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The presented paper aims to describe the general idea, simulations and prototyping process of an assisting flight control system (FCS) for light sport aircraft (LSA). The proposed FCS framework is intended to simplify piloting, reduce pilot workload, and improve system's reliability and handling qualities of manual flying.

Assisting flight control strategy integrates mechanical and digital FCS into a synergic platform, combining the high reliability of mechanical controls with the computation and actuation power introduced through a single line digital FCS. Concepts drawn from classical control theory along with flight envelope protection algorithms have been used throughout the design of the flight control laws. A prototype of the assisting FCS has been subjected to validation trials during series of hardware-in-the-loop simulations.

Despite controversies between the pilots' perception of a modern aircraft and limitations imposed by the legacy airworthiness codes, it has been shown that a pilot assisting and workload reducing control system can be successfully implemented on board of a LSA while satisfying the expectations on a state-of-the-art equipment meeting required level of safety defined by the current legislation.

A transition between specific flight modes as well as nonlinearities in the FCS may lead to unfavorable and unpredictable forms of aircraft-pilot interactions. The number of accessible flight control modes should be therefore limited to the most significant ones.

Sport aircraft are mostly flown by a single pilot, who could benefit from the pilot assisting FCS as the system has the potential to supervise the aircraft's safe operation in various flight conditions.

Introducing an assisting FCS on board of a LSA through an innovative approach which utilizes hidden and unused resources of modern digital automatic FCSs while respecting the limitations imposed through the weight and cost sensitive nature of the LSA market.

The purpose of this paper is to propose a novel Unmanned Combat Air Vehicle (UCAV) flight controller parameters identification method, which is based on predator-prey Biogeography-Based Optimization (PPBBO) algorithm, with the objective of optimizing the whole UCAV system design process.

The hybrid model of predator-prey theory and biogeography-based optimization (BBO) algorithm is established for parameters identification of UCAV. This proposed method identifies controller parameters and reduces the computational complexity.

The basic BBO is improved by modifying the search strategy and adding some limits, so that it can be better applied to the parameters identification problem. Comparative experimental results demonstrated the feasibility and effectiveness of the proposed method: it can guarantee finding the optimal controller parameters, with the rapid convergence.

The proposed PPBBO algorithm can be easily applied to practice and can help the design of the UCAV flight control system, which will considerably increase the autonomy of the UCAV.

A hybrid model of predator-prey theory and BBO algorithm is proposed for parameters identification of UCAV, and a PPBBO-based software platform for UCAV controller design is also developed.

The purpose of this paper is to describe the general idea, design, and implementation of control system for general aviation aircraft which reduces pilot workload.

Proposed indirect flight control system framework is intended to simplify piloting, reduce pilot workload, and allow low‐end general aviation aircraft to operate under deteriorated meteorological conditions. Classical control theory is used for the design of the flight control laws. Although not inherently robust, controllers with classical control logic are made sufficiently stable using a correct and updated controller structure.

Despite controversies between perception of a modern manned aerial vehicle and limitations imposed by legacy airworthiness codes it is shown that a pilot workload reducing system can be successfully implemented onboard of a low‐end general aviation aircraft.

Hi‐level control laws and optimization of handling qualities can lead to unfavourable and unpredictable forms of man‐machine interactions, e.g. pilot‐induced oscillations.

General aviation aircraft are mostly flown by a single pilot, who could benefit from an intelligent system or “virtual copilot” assisting in or supervising the aircraft's safe operation under any conditions. Aircraft with this capability represents a next step in the evolution that might ultimately lead to trajectory‐based free‐flight concept of aircraft operations.

The paper introduces a safety enhanced digital flight control system on board small general aviation aircraft.

A proposal of the perspective solution of the general aviation aircraft control system is presented. The objective of the proposed concept for the control system is to assist pilots with limited aviation training by: automatic stabilization of the aircraft's attitude, altitude, airspeed, and heading and decoupling of the flight controls. The structure and main functions of the control system is presented, and method of control laws synthesis is proposed. Flight control system is based on the model‐following design technique. Two kinds of flight control systems are taken into consideration. The first solution is based on the optimal full‐state feedback controller, the second one is the simplified controller, using the easy observed states for feedback loop only. The project calculation of the flight control system for PZL‐110 “Koliber” aircraft, computer simulations and preliminary flight testing results will be presented.

The purpose of this paper is to present the generic conception of the aircraft control system with the voice command interpretation interface. The paper's intention is also to present the first steps of work under control system for general aviation aircraft, which assists pilots using speech interpretation module.

The paper defines the main rules governing projecting and operating such systems, and defines and discusses the main functionality levels. The use of voice commands for the direct controlling of the flight of the plane is also presented and analyzed in detail.

The paper presents general rules, which could be applied for work under control systems with speech interpretation modules intended for general aviation aircraft.

The analyses and opinions included in this paper can be generic basis for future projects, which will try to use pilot's voice command to control the general aviation airplane.

This paper presets some conception of the control system with the speech recognition interface. There are main rules generally defining both the structure and the functionality the of such aircraft control system, included in this paper.

Smiths Industries is to supply the head‐up display system for the Sea Harrier. The company will design, develop and make the electronic head‐up display and weapon aiming computer system for the latest version of the HS Harrier which will operate from Royal Navy ships.

IN recent years the regularity of scheduled services has become an increasingly important factor in the economics of the air transport industry. Service regularity is dependent to a marked extent upon aircraft reliability and upon the ability to operate in reduced weather limits. For this reason the requirements for low weather operations and for improved equipment reliability have become principal factors affecting the development of flight control equipment.

THE automatic flight control system (AFCS) for the Concorde has been jointly developed by Elliott‐Automation Ltd. and SFENA (Société Francaise pour la Navigation Aérienne) for the production aircraft. Elliott carry the overall design responsibility and the equipment will be supported in the field by both Elliott and SFENA. The pitch axis of the autopilot and flight director, the autothrottle, all aspects of the control of speed, all pilot/ AFCS interfaces and the landing display are Elliott responsibilities for the pre‐production and production aircraft, while SFENA are responsible for the three‐axis autostabiliser, azimuth axes of the autopilot and flight director, electric trim system and the flight test instrumentation for the AFCS. The Bendix Corporation participated in the programme for the prototype aircraft with the design and manufacture of the azimuth axes of the autopilot and flight director, and the electric trim system.

This study presents an image processing algorithm capable of calculating selected flight parameters requested by flight control systems to guide aircraft along the horizontal projection of the landing trajectory. The parameters identified based on the basics of the image of the Calvert light system appearing in the on-board video system are used by flight control algorithms that imitate the pilot’s schematics of control. Controls were generated using a fuzzy logic expert system. This study aims to analyse an alternative to classical solutions that can be applied to some specific cases.

The paper uses theoretical discussions and breakdowns to create the basics for the development of structures for both image processing algorithms and control algorithms. An analytical discussion on the first stage was transformed into laboratory rig tests using a real autopilot unit. The results of this research were verified in a series of software-in-the-loop computer simulations.

The image processing method extracts the most crucial parameters defining the relative position of the aircraft to the runway, as well as the control algorithm that uses it.

In flight control systems that do not use any dedicated ground or satellite infrastructure to land the aircraft.

This paper presents the original approach of the author to aircraft control in cases where visual signals are used to determine the flight trajectory of the aircraft.