Application of NDI flight control to a second generation supersonic transport aircraft

Steer, Anthony J.

doi:10.1049/cce:20010302

Cited by 6 publications

(3 citation statements)

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“…They have traditionally been designed using 'classical' techniques, which provide functional visibility for 'real-world' applications, and are therefore universally accepted by the aerospace industry and regulatory authorities. In addition, predominantly within the research community certain multi-variable control (MVC) law design techniques, such as non-linear dynamic inversion (NDI), have proved themselves as very capable flight control law prototyping and analysis tools (12,13) .…”

Section: Flight Controlmentioning

confidence: 99%

Supersonic transport aircraft longitudinal flight control law design

Steer

2004

Aeronaut. j.

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Modern civil transport aircraft utilise increasingly complex command and stability augmentation systems to restore stability, optimise aerodynamic performance and provide the pilot with the optimum handling qualities. Provided it has sufficient control power a second generation fly-by-wire supersonic transport aircraft should be capable of exhibiting similarly desirable low-speed handling qualities. However, successful flight control law design requires identification of the ideal command response type for a particular phase of flight, a set of valid handling quality design criteria and piloted simulation evaluation tasks and metrics. A non-linear mathematical model of the European supersonic transport aircraft has been synthesized on the final approach to land. Specific handling quality design criteria have been proposed to enable the non-linear dynamic inversion flight control laws to be designed, with piloted simulation used for validation. A pitch rate command system, with dynamics matched to the aircraft's flight path response, will consistently provide Level 1 handling qualities. Nevertheless, pre-filtering the pilot's input to provide a second order pitch rate response, using the author's suggested revised constraints on the control anticipation parameter will generate the best handling qualities during the terminal phase of flight. The resulting pre-filter can be easily applied to non-linear dynamic inversion inner loop controllers and has simple and flight proven sensor requirements.

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Section: Flight Controlmentioning

confidence: 99%

Supersonic transport aircraft longitudinal flight control law design

Steer

2004

Aeronaut. j.

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“…Before the 1990s the linear method was playing a major role in the windshear researches. However, with the development and application of nonlinear inverse dynamics (NID) method (1,2) , more effective windshear penetration or escape strategies based on the physical essence of windshear have appeared in recent years (3)(4)(5)(6) . The NID method, by employing the localised information (like the wind velocity and its first and second order derivatives) for feedback, accomplishes the feedback decou-…”

Section: Introductionmentioning

confidence: 99%

Aircraft flight characteristics in conditions of windshear and icing

Cao

Yuan

2007

Aeronaut. j.

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Complex weather conditions, especially windshear and icing encounter, have severe effects on aircraft flight safety. The effect of low-altitude windshear and ice accretion on aircraft performance and control has been studied in this paper. With the employment of a windshear model and nonlinear inverse dynamics (NID) method, a low-altitude windshear penetration flight control law is designed. The effect of ice accretion was modeled on the stability and control of an aircraft. Several icing parameters are imported to the small disturbance flight dynamics model to calculate the change of performance, stability and control derivatives between clean and iced aircraft. These derivatives were used to calculate the elevator, the aileron and the rudder step responses to investigate the icing effect. The simulation results indicate that the NID control logic works effectively in the trajectory control of the aircraft during the penetration of windshear. The method used to study the effect of ice accretion on aircraft is valid and it can provide data for real-time calculation for icing encounter.

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“…Before the 1990s, the linear method was playing a major role in the windshear researches. However, with the development and application of nonlinear inverse dynamics (NID) method (Mulgund, 1993; Mulgund and Stengel, 1995), more effective windshear penetration or escape strategies based on the physical essence of windshear have appeared in recent years (Elferink and Visser, 2001; Steer, 2001). The NID method, by employing the localized information (like the wind velocity and its first‐and second order derivatives) for feedback, accomplishes the feedback decoupling of the flight management system so as to achieve realtime/online control.…”

Section: Introductionmentioning

confidence: 99%

Nonlinear inverse dynamics control of the aircraft in the presence of windshear

Cao

Chen

Yuan

et al. 2004

Aircraft Engineering and Aerospace Technology

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Control laws that are based on the nonlinear inverse dynamics (NID) of the aircraft offer the potential for providing improved levels of performance over conventional flight control designs. The NID and its application in the flight control during windshear penetration are introduced here. With the employment of a real engineering windshear model and NID, a low‐altitude windshear penetration flight control law is designed. The simulative calculation results indicated that the NID control logic works effectively in the trajectory control of the aircraft during the penetration of windshear.

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Application of NDI flight control to a second generation supersonic transport aircraft

Cited by 6 publications

References 0 publications

Supersonic transport aircraft longitudinal flight control law design

Supersonic transport aircraft longitudinal flight control law design

Aircraft flight characteristics in conditions of windshear and icing

Nonlinear inverse dynamics control of the aircraft in the presence of windshear

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