The electric vehicle industry - land, water and air - is rapidly rising to become a market of over $533 billion by 2025. Some run entirely on harvested energy as with solar lake boats. Others recycle energy as with regenerative braking of cars, buses and military vehicles harvesting kinetic energy. Others use different forms of harvesting either to charge the traction batteries, or to drive autonomous device. In some cases, harvesting is making completely new forms of electric vehicle possible such as "glider" Autonomous Underwater Vehicles (AUVs) that can stay at sea for years, gaining electricity from both wave power and sunshine. Multiple forms of energy harvesting on one vehicle are becoming more common from cars to superyachts.
This SAE Aerospace Standard (MA) defines the requirements for a convoluted polytetrafluoroethylene (PTFE) lined, metallic reinforced, hose assembly suitable for use in aircraft fluid systems at temperatures of -55 to 204 °C and at operating pressures per Table 1.
This SAE Metric Aerospace Recommended Practice (MAP) establishes the requirements for preparing a specification for fluid couplings for spacecraft servicing. The objective of this document is to provide design, development, verification, storage, and delivery requirement guidelines for the preparation of specifications for fluid couplings and the ancillary hardware for use with serviceable spacecraft designed for use in the space environment. The couplings shall be capable of resupplying storable propellants, cryogenic liquids, and gases to a variety of spacecrafts.
This international standard establishes flexure and pressure impulse test procedures for determining and classifying the fatigue strengths of bent aircraft hydraulic tubing. The procedures are intended for use with high- and low-pressure system assemblies for evaluation of new materials or for qualification purposes.
This specification covers lightweight hose assemblies intended for use in high-temperature, 204 °C, high-pressure, 21 000 kPa (210 bar) aircraft hydraulic systems, also for use in pneumatic systems which allow some gaseous diffusion through the PTFE wall.
This Aerospace Standard covers hose assemblies intended for use in aircraft high temperature fluid systems. The specified temperature range is -55°C (-67°F) to +204°C (400°F). Operating pressures are listed in Table I.
This SAE Aerospace Standard (AS) specifies test methods for fitting assemblies used in aircraft fluid systems in the pressure classes B, D, and E, and in temperature Types I, II, and III of MA 2001. This document applies each time that it is referred to in a procurement specification or other definition document. Fluids and materials used for the tests are listed in Section 2.