Low-Cost Sensor Based Integrated Airdata and Navigation System for General Aviation Aircraft

Myschik, Stephan; Holzapfel, Florian; Sachs, Gottfried

doi:10.2514/6.2008-7423

Cited by 14 publications

(5 citation statements)

References 5 publications

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“…with e T y being the unit vector in the y direction of the associated frame (in this case in the A frame). For many aircraft, including small or subscale aircraft, a measurement or estimate of α A and β A , as, for example, investigated in [122], may not be feasible. An approximation may be obtained considering M AB ≈ I, r K cos α A ≈ r K and p K sin α A ≈ 0.…”

Section: Flow Angle Derivatives For State Feedbackmentioning

confidence: 99%

Practical System Identification and Incremental Control Design for a Subscale Fixed-Wing Aircraft

Steffensen,

Ginnell,

Holzapfel

2024

Actuators

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An incremental differential proportional integral (iDPI) control law using eigenstructure assignment gain design is tested in flight on a subscale platform to validate its suitability for fixed-wing flight control. A kinematic relation for the aerodynamic side-slip angle rate is developed to apply a pseudo full state feedback. In order to perform the gain design and assessment, a plant model is estimated using flight test data from gyro, accelerometer, airspeed and surface deflection measurements during sine-sweep excitations. Transfer function models for the actuators and surface deflections are identified both in-flight and on the ground for several different actuators and control surfaces using hall sensor surface deflection measurements. The analysis reveals a large variation in bandwidth between the different types of servo motors. Flight test results are presented which demonstrates that the plant model estimates based on tests with good frequency excitation, high bandwidth actuators and surface deflection measurements can be used to reasonably predict the closed-loop dynamic behavior of the aircraft. The closed-loop flight test results of the iDPi control law show good performance and lays the groundwork for further development.

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Section: Flow Angle Derivatives For State Feedbackmentioning

confidence: 99%

Practical System Identification and Incremental Control Design for a Subscale Fixed-Wing Aircraft

Steffensen,

Ginnell,

Holzapfel

2024

Actuators

Self Cite

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“…In equations (8) and (9), sgn(Á) is the sign function. Therefore, it can be stated that and asymptotically go to zero for arbitrary positive scalar and in accordance with Lyapunov stability theorem.…”

Section: Nonlinear Load Relief Approachmentioning

confidence: 99%

“…However, it is difficult to accurately measure or estimate the angle of attack or the lateral acceleration of the launch vehicle. 9,10 In this work, the nonlinear load relief scheme is proposed to regulate aerodynamic angles. Based on the proposed controller and traditional load relief schemes, a hybrid load relief controller is suggested.…”

Section: Introductionmentioning

confidence: 99%

Load relief control of launch vehicle using aerodynamic angle estimation

Park

et al. 2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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A nonlinear closed-loop load relief scheme is proposed to reduce the aerodynamic load during the ascent phase of a launch vehicle. The proposed controller is designed based on a back-stepping and sliding-mode control scheme with aerodynamic angle feedback. A hybrid load-relief strategy using the load relief scheme around the period of the maximum dynamic pressure and the traditional minimum-drift scheme during the other period is proposed. An aerodynamic angle estimator is also developed using a Kalman filter for the feedback of the load relief control. Numerical simulation is conducted to demonstrate the performance of the proposed strategy as well as the potential benefits.

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“…The estimation of α and β was first derived from aircraft acceleration measurements, in which wind disturbance was described by random noise [5]. Since the acceleration-based algorithm failed to provide adequate stability under severe disturbance, the equations of motion of aircraft were integrated, in which α and β were estimated with measured attitude angles from inertial sensors [6,7]. The independent wind field estimation based on navigation and pitot system parameters appeared in the study of airspeed calibration [8] and formation flight [9], in which the measurements of air data were assumed to be accurate.…”

Section: Introductionmentioning

confidence: 99%

Flight Data-Based Wind Disturbance and Air Data Estimation

et al. 2021

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The instantaneous wind field and air data, including true airspeed, angle of attack, angle of sideslip, cannot be measured and recorded accurately in wind disturbance. A new air data and wind field estimation method is proposed based on flight data in this study. Since the wind field is the horizontal prevailing wind added by turbulence, the slowly time-varying prevailing wind and small-scale turbulence are described by the exponentially correlated stochastic wind model and von Karman turbulence model, respectively. The system update equation of air data is built based on inertial measurements instead of the complex aerodynamic and aero-engine model of aircraft. Benefitted by the post-analysis characteristics of flight data, a forward–backward filtering algorithm was designed to improve the estimation accuracy. Simulation results indicate that the forward–backward filter integrated with the von Karman turbulence model can reduce the estimation error and ensure filtering stability. A further test with actual flight data shows that the forward–backward filter is not only able to track the wide-range change in prevailing wind but also reduce the adverse effects of uncertain disturbance on estimation accuracy.

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Low-Cost Sensor Based Integrated Airdata and Navigation System for General Aviation Aircraft

Cited by 14 publications

References 5 publications

Practical System Identification and Incremental Control Design for a Subscale Fixed-Wing Aircraft

Practical System Identification and Incremental Control Design for a Subscale Fixed-Wing Aircraft

Load relief control of launch vehicle using aerodynamic angle estimation

Flight Data-Based Wind Disturbance and Air Data Estimation

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