Browse Topic: Hypersonic and supersonic aircraft

Items (389)
Find
Longitudinal Air-Breathing Hypersonic Vehicle Nonlinear Dynamic Simulation with Different Control Inputs01-17-02-001503/04/2024
The air-breathing hypersonic vehicle (AHV) holds the potential to revolutionize global travel, enabling rapid transportation to low-Earth orbit and even space within the next few decades. This study focuses on investigating the nonlinear dynamic simulation, trim, and stability analysis of a three-degrees-of-freedom (3DOF) longitudinal model of a generic AHV for variable control surface deflection,and. A simulation is developed to analyze the burstiness of the AHV’s nonlinear longitudinal behavior, considering the complete flight envelope across a wide range of Mach numbers, from= 0 to 24, for selected stable. The presented simulation assesses trim analysis and explores the dynamic stability of the AHV through its flight envelope and bifurcation method analysis is carried out to gain insight and validate the dynamic stability using eigen value approach.
Singh, Ritesh, Prakash, Om, Joshi, Sudhir, Sharma, Rakesh Chandmal
Sonic Boom Velocity and Altitude Sensitivity Analysis of a Hypersonic Aircraft Concept2025-01-003505/05/2023
During the last decades there has been a renewed interest in the development of a new generation of supersonic aircraft for civil purposes. However, the noise generated by supersonic aircraft during supersonic flight, commonly referred to as "sonic boom", is still creates annoyance to community on the ground that prohibits supersonic overland flight. To prepare for the advent of a new generation of supersonic aircraft and to define new regulations for them, an increasing number of sonic boom studies is being published. This paper presents numerical simulations of the sonic boom of a hypersonic (Mach 5) aircraft concept. The study describes a sensitivity analysis of the two parameters velocity and altitude. The extensive simulations characterize the sonic boom carpet of the aircraft for different speeds between Mach 1.2 and Mach 5.0, and for two altitudes of 11.3 km and 28.0 km above sea level. The simulation approach is divided into two main regions. This approach is well understood
Graziani, Samuele, Jäschke, Jacob Jens, Viola, Nicole, Gollnick, Volker
Sonic Boom propagation using high and low-fidelity methods2025-01-003405/05/2023
A bottle neck to the introduction of civil supersonic aircraft is represented by the noise produced by shock waves during the cruise flight, the so-called "sonic boom". Authorities prohibit supersonic flight over land due to the exceeding noise levels produced by sonic boom. This work deals with a comprehensive methodology for assessing the aircraft sonic-boom signature at ground level starting from an accurate estimation of the near-field pressure signature caused by shock-wave pressure. High fidelity computational fluid dynamics (CFD) is typically used to calculate near-field sonic booms, whereas proper models are used for propagating at long distances, since CFD becomes computationally demanding as propagation distances exceed 10 km. The present study focuses on assessing a low-fidelity technique (e.g. Whitam's equation) against the direct application of a high-fidelity CFD method for sonic boom propagation at a medium distance. The former propagates the pressure signature through
Glorioso, Antimo, Fasulo, Giovanni, Petrosino, Francesco, Barbarino, Mattia
Infrared Signature of Fixed and Variable Area C-D Nozzle of Aircraft Engine01-16-02-001101/02/2023
The use of converging-diverging (C-D) variable area nozzle (VAN) in military aeroengines is now common, as it can give optimal expansion and control over engine back pressure, for a wide range of engine operations. At higher main combustion temperatures (desired for supercruise), an increase in the nozzle expansion ratio is needed for optimum performance. But changes in the nozzle throat and exit areas affect the visibility of engine hot parts as the diverging section of the nozzle is visible for a full range of view angle from the rear aspect. The solid angle subtended by engine hot parts varies with change in visibility, which affects the aircraft infrared (IR) signature from the rear aspect. This study compares the performances of fixed and variable area nozzles (FAN and VAN) in terms of engine thrust and IR signature of the engine exhaust system in the boresight for the same increase in combustion temperature. This study is performed for two cases: (i) variable throat area and
Baranwal, Nidhi, Mahulikar, Shripad P.
Challenges with Commercial Supersonic Travel and some resolutions 2022-26-121505/26/2022
Innovation is the fulcrum for the Modern world.Aviation sector has adapted niche technologies for the improvement and sustainability of the business.Supersonic aircrafts were designed and developed for faster and seamless transportation. Use of Supersonic Aircrafts in the commercial arena has many technological and regulatory challenges.The NASA Advanced Air Vehicles Program Commercial Supersonic Transport (CST) Project was initiated in this regard and it details out the propositions laid out to bring Supersonic Aircrafts into the Commercial use. This highlights the importance of the Commercial Supersonic Aircraft.Intent of this paper is to provide technical analysis and solution to the norms in line with NASA Research for the Super sonic travel Infrastructure. This includes steps taken to modularize technical, logistical and Operational changes required for the Infrastructure of Commercial Supersonic Travel without discounting safety and reliability of the existing setup Integrated
JOSHI, SRIKANTH, Ramaiah, chethan prasad, Palanikumar, Senthil Kumar, Reddy, Vikramasimha
Hypersonic Bi directional Blended Wing Body UAV Conceptual Development.2022-26-113705/26/2022
This paper looks to develop a conceptual Hypersonic Bi-directional BWB UAV for high efficiency hypersonic systems.This concept successfully allows for many technical challenges involved in supersonic flight which are also present in hypersonic flight to be overcome; however some of these challenges become even greater, in addition to the new phenomena present at hypersonic speeds.The bi-directional BWB UAV concept consists of a symmetric planform which enables flight to occur at two different geometric configurations. The subsonic configuration would have a high aspect ratio and a low sweep and in the hypersonic configuration the UAV would then rotate 90 degrees which would have a low aspect ratio and high sweep. This design overcomes the inherent conflict between subsonic and hypersonic flight in conventional hypersonic launch systems.The airfoil of the subsonic configuration is thicker than that for the hypersonic configuration, a thick airfoil is needed to achieve a high lift
Fernandes, Shane
Aircraft Tail BumpersAIR1800B (Current)06/22/2021
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
Aircraft Tail BumpersAIR1800A (Historical)02/03/2021
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
High-Fidelity Sonic Boom Propagation ToolTBMG-3848402/01/2021
The primary challenge with supersonic flight remains the mitigation of the sonic boom to levels that will be acceptable to humans on the ground. As industry progresses towards realizing a commercial supersonic aircraft, the push from regulators to reduce noise levels has intensified. Innovators at NASA Langley Research Center have developed a system for predicting sonic boom propagation of supersonic aircraft. The sBOOMTraj tool enables efficient computation and mitigation of sonic boom loudness across the entire duration of a flight mission.
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
AC-9 Aircraft Environmental Systems Committee
SAE TOMORROW TODAY: How the Space Coast Became the Comeback Coast1290208/13/2020
The State of Florida is open for business and building a name for itself as a hub for the space industry, supersonic jets and autonomous vehicles. Jimmy Patronis, the state's Chief Financial Officer, is the man who manages all the budgets, keeps the trains running and even serves as the fire marshal. He sits down with host Grayson Brulte to talk about the revitalization of the "Space Coast" and how emerging technology companies can succeed in Florida. Before the conversation kicks off though, Grayson gets Jimmy to explain his ongoing Twitter pursuit of Elon Musk to bring SolarCity to Florida. The two segue into how the "Space Coast" has revitalized itself into the "Comeback Coast" as private sectors have come to Florida to start businesses and add jobs. Jimmy explains the role that government plays in this process to help industries grow and prosper. The conversation explores the commercialization of space flights and how space tourism can bolster Florida's economy; what's next for
Hineman, Marcie
SAE TOMORROW TODAY: Supersonic Travel: Getting You Across the Globe in 3 Hours1290007/30/2020
Aerion plans to bring back the Golden Age of Flying, only this time, it will be done by an environmentally conscious, technology-innovative company. Tom Vice, Chairman, President and CEO of Aerion, lends his expertise in supersonic aviation to the podcast for a conversation with host Grayson Brulte on all things Aerion, plus insights into why the aviation industry stopped innovating and what the future holds. Tom walks us through his journey into aviation, from watching every Apollo launch on a small, black and white TV to working on the B2 Bomber to the "most incredible thing" he worked on at Northrop Grumman: the James Webb Space Telescope, which Tom believes could be the tool that finds life beyond Earth. Tom recalls the lessons he's learned along the way and how they have shaped his vision for innovation and sustainability. Tom shares the vision for Aerion Connect, which builds out the entire travel ecosystem and experience -- FBOs, travelling to-from airports, airplanes -- to
Hineman, Marcie
Supersonic Spike DiffuserTBMG-3682405/01/2020
The basic mode of operation for all passive supersonic diffusers is to enable a plume’s inherent power to drive the outer boundary of the exhaust jet to the diffuser wall so that the entire cross-section of the flow has a speed greater than that of sound. This allows mass removal from the area surrounding the nozzle via entrainment. The result is a low-pressure environment similar to the altitude at which the nozzle was designed to operate. Additionally, the nature of supersonic flow prevents pressure interference from the downstream environment.
Products of Tomorrow: January 2020TBMG-3581401/01/2020
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.
Facility Focus: NASA’s Armstrong Flight Research CenterTBMG-3528110/01/2019
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.
Schlieren System Captures Brilliant Shockwave ImagesTBMG-3525410/01/2019
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.
Video Graphics ModulesTBMG-3453606/01/2019
WOLF Advanced Technology Stouffville, Ontario, Canada 905-852-1163
Effects of Reynolds and Mach Numbers in Large Eddy Simulation of Supersonic Round JetsTBMG-3393703/01/2019
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.
Spanwise Adaptive WingTBMG-3361401/01/2019
NASA's Glenn Research Center developed a novel means of articulating the outboard portion of an aircraft wing to create the optimal geometry for given flight conditions. The Spanwise Adaptive Wing (SAW) concept employs a high-force, solid-state Shape Memory Alloy (SMA)-based actuator to develop a structurally efficient and reliable method of deflecting a portion of the wing in flight. This ability enables significant increases in lateral-directional stability and control augmentation, thereby enhancing aircraft efficiency by reducing the rudder motion to control yaw.
Modular Cross-Platform System Gives High-Speed Pilots Better Visual AidsTBMG-3358701/01/2019
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-3302410/01/2018
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-3312210/01/2018
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)07/02/2018
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-2904806/01/2018
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.
2021-12-29.TEST Development of a Vehicle-Based Experimental Platform for Quantifying Passenger Motion Sickness during Test Track Operations2018-01-002804/03/2018
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
Jones, Monica Lynn Haumann, Sienko, Kathleen, Ebert-Hamilton, Sheila, Kinnaird, Catherine, Miller, Carl, Lin, Brian, Park, Byoung-Keon, Sullivan, John, Reed, Matthew, Sayer, James
CFD Simulation of a Supercritical CO 2 Rolling Rotor Expander for Waste Heat Recovery System of Engines2018-01-005804/03/2018
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
Shu, Ge-Qun, Li, Daiqiang, Yu, Guopeng, Huang, Guangdai
1D Engine Simulation Approach for Optimizing Engine and Exhaust Aftertreatment Thermal Management for Passenger Car Diesel Engines by Means of Variable Valve Train (VVT) Applications2018-01-016304/03/2018
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
Deppenkemper, Kai, Özyalcin, Can, Ehrly, Markus, Schoenen, Markus, Bergmann, Dirk, Pischinger, Stefan
Development of a Robust AIS Parametric Model for V8 Engines Using Design for Six Sigma Approach2018-01-014004/03/2018
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
Zhang, Weiguo, Likich, Mark, Butler, Brian
XPONENTIAL 2018 – An AUVSI ExperienceTBMG-2877904/01/2018
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-2832902/01/2018
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-2768510/01/2017
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-2643902/01/2017
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_0402/01/2017
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-2621101/01/2017
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-2600312/01/2016
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 Transport2016-01-205509/20/2016
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
Muraoka, Koji, Hirabayashi, Daisuke, Sato, Masayuki, Aoki, Yoshihisa
Toughened Uni-piece Fibrous Reinforced Oxidation-Resistant Composite (TUFROC)TBMG-2535309/01/2016
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-2496707/01/2016
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 (Current)05/20/2016
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
LED Landing, Taxiing, Runway Turnoff, and Recognition LightsARP6402A-TEST-REC (Historical)05/20/2016
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-2386702/01/2016
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-2349612/01/2015
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-2265408/01/2015
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-2143202/01/2015
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 Configuration2014-36-019309/30/2014
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
Barbosa, Luciano Magno Frágola, Maciel, Francelle Maria Oliveira, de Barros, José Eduardo Mautone
Toughened Uni-piece Fibrous Reinforced Oxidation-Resistant Composite (TUFROC)TBMG-2051709/01/2014
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-2017707/23/2014
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-2001607/01/2014
Embedded heat pipe assembly Thermacore Lancaster, PA 717-569-6551
Europe's Aerospace Industry Looking ConfidentTBMG-1975506/01/2014
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.
Europe's Aerospace Industry Looking Confident14AERP06_0106/01/2014
Apart from Airbus's highly visible presence in defense and commercial aircraft, Europe also has successful capabilities in helicopters, business jets, and aero engines, and in all these areas their global market share is growing. 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. At one stage it looked as if a proposed merger between EADS and BAE Systems might create the world's largest combined aerospace and defense company, but a German political veto put an end to this plan, largely because of sensitivity over the defense aspects of such a deal.
Gardner, Richard
Items per page:
1 – 50 of 389