Combining Stable Inversion and H∞ Synthesis for Trajectory Tracking and Disturbance Rejection Control of Civil Aircraft Autolanding
Abstract
:1. Introduction
- (1).
- A robust autolanding controller (RAC) is designed based on synthesis, which can handle with the disturbances during landing procedure, such as windshear and noise.
- (2).
- A stable inversion (SI) based robust autolanding controller (SIRAC) is proposed to improve the RAC scheme. The SI algorithm is used to enhance the trajectory tracking ability of aircraft autolanding system, which calculates the desired input and state through the desired landing trajectory. While the disturbance rejection ability is also increased due to the integration of the SI algorithm and synthesis.
2. Dynamics Modelling and Problem Formulation
2.1. Aircraft Dynamics and Actuator Modelling
2.2. Windshear Model
2.3. The Desired Landing Trajectory
3. Design of SIRAC
3.1. The SI Algorithm
3.2. Design of RAC
3.3. Combining the SI Algorithm and RAC
- Step 1
- Calculating .
- Step 2
- Knowing , solve Equation (29) and Equation (34) using SI algorithm to find the and .
- Step 3
- Knowing and , solve .
- Step 4
- Knowing , solve for the input of RAC: .
- Step 5
- Knowing , solve Equation (36) for the output of RAC: .
- Step 6
- Knowing , solve for the input of the aircraft: .
- Step 7
- Knowing , solve the system equation of aircraft for .
- Step 8
- Iterate over Step 3 to 7 until the landing process is done.
4. Simulation Analysis
4.1. Scenario 1
4.2. Scenario 2
5. Conclusions
Author Contributions
Funding
Acknowledgments
Conflicts of Interest
Nomenclature
aircraft mass | |
elevator deflection angle and throttle position changing, respectively | |
elevator command and throttle command, respectively | |
altitude and desired altitude, respectively | |
longitudinal speed and desired longitudinal speed, respectively | |
angle of attack, pitch angle and flight path angle, respectively | |
pitch rate | |
thrust inclination angle | |
principal moment of inertia in pitch axis | |
pitching moment | |
thrust, lift and drag, respectively | |
aerodynamic coefficients of lift, drag and pitching moment, respectively | |
angle of attack derivative of lift, drag and pitching moment, respectively | |
elevator variation derivative of lift, drag and pitching moment, respectively | |
angle of attack rate derivative of lift, drag and pitching moment, respectively | |
pitch rate derivative of lift, drag and pitching moment, respectively | |
throttle variation derivative of thrust | |
wing reference area | |
mean aerodynamic chord | |
air density | |
horizontal and vertical wind speed, respectively | |
strengths of windshear |
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Parameter | Value | Unit | Description |
---|---|---|---|
250,000 | kg | Mass | |
510 | m2 | Wing reference area | |
8.3 | m | Mean aerodynamic chord | |
kg·m2 | Pitch axis inertia | ||
0.044 | rad | Thrust inclination angle | |
1.71 | |||
5.67 | 1/rad | Angle of attack derivative for lift | |
0.36 | 1/rad | Elevator variation derivative for lift | |
6.7 | s/rad | Angle of attack rate derivative for lift | |
5.65 | s/rad | Pitch rate derivative for lift | |
0.263 | |||
1.13 | 1/rad | Angle of attack derivative for drag | |
0 | 1/rad | Elevator variation derivative for drag | |
0 | s/rad | Angle of attack rate derivative for drag | |
0 | s/rad | Pitch rate derivative for drag | |
−0.093 | |||
−1.45 | 1/rad | Angle of attack derivative for moment | |
−1.40 | 1/rad | Elevator variation derivative for moment | |
−3.3 | s/rad | Angle of attack rate derivative for moment | |
−21.4 | s/rad | Pitch rate derivative for moment | |
382.572 | kN | ||
7801.63 | kN/rad | Throttle variation derivative for thrust |
Parameters | Value | Unit | Description |
---|---|---|---|
0 | m | Altitude | |
67.4 | m/s | Initial speed | |
1.225 | kg/m3 | Air density | |
0.148 | rad | Trim angle of attack | |
0 | rad | Trim flight path angle |
0.35(rad) | 0.26(rad/s) | 0.088(rad) | 0.017(rad/s) |
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Wang, X.; Sang, Y.; Zhou, G. Combining Stable Inversion and H∞ Synthesis for Trajectory Tracking and Disturbance Rejection Control of Civil Aircraft Autolanding. Appl. Sci. 2020, 10, 1224. https://doi.org/10.3390/app10041224
Wang X, Sang Y, Zhou G. Combining Stable Inversion and H∞ Synthesis for Trajectory Tracking and Disturbance Rejection Control of Civil Aircraft Autolanding. Applied Sciences. 2020; 10(4):1224. https://doi.org/10.3390/app10041224
Chicago/Turabian StyleWang, Xudong, Yuanjun Sang, and Guangrui Zhou. 2020. "Combining Stable Inversion and H∞ Synthesis for Trajectory Tracking and Disturbance Rejection Control of Civil Aircraft Autolanding" Applied Sciences 10, no. 4: 1224. https://doi.org/10.3390/app10041224
APA StyleWang, X., Sang, Y., & Zhou, G. (2020). Combining Stable Inversion and H∞ Synthesis for Trajectory Tracking and Disturbance Rejection Control of Civil Aircraft Autolanding. Applied Sciences, 10(4), 1224. https://doi.org/10.3390/app10041224