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This Purchasing Specification, AMS6885/4, specifies the batch release and delivery requirements for film adhesive used for repair. This specification is applicable only when the film adhesive is used as part of the repair system defined in AMS6885 and AMS6885/1. This specification also defines the procedure and requirements for storage life extension of materials purchased against this specification. It is only applicable for materials qualified against AMS6885 (refer to PRI-QPL-AMS6885), and shall be carried out within the responsibility of the purchaser and under control of its Quality organisation.
AMS CACRC Commercial Aircraft Composite Repair Committee
This specification covers polythioether rubber fuel-resistant sealing compounds supplied as a two-component system that cures at room temperature.
AMS G9 Aerospace Sealing Committee
This FMEA standard describes potential failure mode and effects analysis in design (DFMEA), supplemental FMEA-MSR, and potential failure mode and effects analysis in manufacturing and assembly processes (PFMEA). It assists users in the identification and mitigation of risk by providing appropriate terms, requirements, rating charts, and worksheets. As a standard, this document contains requirements—”must”—and recommendations—”should”—to guide the user through the FMEA process. The FMEA process and documentation must comply with this standard as well as any corporate policy concerning this standard. Documented rationale and agreement with the customer are necessary for deviations in order to justify new work or changed methods during customer or third-party audit reviews.
Automotive Quality and Process Improvement Committee
This specification establishes requirements for chrome-free surface pretreatment materials used for surface preparation of metallic surfaces prior to applying organic coatings.
AMS G8 Aerospace Organic Coatings Committee
The ice bath recommended herein is similar to that described in SAE AIR 46.* Some material not presented in AIR 46, including preferred dimensions, has been added.
E-32 Aerospace Propulsion Systems Health Management
This standard defines a color index system used by, but not limited to, Government activities in a format suitable for color identification, color selection, color matching, and quality control inspection. It also describes the designation and use of color media that is available to conduct these activities. Use of the color index referenced in this standard is intended to promote standardization and consistency in the color of items produced for Government use. Color media is described as follows: Color Chip Representation, Fan Deck: Suitable for color identification and selection. Color Chip Representation, Color Book: Suitable for color identification and selection. Precise Color Matching, Individual Color Chips: Suitable for color matching and quality control inspection purposes. Precise Color Matching, Set of Color Chips: Suitable for color matching and quality control inspection purposes.
AMS G8 Aerospace Organic Coatings Committee
This specification establishes hardness and electrical conductivity acceptance criteria for finished or semifinished parts made from wrought aluminum alloys after heat treatment (see 8.6).
AMS D Nonferrous Alloys Committee
This SAE Aerospace Recommended Practice (ARP) document establishes criteria and recommended practices for the use of airborne icing tankers to aid in design and certification of aircraft ice protection systems and components. Several icing tankers are described, along with their capabilities and suggested use. Sample data for these tanker spray systems are included, shown with 14 CFR Parts 25 and 29, Appendix C icing envelopes for continuous maximum and intermittent maximum icing conditions. (Note: In the remainder of this document, the phrase “Appendix C icing envelopes” will be used for brevity.) This ARP is intended as a guide toward standard practice and is subject to change to keep pace with experience and technical advances.
AC-9C Aircraft Icing Technology Committee
This specification covers a premium aircraft-quality maraging steel in the form of bars and forgings, 0.50 to 8.00 inches (12.7 to 203.2 mm) in nominal diameter or least distance between parallel sides, and forging stock of any size.
AMS E Carbon and Low Alloy Steels Committee
This Purchasing Specification, AMS6885/3, specifies the batch release and delivery requirements for unidirectional carbon fiber tape epoxy prepreg used for repair. This specification is applicable only when the unidirectional carbon fiber tape epoxy prepreg is used as part of the repair system defined in AMS6885 and AMS6885/1. This specification also defines the procedure and requirements for storage life extension of materials purchased against this specification. It is only applicable for materials qualified against AMS6885 (refer to PRI-QPL-AMS6885) and shall be carried out within the responsibility of the purchaser and under control of its Quality organisation.
AMS CACRC Commercial Aircraft Composite Repair Committee
E-25 General Standards for Aerospace and Propulsion Systems
AMS6885/5 is the Material Specification (MS) which defines the requirements of a unidirectional carbon fiber tape epoxy repair prepreg capable of curing under vacuum for repair of carbon fiber reinforced epoxy structures. It also defines the requirements of an epoxy film adhesive to be applied in a co-bonding process with the prepreg for solid laminate and sandwich bonding.
AMS CACRC Commercial Aircraft Composite Repair Committee
This SAE Standard specifies the test requirements in addition to those given in ISO 3046-1 for determining the power, at a single point or as a power curve, of marine propulsion engines or systems for recreational craft and other small craft using similar propulsion equipment of less than 24 m length of the hull. It also provides the means for documenting and checking the declared (rated) power published by the manufacturer.
Marine Technical Steering Committee
This document applies to off-road forestry work machines defined in SAE J1116 or ISO 6814.
MTC4, Forestry and Logging Equipment
The process detailed within this document is generic and applies to the entire end-to-end health management capability, covering both on-board and on-ground elements, in both commercial and military applications throughout their lifecycle. This ARP addresses a gap in guidance related to usage of ground-based health management equipment for airworthiness credit, ensuring a level of integrity commensurate with the potential aircraft-level consequences of the relevant failure conditions. The practical application of this standardized process is detailed in the form of a checklist. The on-board elements described here are typically the source of the data acquisition used for off-board analysis. The on-board aspects relating to airworthiness and/or safety of flight, e.g., pilot notification, are addressed by existing guidance and policy documents. If a proposed health management capability for airworthiness credit involves modification of the on-board systems, the substantiation of those
E-32 Aerospace Propulsion Systems Health Management
Diesel engines used for the main power supplier of submarine normally run in high back pressure and low intake pressure, causing unstable performances. Furthermore, when a submarine runs under the sea the exhaust pipe of the diesel engine is under the seawater. Once the lowest pressure in the exhaust pipe is not sufficient to push all the water out, the water will flow into the exhaust pipe and damage the diesel engine. Modeling can provide a useful guide for designing diesel engines, intake and exhaust pipes, and turbocharging systems to avoid water flowing into diesel engine. However, existing simulation methods cannot well simulate the exhaust system of an underwater diesel engine, in which the interface between the liquid water and the exhaust gas is variable. To overcome the drawbacks of existing simulation methods in handling the variable interface between the two phases, a variable interface finite volume method (FVM) is proposed, and a corresponding model is developed in this
Guo, DongshaoZhang, LichengYang, ShiyouSun, YongAbidin, ZainalLin, Shujun
A full lithium-ion battery (LIB) pack has hundreds to thousands of cells, coolant flow lines and channels, and channel bends to control cell temperature within its operating window and minimize cell internal resistance, aging, and fire risk. A 75 kWh LIB pack has four modules, and each has 23–25 bricks. Two challenges in battery state predictions for hot and subzero temperatures are battery temperature (Tbatt ) and coolant flow within the whole pack. In this work, a 1D 75 kWh full-pack model with its thermal management system is developed using a holistic reverse-engineering method, which can predict Tbatt at any bricks/modules and inlet/outlet coolant flow characteristics. A Tesla Model Y equipped with dual e-motors is tested on an in-house state-of-the-art chassis dynamometer. The test data at V = 60–80 km/h, 100–150 A constant discharge, and Tbatt = −10°C to 40°C are used to develop the model. The 75 kWh pack model features 4000+ cylindrical cells (96S46P, Panasonic 21700-format
Sok, RatnakKusaka, Jin
Autonomous vehicles exhibit extremely strong nonlinearity during drift. However, existing autonomous drift algorithms often neglect previewed path curvature and offer only limited consideration of road surface uncertainty because of the influence of vehicle nonlinear dynamics, which can affect tracking accuracy and robustness of drift control. To solve these problems, this study proposes a robust optimal drift control framework based on curvature preview. First, a preview vehicle kinematic model is constructed, and a preview model predictive control path-tracking controller that considers the forthcoming curvature is designed. Through the analysis of equilibrium points with additional yaw moment, a robust optimal drift controller is developed, which employs a three-degrees-of-freedom vehicle model with an additional yaw moment. This controller adopts integral sliding mode control with a super-twisting algorithm (STA) and exhibits good stability, which is verified through Lyapunov
Gan, YurunSong, ZiyuGu, TongtongDing, HaitaoXu, NanZhang, Jianwei