The Design of Actuating Cylinder Salt Spray Testing Device Based on Lab Windows/CVI and PLC Control

2011 ◽  
Vol 411 ◽  
pp. 269-273
Author(s):  
Geng He Luo ◽  
Yu Wang ◽  
Bin Gao Yu
Keyword(s):  
Salt Spray ◽  
Computer Software ◽  
Experimental Device ◽  
Control Precision ◽  
Aircraft Landing ◽  
Plc Control ◽  
Test Parameters ◽  
Aircraft Landing Gear ◽  
Test Requirements ◽  
And Storage

The performance tests and the requirements of experiments on aircraft alighting gear actuating cylinder in the salt spray and hot and humid environment are presented in this paper, and the hydraulic system of experimental device is designed. The host computer software is developed by Lab Windows/CVI for actuating cylinder on test parameters settings, monitoring, and storage and record, The Siemens PLC are used at the sub-processors to control the salt spray experimental device. The field-test shows that the device control precision is higher to pressure, flow rate, and the parameters such as temperature, and it can realize the simulation for different salt spray and hot and humid environments. The test on aircraft landing gear by using actuating cylinder has a good human-computer interaction and communication function. The device is safe, reliable and it can reach the test requirements.

scholarly journals FACILITY FOR HYDROGENATION AND THERMAL TESTING OF INTERNALLY PRESSURIZED DUMMY FUEL RODS

2020 ◽  
pp. 195-197
Author(s):  
V.A. Dolgiy ◽  
V.A. Chunosov ◽  
D.L. Kokosha ◽  
Т.P. Chernyayeva ◽  
V.M. Grytsyna ◽  
...  
Keyword(s):  
Hydrogen Concentration ◽  
Thermal Testing ◽  
Fuel Rods ◽  
Fuel Rod ◽  
Tangential Stresses ◽  
Test Parameters ◽  
Measurement Devices ◽  
Hydride Reorientation ◽  
Test Requirements ◽  
And Storage

A facility allowing to conduct experiments on dummy fuel rods up to 250 mm long, at temperatures up to 700 °C is presented. The designed facility is unique in that the conditions for the tests to be conducted on it most closely resemble (except for irradiation) those of fuel rods operation, loading and storage in SFDSF. All test parameters are programmed and regulated by special sensors, which brings the experiment on fuel rod temperature effect and pressure under the cladding as close as possible to the conditions of fuel rod operation in reactor and further storage in SFDSF. Hydride Reorientation Test (HRT) was conducted on dummy fuel rod sunder internal pressure of 3...5 MPa (at room temperature) and with hydrogen concentration of 50...300 ppm in the modes that simulate SNF handling with limiting heating to 410 °С and accidents with seven 410↔300 and 410↔180 °С thermal cycles. It has been demonstrated that the effectiveness of the influence of the test conditions in the specified modes on hydride reorientation increases with increasing hydrogen concentration and tangential stresses in the dummy fuel rod claddings. It has been shown that the test samples design, control and measurement devices, as well as the parameters estimated during the test and further investigations fully meet the test requirements.

COMPARATIVE CHARACTERISTICS OF PHYSICAL AND MECHANICAL PROPERTIES OF COMPOSITE MATERIALS AND HIGH-STRENGTH STEEL 30FGSN2A

2020 ◽  
Author(s):  
I.R. Antypes ◽  
◽  
V.V. Zaitsev ◽  
Keyword(s):  
Composite Materials ◽  
High Strength Steel ◽  
Critical Stress ◽  
Physical And Mechanical Properties ◽  
High Strength ◽  
Aviation Industry ◽  
Specific Strength ◽  
Aircraft Landing ◽  
Carbon Plastics ◽  
Aircraft Landing Gear

Currently, the use of composite materials is increasingly used in various areas of the national economy, including the aviation industry. The materials of this article are devoted to the study of the use of composite materials for the manufacture of aircraft landing gear in comparison with the traditionally used brand of steel. As a result of the work carried out, it was found that the slope made of carbon fiber showed a critical stress twice as high as its design made of 30xgsn2a steel. In addition, carbon plastics are superior to high-strength steel in terms of specific strength, stiffness, and tensile strength.

ALMAR 20

Alloy Digest ◽  
1964 ◽  
Vol 13 (4) ◽  
Keyword(s):  
Corrosion Resistance ◽  
Low Temperature ◽  
Solid Fuel ◽  
Precipitation Hardening ◽  
Martensitic Steel ◽  
Heat Treating ◽  
Aircraft Landing ◽  
Temperature Performance ◽  
Aircraft Landing Gear ◽  
High Nickel

Abstract ALMAR 20 is a high nickel martensitic steel which is strengthened by precipitation hardening. It has excellent combination of strength and toughness particularly in the presence of notches and cracks. It is recommended for applications such as solid fuel rocket cases and aircraft landing gear. This datasheet provides information on composition, physical properties, hardness, elasticity, and tensile properties. It also includes information on low temperature performance and corrosion resistance as well as forming, heat treating, machining, joining, and surface treatment. Filing Code: SA-162. Producer or source: Allegheny Ludlum Corporation.

FERRIUM S53

Alloy Digest ◽  
2008 ◽  
Vol 57 (12) ◽  
Keyword(s):  
Mechanical Properties ◽  
Fracture Toughness ◽  
Corrosion Resistance ◽  
Heat Treating ◽  
Corrosion Resistant Steel ◽  
Resistant Steel ◽  
Corrosion Resistant ◽  
Aircraft Landing ◽  
Aircraft Landing Gear ◽  
Better Than

Abstract Ferrium S53 was developed for use as a structural corrosion resistant steel for aircraft landing gear. S53 has a corrosion resistance equivalent to 440C, strength equivalent to or better than 300M (AMS 6257A) and SAE 4340 (see Mechanical Properties), optimum microstructure features for maximum fatigue resistance, and a surface hardenability equal to or greater than 67 HRC for wear and fatigue. This datasheet is an update to Alloy Digest SS-942 and SS-1003. This datasheet provides information on composition, physical properties, hardness, and tensile properties as well as fracture toughness. It also includes information on corrosion resistance as well as heat treating and machining. Filing Code: SA-589. Producer or source: QuesTek Innovations, LLC.

Differential Performance Signature Qualification for Additively Manufactured Parts

2018 ◽  
Author(s):  
John G. Michopoulos ◽  
John C. Steuben ◽  
Athanasios P. Iliopoulos
Keyword(s):  
Additive Manufacturing ◽  
Graphical Representation ◽  
Functional Performance ◽  
Complex Objects ◽  
Aircraft Landing ◽  
Differential Performance ◽  
Aircraft Landing Gear ◽  
Am Processes ◽  
Comparison Measures ◽  
Quantities Of Interest

Additive Manufacturing (AM) technologies and associated processes, enable successive accretion of material to a domain, and permit manufacturing of highly complex objects which would otherwise be unrealizable. However, the material micro- and meso-structures generated by AM processes can differ remarkably from those arising from conventional manufacturing (CM) methods. Often, a consequence of this fact is the sub-standard functional performance of the produced parts that can limit the use of AM in some applications. In the present work, we propose a rapid functional qualification methodology for AM-produced parts based on a concept defined as differential Performance Signature Qualification (dPSQ). The concept of Performance Signature (PerSig) is introduced both as a vector of featured quantities of interest (QoIs), and a graphical representation in the form of radar or spider graph, representing the QoIs associated with the performance of relevant parts. The PerSigs are defined for both the prequalified CM parts and the AM-produced ones. Comparison measures are defined and enable the construction of differential PerSigs (dPerSig) in a manner that captures the differential performance of the AM part vs. the prequalified CM one. The dPerSigs enable AM part qualification based on how their PerSigs are different from those of prequalified CM parts. After defining the steps of the proposed methodology, we describe its application on a part of an aircraft landing gear assembly and demonstrate its feasibility.

Characterization of a AISI/SAE 4340 Steel in Different Microstructural Conditions

2014 ◽  
Vol 775-776 ◽  
pp. 136-140 ◽  
Author(s):  
Renato Araujo Barros ◽  
Antonio Jorge Abdalla ◽  
Humberto Lopes Rodrigues ◽  
Marcelo dos Santos Pereira
Keyword(s):  
High Strength Steels ◽  
High Strength ◽  
Aviation Industry ◽  
Sodium Metabisulfite ◽  
Aerospace Applications ◽  
Aircraft Landing ◽  
Aircraft Landing Gear ◽  
Structural Applications ◽  
Ultra High Strength Steels ◽  
Pin On Disk

The 4340 are classified as ultra-high strength steels used by the aviation industry and aerospace applications such as aircraft landing gear and several structural applications, usually in quenched and tempered condition. In this situation occurs reduction of toughness, which encourages the study of multiphasic and bainític structures, in order to maintain strength without loss of toughness. In this study, ferritic-pearlitic structure was compared to bainitic and martensitic structure, identified by the reagents Nital, LePera and Sodium Metabisulfite. Sliding wear tests of the type pin-on-disk were realized and the results related to the microstructure of these materials and also to their hardnesses. It is noted that these different microstructures had very similar behavior, concluding that all three tested pairs can be used according to the request level.

scholarly journals 1002 Aerodynamic noise reduction for aircraft landing gear

2009 ◽  
Vol 2009 (0) ◽  
pp. 321-322
Author(s):  
Kazuhide Isotani ◽  
Kenji Hayama ◽  
Akio Ochi ◽  
Toshiyuki Kumada
Keyword(s):  
Noise Reduction ◽  
Landing Gear ◽  
Aerodynamic Noise ◽  
Aircraft Landing ◽  
Aircraft Landing Gear
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