Flight Path Reconstruction for a Coaxial Helicopter Equipped with Rotational Accelerometers

Hofmann, Rodolfo; Hosseini, Seyedbarzin; Fang, Xiang; Holzapfel, Florian

doi:10.2514/6.2023-3292

Cited by 1 publication

(2 citation statements)

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“…System identification for aircraft is a wide topic, and many branches of the field are discussed in [4][5][6]. Recent advances in aircraft system identification include [7][8][9][10][11][12][13][14][15][16][17][18][19][20][21][22][23][24][25]. Several methods above use frequency domain identification, which was also studied in [26][27][28][29].…”

Section: Introductionmentioning

confidence: 99%

“…These FRFs contain all the effects on the real aircraft, and give the most accurate pointwise estimate of the stability and robustness characteristics, as depicted in Figure 20. The SISO loop breaks are calculated using Equations ( 17) and (18), which ensures only the loop break under consideration is open; i.e., the other loop break is closed. The structure is depicted in Figure 22.…”

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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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