Browse Topic: Hypersonic and supersonic aircraft

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LED Landing, Taxiing, Runway Turnoff, and Recognition LightsARP6402B (Current)11/26/2025
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
A-20B Exterior Lighting Committee
Aircraft Tail BumpersAIR1800B (Current)6/22/2021
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.
A-5B Gears, Struts and Couplings Committee NEW Name Goes Her
Aircraft Tail BumpersAIR1800A (Historical)2/3/2021
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.
A-5B Gears, Struts and Couplings Committee NEW Name Goes Her
2.0.104 - Tackling Three Critical Issues of Transportation: Environment, Safety and Congestion Via Semi-autonomous PlatooningSAE-PP-002142/1/2021
In recent years, platooning emerged as a realistic configuration for semi-autonomous driving. In the SARTRE project, simulation and physical tests were performed to validate the platooning system not only in testing facilities but also in conventional highways. Five vehicles were adapted with autonomous driving systems to have platooning functionalities, enabling to perform platoon tests and assess the feasibility, safety and benefits. Although the tested system was in a prototype, it demonstrated sturdiness and good functionality, allowing performing conventional road tests. First of all the fuel consumption decreased up to 16% in some configurations and different gaps between the vehicles were tested in order to establish the most suitable for platooning in terms of safety and economy. Additionally, the platooning technology enables a new level of safety in highways. Around 85% of the accident causation is the human factor. With platooning, the human factor is reduced almost entirely, making it a more efficient and safer system. With platooning, the traffic flow is more homogeneous with several vehicles travelling at the same speed and therefore accident situations are less probable while helping to maintain a steady traffic flow with no stop and go situations. For the same reason, the traffic flow is more manageable enabling advanced traffic management. Thus, the traffic congestion can be reduced and, again, reducing another source of emissions. All the potential advantages of a platooning technology which has been developed and tested are studied in this paper through test results and simulations.
Mutagaana, Festo
Aircraft Thermal Management System EngineeringAIR5744 (Current)10/26/2020
The intent of this report is to encourage that the thermal management system architecture be designed from a global platform perspective. Separate procurements for air vehicle, propulsion system, and avionics have contributed to the development of aircraft that are sub-optimized from a thermal management viewpoint. In order to maximize the capabilities of the aircraft for mission performance and desired growth capability, overall system efficiency and effectiveness should be considered. This document provides general information about aircraft Thermal Management System Engineering (TMSE). The document also discusses approaches to processes and methodologies for validation and verification of thermal management system engineering. Thermal integration between the air vehicle, propulsion system, and avionics can be particularly important from a thermal management standpoint. Due to these factors, this report is written to encourage the development of a more comprehensive system engineering approach to help eliminate and/or reduce mission limitations as a result of materials and components nearing temperature limits.
AC-9 Aircraft Environmental Systems Committee
Products of Tomorrow: January 2020TBMG-358141/1/2020
This column presents technologies that have applications in commercial areas, possibly creating the products of tomorrow. To learn more about each technology, see the contact information provided for that innovation.
Schlieren System Captures Brilliant Shockwave ImagesTBMG-3525410/1/2019
Supersonic flight over land is generally prohibited because sonic booms created by shockwaves disturb people on the ground and can damage property. Armstrong innovators are working to solve this problem with a novel system for capturing images of shockwaves created by supersonic aircraft. The Background Oriented Schlieren Using Celestial Objects (BOSCO) technology uses a celestial object, such as the Sun, as a background to secure unique, measurable shockwave images of full-scale aircraft. The patented image-processing technology captures hundreds of observations with each shockwave, benefitting NASA engineers in their efforts to develop a supersonic aircraft that will produce a soft “thump” in place of a disruptive sonic boom.
Facility Focus: NASA’s Armstrong Flight Research CenterTBMG-3528110/1/2019
Located in Edwards, California in the western Mojave Desert, the Hugh L. Dryden Flight Research Center was renamed in 2014 to honor astronaut Neil Armstrong. NASA Armstrong is chartered to research and test advanced aeronautics, space, and related technologies that are critical to carrying out NASA’s missions of space exploration, space operations, scientific discovery, and aeronautical research and development.
Video Graphics ModulesTBMG-345366/1/2019
WOLF Advanced Technology Stouffville, Ontario, Canada 905-852-1163
Effects of Reynolds and Mach Numbers in Large Eddy Simulation of Supersonic Round JetsTBMG-339373/1/2019
Rockets/landers arrive on the Moon with supersonic speed and impact lunar regolith. There is no reliable software to computationally simulate in an effective way the supersonic plumes escaping from these rockets/devices. A Large Eddy Simulation (LES) model and hybrid WENO (weighted essentially non-oscillatory) scheme numerical method were developed to address this problem.
Modular Cross-Platform System Gives High-Speed Pilots Better Visual AidsTBMG-335871/1/2019
The ability to fly at supersonic speed without producing unsettling sonic booms would re-open a path to faster commercial aviation. In pursuit of aerodynamics that would soften the boom to a dull thud, NASA's Armstrong Flight Research Center engineers developed a ground-based schlieren imaging system that allowed them to photograph shockwaves produced by an aircraft traveling at supersonic speeds.
Burner Rig Testing of A500® C/SiCTBMG-3302410/1/2018
There is growing interest in developing, testing, and deploying ceramic-matrix composites (CMCs) into commercial and military aerospace gas turbine engines due to their durability under extreme conditions and weight-savings potential. For military applications, the focus is on the afterburning section of the turbine engine, including the flameholder, augmentor liner, and both the convergent and divergent segments of the exhaust nozzle. These are demanding applications because of the high temperatures and rapid thermal cycles.
3D Printer Aims to Accelerate Materials DevelopmentTBMG-3312210/1/2018
Spinoff is NASA's annual publication featuring successfully commercialized NASA technology. This commercialization has contributed to the development of products and services in the fields of health and medicine, consumer goods, transportation, public safety, computer technology, and environmental resources.
Landing and Taxiing Lights - Design Criteria for InstallationARP693E (Current)7/2/2018
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.
A-20B Exterior Lighting Committee
Airborne Background Oriented Schlieren TechniqueTBMG-290486/1/2018
NASA has developed a novel method to render visible the density changes in air that cause a refractive index change by an airborne vehicle. These density changes include shock waves, vortices, engine exhaust, and wakes. The determination of location and strength of shock waves and vortices is fundamental to understanding the flow around an aircraft. These features are strong enough to affect the environment that the vehicle inhabits; for example, they can cause drag and/or produce undesirable noise. The researcher must be able to predict and mitigate the effects of these flow features.
Real-Time Path Correction of an Industrial Robot for Adhesive Application on Composite Structures2018-01-13904/3/2018
Due to their unique and favorable properties as well as high strength to weight ratio, composite materials are finding increasing applications in automotive, aircraft and other vehicle manufacturing industries. High demand, production rates and increasing part complexity, together with design variations require fast, flexible and fully automated assembly techniques. In automotive and aircraft manufacturing, widely used bonding and sealing processes are automated using industrial robots due to their speed, flexibility and large working volume. However, there are limitations in achieving complete automation of these processes due to the inherent inaccuracies of the industrial robots, workpiece positioning and process tolerances. Currently, the robot programs are generated in CAD/CAM environment and are adjusted manually according to the actual workpiece. An alternate solution is proposed with an on-board vision based sensor setup to adapt the robot path compensating for the robot kinematic inaccuracies, workpiece referencing errors and unique local deformations of the workpiece via a real-time interface. The realized setup consists of a prototype dosing system with two laser line triangulation sensors on the end-effector of a serial robot. The developed real-time application computes the 5 Degrees of Freedom (DOF) deviations and corresponding robot correction signals. The robot executes the generated offline programs for the application process. The implemented “real-time” control scheme adapts the programmed trajectory in accordance with the position, orientation and tolerances of the actual workpiece so that the process tolerances are met.
Shah, Nihar Hasmukhbhai, Subramanian, Shivaprakash, Wollnack, Jörg
1D Engine Simulation Approach for Optimizing Engine and Exhaust Aftertreatment Thermal Management for Passenger Car Diesel Engines by Means of Variable Valve Train (VVT) Applications2018-01-01634/3/2018
Using a holistic 1D engine simulation approach for the modelling of full-transient engine operation, allows analyzing future engine concepts, including its exhaust gas aftertreatment technology, early in the development process. Thus, this approach enables the investigation of both important fields - the thermodynamic engine process and the aftertreatment system, together with their interaction in a single simulation environment. Regarding the aftertreatment system, the kinetic reaction behavior of state-of-the-art and advanced components, such as Diesel Oxidation Catalysts (DOC) or Selective Catalytic Reduction Soot Filters (SCRF), is being modelled. Furthermore, the authors present the use of the 1D engine and exhaust gas aftertreatment model on use cases of variable valve train (VVT) applications on passenger car (PC) diesel engines. The VVT applications consider a wide range of variables such as exhaust cam phasing, late intake valve opening, Miller, 2nd exhaust event and cylinder deactivation. The model has been validated with the results of experimental investigations to do this in a first step. Secondly, the VVT applications are implemented to the model to analyze their heating potential according to an efficient engine and exhaust gas thermal management. Various heating strategies have been investigated for a full-size vehicle within extended engine speed and load ranges which are relevant for the Worldwide Harmonized Light Vehicles Test Cycle (WLTC) and even more for the determination of Real Driving Emissions (RDE). The results are compared to a conventional heating measure to demonstrate the potential in terms of a faster aftertreatment light-off with increased conversion efficiencies and benefits in CO2 emissions. As conclusion out of the investigations it can be seen, that a cylinder deactivation or a second exhaust event could provide up to 5-10% CO2 reduction under RDE conditions that comply with the EU6d legislation limit.
Deppenkemper, Kai, Özyalcin, Can, Ehrly, Markus, Schoenen, Markus, Bergmann, Dirk, Pischinger, Stefan
2021-12-29.TEST Development of a Vehicle-Based Experimental Platform for Quantifying Passenger Motion Sickness during Test Track Operations2018-01-00284/3/2018
Motion sickness in road vehicles may become an increasingly important problem as automation transforms drivers into passengers. Motion sickness could be mitigated through control of the vehicle motion dynamics, design of the interior environment, and other interventions. However, a lack of a definitive etiology of motion sickness challenges the design of automated vehicles (AVs) to address motion sickness susceptibility effectively. Few motion sickness studies have been conducted in naturalistic road-vehicle environments; instead, most research has been performed in driving simulators or on motion platforms that produce prescribed motion profiles. To address this gap, a vehicle-based experimental platform using a midsize sedan was developed to quantify motion sickness in road vehicles. A scripted, continuous drive consisting of a series of frequent 90-degree turns, braking, and lane changes were conducted on a closed track. The route was selected to be representative of naturalistic urban driving conditions and parameterized in terms of lateral and longitudinal acceleration intensities likely to produce motion sickness. Vehicle instrumentation included simultaneous measure of vehicle acceleration, passenger head kinematics, self-reported motion sickness ratings and associated sensations, and physiological responses. A no-task condition involved normative passenger behavior and unconstrained gaze. During the task condition, passengers read a handheld mini iPad tablet. The resulting vehicle-based experimental platform provided a reliable methodology designed to quantify motion sickness. Knowledge generated from studies with this platform will inform the design of AVs and the development and evaluation of countermeasures.
Jones, Monica Lynn Haumann, Sienko, Kathleen, Ebert-Hamilton, Sheila, Kinnaird, Catherine, Miller, Carl, Lin, Brian, Park, Byoung-Keon, Sullivan, John, Reed, Matthew, Sayer, James
Development of a Robust AIS Parametric Model for V8 Engines Using Design for Six Sigma Approach2018-01-01404/3/2018
The automotive Air Induction System (AIS) is an important part of the engine systems which delivers the air to the engine. A well-designed AIS should have low flow restriction and radiates a good quality sound at the snorkel. The GT-Power simulation tool has been widely utilized to evaluate the snorkel noise in industry. In Fiat Chrysler Automobiles, the simulation method enhanced with Design For Six Sigma (DFSS) approach has been developed and implemented in AIS development to meet the functional requirements. The development work included different types of DFSS projects such as identifying new concept, robust optimization and robust assessment etc. In this paper, the work of a robust optimization project is presented on developing an AIS parametric model to achieve optimized snorkel noise performance for a V8 engine. First, the theory of AIS acoustic modeling using GT-power and DFSS robust optimization using Taguchi’s parameter design method are described. Secondly, the effects of several AIS design control factors on the AIS sound attenuation and snorkel performance are studied. Finally, the eight steps of Taguchi’s parameter design method are presented on developing a parametric AIS model for a V8 engine. Based on the results from the verification step, an optimized AIS parametric model to this specified V8 engine is suggested. The optimized model is more robust against temperature variation and has better snorkel noise performance. The lessons learned from this project and future work are discussed in the conclusion section.
Zhang, Weiguo, Likich, Mark, Butler, Brian
CFD Simulation of a Supercritical CO 2 Rolling Rotor Expander for Waste Heat Recovery System of Engines2018-01-00584/3/2018
The supercritical CO2 power cycle system for waste heat recovery (WHR) of internal combustion engine (ICE) has widely been concerned as a research hotspot. And the expander is a key component in the supercritical CO2 power system. Rolling rotor expander has the following advantages: compact size, light weight, less moving parts, high stability and long service life, which qualify it a very suitable choice for engine’s waste heat recovery system. For a self-designed rolling rotor expander using supercritical CO2 as its working fluid, FLUENT software was used to simulate its internal flow field in this study, obtaining the changes of the internal pressure field and turbulent kinetic energy. The causes of local vortex in the expansion process were analyzed. Under different working conditions of the expander, the change of internal pressure and the distribution of P-V curve were observed, and the work capacity under different inlet pressure was analyzed. Results show that, the work capacity increases if the intake pressure increases within a certain range. However, if the inlet pressure keeps increasing and exceeds a reasonable limit, the local vortex in the suction process is enhanced and the pressure loss is increased and the degree of the turbulence is strengthened, which causes a certain impact on the expansion process and expander service life. The rotating speed has a great influence on the operation of the expander. These results provide guidance for the design and optimization of the supercritical CO2 expander in the future.
Shu, Ge-Qun, Li, Daiqiang, Yu, Guopeng, Huang, Guangdai
XPONENTIAL 2018 – An AUVSI ExperienceTBMG-287794/1/2018
The Association for Unmanned Vehicle Systems International (AUVSI) is bringing this year's XPONENTIAL 2018 to the Colorado Convention Center in Denver, CO. The event, which runs from April 30 – May 3, will feature more than 200 presentations and panel discussions focused on all aspects of the unmanned vehicle and robotics market. Over 725 exhibitors representing more than 20 different industries will be showcasing their latest technology to an estimated 7,000 attendees from all over the world.
Optical Method for Detecting Displacements and Strains at Ultra-High Temperatures During Thermo-Mechanical TestingTBMG-283292/1/2018
NASA's Langley Research Center has developed an optical method for detecting displacements and strains at ultra-high temperatures during thermo-mechanical testing. This innovation will provide displacement and strain measurements in high-temperature applications where conventional measurement technologies cannot physically survive. The measurement system has operated in laboratory environments in excess of 2,800 °F.
Using Aerial Towing to Study Sonic BoomsTBMG-2768510/1/2017
Researchers at NASA's Armstrong Flight Research Center (AFRC) recently completed a study of the feasibility of aerial towing an unpiloted, sub-scale vehicle to supersonic flight conditions to examine the sonic boom that is produced — or, preferably, not produced.
Simulating and Analyzing Flow for an Air-to-Air Refueling SystemTBMG-264392/1/2017
Long-range bombers may have missions halfway around the world. Fighter jets may have to stay in the air longer than their relatively small fuel tanks will allow, or may find they have exhausted their fuel unexpectedly, such as during supersonic flight or evasive maneuvers. In these situations, large tanker aircraft are deployed that carry sufficient fuel to refill several smaller aircraft in a single mission (Figure 1). The task of injecting volatile jet fuel from one aircraft to another while both are moving at high speed and altitude is fraught with risk.
Simulating and Analyzing Flow for an Air-to-Air Refueling System17AERP02_042/1/2017
Long-range bombers may have missions halfway around the world. Fighter jets may have to stay in the air longer than their relatively small fuel tanks will allow, or may find they have exhausted their fuel unexpectedly, such as during supersonic flight or evasive maneuvers. In these situations, large tanker aircraft are deployed that carry sufficient fuel to refill several smaller aircraft in a single mission (Figure 1). The task of injecting volatile jet fuel from one aircraft to another while both are moving at high speed and altitude is fraught with risk.
New Horizons for Aviation TechnologyTBMG-262111/1/2017
Thanks to advancements developed by NASA, today’s aviation industry is better equipped than ever to safely and efficiently transport passengers to their destinations. In fact, every U.S. aircraft and air traffic control tower uses NASA-developed technology. Streamlined aircraft bodies, quieter jet engines, drag-reducing winglets, and lightweight composite structures are an everyday part of flying thanks to NASA research that traces its origins back to the earliest days of aviation. But NASA isn’t finished. Here are some new technologies that could change the airline industry of the future.
Distributed Propulsion Concepts and Superparamagnetic Energy Harvesting Hummingbird EngineTBMG-2600312/1/2016
A new engine concept from NASA’s Glenn Research Center allows for truly distributed propulsion. The concept enables airframe and system modularity by allowing parts to be swapped or repaired easily. Design changes can be applied to individual components and not the entire propulsion system. The NASA Glenn innovation eliminates heavy shafts and disks, and allows for airplane modularity as well. This design also enables subsonic to high supersonic flight with the same flowpath. If parts are damaged during flight, only a small percentage of thrust is lost. In addition, the blades can be retracted to enable ramjet or scramjet mode.
Research on the Quad Tilt Wing Future Civil VTOL Transport2016-01-20559/20/2016
JAXA (Japan Aerospace Exploration Agency) has been conducting a research on a future commercial tilt wing VTOL (Vertical TakeOff and Landing) transport under JAXA's "Sky Frontier" Program aiming to develop technologies for aircraft innovation. The research focuses on QTW (Quad Tilt Wing) civil VTOL transport, which features tandem tilt wings with propellers mounted at the mid-span of each wing. The goals of the research in the present phase are to propose a concept of a QTW business VTOL transport system and to pursue the essential technologies development such as OEI (One-Engine-Inoperative) safe recovery, transition flight control and cruise efficient aerodynamic design. Nine passengers business QTW concept was designed and trade-off analysis of the propulsion system architecture for OEI safety was conducted. The result suggests the architecture having no cross-shaft mechanism with auto-failure-compensation is the most effective in terms of the system weight and operating cost. Controller design technology for full-envelope auto-guidance mode has been developed and a series of flight evaluations has been started using a small QTW UAV (Unmanned Aerial Vehiclde) demonstrator. A CFD (Computational Fluid Dynamics) tool for cruise efficient tandem wing design has also been developed and its preliminary validation has been conducted. This paper summarizes the overview of the research program and the current progress of the system concept design and the essential technology research.
Muraoka, Koji, Hirabayashi, Daisuke, Sato, Masayuki, Aoki, Yoshihisa
Toughened Uni-piece Fibrous Reinforced Oxidation-Resistant Composite (TUFROC)TBMG-253539/1/2016
The Toughened Uni-piece Fibrous Reinforced Oxidation-Resistant Composite (TUFROC) allows for much more affordable and sustainable operations involving Space Launch Services and other systems that utilize Earth re-entry vehicles. TUFROC has an exposed surface design and appropriate materials combination that will allow a space vehicle to survive both the mechanical stresses during launch and the extreme heating and stress of re-entry. It provides a thermal protection tile attachment system that is suitable for not only spacecraft applications, but also could be used where there are extreme heating environments [up to 3100 °F for 5 to 10 minutes and 3600 °F, and possibly higher, for very short time intervals (one-minute or less)].
Aluminoborosilicate Supplement for Thermal Protection of a Re-entrant VehicleTBMG-249677/1/2016
The Toughened Uni-piece Fibrous Reinforced Oxidation-Resistant Com posite (TUFROC) allows for much more affordable and sustainable operations involving Space Launch Services and other systems that utilize Earth reentry vehicles. TUFROC has an exposed surface design and appropriate materials combination that will allow a space vehicle to survive both the mechanical stresses of the initial ascent, and the extreme heating and stress of re-entry. It provides a thermal protection tile attachment system that is suitable for application to a space vehicle leading edge, and for other uses in extreme heating environments (up to 3600 °F, and possibly higher, for short time intervals).
LED Landing, Taxiing, Runway Turnoff, and Recognition LightsARP6402A (Historical)5/20/2016
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
A-20B Exterior Lighting Committee
Thermal Management Coating (TMC)TBMG-238672/1/2016
An experimental study was conducted in conjunction with the research and development program at the NASA Marshall Space Flight Center (MSFC) on thermal protection systems (TPS) for aerospace applications, a new concept for reusable TPS material. The new system uses a micro-encapsulated phase-change material rather than an ablative material to dissipate the heat produced during supersonic flight. This new material absorbs energy as it goes through a phase change during the heating portion of the flight profile and then the energy is released as the material cools. This new TPS consists of micro-encapsulated phasechange material and a resin system to adhere the coating to the structure. The technology has been successfully tested in the hot gas tunnel (aero-thermal heating). The figure shows the test results.
Stereoscopic Planar Laser-Induced Fluorescence Imaging for Time-Resolved 3D Movies in Hypersonic FlowTBMG-2349612/1/2015
Understanding and predicting transition from laminar to turbulent flow in hypersonic boundary layers is an active and important field of research because transitional and turbulent heating can be four or more times higher than laminar heating on hypersonic vehicles, including the Orion Crew Exploration Vehicle (CEV).
Propulsion Performance Model for Efficient Supersonic AircraftTBMG-226548/1/2015
For the design process of the class of aircraft known as an efficient supersonic air vehicle (ESAV), particular attention must be paid to the propulsion system design as a whole including installation effects integrated into a vehicle performance model. The propulsion system assumed for an ESAV considered in a recent study done by Optimal Flight Sciences LLC and the Air Force Research Laboratory was a three-stream variable cycle engine (VCE).
NACA to NASA: 100 Years of Aeronautics InnovationTBMG-214322/1/2015
Streamlined aircraft bodies, quieter jet engines, techniques for preventing icing, drag-reducing winglets, lightweight composite structures, and so much more are an everyday part of flying thanks to NASA research that traces its origins back to the earliest days of aviation.
Study of Unmanned Supersonic Aircraft Configuration2014-36-01939/30/2014
The aim of this work is to present the preliminary performance studies of the unmanned, lightweight (less than 10 kg), supersonic research aircraft. The studies comprise the typical mission for the aircraft's first supersonic version, based on the aerodynamic, thrust, and mass characteristics presented in a previous work. The aircraft, named as “Pohox”, is an Unmanned Air Vehicle, or “UAV”, and is intended to be the flying test bed for a multi cycle engine capable to provide thrust in subsonic, transonic and supersonic regimes. Different tools have been developed to perform the analysis. In the analysis, different flight paths are considered in order to provide insights in terms of fuel consumption, altitude and speed gain. Aircraft ‘excess power’ diagrams have been generated, to provide guidance for the definition of the flight paths to be analyzed. Drag dependency with Mach number is considered in the analysis. In addition, two important regions in the Aircraft's altitude versus speed diagram are determined: the “feasibility flight corridor” which is the region the aircraft can perform sustained horizontal or climb flight, and the “supersonic jump region”, which is the most suitable Altitude-Speed location to cross the sound barrier. The present analysis can be considered as the natural step, after aircraft first definitions, towards the aircraft detailed design; and the results obtained provide good indications of the technical feasibility of the aircraft.
Barbosa, Luciano Magno Frágola, Maciel, Francelle Maria Oliveira, de Barros, José Eduardo Mautone
Toughened Uni-piece Fibrous Reinforced Oxidation-Resistant Composite (TUFROC)TBMG-205179/1/2014
TUFROC has an exposed surface edge design and an appropriate materials combination for a space vehicle that will survive the mechanical stresses induced in the initial ascent, and will subsequently survive the extreme heating and mechanically stressful environment of re-entry. It provides a thermal protection tile attachment system, suitable for application to a space vehicle leading edge, and for other uses in extreme heating environments [up to 3,600 °F (1,982 °C), and possibly higher, for short time intervals].
Dr. Keith Gendreau, Principal Investigator, Goddard Space Flight Center, Greenbelt, MDTBMG-201777/23/2014
Dr. Keith Gendreau is the principal investigator of the upcoming Neutron star Interior Composition ExploreR (NICER) mission. He was the 2011 Innovator of the Year at Goddard Space Flight Center, and he has been developing X-ray detectors, optics, and other instrumentation to support a number of NASA missions.
Heat Pipe Assembly Passes NASA Hypersonic TestsTBMG-200167/1/2014
Embedded heat pipe assembly Thermacore Lancaster, PA 717-569-6551
Europe's Aerospace Industry Looking ConfidentTBMG-197556/1/2014
Talk of further consolidation within Europe’s dynamic aerospace sector has been on the lips of industry watchers for several years, but although the major European-based global players have not progressed toward further mergers, the continent’s biggest aerospace company, the former EADS, has achieved a very significant business restructuring, sweeping all its diverse companies into one giant, three-division entity, and adopting the new corporate identity of the Airbus Group.
Study of Unmanned Supersonic Aircraft Configuration2013-36-035310/7/2013
The aim of this work is to present the preliminary configuration design studies for an unmanned, lightweight (less than 15 kg), supersonic research aircraft. The studies comprise the aircraft typical mission, the aerodynamic and structural arrangement, preliminary performance, as well as mass distribution. The aircraft, an Unmanned Air Vehicle, or “UAV”, is named as Pohox (“arrow” in Maxakali indian language). It is intended to be the flying test bed for a multicycle engine capable to provide thrust in subsonic, transonic and supersonic regimes. In order to provide validation of the analysis tools, flight performance characteristics of a known, high speed aircraft - North American X-15 - have been also evaluated and compared with the available flight test data. The present analysis is an important step towards the aircraft detailed definition. And the features associated with the configuration obtained are good indications of the technical feasibility of this supersonic UAV.
Barbosa, Luciano Magno Frágola, de Barros, José Eduardo Mautone
Enhancing Microwave Spectroscopy in Astrophysics ApplicationsTBMG-1745610/1/2013
In popular perception, the vastness of space is an empty vacuum dotted with stars, planets, black holes, and other celestial formations. In reality, astrophysicists have shown that space contains low-density matter — gas clouds, dust grains, and more — existing in ionic, atomic, or molecular phases.
High-Pressure Lightweight ThrustersTBMG-1744510/1/2013
Returning samples of Martian soil and rock to Earth is of great interest to scientists. There were numerous studies to evaluate Mars Sample Return (MSR) mission architectures, technology needs, development plans, and requirements. The largest propulsion risk element of the MSR mission is the Mars Ascent Vehicle (MAV). Along with the baseline solid-propellant vehicle, liquid propellants have been considered. Similar requirements apply to other lander ascent engines and reaction control systems.
Curiosity: One Year LaterTBMG-172489/1/2013
On August 5, 2012, the Mars Science Laboratory (MSL) rover, Curiosity, landed in Gale Crater in a perfectly executed procedure originally referred to as “7 Minutes of Terror.” A year into its two-year exploration of the Red Planet, Curiosity has already achieved the major goal of its mission.
Electromagnetic Interference on Aircraft from Jet Engine ChargingAIR1147A (Historical)2/24/2013
Engine charging of aircraft has been observed for many years. This SAE Aerospace Information Report (AIR) reviews the history of observations, physical characteristics, and possible techniques for minimizing the effects.
AE-4 Electromagnetic Compatibility (EMC) Committee
Analysis of the Effects of Streamwise Lift Distribution on Sonic Boom SignatureTBMG-154751/1/2013
Investigation of sonic boom has been one of the major areas of study in aeronautics due to the benefits a low-boom aircraft has in both civilian and military applications. Current Federal Aviation Administration regulations prohibit supersonic flight over land due to potential effects the sonic boom may have on structures and humans.
Energy Optimized Aircraft: What is it and how do we make one?2012-01-217910/22/2012
Efforts are underway to develop technologies to create a more Energy Optimized Aircraft (EOA). The question becomes how should one define an Energy Optimized Aircraft and how should energy optimization be measured to determine what is optimal? This paper provides a top level point of view for the goal of an Energy Optimized Aircraft. It outlines how one should approach the design of such an aircraft, the relevant vehicle systems technologies to enable energy optimization for fighter aircraft, and potential aircraft level measurands for determining degrees of goodness associated with incorporating different technologies. The top-to-bottom approach is provided for traceability of technologies being developed to aircraft and mission level goals.
Griggs, Steven C., Iden, Steven Mark, Lamm, Peter T.
Landing and Taxiing Lights - Design Criteria for InstallationARP693D (Historical)3/1/2012
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
A-20B Exterior Lighting Committee
Flight Test Results from the Rake Airflow Gage Experiment on the F-15BTBMG-1186311/1/2011
The results are described of the Rake Airflow Gage Experiment (RAGE), which was designed and fabricated to support the flight test of a new supersonic inlet design using Dryden’s Propulsion Flight Test Fixture (PFTF) and F-15B testbed airplane (see figure). The PFTF is a unique pylon that was developed for flight-testing propulsion-related experiments such as inlets, nozzles, and combustors over a range of subsonic and supersonic flight conditions.
Automated Planning, Exploration and Mapping of Complex Operational Domains of Flight Using Multifactor Situational Trees2011-01-265910/18/2011
A critical situation can suddenly develop in the ‘pilot (automaton) - aircraft - operational environment’ system behavior as a result of unfavorable mixing and cross-coupling of several demanding operational factors. The latter can include adverse weather effects, pilot (automaton) errors, mechanical failures and hidden design flaws. These factors are typically linked by strong cause-and-effect relationships, which can disturb the normal flow of external forces and moments acting on the aircraft. As a result, a multifactor situation can quickly propagate towards a chain reaction type accident. Specialists (designers, flight test pilots/engineers, regulators, investigators, educators/instructors, line pilots) have limited resources to address multifactor cases during the aircraft life cycle. The main difficulty is combinatorics (‘the curse of dimensionality’) which determines technical, time and budget constraints. Potentially unsafe complex domains of flight can be identified and screened in advance using the system dynamics model as a virtual flight test article. The developed methodology makes it possible to automatically plan, explore, analyze and map a broad set of realistic multifactor scenarios in autonomous fast-time modeling and simulation experiments. The outcome is a situational tree. This is a collection of branching (what-if) flight paths that are specially planted around a baseline situation to thread a complex operational domain of interest. Special techniques are used to mine and granulate the system level flight safety knowledge from these data structures. Multifactor situational trees can be helpful to locate potential anomalies in the system behavior, quantify critical combinations of events and processes (accident precursors), suggest available recovery options, and depict the aircraft's safety performance under multifactor conditions using ‘a bird's eye view’ knowledge maps. In this paper, the key concepts, algorithms, data structures, research steps and application examples of the developed methodology are presented using realistic flight cases.
Burdun, Ivan Y.
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