Fly-by-wire flight control systems are becoming more common in both civil and military aircraft. These systems give many benefits, but also present a new set of problems due to their increased complexity compared to conventional systems and the larger choice of options that they provide. The work presented here considers the application of fly-by-wire to a generic regional transport aircraft. The flying qualities criteria used for typical flying qualities evaluations are described briefly followed by analysis of several past transport aircraft flying qualities programmes against these criteria. From these results, some control law independent design requirements are formulated for a civil aircraft for the approach and landing task. These control law independent flying qualities criteria are intended to be used with any generic rate-like control law for a transport aircraft and enabled a number of different control laws to be designed. The results of a number of flying qualities evaluations are presented. Both an ILS approach task and a formation flying task were used. The effects of windshear were also considered. It was found that control laws which maintain flight path are suitable for the ILS approach task, while most rate-like response characteristics give good flying qualities for the formation flying task. Finally, the conclusions drawn from these evaluations are presented, and both the Civil and Military current airworthiness requirements are assessed. In addition to the flying qualities work, a study is made of the management issues associated with fly-by-wire design. A fly-by-wire aircraft design programme was proposed and the project management issues associated with this were considered. A timescale was proposed for the design process for a generic regional aircraft, and the critical path for this process is presented.

Fly-by-wire flight control systems are becoming more common in both civil and military aircraft. These systems give many benefits, but also present a new set of problems due to their increased complexity compared to conventional systems and the larger choice of options that they provide. The work presented here considers the application of fly-by-wire to a generic regional transport aircraft. The flying qualities criteria used for typical flying qualities evaluations are described briefly followed by analysis of several past transport aircraft flying qualities programmes against these criteria. From these results, some control law independent design requirements are formulated for a civil aircraft for the approach and landing task. These control law independent flying qualities criteria are intended to be used with any generic rate-like control law for a transport aircraft and enabled a number of different control laws to be designed. The results of a number of flying qualities evaluations are presented. Both an ILS approach task and a formation flying task were used. The effects of windshear were also considered. It was found that control laws which maintain flight path are suitable for the ILS approach task, while most rate-like response characteristics give good flying qualities for the formation flying task. Finally, the conclusions drawn from these evaluations are presented, and both the Civil and Military current airworthiness requirements are assessed. In addition to the flying qualities work, a study is made of the management issues associated with fly-by-wire design. A fly-by-wire aircraft design programme was proposed and the project management issues associated with this were considered. A timescale was proposed for the design process for a generic regional aircraft, and the critical path for this process is presented. / EPSRC; Avro International Aerospace.

Techn. Univ., Diss.--Darmstadt, 1999. / Literaturverz. S. 193 - 202.

Zugl.: Darmstadt, Techn. Universiẗat, Diss., 1999.

The introduction of fly-by-wire electronic flight control systems into transport aircraft has given the flying qualities engineer the opportunity to optimise the flying qualities of these aircraft for their specific tasks. With this technology has come the opportunity to introduce new technologies into the cockpit, such as non-linked or backfed sidesticks and non-backfed throttle levers. A comparative survey of airline pilots flying such a very high technology unconventional aircraft and a high technology but conventional aircraft suggests that these technologies may reduce the available channels of communication to the pilot in the very high technology aircraft, resulting in the possibility of reduced situational awareness. A closed loop piloted simulation survey of ten transport aircraft in current operation was undertaken which demonstrated that they all suffered from flying qualities deficiencies, limiting the performance that the pilot could achieve. In particular poor dynamics precluded the pilot adopting tight closed loop, or compensatory, control. Instead it was necessary to adopt a more open loop, precognitive, technique with medium frequency modulation, resulting in a degradation in landing performance. Through appropriate flight control system design it should be possible to produce aircraft that can be flown using the full range of control inputs from open to closed loop. The major study of this thesis assessed, through piloted simulation evaluations, the suitability of a wide range of longitudinal commanded response types for the approach and landing tasks. It was concluded that a response type that closely resembles that of angle of attack is optimum for these tasks due to its conventional characteristics of speed stability on the approach and monotonic stick forces in the flare. Such a system, appropriately implemented, should allow the transport aircraft pilot the full range of piloted control inputs, from open loop, precognitive, to closed loop, compensatory, resulting in improved landing performance.

Zugl.: Hamburg, Techn. Univ., Diss., 2009

Zugl.: Hamburg, Techn. Univ., Diss., 2009

No description available.

This thesis is dealing with selection of proper airplane data bus for distributed Fly-by-Wire system. The parameters of such data bus are defined here and description of such data buses are given as well. The proper data bus which fulfils the given parameters is selected. Next the safety and time-delay analysis are provided.

Digitální Fly-by-Wire systém je novým přístupem k řídícímu systému letadla, na jehož základě firma Honeywell - HTS CZ začala výzkumný projekt s názvem “Next Generation Distributed Fly-by-Wire System” a tato práce je jeho součástí. Řídící plochy letadla jsou řízeny dvěma nebo třemi elektrohydraulickými (či elektrickými) servy a každé servo je ovládáno nezávislou řídící jednotkou. Díky provozním tolerancím systému a drobným odchylkám vstupních dat v řídících jednotkách, dostává každé servo mírně odlišné povely a rozdíl v poloze serv vede k namáhání řídící plochy i k namáhání serv. Hlavním cílem této práce je navrhnout algoritmus, který bude eliminovat rozdíly mezi polohami jednotlivých serv, a tudíž sníží sílu, která namáhá řídící plochu, na přípustnou mez. Implementace řídícího systému letadla byla do detailu analyzována a algoritmus redukce síly na kontrolní ploše letadla byl navržen a implementován v prostředí Simulink. Iterační kriteriální ladící metoda byla vyvinuta a za účelem co nejlepšího nastavení algoritmu redukce síly. Práce také analyzuje vliv časových zpoždení na sběrnici na kvalitu algoritmu redukce síly.