Gain-scheduled directional guidance controller design using a genetic algorithm for automatic precision landing

Ha, Cheolkeun

doi:10.1007/s12555-010-0114-y

Cited by 6 publications

(5 citation statements)

References 18 publications

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“…However, in the nonlinear model highly nonlinear modeling errors and unknown parameter errors still exist. In order to deal with the uncertainties, various adaptive control theories are introduced: neural network, parameter adaptation, fuzzy logic, and genetic algorithm [11][12][13][14][15][16]. Saini et al compared adaptive critic based neural networks with the PID controller in the aircraft landing [11].…”

Section: Et Al Constructed a Linear Fractional Model Whichmentioning

confidence: 99%

“…Nho and Agarwal developed a fuzzy logic control system for the automatic landing of both linear and nonlinear aircraft models [15]. Ha modified the fuzzy logic controller through the optimization of the gain-scheduled controller by using a genetic algorithm in the automatic landing and touchdown flight [16].…”

Section: Et Al Constructed a Linear Fractional Model Whichmentioning

confidence: 99%

“…In Ref. 16, wind shear turbulence near the ground is modeled as head wind, crosswind, and downdraft, and the influence of the strong wind on the aircraft is analyzed. On the other hand, the probability of the actuator fault during the landing phase is higher compared to that during the cruise phase.…”

Section: Et Al Constructed a Linear Fractional Model Whichmentioning

confidence: 99%

See 2 more Smart Citations

Constrained Adaptive Backstepping Controller Design for Aircraft Landing in Wind Disturbance and Actuator Stuck

Yoon¹,

Kim²,

Park³

2012

International Journal of Aeronautical and Space Sciences

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An adaptive backstepping controller is designed for the automatic landing of a fixed-wing aircraft. The backstepping control scheme is adopted by using the nonlinear six degree-of-freedom dynamics of the aircraft during the landing phase. The adaptive law is integrated along with the backstepping controller in order to estimate the aircraft modeling errors as well as the external disturbance. The dynamic constraints of the states and the actuator inputs are taken into account in the parameter adaptation. This is done to prevent an aggressive adaptation and to provide reliable control commands. Numerical simulations were performed to verify the performance of the proposed control law for the landing of the aircraft with the presence of gust and actuator stuck.

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Section: Et Al Constructed a Linear Fractional Model Whichmentioning

confidence: 99%

Section: Et Al Constructed a Linear Fractional Model Whichmentioning

confidence: 99%

See 1 more Smart Citation

Constrained Adaptive Backstepping Controller Design for Aircraft Landing in Wind Disturbance and Actuator Stuck

Yoon¹,

Kim²,

Park³

2012

International Journal of Aeronautical and Space Sciences

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“…The robust gainscheduled control technique can guarantee the robust stability and the robust performance of the LPV system during the whole design region. Robust gain-scheduled technique is widely used in flight control [15][16][17][18][19].…”

Section: Robust Gain-scheduled Attitude Autopilot Designmentioning

confidence: 99%

Robust optimal trajectory design by integrating genetic algorithm with min-max method

Song

Chen

Li³

et al. 2011

Int. J. Control Autom. Syst.

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A robust optimal trajectory design method is proposed in this paper. Genetic Algorithm (GA) is employed to optimize the whole trajectory to improve the terminal attack performance. To enhance the robustness of the trajectory to disturbances, the min-max method is integrated into the GA optimization process. The proposed approach is carefully illustrated with the robust optimization design of the trajectory for a portable short-range top-attack (PSRTA) missile. The H ∞ robust gainscheduled technique is used to design the attitude tracking autopilot to facilitate the trajectory design. The damp feedback loop of the weakly-damped missile body is innovatively treated as the Linear Parameter Varying system (the controlled plant), which is good for practical use. The proposed robust optimal trajectory design method and the H ∞ robust gain-scheduled attitude tracking autopilot are demonstrated to be effective from the whole trajectory simulation results of the PSRTA missile, which also exhibit high applicability for practical engineering problems.

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“…At the same time, the speed of the plane increases. In most cases, pilots do not notice this phenomenon and reduce the power of the engine [12]. In the next step, the aircraft enters a strong downdraft, suddenly the aircraft's descent speed increases, the altitude decreases significantly [13] and it encounters a tailwind [14].…”

Section: Introductionmentioning

confidence: 99%

The Effects of Microburst Nonlinear Varying Loads on Aircraft Using a Multi-Point Approach

Pourmoradi,

Sabzehparvar

2024

Preprint

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Microburst is an atmospheric phenomenon that poses a dangerous and unavoidable threat to flying aircraft during takeoff and landing. The dynamic response of the aircraft encountered to the microburst was studied. Research on the interaction between microburst and aircraft motion is needed to assess the effects of aerodynamic forces and momentum. Unlike recent studies using conventional integrated aerodynamic models, the multi-point loading approach allows microburst nonlinear wind loading at any point on the wing and tail combination. In this method, a general reconstruction of aerodynamic forces and moments is calculated by microburst integration with different non-uniformly distributed loads functions on each surface of the aircraft. This algorithm solves the nonlinear equations of motion of a plane with six degrees of freedom and updates the plane's dynamic parameters as input to calculate time- and space-varying microburst effects for each element. The computational complexity of this method is therefore much reduced compared to CFD analysis and at the same time the details of the flight characteristics are taken into account without simplification in the simulation, which takes about 90 seconds of simulation time. We simulate and compare the results of a new and existing micro-race modeling approach. Comparing the two models shows significant differences in flight conditions such as aircraft flight path, angle of attack and angular velocity.

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Gain-scheduled directional guidance controller design using a genetic algorithm for automatic precision landing

Cited by 6 publications

References 18 publications

Constrained Adaptive Backstepping Controller Design for Aircraft Landing in Wind Disturbance and Actuator Stuck

Constrained Adaptive Backstepping Controller Design for Aircraft Landing in Wind Disturbance and Actuator Stuck

Robust optimal trajectory design by integrating genetic algorithm with min-max method

The Effects of Microburst Nonlinear Varying Loads on Aircraft Using a Multi-Point Approach

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