminate landing risk and air wake disturbance and improve flight quality during landing. First of all, the mathematical model for an aircraft during carrier landing is established and transformed into a low-order linear perturbed model with the involved state variables, which denotes the reference model. Second, a high-dimension field of the landing risk is addressed, which reflects the current and the potential risk degrees due to the subjective prediction of the pilots. The coefficients of the landing risk field are established based on a pilot behavioral model. Third, a concept of compensating states is proposed by this paper. On one hand, the compensating states of the air wake disturbance are estimated from the nonlinear and reference models. On the other hand, the compensating states of the landing risk are composed of the high-dimension risk field. Fourth, automatic carrier landing control law is built with the compensating states of air wake and landing risk, nonlinear dynamic inversion, and feedback signals of the flight states. In the rolling optimization progress, the landing risk, air wake, and nonlinear factors of flight states are dynamically introduced to control the state deviations and suppress landing risk. Test results based on a semi-physical simulation platform indicate that the proposed algorithm brings about an excellent landing performance and an ability to eliminate landing risk and air wake.INDEX TERMS Automatic carrier landing system, nonlinear dynamic inverse, compensating states, landing risk, air wake.

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Robust Landing Guidance Law for Impaired Aircraft

Cited by 26 publications

References 26 publications

Auto-landing guidance for unmanned aerial vehicle with engine flame-out

Auto-landing guidance for unmanned aerial vehicle with engine flame-out

Bulletin of the Polish Academy of Sciences: Technical Sciences

Design of Automatic Carrier-Landing Controller Based on Compensating States and Dynamic Inversion

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