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Safety Materials properties AC-9 Aircraft Environmental Systems Committee Exhaust emissions

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Standard

Environmental Control Systems (ECS) for UA (Unmanned Aircraft)
2022-06-24
WIP
AIR7063
This document provides guidance for establishing ECS for UA by primarily referencing existing AC-9 documents that apply with some indication how they need to be adapted. The document primarily addresses cooling requirements for UA equipment. Limited information is provided for ECS requirements for future UA that may carry passengers. The document does not intend to provide detail design guidance for all types of UA. This document only provides guidance related to environmental control of onboard equipment, cargo and possible animals and passengers. It does not pertain to the related ground stations that may be controlling the UA.
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

Aircraft Electrical Heating Systems
2011-10-17
CURRENT
AIR860B
It is intended that the scope of this information report be limited to electrical heating of passenger, crew, and cargo compartments only. No attempt has been made to develop the complete electrical circuitry associated with the electrical heating components; however, the electrical circuitry required for heating component operation, safety, and monitoring will be included as available. Specific design information is given for various modern aircraft utilizing electrical heating. Each aircraft discussed will be identified by alphabetical letter designation and included in the appropriate appendix.
Standard

Aircraft Electrical Heating Systems
2006-03-24
HISTORICAL
AIR860A
It is intended that the scope of this information report be limited to electrical heating of passenger, crew, and cargo compartments only. No attempt has been made to develop the complete electrical circuitry associated with the electrical heating components; however, the electrical circuitry required for heating component operation, safety, and monitoring will be included as available. Specific design information is given for various modern aircraft utilizing electrical heating. Each aircraft discussed will be identified by alphabetical letter designation and included in the appropriate appendix.
Standard

AIRCRAFT ELECTRICAL HEATING SYSTEMS
1992-03-01
HISTORICAL
AIR860
It is intended that the scope of this information report be limited to electrical heating of passenger, crew, and cargo compartments only.
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

Aircraft Humidification
2021-01-14
CURRENT
AIR1609B
This SAE Aerospace Information Report (AIR) covers the design parameters for various methods of humidification applicable to aircraft, the physiological aspects of low humidities, the possible benefits of controlling cabin humidity, the penalties associated with humidification, and the problems which must be solved for practical aircraft humidification systems. The design information is applicable to commercial and military aircraft. The physiological aspects cover all aircraft environmental control applications.
Standard

HEAT TRANSFER PROBLEMS ASSOCIATED WITH AEROSPACE VEHICLES
1978-04-01
CURRENT
AIR732
The discipline of heat transfer concerns itself basically with the three modes of transferring thermal energy (convection, conduction, and radiation) and their inter-relations. In any phase of aerospace vehicle design, the importance of any of these basic modes will vary depending upon the natural and induced environment the mission imposes as well as the vehicle configuration.
Standard

AIR CONDITIONING OF SUBSONIC AIRCRAFT AT HIGH ALTITUDE
1984-03-01
CURRENT
AIR795A
This report is limited to the special problems of air quantity, purity, movement, pressure, temperature, and humidity which arise from the requirements of the human body during high altitude flight, together with the associated aircraft design problems.
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 Equipment Environmental Control
2006-03-24
HISTORICAL
AIR1168/13
This part of the manual presents methods for arriving at a solution to the problem of spacecraft inflight equipment environmental control. The temperature aspect of this problem may be defined as the maintenance of a proper balance and integration of the following thermal loads: equipment-generated, personnel-generated, and transmission through external boundary. Achievement of such a thermal energy balance involves the investigation of three specific areas: 1 Establishment of design requirements. 2 Evaluation of properties of materials. 3 Development of analytical approach. The solution to the problem of vehicle and/or equipment pressurization, which is the second half of major environmental control functions, is also treated in this section. Pressurization in this case may be defined as the task associated with the storage and control of a pressurizing fluid, leakage control, and repressurization.
Standard

Spacecraft Equipment Environmental Control
2011-07-25
CURRENT
AIR1168/13A
This part of the manual presents methods for arriving at a solution to the problem of spacecraft inflight equipment environmental control. The temperature aspect of this problem may be defined as the maintenance of a proper balance and integration of the following thermal loads: equipment-generated, personnel-generated, and transmission through external boundary. Achievement of such a thermal energy balance involves the investigation of three specific areas: 1 Establishment of design requirements. 2 Evaluation of properties of materials. 3 Development of analytical approach. The solution to the problem of vehicle and/or equipment pressurization, which is the second half of major environmental control functions, is also treated in this section. Pressurization in this case may be defined as the task associated with the storage and control of a pressurizing fluid, leakage control, and repressurization.
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.
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