Search Results

Standard

Spacecraft Life Support Systems

2011-06-20

HISTORICAL

AIR1168/14

A life support system (LSS) is usually defined as a system that provides elements necessary for maintaining human life and health in the state required for performing a prescribed mission. The LSS, depending upon specific design requirements, will provide pressure, temperature, and composition of local atmosphere, food, and water. It may or may not collect, dispose, or reprocess wastes such as carbon dioxide, water vapor, urine, and feces. It can be seen from the preceding definition that LSS requirements may differ widely, depending on the mission specified, such as operation in Earth orbit or lunar mission. In all cases the time of operation is an important design factor. An LSS is sometimes briefly defined as a system providing atmospheric control and water, waste, and thermal management.

Standard

AIRPLANE CABIN PRESSURIZATION

1948-11-01

HISTORICAL

ARP367

These recommendations cover the general field of airplane cabin supercharging equipment and are subdivided as follows:

Standard

AIRPLANE CABIN PRESSURIZATION

1959-11-15

HISTORICAL

ARP367A

These recommendations cover the general field of airplane cabin pressurization equipment and are subdivided as follows: GENERAL REQUIREMENTS FOR PRESSURIZED AIRPLANES CABIN AIR COMPRESSORS CABIN PRESSURE REGULATING EQUIPMENT ENGINE BLEED AIR DUCT SYSTEMS CABIN PRESSURE DUCTING SYSTEM

Standard

AIRPLANE CABIN PRESSURIZATION

1960-03-01

HISTORICAL

ARP367B

These recommendations cover the general field of airplane cabin pressurization equipment and are subdivided as follows: GENERAL REQUIREMENTS FOR PRESSURIZED AIRPLANES CABIN AIR COMPRESSORS CABIN PRESSURE REGULATING EQUIPMENT ENGINE BLEED AIR DUCT SYSTEMS CABIN PRESSURE DUCTING SYSTEM

Standard

HEATERS, AIRPLANE, INTERNAL COMBUSTION HEAT EXCHANGER TYPE

1949-02-01

HISTORICAL

AS143B

These standards are written to cover internal combustion heat exchanger type heaters used in the following applications:

Standard

AIR CONDITIONING, HELICOPTER, GENERAL REQUIREMENTS FOR

1970-10-26

HISTORICAL

ARP292B

These recommendations are written to cover the general requirements of helicopter air conditioning and are sub-divided as follows: (1) Air Conditioning System - Dealing with the general design aspects. (2) Air Conditioning Equipment - Design requirements for satisfactory system function and performance. (3) Air Conditioning System Design Requirements -General information for use of those concerned in meeting requirements contained herein.

Standard

ENVIRONMENTAL CONTROL FOR CIVIL SUPERSONIC TRANSPORT

1993-06-01

HISTORICAL

AIR746A

This document supplements and in some cases supersedes the recommendations presented in ARP 85D, which refers to subsonic civil transports.

Standard

ENVIRONMENTAL CONTROL* FOR CIVIL SUPERSONIC TRANSPORT

1962-12-01

HISTORICAL

AIR746

Standard

NBC Protection Considerations for ECS Design

2014-07-01

CURRENT

AIR4362A

This SAE Aerospace Information Report (AIR) provides Nuclear, Biological and Chemical (NBC) protection considerations for environmental control system (ECS) design. It is intended to familiarize the ECS designer with the subject in order to know what information will be required to do an ECS design where NBC protection is a requirement. This is not intended to be a thorough discussion of NBC protection. Such a document would be large and would be classified. Topics of NBC protection that are more pertinent to the ECS designer are discussed in more detail. Those of peripheral interest, but of which the ECS designer should be aware are briefly discussed. Only radiological aspects of nuclear blast are discussed. The term CBR (Chemical, Biological, and Radiological) has been used to contrast with NBC to indicate that only the radiological aspects of a nuclear blast are being discussed.

Standard

Spacecraft Boost and Entry Heat Transfer

2008-02-19

HISTORICAL

AIR1168/11

The prediction of vehicle temperatures during ascent through the earth’s atmosphere requires an accurate knowledge of the aerodynamic heating rates occurring at the vehicle surface. Flight parameters required in heating calculations include the local airstream velocity, pressure, and temperature at the boundary layer edge for the vehicle location in question. In addition, thermodynamic and transport air properties are required at these conditions. Both laminar and turbulent boundary layers occur during the boost trajectory. Experience has shown that laminar and turbulent heating are of equivalent importance. Laminar heating predominates in importance in the stagnation areas, but the large afterbody surfaces are most strongly affected by turbulent heating. Once the local flow conditions and corresponding air properties have been obtained, the convective heating rate may be calculated for a particular wall temperature.

Standard

Spacecraft Boost and Entry Heat Transfer

2011-07-25

CURRENT

AIR1168/11A

The prediction of vehicle temperatures during ascent through the earth’s atmosphere requires an accurate knowledge of the aerodynamic heating rates occurring at the vehicle surface. Flight parameters required in heating calculations include the local airstream velocity, pressure, and temperature at the boundary layer edge for the vehicle location in question. In addition, thermodynamic and transport air properties are required at these conditions. Both laminar and turbulent boundary layers occur during the boost trajectory. Experience has shown that laminar and turbulent heating are of equivalent importance. Laminar heating predominates in importance in the stagnation areas, but the large afterbody surfaces are most strongly affected by turbulent heating. Once the local flow conditions and corresponding air properties have been obtained, the convective heating rate may be calculated for a particular wall temperature.

Standard

Aerothermodynamic Test Instrumentation and Measurement

2011-07-25

CURRENT

AIR1168/5A

Like the technologies to which it contributes, the science of instrumentation seems to be expanding to unlimited proportions. In considering instrumentation techniques, primary emphasis was given in this section to the fundamentals of pressure, temperature, and flow measurement. Accent was placed on common measurement methods, such as manometers, thermocouples, and head meters, rather than on difficult and specialized techniques. Icing, humidity, velocity, and other special measurements were touched on briefly. Many of the references cited were survey articles or texts containing excellent bibliographies to assist a more detailed study where required.

Standard

Aerothermodynamic Test Instrumentation and Measurement

2006-03-27

HISTORICAL

AIR1168/5

Like the technologies to which it contributes, the science of instrumentation seems to be expanding to unlimited proportions. In considering instrumentation techniques, primary emphasis was given in this section to the fundamentals of pressure, temperature, and flow measurement. Accent was placed on common measurement methods, such as manometers, thermocouples, and head meters, rather than on difficult and specialized techniques. Icing, humidity, velocity, and other special measurements were touched on briefly. Many of the references cited were survey articles or texts containing excellent bibliographies to assist a more detailed study where required.

Standard

TESTING OF PROTOTYPE AIRPLANE AIR CONDITIONING SYSTEMS

1960-03-01

HISTORICAL

ARP217A

These recommendations are written to cover the testing of air conditioning equipment functioning as a complete and installed system in prototype civil aircraft for the purpose of: A Demonstrating the safety of the installation and equipment. B Demonstrating performance of the installation and equipment. a Source of heat b Source of fresh air and/or ventilation c The cooling system d Distribution system including ducting, joints, etc. e Water separator f Exhaust system g Temperature control system. h Cabin pressurisation system including flow and pressure controls. C Obtaining data for future design and to aid in the analysis of in-service performance of the systems and equipment.

Standard

HEATER, AIRPLANE, EXHAUST HOT AIR TYPE

1943-01-01

HISTORICAL

ARP86

These specifications are written to cover the subject of exhaust hot air type heaters under three classifications, namely. A EXHAUST HOT AIR TYPE HEATERS - GENERAL - Dealing with features applicable to all makes and users. B EXHAUST HOT AIR TYPE HEATERS - MILITARY AND COMMERCIAL -Covering features applicable to military and commercial aircraft. C DESIRABLE DESIGN FEATURES - General information for use of those concerned with meeting requirements contained herein.

Standard

Air Quality for Commercial Aircraft Cabin Particulate Contaminants

2018-10-17

WIP

AIR4766/1A

This SAE Aerospace Information Report (AIR) covers airbone particulate contaminants that may be present in commercial aircraft cabin air during operation. Discussions cover sources of contaminants, methods of control and design recommendations. Air quality, ventilation requirements and standards are also discussed.

Standard

Air Quality for Commercial Aircraft Cabin Particulate Contaminants

2018-08-23

CURRENT

AIR4766/1

This SAE Aerospace Information Report (AIR) covers airbone particulate contaminants that may be present in commercial aircraft cabin air during operation. Discussions cover sources of contaminants, methods of control and design recommendations. Air quality, ventilation requirements and standards are also discussed.

Standard

Heater and Accessories, Aircraft Internal Combustion Heat Exchanger Type

2019-10-01

CURRENT

AS8040C

This SAE Aerospace Standard (AS) covers combustion heaters and accessories used in, but not limited to, the following applications: a Cabin heating (all occupied regions and windshield heating) b Wing and empennage anti-icing c Engine and accessory heating (when heater is installed as part of the aircraft) d Aircraft deicing

Standard

Air Quality for Commercial Aircraft Cabins

2018-08-23

CURRENT

AIR4766

This SAE Aerospace Information Report (AIR) provides information on air quality and some of the factors affecting the perception of cabin air quality in commercial aircraft cabin air. Also a typical safety analysis process utilizing a Functional Hazard Assessment approach is discussed.

Standard

Heat and Mass Transfer and Air-Water Mixtures

2007-12-03

HISTORICAL

AIR1168/2

Heat transfer is the transport of thermal energy from one point to another. Heat is transferred only under the influence of a temperature gradient or temperature difference. The direction of heat transfer is always from the point at the higher temperature to the point at the lower temperature, in accordance with the second law of thermodynamics. The fundamental modes of heat transfer are conduction, convection, and radiation. Conduction is the net transfer of energy within a fluid or solid occurring by the collisions of molecules, atoms, or electrons. Convection is the transfer of energy resulting from fluid motion. Convection involves the processes of conduction, fluid motion, and mass transfer. Radiation is the transfer of energy from one point to another in the absence of a transporting medium. In practical applications several modes of heat transfer occur simultaneously.