Investigation and Preliminary Development of a Modified Pseudo Control Hedging for Missile Performance Enhancement

Lam, Quang M.; Hindman, Rick; Shell, William M.; Ridgely, D. Brett

doi:10.2514/6.2005-6458

Cited by 6 publications

(3 citation statements)

References 5 publications

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“…Besides the constraint of time delay, actuator saturation is very common and a more general problem in the helicopter due to the limitation of actuators in terms of the position and rate saturation. Therefore, many recent works have been carried out on actuator saturation nonlinearity as it causes the windup phenomenon [30][31][32][33][34][35]. Based on nonlinear partial differential inequalities, an optimal saturation compensator was developed in [32].…”

Section: Introductionmentioning

confidence: 99%

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Incremental Nonlinear Dynamic Inversion Attitude Control for Helicopter with Actuator Delay and Saturation

Zhang

2023

Aerospace

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In this paper, an incremental nonlinear dynamic inversion (INDI) control scheme is proposed for the attitude tracking of a helicopter with model uncertainties, and actuator delay and saturation constraints. A finite integral compensation based on model reduction is used to compensate the actuator delay, and the proposed scheme can guarantee the semi-globally uniformly ultimately bounded tracking. The overall attitude controller is separated into a rate, an attitude, and a collective pitch controller. The rate and collective pitch controllers combine the proposed method and INDI to enhance the robustness to actuator delay and model uncertainties. Considering the dynamic of physical actuators, pseudo-control hedging (PCH) is introduced both in the rate and attitude controller to improve tracking performance. By using the proposed controller, the helicopter shows good dynamics under the multiple restrictions of the actuators.

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Section: Introductionmentioning

confidence: 99%

“…Ref. [33] further expanded the PCH theory and [34] applied the method to the development of the Boeing 747 flight control system.…”

Section: Introductionmentioning

confidence: 99%

Incremental Nonlinear Dynamic Inversion Attitude Control for Helicopter with Actuator Delay and Saturation

Zhang

2023

Aerospace

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“…If the missile does not spin, the fin deflection angle commands can be limited directly due to the actuator's capability and the respondent fin deflection angles can be stable. Literatures about controller design [1]- [3] considered the actuator saturation and took some treatments to make the control system stable. While for the spinning missile, because of the periodic motion, the actual fin deflection angles limited by the actuator's physical capability could make the respondent pseudo fin deflection angles much different from the pseudo fin deflection angle commands.…”

Section: Introductionmentioning

confidence: 99%

Controller Design for Spinning Missile with the Actuator Limit

Liu

Chen

2011

AMR

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A nonlinear two time-scale dynamic inversion controller is designed. Actuator saturation in the spinning missile will limit the control commands responses. And the periodic motion and the physical limits of the actuator’s angle and angular velocity would make the respondent pseudo fin deflection angles much different from the desired dynamics. So a kind of command shaping method which limits the fin deflection angle commands in the pseudo body coordinates before the actuator’s limiter is proposed. Meanwhile, a feedback compensation method is applied to eliminate the cross coupling between the pitch and yaw channels in the actuator due to the spinning of the missile. Finally the performance of the controller with the command shaping and decoupling treatment is analyzed.

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An acceleration measurements-based approach for helicopter nonlinear flight control using Incremental Nonlinear Dynamic Inversion

Simplicio

Pavel

Kampen

et al. 2013

Control Engineering Practice

166

118

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Investigation and Preliminary Development of a Modified Pseudo Control Hedging for Missile Performance Enhancement

Cited by 6 publications

References 5 publications

Incremental Nonlinear Dynamic Inversion Attitude Control for Helicopter with Actuator Delay and Saturation

Incremental Nonlinear Dynamic Inversion Attitude Control for Helicopter with Actuator Delay and Saturation

Controller Design for Spinning Missile with the Actuator Limit

An acceleration measurements-based approach for helicopter nonlinear flight control using Incremental Nonlinear Dynamic Inversion

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