Electro Hydraulic Actuation (EHA) systems for primary flight control, landing gear and other type of actuation

Author(s):  
Anton Gaile ◽  
Yuan Lue
Keyword(s):  
2014 ◽  
Vol 31 (4) ◽  
Author(s):  
Benjamin Gal-Or

AbstractThe jet engine is the prime flight controller in post-stall flight domains where conventional flight control fails, or when the engine prevents catastrophes in training, combat, loss of all airframe hydraulics (the engine retains its own hydraulics), loss of one engine, pilot errors, icing on the wings, landing gear and runway issues in takeoff and landing and in bad-whether recoveries. The scientific term for this revolutionary technology is “jet-steering”, and in engineering practice – “thrust vectoring”, or “TV”.Jet-Steering in advanced fighter aircraft designs is integrated with stealth technology. The resulting classified Thrust-Vectoring-Stealth (“TVS”) technology has generated a second jet-revolution by which all Air-&-Sea-Propulsion Science and R&D are now being reassessed.ClassifiedOne, and perhaps a key conclusion presented here, means that bothMobile telecommunication of safe links between flyers and combat drones (“UCAVs”) at increasingly deep penetrations into remote, congested areas, can gradually be purchased-developed-deployed and then operated by extant cader of tens of thousandsWe also provide 26 references [17–43] to a different, unclassified technology that enhances TV-inducedExpected benefits include anti-terror recoveries from emergencies, like forced landing on unprepared runways or highways, or recoveries from all airframe-hydraulics-outs, asymmetric ice on wings, landing gear catastrophes, and recoveries from pilot errors and bad-whether incidents [Rule 9(7)].


Author(s):  
D G Tilley ◽  
S P Tomlinson

The increasing use of simulation for both circuit and component analysis in the aircraft industry has come about due to the requirement for acceptable transient as well as steady state performance of aircraft systems. The computer simulation package, Bathfp, developed at the Fluid Power Centre, University of Bath, is suitable for investigations into both of these. Utilities are provided which allow a model of a complicated system or component to be built up from its elements, which can be introduced to the model library of components so that particular dedicated areas of interest such as flight control actuation systems and braking and landing gear may be examined in detail. Component models enable the internal details of valves, pumps, motors, actuators and other elements to be simulated to a high degree of accuracy. This paper describes the application of the simulation package to perform a detailed analysis of the bi-stable valve in the A340 landing gear shock absorber. In the original design, a malfunction of the valve during impact on landing was clearly identified by an experimental test. Parametric variations are made in the simulation to identify the possible cause of the malfunction.


Author(s):  
S.B. Maryin ◽  
D.A. Potyanikhin ◽  
Wai Aung Phyo ◽  
Ko Hlaing Min

A significant problem in the aircraft industry remains the production of reliable hydro-gas systems, such as flight control, landing gear retraction and release, wheel turn control of the front landing gear, control of air brakes and spoilers, engine thrust reversal control, et al., providing a high degree of performance and reliability. The article discusses the technological processes of manufacturing parts for hydro-gas systems of aircraft. Research has been carried out on the expansion of the middle part of thin-walled tubular billets by cold plastic deformation, which showed that the most dangerous is the middle part of the considered part of the billet, where there are significant tensile stresses. The reduction in tensile stresses that occurs when creating an ice retainer allows to increase in the expansion ratio. The application of new types of working bodies is proposed for transferring pressure to the deformation zone.


2017 ◽  
Vol 7 (1) ◽  
pp. 28-41 ◽  
Author(s):  
Robert J. de Boer ◽  
Karel Hurts

Abstract. Automation surprise (AS) has often been associated with aviation safety incidents. Although numerous laboratory studies have been conducted, few data are available from routine flight operations. A survey among a representative sample of 200 Dutch airline pilots was used to determine the prevalence of AS and the severity of its consequences, and to test some of the factors leading to AS. Results show that AS is a relatively widespread phenomenon that occurs three times per year per pilot on average but rarely has serious consequences. In less than 10% of the AS cases that were reviewed, an undesired aircraft state was induced. Reportable occurrences are estimated to occur only once every 1–3 years per pilot. Factors leading to a higher prevalence of AS include less flying experience, increasing complexity of the flight control mode, and flight duty periods of over 8 hr. It is concluded that AS is a manifestation of system and interface complexity rather than cognitive errors.


2014 ◽  
Vol 134 (9) ◽  
pp. 1269-1270 ◽  
Author(s):  
Hiroki Noma ◽  
Shun Tanabe ◽  
Takao Sato ◽  
Nozomu Araki ◽  
Yasuo Konishi

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