Realization of the Eurofighter 2000 Primary Lateral/Directional Flight Control Laws with Differential PI-Algorithm

Osterhuber, Robert; Hanel, Martin; Hammon, Rainer

doi:10.2514/6.2004-4751

Cited by 9 publications

(5 citation statements)

References 1 publication

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“…The surface allocation strategy with control matrix inversion and coupling derivative compensation to decouple lateral and directional axes within full state feedback system are discussed in (Osterhuber and Hanel 2004). In contrast to (Osterhuber and Hanel 2004), our method of design for the inner loops achieves simultaneous state and control decoupling in the lateral-directional.…”

Section: Innermentioning

confidence: 99%

“… Bifurcation control to stabilize a high-alpha vehicle (Abed 1989)  Thrust vectoring control (Albion and Joseph 1996;Stalford and Hoffman 1989)  Control laws based on Differential PI algorithms (Osterhuber and Hanel 2004) This paper discusses the development of NDI based controller using stability axis angular rates instead of the body axis angular rates and control decoupling using an optimally chosen fixed control allocation matrix. The major contribution of the paper is to demonstrate that the right hand sides of the equations of motion can be approximated by using flight path variables (…”

Section: Introductionmentioning

confidence: 99%

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Design of Nonlinear Flight Controller for Fighter Aircraft

Lathasree

Ismail

Pashilkar

2014

IFAC Proceedings Volumes

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A nonlinear flight controller is developed using dynamic inversion principles. The nonlinearities in the equations of motion arising from inertia coupling and the gravity vector are compensated by dynamic inversion. Control and state decoupling is demonstrated for conventional aileron, elevator and rudder control surfaces using a static control allocation matrix and choice of stability axis rates for feedback respectively. We demonstrate that the right hand sides of the equations of motion can be approximated by using flight path variables and traditional feedback signals like normal and lateral accelerations. Further, except for the inertia compensation and gravity compensation terms which contain sine and cosine functions, the remainder of the controller can be designed in the linear domain. The simulation results are presented for a case where a nonlinear high performance fighter aircraft is undergoing a high angle of attack stability axis roll maneuver. This maneuver exercises the aircraft over a very wide dynamic range in a short time and demonstrates the capabilities of the nonlinear controller.

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Section: Innermentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Design of Nonlinear Flight Controller for Fighter Aircraft

Lathasree

Ismail

Pashilkar

2014

IFAC Proceedings Volumes

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“…Fixed wing flight control is also a wide field with many different approaches and objectives; an excerpt is discussed in [39][40][41][42][43][44][45][46][47][48][49][50][51]. The control method of this paper is based on incremental methods, which are an active field of research.…”

Section: Introductionmentioning

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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“…In order to gain better comparability in terms of the basic FCS functionality with the Eurofighter Typhoon aircraft, the DPI approach was chosen for the design of the baseline controller [21,20,4]. It is very similar to the well-known PI controller, but distinguishes crucially with the introduction of differentiation operators at every input (i.e.…”

Section: Baseline Controllermentioning

confidence: 99%

“…For the following application on a model of the F16 aircraft, L1 Adaptive Control [13] is used to augment the DPI baseline controller [21,20,4]. As stated in [28], L1 Adaptive Control offers guaranteed transient performance and robustness through its architecture.…”

Section: Introductionmentioning

confidence: 99%

Comparison of L1 Adaptive Augmentation Strategies for a Differential PI Baseline Controller on a Longitudinal F16 Aircraft Model

Hellmundt

Wildschek

Maier

et al. 2015

Advances in Aerospace Guidance, Navigation and Control

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Abstract. In this paper two different approaches are presented to design an adaptive augmentation using L1 Adaptive Control. In terms of reference dynamics, the first one takes the closed-loop aircraft with baseline controller into account. The second approach tries to maintain nominal open-loop aircraft dynamics, with the baseline controller wrapped around the adaptive augmentation. They are compared by application to a model of the longitudinal dynamics of a F16 aircraft. The aircraft model is equipped with a Differential PI (DPI) baseline controller. The design of the combination of baseline controller and augmentation takes saturation as well as rate limitation of the control signal directly into account. Simulation results show the nominal closed-loop behavior is not harmed by the adaptive augmentation and that an increase of performance in case of uncertainty can be achieved. As an exemplary uncertainty case a rapid shift of the center of gravity (CG) is examined. The robustness of the controller structure is assessed by the use of both linear and nonlinear methods to obtain the Time Delay Margin (TDM) and the Gain Margin (GM) of the closed loop system. It can be observed, the adaptive augmentation leads to a significant decrease of robustness w.r.t. the plant input channel. This drop in TDM and GM can be fully restored by the application of a hedging strategy.

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Realization of the Eurofighter 2000 Primary Lateral/Directional Flight Control Laws with Differential PI-Algorithm

Cited by 9 publications

References 1 publication

Design of Nonlinear Flight Controller for Fighter Aircraft

Design of Nonlinear Flight Controller for Fighter Aircraft

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

Comparison of L1 Adaptive Augmentation Strategies for a Differential PI Baseline Controller on a Longitudinal F16 Aircraft Model

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