TECS Generalized Airplane Control System Design – An Update

Lambregts, A. A.

doi:10.1007/978-3-642-38253-6_30

Cited by 35 publications

(16 citation statements)

References 2 publications

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“…The autopilot for the lateral motion / THCS similary adjusts roll angle and yaw rate commands in order to track commanded heading and sideslip angles, where the roll rate works to cancel the sum and the yaw rate to adjust the difference of the angle errors. Details on the concepts of TECS and THCS given in the original patent of Lambregts [23] and later adaptations [24,25].…”

Section: Flight Control Lawsmentioning

confidence: 99%

Analysis of Automatic Control Function Effects on Vertical Tail Plane Critical Load Conditions

Kier

Müller

Looye

2020

AIAA Scitech 2020 Forum

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This paper presents a modelling scheme suitable for loads analysis of maneuvers and gusts of flexible aircraft with active control systems. In contrast to most ongoing research the component to be investigated is not the wing but the vertical tail plane (VTP). Critical load conditions for vertical tail plane include yawing maneuver conditions as well as discrete lateral gusts. A new rudder reversal load condition features a three full reversals of the rudder pedal input instead of just one step input and a mere return to neutral. This condition, where resulting loads are considered ultimate, was mainly motivated by wake vortex encounters during which the pilots made excessive use of the rudder. The design loads resulting from all conditions are heavily influenced by the flight control system, the underlying control law design method, and associated control law parameters. This gives rise to interesting trade-offs between handling qualities and loads sizing the VTP structure. Therefore, in this paper the influence of different types of lateral control laws on the loads of the different gust and maneuver conditions for certification as specified by the authorities is analysed. The control laws considered vary from basic yaw damping with rudder travel limitation to full roll and yaw command augmentation systems. From a design methodology point of view, classical and (incremental) Nonlinear Dynamic Inversion-based methods are analysed.

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Section: Flight Control Lawsmentioning

confidence: 99%

Analysis of Automatic Control Function Effects on Vertical Tail Plane Critical Load Conditions

Kier

Müller

Looye

2020

AIAA Scitech 2020 Forum

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“…where k and k p are gains for the roll control loop and k r a gain for the yaw control loop. The following equations describe the fixed-wing aircraft lateraldirectional dynamics (13) in closed loop with the controller (14) _ ¼p þr t…”

Section: Partial Linearizing State Feedbackmentioning

confidence: 99%

“…The closed-loop dynamics (13) to (21) are described by the following differential equations _ ¼p þr t…”

Section: Remarkmentioning

confidence: 99%

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A coordinated turn controller for a fixed-wing aircraft

Corona-Sánchez

Caso

Rodriguez-Cortes

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper describes the design of a controller for a fixed-wing aircraft to make it perform coordinated turns. First, a state feedback partial linearization controller drives the airplane to carry out an ideal coordinated turn. A second control loop, inspired by the total heading control system technique, mixes the ailerons and rudder inputs to perform a coordinated turn considering the sideslip dynamics. The control design development gives new insights to establish the fundamental basis for the total heading control system. Simulations in an advanced flight simulator (X-Plane 10) are presented to show the closed-loop system behavior.

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“…Deciding on what system 'state variables' are used to design the interface and automated tools is crucial. Aviation has several examples where, because of (on hindsight) unfortunate design decisions early on in the development of systems -like in autopilots, see (Lambregts, 2013) -interfaces and automation are not complete. The resulting (human factors) problems will continue to pop up now and then, but the real problem is rooted deeper inside these legacy systems.…”

Section: Closing Statementsmentioning

confidence: 99%

Designing for Situation Awareness - Aviation Perspective

Mulder

Borst

Paassen

2017

Proceedings of the International Conference on Computer-Human Interaction Research and Applications

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Abstract:In the design of human-machine interfaces and automation, an important question is how to obtain and validate a design that is capable of supporting the operator's understanding and situation awareness of the process under control. Whereas many research efforts address the question of 'what is the operator aware of?' -the awareness -only a few investigations focus on studying what the operator should be aware of in the first place, i.e., 'what is the situation?' In this paper we briefly discuss some of our research activities which aim at answering this second question, following an 'ecological approach' to interface design. The clever use of automation tools and novel visualizations will be presented that allows human operators working in aviation (pilots, air traffic controllers) in dealing with complex tasks. The airborne self-separation task will be discussed, as an example of showing how ecological interfaces can support pilots in their decision making.

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TECS Generalized Airplane Control System Design – An Update

Cited by 35 publications

References 2 publications

Analysis of Automatic Control Function Effects on Vertical Tail Plane Critical Load Conditions

Analysis of Automatic Control Function Effects on Vertical Tail Plane Critical Load Conditions

A coordinated turn controller for a fixed-wing aircraft

Designing for Situation Awareness - Aviation Perspective

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