SCIENTIFIC AND TECHNICAL AEROSPACE REPORTS
A Biweekly Publication of the National Aeronautics and Space Administration
VOLUME 43, ISSUE 16 - AUGUST 12, 2005
05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE - PART II
Includes all stages of design of aircraft and aircraft structures and systems.
Also includes aircraft testing, performance, and evaluation, and aircraft and flight simulation technology.
For related information see also 18 Spacecraft Design, Testing and Performance; and 39 Structural Mechanics.
For land transportation vehicles see 85 Technology Utilization and Surface Transportation.
20050194639 Forest Service, Missoula, MT, USA, Bureau of Land Management, Washington, DC, USA
Professional Helicopter Pilot Guide
Feb. 1996; 146 pp.; In English Report No.(s): PB2005-107916; No Copyright; Avail: CASI; A07, Hardcopy
The Professional Helicopter Pilot Guide is organized into a topic format style. Each chapter provides a complete discussion of the topic. As such, there exists some duplicate discussion or description of material from chapter to chapter. This was done such that as a reference source, the reader can consult any given topic and receive all of the pertinent information, rather than be referred back and forth to other chapters for needed information to fully understand the topic in question. This document is an introduction to the arena of wildland firefighting, as it applies to the helicopter pilot. For the helicopter to be a fully effective tool in fire suppression it is essential that pilots work closely with the individuals involved in management and use of helicopters. These people are primarily the helicopter manager and the crew, but may include any member of the firefighting team. A helicopter is a valuable and efficient fire fighting resource available to the wildland fire service. To attain the highest efficiency, close cooperation must take place between the pilot and incident management personnel. NTIS
Fire Fighting; Fires; Helicopters; Flight Safety; Human Performance
20050196043 Army Aeromedical Research Lab., Fort Rucker, AL USA
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Self-Report and Ocular Measures of Fatigue in U.S. Army Apache Aviators Following Flight
LeDuc, Patricia A.; Greig, Joanna L.; Dumond, Shannen L.; May 2005; 16 pp.; In English; Original contains color illustrations Report No.(s): AD-A434859; USAARL-2005-10; No Copyright; Avail: CASI; A03, Hardcopy
AH-64 Apache helicopter pilots fly the aircraft using a monocular helmet-mounted display that provides imagery from two separate forward-looking infrared sensors mounted on the nose of the aircraft. Studies have documented complaints of fatigue, headaches, and visual problems associated with the use of this sighting system. The goal of this study were 1)to quantify possible flight-induced fatigue in Apache aviators and 2)to evaluate minimally intrusive neurophysiologic measures of fatigue for potential use in operational environments. Methods: Using a pre-post design, we assessed self-reported levels of alertness, physical, cognitive, and visual fatigue and ocular indices of fatigue obtained using an instrument specifically designed to capture various eye responses. Fifty-three aviators contributed data to this study. Results: Significant differences in all pre- and postflight ocular responses were observed. Pupil size and constriction latency increased while constriction amplitude and saccadic velocity decreased. Significant pre- and postflight differences also were seen on all self-report measures. Pilots reported less alert and more fatigued following flight. Conclusions: We found that flight in an AH-64 Apache was a significant factor in producing changes in ocular and self-report measures similar to those produced by sleep loss. DTIC
Aircraft Pilots; Eye Movements; Flight
20050196061 Air Force Inst. of Tech., Wright-Patterson AFB, OH USA
Controlling Sideslip Angle to Reduce the Radar Exposure of a Tactical, Rotary Winged UAV
Bulseco, Jonathan D.; Mar. 2005; 117 pp.; In English; Original contains color illustrations Report No.(s): AD-A434892; AFIT/GAE/ENY/05-M26; No Copyright; Avail: Defense Technical Information Center (DTIC)
This work investigates another way of contributing to the radar minimization solution for air vehicles in a threat environment. While much research has been conducted on structural solutions to radar exposure minimization, not much work has been done in the area of using control to continuously assess and present the smallest radar cross section of an air vehicle to oncoming threat radar systems by changing the aircraft’s orientation. This work looks at the application of sideslip/beta angle feedback control of an unmanned helicopter to minimize radar cross section exposure in a hostile radar environment. A new way of controlling aircraft trajectory is introduced that incorporates both path and orientation optimization feedback; the aircraft’s heading is controlled to orient the vehicle in a way that reduces its radar cross section, while sideslip angle is used to control the aircraft’s path. A representative hostile environment is created and results show that a substantial reduction in radar cross section exposure can be achieved with beta feedback control. A linear state space model is derived for the OH-6A helicopter with the JANRAD software program. Eigenstructure assignment is used to shape the response of the helicopter into desired response modes.AMatlab based flight control system is developed around the derived helicopter model with altitude, heading, and beta angle command signals that drive four conventional helicopter control inputs. DTIC
Exposure; Flight Control; Helicopters; Radar Cross Sections; Sideslip
20050196171 Air Force Systems Command, Brooks AFB, TX USA
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US Military Unmanned Aerial Vehicle Mishaps: Assessment of the Role of Human Factors Using Human Factors Analysis and Classification System (HFACS)
Tvaryanas, Anthony P.; Thompson, William T.; Constable, Stefan H.; Mar. 2005; 37 pp.; In English Report No.(s): AD-A435063; HSW-PE-BR-TR-2005-0001; XC-311TH HSW; No Copyright; Avail: CASI; A03, Hardcopy
Background: This study was a 10-year cross sectional analysis of human factors in U.S. military UAV mishaps. Methods: Class A-C UAV mishap reports were reviewed and human factors coded using the Human Factors Analysis and Classification System (HFACS). Binary logistic regression was used to create models predicting unsafe operator acts. Results: 133/221(60.2%) UAV mishaps were human related. Predictors of unsafe acts were technological environment and cognitive factors in the Air Force (P \h 0.010), organizational processes, psycho-behavioral factors, and crew resource management in the Army (P \h 0.001), and work and attention and risk management in the Navy (P \h 0.025). The frequency of specific types of unsafe acts differed between the services with skill-based errors more common in the Air Force (P = 0.001) and violations in the Army (P = 0.016). Conclusion: Recurring latent failures at the organizational, supervisory, and preconditions levels contributed to more than half of UAV mishaps. The patterns of latent failures and unsafe acts differed between the services. DTIC
Accidents; Classifications; Human Factors Engineering; Pilotless Aircraft; Statistical Analysis
20050196203 Army Combined Arms Center, Fort Leavenworth, KS USA
Air Defense with an Attitude: Helicopter v. Helicopter Combat
Grau, Lester W.; Adams, James H., III; Feb. 2003; 11 pp.; In English Report No.(s): AD-A435109; No Copyright; Avail: Defense Technical Information Center (DTIC)
Helicopters are proliferating among the world’s armies. This growing inventory includes armed helicopters equipped with weapons systems suitable for engaging other helicopters in aerial combat. In a major regional conflict, armed helicopters might pose a threat that neither the U.S. Air Force nor U.S. Army is prepared to counter. DTIC
Air Defense; Attack Aircraft; Combat; Helicopters; Military Helicopters; Warfare; Weapon Systems
20050196216 BAE Systems Advanced Information Technologies, Inc., Arlington, VA USA
Dynamic Control and Formal Models of Multi-Agent Interactions and Behaviors
Roszman, Larry; Armstrong, Derek; Khalali, Aram; Hickling, Gwen; May 2005; 51 pp.; In English; Original contains color illustrations Contract(s)/Grant(s): F30602-00-C-0182; DARPA ORDER-K542; Proj-TASK Report No.(s): AD-A435125; AFRL-IF-RS-TR-2005-188; No Copyright; Avail: Defense Technical Information Center (DTIC)
New Multi-Agent System (MAS) approaches to complex DoD problems hold the promise of previously unrealized levels of autonomy, adaptability, and flexibility of agent-controlled systems. These systems will provide essential capabilities in command and control, surveillance, automated targeting and weapons delivery, and biochem monitoring. BAE SYSTEMS Advanced Information Technologies’ work focused on three areas. First was the development of the Open Experimentation Framework to facilitate research, evaluation, and characterization of the emerging science of Multi-Agent Systems. Second was the design and facilitation of a project-wide demonstration in which all Principal Investigators participate. Third was our theoretical research into cooperative and adaptive methods for multi-agent systems to service asynchronously appearing pop up tasks. DTIC
Adaptation; Dynamic Control; Optimization
20050196219 Industrial Coll. of the Armed Forces, Washington, DC USA
Industry Study Paper: The Aircraft Industry, AY 2004, Seminar 2
Morris, Stephen H.; Archibald, Dominic; Berg, Gerry C.; McDermott, Edwin; Rehberg, Carl D.; Jan. 2004; 41 pp.; In English; Original contains color illustrations Report No.(s): AD-A435134; No Copyright; Avail: Defense Technical Information Center (DTIC)
The aircraft industry now appears to have weathered the ‘perfect storm’ of Severe Acute Respiratory Syndrome (SARS) and the Global War on Terrorism (GWOT), emerging somewhat battered but poised to begin a slow recovery in the coming years. Orders for new aircraft are up and thus revenues and profits should begin to climb in 2005, reversing declining trends since 2001. However, airlines remain under intense pressure to cut costs to remain profitable, forcing aircraft and engine manufacturers to adopt austere measures. Meanwhile, defense expenditures have received a boost from heightened security concerns and developing technologies such as unmanned air vehicles (UAVs) and unmanned combat air vehicles (UCAVs). The defense market also will continue to enjoy expansion as a result. The overall outlook for the aircraft industry now appears to indicate steady growth over the next decade and should provide sufficient demand for both Airbus’ A380 and Boeing’s 7E7, as well as the growing regional jet market, albeit in an atmosphere of intense competition. However, security remains a top concern, as another terrorist attack on or involving passenger aircraft would have devastating long-term effects on the entire industry. This report focuses on four sectors of the aircraft industry: commercial fixed wing; military fixed wing; rotor craft (helicopters and tilt rotor aircraft); and aircraft jet engines. Key players in the individual sectors will be highlighted in the respective sections of the report. Special focus segments have also been included on regional jets and UAVs. DTIC
Airline Operations; Commercial Aircraft; Economics; Forecasting; Helicopters; Industries; Jet Engines
20050196250 Air Force Inst. of Tech., Wright-Patterson AFB, OH USA
Modeling Information Quality Expectation in Unmanned Aerial Vehicle Swarm Sensor Databases
Baldwin, Patrick D.; Mar. 2005; 122 pp.; In English; Original contains color illustrations Report No.(s): AD-A435192; AFIT/GCS/ENG/05-01; No Copyright; Avail: Defense Technical Information Center (DTIC)
Swarming Unmanned Aerial Vehicles (UAVs) are the future of Intelligence, Surveillance and Reconnaissance (ISR). Swarms of hundreds of these vehicles, each equipped with multiple sensors, will one day fill the skies over hostile areas. As the sensors collect hundreds of gigabytes of data, telemetry data links will be unable to transmit the complete data picture to the ground in real time. The collected data will be stored on board the UAVs and selectively downloaded through queries issued from analysts on the ground. Analysts expect to find relevant sensor data within the collection of acquired sensor data. This expectation is not a quantified value, rather a confidence that this relevant data exists. An expectation of the likely quality of the available sensor information is determined by the user through the use of the methods and tools developed in this thesis. This work develops swarm coverage analysis models using position in time data from the swarm. With these models, a geometric analysis of the swarm is conducted that shows analysts when and where the swarm likely collected sensor data most relevant to a need. Convex hulls are used to calculate areas of coverage as well as swarm and sensor densities. Target profiling algorithms are developed that show target coverage over time from the swarm for each sensor type. Target-centric and sensor-centric analyses allow analysts to quickly determine where individual swarm agents were relative to a target at any point during the mission. Finally a series of visualizations of the swarm and targets are created that allow the analyst to view swarm activity from the perspective of individual swarm members or targets. DTIC
Data Bases; Expectation; Information Theory; Pilotless Aircraft; Reconnaissance
20050196283 Naval Postgraduate School, Monterey, CA USA The Raven Small Unmanned Aerial Vehicle (SUAV), Investigating Potential Dichotomies Between Doctrine and Practice Jenkins, Glenn E.; Snodgrass, William J., Jr; Jun. 2005; 75 pp.; In English; Original contains color illustrations Report No.(s): AD-A435397; No Copyright; Avail: Defense Technical Information Center (DTIC)
The goal of this MBA Project is to investigate possible disconnects between doctrine and practice in the employment of the Raven Small Unmanned Aerial Vehicle (SUAV). The Army’s current Small UAV requirements are based upon the Future Combat System’s Operations Requirements Document and has not been validated at the platoon or company level. The Raven SUAV is a Commercial off the Shelf (COTS) item that swiftly became the Army’s Small UAV of choice for operations in Afghanistan and Iraq. Doctrine and Techniques. Tactics. and Procedures (TTP) have been written for the Raven SUAV; however, it is not standard practice for all units operating the system abroad. The last review of the SUAV operational requirements was conducted in 2003 but did not specifically address its usage on the battlefield. In an attempt to fill that gap, this project focuses on real-world usage of the Raven SUAV system. We compare doctrine versus practice using the Department of Defense’s (DoD) Doctrine, Organization, Training, Material. Leadership, Personnel, Facilities (DOTML-PF) model as the primary logic construct. The report begins by providing a background of the Raven SUAV. to include its evolution from a COTS item to the Army’s SUAV of choice, and how it has impacted the warfighter. Next, the authors provide an overview of DOTML-PF in order to provide a basis for comparing doctrine and practice. The study then looks in-depth at doctrine and practice using DOTML-PF as the model for revealing differences between the two. Finally, the authors analyze these differences and recommend solutions to mitigate shortfalls in actual Raven SUAV usage on the battlefield. DTIC
Aircraft; Commercial Off-the-Shelf Products; Dichotomies; Pilotless Aircraft
20050196547 Stavatti Military Aerospace, Saint Paul, MN USA
A Business Overview & Summary of the SM-27S/T MACHETE RDT&E Program as Undertaken by the Military Aerospace/Tactical Air Warfare Systems Division of STAVATTI
Beskar, Christopher R.; Jun. 2005; 79 pp.; In English; Original contains color illustrations Report No.(s): AD-A435236; SD-87700-WS; No Copyright; Avail: Defense Technical Information Center (DTIC)
The SM-27 MACHETE is a next generation, COunter INsurgency (COIN), Light Attack (LA) and Advanced Trainer (AT) aircraft developed by STAVATTI as a privately financed, corporate initiative to replace OV-10 BRONCO, A-37 DRAGONFLY and OA-10A platforms in the COIN/FAC role. Marketed as a product for DCS, the SM-27 will be available for export to qualified NATO allies with IOC prior to 2009. This document provides a summary of the RDT&E program associated with the SM-27S/T turboprop variant of the MACHETE family, focusing upon principal aspects of system development including a platform, market, competition and engineering/prototype fabrication and flight test/qualification overview as undertaken by the Tactical Air Warfare Systems Division of STAVATTI MILITARY AEROSPACE. DTIC
Aerospace Systems; Aircraft Configurations; Commerce; Fighter Aircraft; Fixed Wings; Warfare
20050196563 NASA Glenn Research Center, Cleveland, OH, USA
Feasibility of Actively Cooled Silicon Nitride Airfoil for Turbine Applications Demonstrated
Bhatt, Ramakrishna T.; Research and Technology 2000; March 2001; 2 pp.; In English; Original contains black and white illustrations; No Copyright; Avail: CASI; A01, Hardcopy
Nickel-base superalloys currently limit gas turbine engine performance. Active cooling has extended the temperature range of service of nickel-base superalloys in current gas turbine engines, but the margin for further improvement appears modest. Therefore, significant advancements in materials technology are needed to raise turbine inlet temperatures above 2400 F to increase engine specific thrust and operating efficiency.
Because of their low density and high-temperature strength and thermal conductivity, in situ toughened silicon nitride ceramics have received a great deal of attention for cooled structures. However, the high processing costs and low impact resistance of silicon nitride ceramics have proven to be major obstacles for widespread applications. Advanced rapid prototyping technology in combination with conventional gel casting and sintering can reduce high processing costs and may offer an affordable manufacturing approach.
Researchers at the NASA Glenn Research Center, in cooperation with a local university and an aerospace company, are developing actively cooled and functionally graded ceramic structures. The objective of this program is to develop cost-effective manufacturing technology and experimental and analytical capabilities for environmentally stable, aerodynamically efficient, foreign-object-damageresistant, in situ toughened silicon nitride turbine nozzle vanes, and to test these vanes under simulated engine conditions.
Starting with computer aided design (CAD) files of an airfoil and a flat plate with internal cooling passages, the permanent and removable mold components for gel casting ceramic slips were made by stereolithography and Sanders machines, respectively. The gel-cast part was dried and sintered to final shape. Several in situ toughened silicon nitride generic airfoils with internal cooling passages have been fabricated. The uncoated and thermal barrier coated airfoils and flat plates were burner rig tested for 30 min without and with air cooling. Without cooling, the surface temperature of the flat plate reached approximately 2350 F. Starting with computer aided design (CAD) files of an airfoil and a flat plate with internal cooling passages, the permanent and removable mold components for gel casting ceramic slips were made by stereolithography and Sanders machines, respectively. The gel-cast part was dried and sintered to final shape.
Several in situ toughened silicon nitride generic airfoils with internal cooling passages have been fabricated. The uncoated and thermal barrier coated airfoils and flat plates were burner rig tested for 30 min without and with air cooling.Without cooling, the surface temperature of the flat plate reached approximately 2350 F. With cooling, the surface temperature decreased to approximately 1910 F--a drop of approximately 440 F.
This preliminary study demonstrates that a near-net-shape silicon nitride airfoil can be fabricated and that silicon nitride can sustain severe thermal shock and the thermal gradients induced by cooling and, thus, is a viable candidate for cooled components. Author
Airfoils; Fabrication; Gas Turbine Engines; Silicon Nitrides; Feasibility Analysis
20050196628 NASA Langley Research Center, Hampton, VA, USA
Proceedings of the 2004 NASA/ONR Circulation Control Workshop, Part 2
Jones, Gregory S., Editor; Joslin, Ronald D., Editor; June 2005; 520 pp.; In English; 2004 NASA/ONR Circulation Control Workshop, 16-17 Mar. 2004, Hampton, VA, USA; See also 20050196629 - 20050196646 Contract(s)/Grant(s): WU 23-762-55-ME Report No.(s): NASA/CP-2005-213509/PT2; L-18395B/PT2; No Copyright; Avail: CASI; A22, Hardcopy
This conference proceeding is comprised of papers that were presented at the NASA/ONR Circulation ControlWorkshop held 16-17 March 2004 at the Radisson-Hampton in Hampton, VA. Over two full days, 30 papers and 4 posters were presented with 110 scientists and engineers in attendance, representing 3 countries. As technological advances influence the efficiency and effectiveness of aerodynamic and hydrodynamic applications, designs, and operations, this workshop was intended to address the technologies, systems, challenges and successes specific to Coanda driven circulation control in aerodynamics and hydrodynamics.
A major goal of this workshop was to determine the state-of-the-art in circulation control and to assess the future directions and applications for circulation control. The 2004 workshop addressed applications, experiments, computations, and theories related to circulation control, emphasizing fundamental physics, systems analysis, and applied research. The workshop consisted of single session oral presentations, posters, and written papers that are documented in this unclassified conference proceeding.
The format of this written proceeding follows the agenda of the workshop. Each paper is followed with the presentation given at the workshop. the editors compiled brief summaries for each effort that is at the end of this proceeding. These summaries include the paper, oral presentation, and questions or comments that occurred during the workshop.
The 2004 Circulation Control Workshop focused on applications including Naval vehicles (Surface and Underwater vehicles), Fixed Wing Aviation (general aviation, commercial, cargo, and business aircraft); V/STOL platforms (helicopters, military aircraft, tilt rotors); propulsion systems (propellers, jet engines, gas turbines), and ground vehicles (automotive, trucks, and other); wind turbines, and other nontraditional applications (e.g., vacuum cleaner, ceiling fan). As part of the CFD focus area of the 2004 CC Workshop, CFD practitioners were invited to compute a two-dimensional benchmark problem for which geometry, flow conditions, grids, and experimental data were available before the workshop. The purpose was to accumulate a database of simulations for a single problem using a range of CFD codes, turbulence models, and grid strategies so as to expand knowledge of model performance/requirements and guide simulation of practical CC configurations. Derived from text
Computational Fluid Dynamics; Data Bases; Jet Engines; Propulsion System Configurations; Systems Analysis; V/STOL Aircraft
20050196630 AdvanTek International, LLC, Boothwyn, PA, USA
Low-Cost, High-Quality Wind Tunnel Testing of a 30 Percent Elliptical Circulation Control Airfoil at Low Blowing Levels for Application to Wind Turbines
Kelso, Frederick J.; Laubsch, Kenneth L.; Haraldsson, Rikard K.; Proceedings of the 2004 NASA/ONR Circulation Control Workshop, Part 2; June 2005, pp. 911-919; In English; See also 20050196628; Original contains color illustrations; No Copyright; Avail: CASI; A02, Hardcopy
Contents include the following: Motivation for wind tunnel testing. Expert team. Test matrix. Design, fabrication and instrumentation. Test results. Conclusion. Path forward. CASI
Wind Tunnel Tests; Circulation Control Airfoils; Design Analysis; Matrix Methods
20050196631 West Virginia Univ., Morgantown, WV, USA
Why Have Only Two Circulation-Controlled STOL Aircraft Been Built And Flown In Years 1974 - 2004
Loth, John L.; Proceedings of the 2004 NASA/ONR Circulation Control Workshop, Part 2; June 2005, pp. 603 - 640; In English; See also 20050196628; Original contains color and black and white illustrations; No Copyright; Avail: CASI; A03, Hardcopy
Circulation Control (CC) by Coanda blowing over a rounded trailing edge is by far the most blowing power efficient method for high lift generation. Only two CC aircraft have ever been build and flight-tested in the past 30 years. Why was one of the questions posed at the end of the 2004 ONR-NASA Circulation Control Workshop. Other high lift systems, such as the jet flap, upper surface blowing, augmenter wing and flap type thrust deflectors have found many applications on STOL aircraft. The two Circulation Control aircraft were the WVU CC Technology Demonstrator STOL flight-tested in 1974 and the Grumman A-6A flight-tested in 1979. This paper aims to provide some answers to that question. The design and construction of the WVU CC Technology Demonstrator STOL aircraft was completed in the period from 1971 to 1973. Starting on April 10, 1974, professional test pilot Shawn Roberts started 25 hours of flight-testing. Author
Upper Surface Blowing; Short Takeoff Aircraft; Trailing Edges; Wing Flaps; Circulation Control Airfoils; Coanda Effect
20050196632 Textron Bell Helicopter, USA
From Concept to Production of the Coanda Driven Exhaust Deflector for the V-22
Wood, T.; Proceedings of the 2004 NASA/ONR Circulation Control Workshop, Part 2; June 2005, pp. 771-789; In English; See also 20050196628; Original contains color illustrations; No Copyright; Avail: CASI; A03, Hardcopy
Contents include the following: Introduction. Need. Concept. Trade study. Ground testing. Production. CASI
V-22 Aircraft; Coanda Effect; Ground Tests
Source: NASA.
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