• SAE AIR 1277 : 2005

    Superseded A superseded Standard is one, which is fully replaced by another Standard, which is a new edition of the same Standard.
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    COOLING OF MILITARY AVIONIC EQUIPMENT

    Available format(s):  Hardcopy, PDF

    Superseded date:  01-16-2018

    Language(s):  English

    Published date:  01-01-2005

    Publisher:  SAE International

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    Table of Contents - (Show below) - (Hide below)

    1 SCOPE
       1.1 Purpose
       1.2 Field of Application
    2 REFERENCES
       2.1 Applicable Documents
           2.1.1 SAE Publications
           2.1.2 U.S. Government Publications
           2.1.3 U.S. Army Publications
           2.1.4 NATO Publications
       2.2 Related Publications
       2.3 Definitions
       2.4 Abbreviations
    3 INTRODUCTION
    4 DESIGN REQUIREMENTS
       4.1 General Requirements
           4.1.1 Contract Specification
           4.1.2 Military or Government Specifications
           4.1.3 System Design Process
       4.2 Avionic Thermal Design Considerations
           4.2.1 Reliability
           4.2.2 Temperature Effect an Avionic Performance
           4.2.3 Environmental Requirements
           4.2.4 Avionic Thermal Control
           4.2.5 Avionic Integrity Requirements
       4.3 Airframe Systems
           4.3.1 Thermal Control Requirements
           4.3.2 Trade-off Studies
           4.3.3 Environmental Requirements
           4.3.4 Moisture Condensation
    5 INTERFACE BETWEEN AVIONICS, ECS, AND AIRCRAFT
       5.1 Interface Cooling Requirements
       5.2 Life Cycle Cost
       5.3 Ram and Compartment Cooling Air
       5.4 Air and Liquid Cooled Systems
           5.4.1 Forced Air Cooling
           5.4.2 Liquid Cooling Systems
       5.5 Fuel Heat Sink
       5.6 Installation
       5.7 Weight
       5.8 Commercial-off-the-shelf (COTS) Avionics
    6 AVIONIC THERMAL CONTROL HARDWARE DESIGN/SELECTION
       6.1 Line-Replaceable-Unit (Weapon Replaceable Assembly)
           Thermal Design
           6.1.1 Passively Cooled (Natural Convection/Radiation) LRUs
           6.1.2 Actively Cooled (Forced Convection) LRUs
           6.1.3 Cold Wall-Cooled LRU Thermal Design
       6.2 Cold Plate Design
           6.2.1 Basic Cold Wall Configurations
       6.3 Heat Exchanger Design
           6.3.1 Plate Fin Heat Exchangers
           6.3.2 Weight and Other Considerations
       6.4 Specialized Thermal Control Technologies
           6.4.1 Thermoelectric Coolers
           6.4.2 Heat Pipes
           6.4.3 Immersion Cooling
           6.4.4 Expendable Liquid Coolants
           6.4.5 Liquid Coolant within Board
       6.5 Thermal Analysis Methods
           6.5.1 Thermal Modeling Techniques
           6.5.2 Finite-Difference Modeling Techniques
           6.5.3 Finite-Element Modeling Techniques
           6.5.4 Computational-Fluid-Dynamics (CFD) Simulation
           6.5.5 ECS Simulation
    7 AIRFRAME THERMAL CONTROL HARDWARE
       7.1 Heat Sink Hardware
           7.1.1 Ram Air
           7.1.2 Fuel
           7.1.3 Expendable Liquid Heat Sinks
           7.1.4 Thermal Storage
       7.2 ECS Hardware
           7.2.1 Transport Loops
           7.2.2 Fluid Refrigeration
       7.3 Thermal Analysis Methods
    8 THERMAL TESTING
       8.1 Thermal Testing of Avionics
       8.2 Thermal Testing of Cooling Systems and ECS
    9 AVIONIC THERMAL MANAGEMENT CASE STUDIES
       9.1 FLIR Turret Thermal Control
           9.1.1 Design for Operation at High Altitude
           9.1.2 Design Verification Testing
           9.1.3 Problems Associated With Forced Convection Cooled
                 Avionics
       9.2 Liquid-Cooled, Phased Array Radar System
           9.2.1 Critical Design Issues
           9.2.2 Temperature Gradient from Module-to-Module Across
                 the Array
           9.2.3 Absolute Temperature of Module Components
           9.2.4 Temperature Cycling
           9.2.5 Module/Gold Plate Thermal Resistance
    10 NOTES

    Abstract - (Show below) - (Hide below)

    Gives information on the thermal design requirements of airborne avionic systems used in military airborne applications.

    General Product Information - (Show below) - (Hide below)

    Committee AC-9
    Document Type Standard
    Publisher SAE International
    Status Superseded

    Standards Referenced By This Book - (Show below) - (Hide below)

    SAE ARP 4729 : 2017 DOCUMENT FOR 270 VOLTAGE DIRECT CURRENT (270 V DC) SYSTEM
    JSSG 2009 : A AIR VEHICLE SUBSYSTEMS (JOINT SERVICE SPECIFICATION GUIDE)
    SAE AIR 6464 : 2013 EUROCAE/SAE WG80/AE-7AFC HYDROGEN FUEL CELLS AIRCRAFT FUEL CELL SAFETY GUIDELINES
    SAE ARP 987 : 2015 THE CONTROL OF EXCESS HUMIDITY IN AVIONICS COOLING
    SAE AIR 1811 : 2015 LIQUID COOLING SYSTEMS
    SAE AIR 1957 : 2015 HEAT SINKS FOR AIRBORNE VEHICLES
    SAE AS 6858 : 2017 INSTALLATION OF FUEL CELL SYSTEMS IN LARGE CIVIL AIRCRAFT

    Standards Referencing This Book - (Show below) - (Hide below)

    MIL HDBK 251 : 0 RELIABILITY/DESIGN THERMAL APPLICATIONS
    AFGS 87145 : A NOTICE 1 ENVIRONMENTAL CONTROL, AIRBORNE
    MIL STD 883 : K TEST METHOD STANDARD - MICROCIRCUITS
    MIL HDBK 87244 : 0 AVIONICS/ELECTRONICS INTEGRITY
    SAE AIR 1957 : 2015 HEAT SINKS FOR AIRBORNE VEHICLES
    MIL STD 810 : G ENVIRONMENTAL ENGINEERING CONSIDERATIONS AND LABORATORY TESTS
    SAE AIR 1168/10 : 1992 THERMOPHYSICAL CHARACTERISTICS OF WORKING FLUIDS AND HEAT TRANSFER FLUIDS
    MIL HDBK 781 : A RELIABILITY TEST METHODS, PLANS, AND ENVIRONMENTS FOR ENGINEERING DEVELOPMENT, QUALIFICATION AND PRODUCTION
    SAE AIR 1812 : 2017 ENVIRONMENTAL CONTROL SYSTEMS LIFE CYCLE COST
    MIL HDBK 454 : B GENERAL GUIDELINES FOR ELECTRONIC EQUIPMENT
    SAE AIR 1811 : 2015 LIQUID COOLING SYSTEMS
    MIL E 18927 : E ENVIRONMENTAL CONTROL SYSTEMS, AIRCRAFT, GENERAL REQUIREMENTS FOR
    MIL T 5842 : B TRANSPARENT AREAS ON AIRCRAFT SURFACES [WINDSHIELDS AND CANOPIES] RAIN REMOVING AND WASHING SYSTEMS FOR, DEFROSTING, DEICING, DEFOGGING, GENERAL SPECIFICATION FOR
    SAE AIR 1706 : 1997 THE ADVANCED ENVIRONMENTAL CONTROL SYSTEM (AECS) COMPUTER PROGRAM FOR STEADY STATE ANALYSIS AND PRELIMINARY SYSTEM SIZING
    MIL HDBK 5400 : 0 ELECTRONIC EQUIPMENT, AIRBORNE GENERAL GUIDELINES FOR
    MIL HDBK 217 : F RELIABILITY PREDICTION OF ELECTRONIC EQUIPMENT
    SAE AIR 1823 : 1996 ENGINEERING ANALYSIS SYSTEM (EASY) COMPUTER PROGRAM FOR DYNAMIC ANALYSIS OF AIRCRAFT ECS
    STANAG 2895 : 1990 EXTREME CLIMATIC CONDITIONS AND DERIVED CONDITIONS FOR USE IN DEFINING DESIGN/TEST CRITERIA FOR NATO FORCES MATERIAL
    JSSG 2009 : A AIR VEHICLE SUBSYSTEMS (JOINT SERVICE SPECIFICATION GUIDE)
    MIL HDBK 310 : 0 DEPARTMENT OF DEFENSE HANDBOOK - GLOBAL CLIMATIC DATA FOR DEVELOPING MILITARY PRODUCTS
    MIL T 18606 : 0 TEST PROCEDURES FOR AIRCRAFT ENVIRONMENT SYSTEMS
    SAE ARP 217 D : 2016 TESTING OF AIRPLANE INSTALLED ENVIRONMENTAL CONTROL SYSTEMS (ECS)
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