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This SAE Recommended Practice is applicable to oil-to-air and oil-to-coolant oil coolers installed on mobile or stationary equipment and provides a glossary of oil cooler nomenclature. Such oil coolers may be used for the purpose of cooling automatic transmission fluid, hydraulic system oil, retarder system fluid, engine oil, etc. This document outlines the methods of procuring the test data to determine the operating characteristics of the oil cooling system and the interpretation of the results.
Cooling Systems Standards Committee
This specification covers a nitriding grade of premium aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock.
AMS E Carbon and Low Alloy Steels Committee
This SAE Recommended Practice provides standardized laboratory tests, test methods, and performance requirements applicable to signal and marking devices used on vehicles 2032 mm or more in overall width.
Heavy Duty Lighting Standards Committee
This specification covers a maraging steel in the form of welding wire.
AMS E Carbon and Low Alloy Steels Committee
This SAE Aerospace Recommended Practice (ARP) provides a procedure for exposing test slabs of fluoroelastomers, representative of those used in aviation gas turbine engines, to a lubricant for a period of 77 days at temperatures between 100 and 160 °C. Conditions outside those specified within the ARP can be used if required; however, the modification to this standard must be detailed alongside test results when reporting data.
E-34 Propulsion Lubricants Committee
This SAE Aerospace Standard (AS) defines the requirements for a polytetrafluoroethylene (PTFE) lined, para-aramid fiber reinforced, hose assembly suitable for use up to 4000 psi, and up to 275 °F, aircraft and missile hydraulic and pneumatic systems.
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This SAE Aerospace Standard (AS) defines the requirements for a convoluted polytetrafluoroethylene (PTFE) lined, metallic reinforced, hose assembly suitable for use in aircraft fluid systems at temperatures of -65 to 400 °F and at operating pressures per Table 1.
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This specification covers a corrosion-resistant steel in the form of investment castings, solution and precipitation heat treated to 150 ksi (1034 MPa) tensile strength.
AMS F Corrosion and Heat Resistant Alloys Committee
This document aims to define the procurement requirements for galling-resistant, corrosion-resistant steel wire, with the chemical composition per UNS S21800 and AMS5848 and spring temper, used in the manufacture of helical coil threaded inserts. It will enable insert manufacturers to adhere to specific standards to meet the criteria outlined in this procurement specification.
E-25 General Standards for Aerospace and Propulsion Systems
This specification covers a premium aircraft-quality, low-alloy steel in the form of sheet, strip, and plate.
AMS E Carbon and Low Alloy Steels Committee
This specification covers spooling and packaging of bare welding wire to ensure cleanliness and freedom from corrosion, spool sizes and weights of spooled wire, and package weights of cut lengths.
AMS B Finishes Processes and Fluids Committee
To describe general guidelines for achieving selected levels of cleanliness in gas turbine engine fuel system components and to describe laboratory methods for measuring and reporting the contamination level of the wetted portion of fuel system components. As in SAE J1227 (covering hydraulic components), this practice includes guidelines for levels of acceptance but does not attempt to set those levels.
AE-5A Aerospace Fuel and Lubrication Systems Committee
This standard provides the recommended requirements for electrostatic spray application of AMS3143 powder coatings to aerospace components. Adherence to these requirements will facilitate satisfactory performance of the applied powder coating.
AMS G8 Aerospace Organic Coatings Committee
This specification covers the requirements for shot peening of surfaces of parts by impingement of media, including metallic, glass, or ceramic shot.
AMS B Finishes Processes and Fluids Committee
This document covers the requirements for insulated, single-conductor, electric wires with tin-coated, silver-coated, or nickel-coated conductors of copper or copper alloy as specified in an applicable generated performance sheet (see Appendix A for sample). It provides general performance requirements, ratings, and information for various characteristics of insulated wire systems used in aerospace applications. Numerical test requirements, or parameters, were originally developed using either English or metric units. The original, primary, units are shown first with the secondary (converted) units in parentheses. Secondary units are listed for information only and are not to be considered requirements. Wire will be assigned a level of performance for many requirements set forth in this standard. These performance levels, in addition to numerical test results, shall be listed in the applicable performance sheet. This standard contains some tests and referenced AS4373 Test Methods that have not been rigorously confirmed as reproducible. Such methods are identified under the Precision and Bias Statements in the individual AS4373 Test Methods. Many requirements have multiple levels of performance. The wire with base level of performance is acceptable for general use; however, there may be special applications that will require wire with higher performance levels.
AE-8D Wire and Cable Committee
AE-8A Elec Wiring and Fiber Optic Interconnect Sys Install
Addressing the performance degradation bottleneck of conventional impact-resistant materials under complex operating conditions, and the limitation of existing research focusing primarily on enhancing single properties while neglecting material equilibrium, this study employs silicon carbide whiskers (SiCw) as the reinforcing phase. Through surface modification techniques, SiCw/celluloid and SiCw/polyimide dual-polymer composite systems were constructed and systematically investigated. Surface modification of SiCw was achieved using titanate and silane coupling agents. Through mechanical testing and X-ray photoelectron spectroscopy (XPS) characterisation, the effects of SiCw loading and modification treatments on composite mechanical properties and interfacial bonding were analysed. Results indicate that SiCw introduction significantly enhances the tensile, flexural, and impact strength of the polymer matrix, with optimal addition ratios identified: 6% for the celluloid system and 1.0% for the polyimide system. Surface modification further optimises toughening effects by reducing surface oxide layers and impurities on SiCw particles while strengthening interfacial bonding. This study provides practical guidance for the system design of high-performance impact-resistant composites. The resulting materials hold broad application prospects in sectors demanding high structural impact resistance, such as aerospace and transportation.
Xue, Kaiming
Aiming at the engineering problems of easy cracking and insufficient impact resistance of traditional airport concrete pavement under complex dynamic loads, this paper studies the application of functionally graded carbon fiber reinforced polymer ( FG-CFRP) in airport pavement. Based on the modified Halpin-Tsai model and the first-order shear deformation theory, the dynamic finite element control equation is established. Based on the COMSOL Multiphysics platform, the modal characteristics and transient impact response analysis are carried out, and the dynamic response of the aircraft under moving wheel load is simulated. The static bending test of FG- CFRP plate samples made in the laboratory was carried out, and the numerical model was calibrated. The relative error of test-simulation was controlled within 5 %, which verified the accuracy of predicting static response. The carbon fiber volume fraction gradient curve was parametrically studied to reveal the sensitivity of the gradient to impact and stress reduction. The key engineering factors such as long-term environmental durability and life cycle cost of FG-CFRP pavement are discussed, and targeted improvement and optimization strategies are proposed. The results show that the fundamental frequency of the gradient plate is about 1.93 % lower than that of the homogeneous plate, and the vibration mode characteristics are highly consistent. The peak displacement of transient impact is reduced by 9.4 %. Under the action of moving wheel load, the peak Von Mises stress decreased from 5.32 MPa to 2.15 MPa, with a decrease of 60 %. The gradient design realizes efficient load diffusion and impact hardening through the surface high modulus layer, and the gradual change of interlayer wave impedance promotes the dissipation of stress wave, which significantly improves the safety reserve and dynamic stability of pavement structure. This study verifies the application feasibility of FG-CFRP in high-performance airport pavement engineering, and provides innovative material solutions and theoretical support for the development of a new generation of long-life and high-reliability airport pavement.
Li, Zhenyue
Gas path faults in aero-engines are a major factor affecting flight safety and maintenance costs. To achieve the transition from time-based maintenance to condition-based maintenance and enhance fault prediction and health management capabilities, this paper conducts research on intelligent diagnostic methods based on performance parameters for engine gas path components. Firstly, a component-level nonlinear steady-state model of a dual-spool turbofan engine is established, employing a variable specific heat capacity method to improve computational accuracy and provide a healthy baseline for diagnosis. Secondly, addressing the strong nonlinearity and measurement underdeterminacy in fault diagnosis, a diagnostic framework integrating a multi-population genetic algorithm and multi-operating-point analysis is proposed. The multi-population genetic algorithm effectively enhances global optimization capability and solution stability through parallel evolution, migration operators, and an elite population strategy; multi-operating-point data increases information content and strengthens fault isolation capability. Finally, simulation experiments under ground test conditions are conducted to validate the diagnosis of single-component faults in the low-pressure compressor, high-pressure compressor, high-pressure turbine, and low-pressure turbine. The results show that the proposed method can accurately invert component performance degradation, with a high fault identification accuracy rate, verifying the effectiveness of the proposed model and algorithm. This research provides a feasible technical solution for intelligent condition monitoring and precise diagnosis of aero-engines.
Cai, Na, Li, Ming, Li, BianJiang, Yu, GuangHui, Ma, ZhongYuan
To provide auxiliary verification for the technical evaluation of low-altitude aircraft operation status and address the limited effectiveness of uncertainty handling, this paper proposes an evaluation method based on fuzzy reasoning and D-S evidence theory. Firstly, the relevant knowledge of D-S evidence theory and fuzzy reasoning is introduced. Secondly, the aircraft operation status levels are constructed, and an intuitionistic fuzzy reasoning system is established based on Gaussian membership functions. The initial basic probability assignments (BPA) are obtained through defuzzification using the intuitionistic fuzzy centroid method. The conflict between evidences is measured by the weighted average of Jensen-Shannon (J-S) evidence distance and conflict coefficient k, followed by multi-cycle discount correction and fusion. Finally, experimental verification proves the rationality of the proposed method, which can provide a reference for related research.
Niu, Xiaowei, Shen, Di, Yu, Fuping, Guo, Yiduo, An, Xiangyu, Xuan, Haoli