Missile pumps are categorized by a moderate testing life and a relatively short operational service life. Generally, the pumps are operated at higher speeds, temperatures, and pressures than those used in manned aircraft systems, yet reliability must be extremely high, since there rarely is a redundant system aboard the missile. Due to the short but critical life and performance requirements, development, reliability and acceptance testing should be focused on eliminating infant mortality failures. Missile pumps must be compatible with very severe environmental conditions during the service life. In general, the temperature, vibration, shock, and acceleration encountered are more severe than those met in manned aircraft. This SAE Aerospace Information Report (AIR) will be confined to describing missile environments and pump usage that differ significantly from those normally encountered in manned aircraft. Since missile pumps are usually driven by a secondary power source, and since this AIR is intended for use by systems designers, as well as pump designers, a brief description of some of these sources and some potential problem areas associated with each are included for reference. A more detailed treatment of auxiliary power sources can be found in AIR744. Detailed test requirements are not included in this AIR since a wide variation exists between those operating conditions and environments that might be encountered on an air-to-air missile, hung beneath the wing of a fighter aircraft, and that of an ICBM (Intercontinental Ballistic Missile), launched from an environmentally controlled silo. Missile pumps frequently have their genesis in standard aircraft pumps, however, what distinguishes them from manned aircraft pumps is that they are usually operated outside of, or at the extreme of their long-life design parameters. Therefore, if a new design pump is being proposed for a missile application, environmental conditions referenced in this AIR should be considered, as opposed to long-life operation and environmental requirements of a manned aircraft, engine-driven pump.
SAE AIR560C-1999 Referenced Document
SAE AIR744 STANDBY AUXILIARY POWER SOURCES FOR TACTICAL MISSILES
SAE AIR974 LONG-TERM STORAGE OF MISSILE HYDRAULIC SYSTEMS
SAE ARP598 PROCEDURE FOR THE DETERMINATION OF PARTICULATE CONTAMINATION OF HYDRAULIC FLUIDS BY THE PARTICLE COUNT METHOD
SAE AS19692-1998 Pumps@ Hydraulic@ Variable Flow@ General Specification for
SAE AS4059B-1995 Aerospace-Cleanliness Classification for Hydraulic Fluids
SAE AS5440-1998 Hydraulic Systems, Aircraft, Design and Installation Requirements for FSC 1650; Should Be Used Instead of MIL-H-5440H, Which Was Cancelled on 13 September 1999