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Technical Paper

Thermal Protection Systems for Hypersonic Transport Vehicles
1990-07-01
901306
Thermal protection systems (TPS) for hypersonic transport vehicles are described and evaluated. During the flight through the atmosphere moderate to high aerodynamic heating rates with corresponding high surface temperatures are generated. ...It is demonstrated that microporous and multiwall insulations are efficient, light weight and reliable TPSs for future hypersonic transportation systems.
Technical Paper

Techniques for Space and Hypersonic Flight Escape (Paracone)
1967-02-01
670578
A single, efficient, reliable emergency escape system is needed to provide, at an acceptable total cost, emergency escape capability throughout the entire mission envelope of hypersonic and orbital vehicles. Analysis and limited testing indicate that the Douglas Paracone emergency escape system will meet this requirement.
Article

Boeing debuts first hypersonic passenger aircraft concept
2018-06-29
Officials and engineers at Boeing in Seattle are offering a glimpse into their vision for hypersonic air travel. They have released, for the first time, images of one of the company’s hypersonic air vehicle concepts for potential military and commercial passenger transport. ...They have released, for the first time, images of one of the company’s hypersonic air vehicle concepts for potential military and commercial passenger transport.
Magazine

Aerospace & Defense Technology: April 2022
2022-04-01
Artificial Intelligence in the Battlespace Key Considerations for a New Way of Fighting War Machining Beryllium Electrified Propulsion for Aerospace Where to Start The Future of Managing Mission-Critical Systems Improving Battlefield Connectivity for the Modern Warfighter How to Test a Cognitive EW System Molded RF Materials for Hypersonic Sensors and Seekers AUVSI XPONENTIAL Multimode Optical Fiber Sensing Although the vast majority of fiber optic strain sensors use single mode fiber, multimode fiber has a higher nonlinear threshold that enables higher light levels and lower noise, while the diversity of spatial modes can be used to develop sensors that are inherently immune to signal fading.
Technical Paper

Space Rotor - A French Concept for a Reusable Recovery System
1967-02-01
670391
In general the combined system, space-rotor-vehicle, can be regarded as a hypersonic glider having a L/D ratio of the order of 1.0 to 1.5. However, whatever are the applications envisaged, booster recoveries, orbital recoveries of manned or unmanned vehicles, the weight penalty incurred by this new system is fairly constant and situated well below that of the equivalent, more conventional, means of reentry and recovery. ...The variable geometry of the space rotor confers to this system the capability to reconcile, in one integral system, the difficult problems of the maneuvrable hypersonic reentry and the soft spot landing. In fact the final flare permits to use the stored kinetic energy of the rotor to reduce the approach velocity of the vehicle from 40 kts to 6 ft/sec.
Technical Paper

Temperature Issues for a Mach 2.4 High Speed Civil Transport
1994-10-01
942160
The High Speed Civil Transport (HSCT) will be exposed to elevated temperatures during Mach 2.4 supersonic flight. While not as extreme as those encountered in other high speed flight efforts (NASP, Shuttle), thermal effects will impact decisions in almost all areas of material selection and design. Accurate temperatures are required to evaluate materials, structural concepts, cooling requirements, etc. Analyses show the importance of structural configuration, use of fuel as a heat sink, and surface properties on structural temperatures. Capability to accurately determine convection and radiation boundary conditions is important for future HSCT design.
Journal Article

Analytical Estimation of Infrared Signature of Converging and Converging-Diverging Nozzles of Jet Engine
2021-04-21
Abstract Jet engine hot parts (e.g., jet nozzle) are a crucial source of aircraft’s infrared (IR) signature from the rearview, in 1.9-2.9 μm and 3-5 μm bands. The exhaust nozzle design used in a jet aircraft affects its performance and IR signature (which is also affected just by performance) from the engine layout. For supersonic aircraft (typically for M ∞ > 1.5), a converging-diverging (C-D) nozzle is preferred over a convergent nozzle for optimum performance. The diverging section of the C-D nozzle has a full range of visibility from the rearview; hence, it was not considered a prudent choice for low IR observability. This theoretical study compares the IR signature of the C-D nozzle with that of the convergent nozzle from the rearview in 1.9-2.9 μm and 3-5 μm bands for the same thrust.
Standard

Icing Technology Bibliography
2013-03-15
CURRENT
AIR4015D
This Icing Technology Bibliography is a compendium of references from the open literature that were published prior to the original 1987 issuance of the AIR, including both national and foreign sources. Due to the generality of the subject, and the difficulty of fully investigating every available source, the Bibliography in this document is not intended to be complete.
Standard

Landing and Taxiing Lights - Design Criteria for Installation
2018-07-02
CURRENT
ARP693E
This document includes requirements of installations of adequate landing and taxiing lighting systems in aircraft of the following categories: a Single engine personal and/or liaison type b Light twin engine c Large multiengine propeller d Large multiengine turbojet/turbofan e Military high-performance fighter and attack f Helicopter This document will cover general requirements and recommended practices for all types of landing and taxi lights. More specific recommendations for LED lights in particular can be found in ARP6402.
Standard

SAE Aerospace Applied Thermodynamics Manual Ice, Rain, Fog, and Frost Protection
2021-02-19
CURRENT
AIR1168/4C
This section presents the basic equations for computing ice protection requirements for nontransparent and transparent surfaces and for fog and frost protection of windshields. Simplified graphical presentations suitable for preliminary design and a description of various types of ice, fog, frost, and rain protection systems are also presented.
Standard

Aircraft Tail Bumpers
2021-06-22
CURRENT
AIR1800B
This SAE Aerospace Information Report (AIR) covers the field of civilian, commercial and military airplanes and helicopters. This summary of tail bumper design approaches may be used by design personnel as a reference and guide for future airplanes and helicopters that require tail bumpers. Those described herein will consist of simple rub strips, structural loops with a wear surface for runway contact, retractable installations with replaceable shock absorbers and wear surfaces and complicated retractable tail landing gears with shock strut, wheels and tires. The information will be presented as a general description of the installation, its components and their functions.
Standard

LANDING AND TAXIING LIGHTS - DESIGN CRITERIA FOR INSTALLATION
1991-01-30
HISTORICAL
ARP693B
This SAE Recommended Practice includes requirements of installations of adequate landing and taxiing lighting systems in aircraft of the following categories: a Single engine personal and/or liaison type b Light twin engine c Large multiengine propeller d Large multiengine turbojet e Military high performance fighter and attack f Helicopter
Standard

Landing and Taxiing Lights - Design Criteria for Installation
2006-06-28
HISTORICAL
ARP693C
This document includes requirements of installations of adequate landing and taxiing lighting systems in aircraft of the following categories: a Single engine personal and/or liaison type b Light twin engine c Large multiengine propeller d Large multiengine turbojet e Military high performance fighter and attack f Helicopter
Standard

Landing and Taxiing Lights - Design Criteria for Installation
2012-03-01
HISTORICAL
ARP693D
This document includes requirements of installations of adequate landing and taxiing lighting systems in aircraft of the following categories: a Single engine personal and/or liaison type b Light twin engine c Large multiengine propeller d Large multiengine turbojet e Military high performance fighter and attack f Helicopter
Standard

POSITION AND ANTI-COLLISION LIGHTS - SST
1967-10-31
HISTORICAL
ARP991
This ARP covers the recommended lighting performance and design criteria for: (a) Left Forward Position Lights (Red) (b) Right Forward Position Lights (Green) (c) Rear Position Lights (White) (d) Anti-Collision Lights (Red or White Flashing)
Standard

LED Landing, Taxiing, Runway Turnoff, and Recognition Lights
2011-06-21
HISTORICAL
ARP6402
This document includes recommendations of installations of adequate landing and taxiing lighting systems in aircraft of the following categories: a Single engine personal and/or liaison type b Light twin engine c Large multiengine propeller d Large multiengine turbojet e Military high performance fighter and attack f Helicopter which are subject to the following CFR Parts certification: Part 23 – Airworthiness Standards: Normal, Utility, Acrobatic and Commuter Aircrafts Part 25 – Airworthiness Standards: Transport Category Aircrafts Part 27 – Airworthiness Standards: Normal Category Rotorcraft Part 29 – Airworthiness Standards: Transport Category Rotorcraft
Standard

Icing Technology Bibliography
2007-04-11
HISTORICAL
AIR4015B
This Icing Technology Bibliography is a compendium of references from the open literature that were published prior to the original 1987 issuance of the AIR, including both national and foreign sources. Due to the generality of the subject, and the difficulty of fully investigating every available source, the Bibliography in this document is not intended to be complete.
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