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AIR1277B
(R) Cooling of Military Avionic Equipment
(R) Cooling of Military Avionic Equipment
2010-05-01
有效
【范围】 This SAE Aerospace Information Report (AIR) contains information on the thermal design requirements of airborne avionic systems used in military airborne applications. Methods are explored which are commonly used to provide thermal control of avionic systems. Both air and liquid cooled systems are discussed. 1.1 Purpose: This document describes guidelines for the configuration and design of military aircraft subsystems that provide cooling to airborne avionic systems and recommendations for the basic cooling concepts, analytical methods and design practices used for the thermal design of those airborne avionic systems. The efficient design of the interface between the airframe system and the avionic system is considered. 1.2 Field of Application: This document is intended to apply to both designers of airborne avionic equipment and of airborne environmental control systems.strRefField
【与前一版的变化】

包含缩略语

CFDcomputational fluid dynamics
CFE
CMOS
DIP
emf
ECS
EMI
FLIR
GFE
IC
ICD
IGBT
IR
LRM
LRU
MCT
PAO
PWB
RTV
SAE
SEM-E
TEC
WRA

替代标准

引用文件/被引文件

Testing of Commercial Airplane Environmental Control Systems
Thermophysical Characteristics of Working Fluids and Heat Transfer Fluids
The Advanced Environmental Control System (AECS) Computer Program for Steady State Analysis and Preliminary System Sizing
Liquid Cooling Systems
Environmental Control Systems Life Cycle Cost
Environmental Control System Transient Analysis Computer Program (EASY)
Heat Sink Thermal Management
Environmental Control
Joint Service Specification Guide
Environmental Control Systems
Microelectronic Device Data Handbook
Reliability Prediction of Electronic Equipment
Reliability/Design
Global Climatic Data for Developing Military Products
General Guidelines For Electronic Equipment
Reliability Test Methods
Electronic Equipment
Avionics/Eletronics Integrity
Environmental Engineering Consideration and Laboratory Test
Test Method Standard
Thermal Design
Transparent Areas on Aircraft Surfaces (Windshields and Canopies)
Test Procedures for Aircraft Environmental Systems
Research
Extreme Climate Conditions and Derived Conditions for Use in Defining Design/Test Criteria for NATO Forces Material

相关标准

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Index of Starting System Specifications and Standards
Performance of Low Pressure Ratio Ejectors for Engine Nacelle Cooling
(R) Control of Water Carryover from the Environmental Control System and Condensation on the Structure
Construction and Calibration of Parallel Plate Transmission Line for Electromagnetic Interference Susceptibility Testing
Installation of Liquid Oxygen Systems in Civil Aircraft
Fault Isolation in Environmental Control Systems of Commercial Transports
Identification and Coding of Fluid and Electrical Piping System Functions

包含图表

formula 1
Failure Mechanisms A
formula 2
Integrated Circuit F
Temperature Effects
Relative Performance
Cabin, Avionics and
Typical Coolant Temp
Direct Liquid Coolin
Indirect Liquid Cool
Typical Avionic Mass
Helicopter Cooling C
Difference Between I
Comparison of Method
formula 3
Values of Heat Trans
formula 4
Direct Air-Cooled Ch
Combined Direct and
Cold Wall/Thermal Pl
PWB Chassis with PWB
PWB Populated with D
Leadless Ceramic Chi
Chassis Populated wi
Cross Section of Flo
Three Common Cold Wa
Liquid-Cooled Cold W
Typical Card Guide T
Isometric Cross Sect
Thermoelectric Coole
Basic Construction o
Operating Temperatur
Basic Heat Pipe Conf
ISEM-2A Heat Pipe Mo
Heat Pipe Applicatio
SEM-E Temperature Pr
Thermal Testing for

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