SCIENTIFIC AND TECHNICAL AEROSPACE REPORTS
A Biweekly Publication of the National Aeronautics and Space Administration
VOLUME 43, ISSUE 19 - SEPTEMBER 23, 2005
05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE
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.
20050212114 NASA Langley Research Center, Hampton, VA, USA
An Overview of the Annual NASA Tire/Runway Friction Workshop and Lessons Learned
Yager, Thomas J.; [2005]; 6 pp.; In English; International Surface Friction Conference on Roads and Runways, 1-4 May 2005, Christchurch, New Zealand Contract(s)/Grant(s): 23-728-80-90; No Copyright; Avail: CASI; A02, Hardcopy
This paper summarizes the organization efforts, objectives, scope, agenda, test procedures and results from eleven years of conducting the NASA Tire/Runway Friction Workshop. The paper will also summarize the lessons learned between 1994 and 2004. A description of the various friction, texture and roughness equipment used during these workshops at NASA Wallops Flight Facility on the eastern shore of Virginia will be provided together with the range of test surfaces available for evaluation. The need for friction measuring equipment calibration centers is discussed and plans for future workshops are identified. Author
Surface Roughness; Runways; Friction; Tires; Textures; Calibrating; Pavements
20050212234 NASA Dryden Flight Research Center, Edwards, CA, USA
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Flight Test of the F/A-18 Active Aeroelastic Wing Airplane
Clarke, Robert; Allen, Michael J.; Dibley, Ryan P.; Gera, Joseph; Hodgkinson, John; August 28, 2005; 43 pp.; In English; AIAA Atmospheric Flight Mechanics Conference and Exhibit, 15-18 Aug. 2005, San Francisco, CA, USA Report No.(s): NASA/TM-2005-213664; H-2613; No Copyright; Avail: CASI; A03, Hardcopy
Successful flight-testing of the Active Aeroelastic Wing airplane was completed in March 2005. This program, which started in 1996, was a joint activity sponsored by NASA, Air Force Research Laboratory, and industry contractors. The test program contained two flight test phases conducted in early 2003 and early 2005. During the first phase of flight test, aerodynamic models and load models of the wing control surfaces and wing structure were developed. Design teams built new research control laws for the Active Aeroelastic Wing airplane using these flight-validated models; and throughout the final phase of flight test, these new control laws were demonstrated. The control laws were designed to optimize strategies for moving the wing control surfaces to maximize roll rates in the transonic and supersonic flight regimes. Control surface hinge moments and wing loads were constrained to remain within hydraulic and load limits. This paper describes briefly the flight control system architecture as well as the design approach used by Active AeroelasticWing project engineers to develop flight control system gains. Additionally, this paper presents flight test techniques and comparison between flight test results and predictions. Author
Aeroelasticity; Flight Control; Flight Tests; Aeroelastic Research Wings; Aircraft Control; Flight Characteristics; Aircraft Design
20050212251 Humansystems, Inc., Guelph, Ontario Canada
Modelling the Sea King Helicopter in the Integrated Performance Modelling Environment (IPME)
Lamoureux, T. M.; Bos, J. C.; Wall, G.; Jennings, D.; Mar. 2004; 61 pp.; In English; Original contains color illustrations Contract(s)/Grant(s): W7711-037859 Report No.(s): AD-A436400; DRDC-TORONTO-CR-2004-071; No Copyright; Avail: CASI; A04, Hardcopy
Defence Research and Development Canada (DRDC) Toronto contracted Humansystems Incorporated (HSI) to conduct a hierarchical goal analysis and construct a human performance model of pilot activities associated with the Sea King helicopter. In particular, DRDC Toronto wanted the human performance model to include activities surrounding Helicopter Deck Landing (HDL) aboard a Navy ship. Ultimately, this model would be used to control a simulated Sea King helicopter. The human performance modelling application used for this project was the Integrated Performance Modelling Environment (IPME). This report describes the output from the goal analysis, the mission used to bound’ the IPME modelling efforts, the data used to populate the IPME model, assumptions and approach used in the modelling effort, conclusions, and recommendations for follow-on work.With respect to the follow-on work, some suggestions are made regarding areas to focus on and approach to take. The IPME model of Sea King helicopter pilots forms a separate deliverable under this contract. DTIC
Helicopter Performance; Helicopters; Models; Pilots; SH-3 Helicopter
20050212256 Pennsylvania Univ., Philadelphia, PA USA
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Hybrid Modeling and Experimental Cooperative Control of Multiple Unmanned Aerial Vehicles
Bayraktar, Selcuk; Fainekos, Georgios E.; Pappas, George J.; Dec. 2004; 34 pp.; In English; Original contains color illustrations Contract(s)/Grant(s): DAAD19-02-1-0383; NSF-ITR-0324977 Report No.(s): AD-A436407; MS-CIS-04-32; No Copyright; Avail: Defense Technical Information Center (DTIC)
Recent years have seen rapidly growing interest in the development of networks of multiple unmanned aerial vehicles (UAVs), as aerial sensor networks for the purpose of coordinated monitoring, surveillance, and rapid emergency response. This has triggered a great deal of research in higher levels of planning and control, including collaborative sensing and exploration, synchronized motion planning, and formation or cooperative control. In this paper, we describe our recently developed experimental testbed at the University of Pennsylvania, which consists of multiple, fixed-wing UAVs. We describe the system architecture, software and hardware components, and overall system integration. We then derive high-fidelity models that are validated with hardware-in-the-loop simulations and actual experiments. Our models are hybrid, capturing not only the physical dynamics of the aircraft, but also the mode switching logic that supervises lower level controllers. We conclude with a description of cooperative control experiments involving two fixed-wing UAVs. DTIC
Control; Formation Flying; Pilotless Aircraft; Remotely Piloted Vehicles
20050212266 Artificial Intelligence Management and Development Corp., Toronto, Ontario Canada
A Generic, Agent-Based Framework for Design and Development of UAV/UCAV Control Systems
Edwards, Jack L.; Feb. 2004; 65 pp.; In English Report No.(s): AD-A436428; AIMDC-AC261; DRDC-TORONTO-CR-2004-062; No Copyright; Avail: CASI; A04, Hardcopy
Unmanned Air Vehicles (UAVs) and Unmanned Combat Air Vehicles (UCAVs) are being investigated for use as a new Integrated Intelligence, Surveillance, and Reconnaissance (IISR) platform within the Canadian Forces. At the moment UAV/UCAV control is operator intensive and can involve high levels of workload. In an effort to alleviate those conditions and reduce manning requirements, the current project examined a variety of theoretical approaches to construct a comprehensive, integrated approach to the design and implementation of an intelligent, adaptive, agent-based system for UAV/UCAV control. The resulting generic framework was constructed from the elements of the following design approaches: CommonKADS, MAS-CommonKADS, IDEF Standards, Explicit Models Design, Perceptual Control Theory and Ecological Interface Design. This report provides overviews of each of those approaches and highlights common and complementary elements as part of a recommended generic framework. A sequence for applying the generic framework is provided. The proposed integration of the above techniques into a comprehensive, cross-disciplinary design approach will help serve the goals of reducing operator workloads and manning requirements, while generating a robust, maintainable and reliable system. DTIC
Adaptive Control; Combat; Drone Vehicles; Reconnaissance Aircraft; Remotely Piloted Vehicles; Surveillance
20050212343 Massachusetts Inst. of Tech., Cambridge, MA USA
Behavioral Representation of Military Tactics for Single-Vehicle Autonomous Rotorcraft via Statecharts
Hickie, Mark M.; Jun. 2005; 116 pp.; In English; Original contains color illustrations Report No.(s): AD-A436599; No Copyright; Avail: CASI; A06, Hardcopy
Over the past several years, aerospace companies have developed unmanned helicopters suitable for integration into military operations as reconnaissance platforms. These rotorcraft, however, require ground-based human controllers varying in number based on the size and complexity of the system controlled. The automation these platforms have achieved is limited to takeoffs, landings and navigation of pre-programmed waypoints. The possibilities for further development then are vast; with growing sensor and communication capabilities, there exists potential for unmanned rotorcraft to execute the full range of aviation missions normally reserved for manned assets. However, before military planners use autonomous helicopters as robust force multipliers, research must attempt to quantify possible tactics for software architecture implementation. DTIC
Autonomy; Helicopters; Military Operations; Rotary Wing Aircraft; Tactics
20050212347 Massachusetts Inst. of Tech., Cambridge, MA USA
Trajectory Optimization With Detection Avoidance for Visually Identifying an Aircraft
Wholey, Leonard N.; Jun. 2005; 119 pp.; In English Report No.(s): AD-A436607; No Copyright; Avail: CASI; A06, Hardcopy
Unmanned aerial vehicles (UAVs) play an essential role for the US Armed Forces by performing missions deemed as ‘dull, dirty, and dangerous’ for a pilot. As the capability of UAVs expand, they will perform a broader range of missions such as air-to-air combat. The focus of this thesis is forming trajectories for the closing phase of an air-to-air combat scenario. A UAV should close with the suspected aircraft in a manner that allows a ground operator to visually identify the suspected aircraft while avoiding visual/ electronic detection from the other pilot. This thesis applies and compares three methods for producing trajectories which enable a visual identification. The first approach is formulated as a mixed integer linear programming problem which can be solved in real time. However, there are limitations to the accuracy of a radar detection model formed with only linear equations, which might justify using a nonlinear programming formulation.With this approach the interceptor’s radar cross section and range between the suspected aircraft and interceptor can be incorporated into the problem formulation. The main limitation of this method is that the optimization software might not be able to reach online an optimal or even feasible solution. The third applied method is trajectory interpolation. DTIC
Aircraft; Detection; Identifying; Trajectories; Trajectory Optimization
20050212371 Army Command and General Staff Coll., Fort Leavenworth, KS USA
The Challenges Affecting Heavy Lift Aircraft Development to Support Sea Basing
Glathar, Kevin D.; Jun. 2005; 130 pp.; In English; Original contains color illustrations Report No.(s): AD-A436672; No Copyright; Avail: CASI; A07, Hardcopy
This thesis examines several successful and unsuccessful military aircraft development programs that serve as a basis for identifying potential challenges that might be encountered by developers of the heavy lift aircraft required to support the sea basing concept. In the wake of 11 September 2001, the U.S. Armed Services began adapting to meet the challenges of a changing global environment. An enhanced sea-basing capability was one solution. The sea-basing concept is focused on eliminating traditional nodes required ashore to support operational maneuver from the sea. An enhanced sea-basing capability is laden with several issues that must be addressed before it can be developed, especially development of new maritime aviation assets. In August 2003, the DoD-directed Defense Science Board Task Force on Sea Basing identified 12 ‘dirty dozen’ issues, three of which were critical. The development of a heavy lift aircraft capability to support sea basing was one of those critical issues. The conclusions reached in this thesis are that design approach, funding, organization, silver bullet theory, vision, technology, and politics are the most prevalent factors that could effect the timely development of heavy lift aircraft to support sea basing. DTIC
Aircraft Design; Budgeting; Seas
20050212412 Colorado Univ., Denver, CO USA
On the Convergence of a Dual-Primal Substructuring Method
Mandel, Jan; Tezaur, Radek; Jan. 2000; 13 pp.; In English Contract(s)/Grant(s): N00014-95-1-0663; NSF-ECS-9725504 Report No.(s): AD-A436826; No Copyright; Avail: CASI; A03, Hardcopy
In the Dual-Primal FETI method, introduced by Farhat et al., the domain is decomposed into non-overlapping subdomains, but the degrees of freedom on crosspoints remain common to all subdomains adjacent to the crosspoint. The continuity of the remaining degrees of freedom on subdomain interfaces is enforced by Lagrange multipliers and all degrees of freedom are eliminated. The resulting dual problem is solved by preconditioned conjugate gradients. We give an algebraic bound on the condition number, assuming only a single inequality in discrete norms, and use the algebraic bound to show that the condition number is bounded by C(1+log2(H/h)) for both second and fourth order elliptic self-adjoint problems discretized by conforming finite elements, as well as for a wide class of finite elements for the Reissner-Mindlin plate model. DTIC
Boundary Value Problems; Convergence; Finite Element Method; Substructures; Tearing
20050214051 NASA Langley Research Center, Hampton, VA, USA
Computational Fluid Dynamics (CFD) Design of a Blended Wing Body (BWB) with Boundary Layer Ingestion (BLI) Nacelles
Morehouse, Melissa B.; NASA Glenn Research Center UEET (Ultra-Efficient Engine Technology) Program: Agenda and Abstracts; [2001], pp. 42; In English; See also 20050214031; No Copyright; Abstract Only; Available from CASI only as part of the entire parent document
A study is being conducted to improve the propulsion/airframe integration for the Blended Wing-Body (BWB) configuration with boundary layer ingestion nacelles. TWO unstructured grid flow solvers, USM3D and FUN3D, have been coupled with different design methods and are being used to redesign the aft wing region and the nacelles to reduce drag and flow separation. An initial study comparing analyses from these two flow solvers against data from a wind tunnel test as well as predictions from the OVERFLOW structured grid code for a BWB without nacelles has been completed. Results indicate that the unstructured grid codes are sufficiently accurate for use in design. Results from the BWB design study will be presented. Author
Nacelles; Computational Fluid Dynamics; Boundary Layer Separation; Systems Integration; Drag Reduction; Engine Airframe Integration; Blended-Wing-Body Configurations
20050214417 NASA Glenn Research Center, Cleveland, OH, USA
Ultra-Efficient Engine Technology Project Continued to Contribute to Breakthrough Technologies
Shaw, Robert J.; Research and Technology 2002; March 2003; 3 pp.; In English; No Copyright; Avail: CASI; A01, Hardcopy
The International Civil Aviation Organization (ICAO), the U.S. Environmental Protection Agency (EPA), local environmental groups, and the public have become increasingly concerned over damage to local air quality from aircraft emissions and the impact of producing greenhouse gases. The NASA Glenn Research Center has been working to develop revolutionary technologies to minimize environmentally harmful engine emissions, such as nitrogen oxides, carbon dioxide, aerosols, and particulates. The two objectives of UEET are (1) to develop technologies to reduce nitrogen oxide (NOx) emissions by 70 percent below 1996 ICAO regulations and (2) to decrease carbon dioxide emissions (CO2) by dramatically increasing performance and efficiency. High temperature engine materials, ultra-low-NOx combustor designs, efficient, highly loaded turbomachinery, and propulsion-airframe integration analysis are technologies being developed at Glenn to meet these goals. Technology developed in the previous Advanced Subsonic Technology Program is being put into commercial production for large and regional aircraft to reduce NOx emissions 50 percent below 1996 ICAO regulations for landing and takeoff cycles. UEET will take the technology to the next quantum leap-reducing emissions to 70 percent below the ICAO regulations level. In addition, NASA-developed research will significantly reduce carbon monoxide, unburned hydrocarbons, and corresponding cruise NOx levels for the next generation of aircraft engines. Glenn’s UEET research will be useful across the whole range of flight: subsonic, supersonic, and hypersonic. It will improve the subsonic transportation that the public depends on, contribute to supersonic commercial aircraft, improve military aircraft, and contribute to the design of a future hypersonic vehicle. These technologies are contributing to a better quality of life on Earth. Derived from text
Environment Protection; Aircraft Design; Engine Design
20050214477 Defence Science and Technology Organisation, Fishermans Bend, Australia
Review of Black Hawk Structural Upgrade Options and Recommendations for the Australian Defence Force
Dore, Christopher; April 2005; 177 pp.; In English Report No.(s): DSTO-TN-0622; DODA-AR-013-366; Copyright; Avail: Other Sources
In the initial design of the UH-60A Black Hawk helicopter fuselage, fatigue was not specified as a design criterion. Consequently, fatigue failures are being observed within the worldwide UH-60 family that challenge the service life of the aircraft. The Original Equipment Manufacturer, Sikorsky Aircraft Corporation, ha designed modification kits as part of a US Army ‘A to A’ Recapitalization program to address the most critical fatigue concerns. This report conducts a review of the currently available options for structural upgrades to the Black Hawk aircraft and makes recommendations as to which kits would be appropriate for the Australian Defence Force’s S-70A-9 fleet. Author
Australia; UH-60A Helicopter; Helicopter Design; Fuselages; Armed Forces (Foreign)
Source: NASA.
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