SCIENTIFIC AND TECHNICAL AEROSPACE REPORTS
A Biweekly Publication of the National Aeronautics and Space Administration
VOLUME 44, ISSUE 9 - MAY 5, 2006
01 AERONAUTICS (GENERAL)
Includes general research topics related to manned and unmanned aircraft and the problems of flight within the Earth's atmosphere.
Also includes manufacturing, maintenance, and repair of aircraft.
For specific topics in aeronautics, see categories 02 through 09.
For information related to space vehicles see 12 Astronautics.
20060011223 Aerospace Industries Association, Arlington, VA, USA
Guidelines to Minimize Manufacturing Induced Anomalies in Critical Rotating Parts
Feb. 2006; 86 pp.; In English Report No.(s): PB2006-107475; No Copyright; Avail.: CASI: A05, Hardcopy
This report was developed by a partnership of the Aerospace Industries Association (AIA) Rotor Manufacturing Project Team (RoMan) and the Federal Aviation Administration in response to accidents and incidents caused by manufacturing induced anomalies in critical rotating parts. According to a 1997 summary from the AIA Rotor Integrity Sub-Committee, about 25% of recent rotor cracks/events have been caused by post-forging manufacturing induced anomalies. The guidelines contained herein represent an industry consensus on the currently available best practices to minimize manufacturing induced anomalies in critical rotating parts consistent with the AIA RoMan team charter and vision. Recommendations for nominal rotor manufacturing process development and control, including process validation, quality assurance, disposition of suspect parts, process monitoring, human factors and training, and non-destructive evaluation, are included to provide an overall framework for a highly reliable manufacturing process. Because critical rotating part reliability has demonstrated particular sensitivity to hole machining practices, specific recommendations for hole making are included. In addition, a section containing industry lessons learned is included to provide guidance on issues common in the industry. NTIS
Aerospace Industry; Anomalies; Manufacturing; Rotation
20060011345 NASA Dryden Flight Research Center, Edwards, CA, USA
| |
| Tools for Aviation/Aerospace |
| IHS sells products and services designed to meet the needs of today's engineers. To learn more, and for a free quote, please complete the form below. |
|
Photogrammetric Trajectory Estimation of Foam Debris Ejected From an F-15 Aircraft
Smith, Mark S.; April 2006; 29 pp.; In English; Original contains color and black and white illustrations Report No.(s): NASA/TM-2006-213675; H-2635; No Copyright; Avail.: CASI: A03, Hardcopy
Photogrammetric analysis of high-speed digital video data was performed to estimate trajectories of foam debris ejected from an F-15B aircraft. This work was part of a flight test effort to study the transport properties of insulating foam shed by the Space Shuttle external tank during ascent. The conical frustum-shaped pieces of debris, called 'divots,' were ejected from a flight test fixture mounted underneath the F-15B aircraft. Two onboard cameras gathered digital video data at two thousand frames per second. Time histories of divot positions were determined from the videos post flight using standard photogrammetry techniques. Divot velocities were estimated by differentiating these positions with respect to time. Time histories of divot rotations were estimated using four points on the divot face. Estimated divot position, rotation, and Mach number for selected cases are presented. Uncertainty in the results is discussed. Author
Photogrammetry; Debris; F-15 Aircraft; High Speed; Cameras; Trajectories; Digital Television; Foams; Flight Tests
20060011579 Research and Technology Organization, Neuilly-sur-Seine, France
Flight Test: Sharing Knowledge and Experience
May 2005; In English; Systems Concepts and Integration Panel (SCI) Symposium, 9-11 May 2005, Warsaw, Poland; See also 20060011580 - 20060011604; Original contains color and black and white illustrations Report No.(s): RTO-MP-SCI-162; AC/323(SCI-162)TP/83; Copyright; Avail.: CASI: C01, CD-ROM
This broad-scope symposium was jointly sponsored by NATOs Research and Technology Organization s (RTO), Systems Concepts and Integration Panel (SCI), and the Society of Flight Test Engineers, European Chapter (SFTE (EC)). The symposium, hosted by the Polish National Delegates of the RTO at the Ministry of Defense Conference Centre, Warsaw, was the first NATO symposium since the mid 1990s to deal comprehensively with aircraft flight test and evaluation, and the first SCI symposium to be conducted jointly with an organization outside of NATO. The symposium theme was the sharing of flight-test related information between the international community with a purpose of improving flight test practices worldwide. The Technical Programme Committee, chaired by Barbara Wood a former SFTE (EC) President and member of SCI-Flight Test Technologies Task Group (FT3), comprised senior specialists representing the international flight test community. Significantly all were members of the SFTE (EC) Board and/or members of FT3. Three Keynote Addresses and 22 papers, presented by speakers representing many of the primary NATO-country aircraft test and development organizations, addressed up-to-date experience from test program operations, program overviews, test methods, and test facilities and instrumentation. The Technical Evaluation Report summarizes significant developments in aircraft test and evaluation (T&E), considerations for the NATO and flight test communities and lessons learned from recent flight test participants. The Symposium was introduced by Mr. J. Wickes, SCI Panel Chairman, and Mr. K. Karlsson, SFTE (EC) President. Keynote Addresses: Polish Aviation History by A. Witczak, T&E in a Multi-National Programme (Eurofighter) by L. Hilditch and The Joint Strike Fighter An International Enterprise by P. Metz. Derived from text
Flight Tests; System Effectiveness; Fighter Aircraft; Engineers; Test Facilities
20060011584 Defence Materiel Administration, Linkoping, Sweden
| |
| Aerospace Engineering Design |
| ESDU packages provide validated design data, methods and software, offering a valuable toolset to aerospace engineers. To learn more, and for a free quote, please complete the form below. |
|
The Flight of Phoenix
Flight Test: Sharing Knowledge and Experience; May 2005, pp. 17-1 - 17-8; In English; See also 20060011579; Original contains color illustrations; Copyright; Avail.: CASI: A02, Hardcopy; Available from CASI on CD-ROM only as part of the entire parent document
During spring 2000, North European Aerospace Test Range (NEAT) started discussions with EADS Space Transportation at Bremen, Germany on how to carry out flight tests on a functional scaled down model (Phoenix) of a future Reusable launch vehicle (RLV/Hopper). The ultimate goal for EADS ST was to verify the performance of the Phoenix test vehicle including its flight control and navigation systems etc, by auto landing on the runway at the FMV Vidsel test site. The way ahead to perform all necessary design, test qualification activities to guarantee airworthiness, performance, safety, quality etc to perform the task within a flight test organization, earlier reduced in capacity by economic demands, is described. The performance included design and verification of a system including necessary test data instrumentation, capable of carrying the 1200 kg Phoenix test vehicle to the release point at app. 5 km from the runway threshold to auto land. The presentation will also show that collaboration between different organisations within and outside the responsible test organization can be used to fulfill a task and lead to a successfully completed mission. Three flights were performed with the Phoenix test vehicle, all with successful landings with roll out on the runway centre line. Author
Reusable Launch Vehicles; Test Vehicles; Navigation; Flight Control; Flight Tests
20060011588 Naval Air Systems Command, Patuxent River, MD, USA
Technical Evaluation Report
Detrick, Roger; Flight Test: Sharing Knowledge and Experience; May 2005, pp. T-1 - T-17; In English; See also 20060011579; Copyright; Avail.: CASI: A03, Hardcopy; Available from CASI on CD-ROM only as part of the entire parent document
This broad-scope, flight-test symposium was jointly sponsored by NATO s Research and Technology Organization (RTO), Systems Concepts and Integration Panel (SCI), and the Society of Flight Test Engineers, European Chapter (SFTE(EC)). The SFTE (www.sfte.org) is a fraternity of engineers and associates, whose principal professional interest is the flight testing of aircraft, fixed and rotary wing, and missiles. The objective of the Society is the advancement of flight test engineering throughout the aircraft industry by providing technical and fraternal communication among individuals, both domestic and international, in the allied engineering fields of test operations, analysis, instrumentation and data systems. The symposium, hosted by the Polish National Delegates of the RTO at the Ministry of Defence Conference Centre, Warsaw, was an unclassified event with participants from 24 countries. This was the first NATO symposium since the formation of RTO to deal comprehensively with aircraft flight test and evaluation (T&E), and the first SCI symposium to be conducted jointly with an organization outside of NATO. Two previous SCI symposiums included significant aspects of flight test: 'Integration of Simulation With Systems Testing,' October 01, Toulouse, FR and 'Aircraft-Stores Certification Testing,' September 98, Chester, UK. The last NATO symposium to broadly review international flight testing was conducted by AGARD in Norway in the mid 90's. The symposium was developed and conducted, in partnership with SFTE(EC) and the RTO Research and Technology Agency, by the SCI Panel s Flight Test Technologies task group (SCI-172, FT3). The FT3 mission (which was well matched to the symposium) is to: (1) disseminate information through publication of AGARDographs on flight test technology derived from best practices which support the development of concepts and systems critical to maintaining NATO s technological and operational superiority; (2) enable advancements in flight test technologies to be discussed in open forum within the NATO community by identifying and distributing flight test training opportunities, and through proposing and facilitating symposia, short courses, lecture series, etc., and (3) serve as the focal point for flight test subjects and issues with the SCI Panel while ensuring the vitality and continuity of the network of flight test experts within the NATO community. Derived from text
Flight Tests; Flight Simulation; Data Systems; System Effectiveness; Rotary Wings
20060011589 Military Univ. of Technology, Warsaw, Poland
Polish Aviation Engineering: Past, Present and Future
Trebinski, Radoslaw; Zalewski, Piotr; Flight Test: Sharing Knowledge and Experience; May 2005, pp. KN1-1 - KN1-8; In English; See also 20060011579; Original contains color and black and white illustrations; Copyright; Avail.: CASI: A02, Hardcopy; Available from CASI on CD-ROM only as part of the entire parent document
The paper presents the history and present status of the Polish aviation engineering. The authors discus the development and evaluation of the Polish aviation concept and its impact on the domestic and international industry. Before and after the WWII Polish aviation sector belonged to the leaders of the world market, unfortunately after the fall of the Berlin wall industry experienced a deep crisis. The market of former Warsaw Pact was shrunk significantly, and number of orders for new aircraft have dropped dramatically. However, thanks to proper experience and knowledge of the Polish aviation engineers, new opportunities for the domestic aviation sector have emerged recently. Author
Aircraft Industry; Poland; Military Operations; Aeronautical Engineering
20060011590 Lockheed Martin Aeronautics Co., Fort Worth, TX, USA
The Joint Strike Fighter: An International Enterprise
Metz, Paul; Flight Test: Sharing Knowledge and Experience; May 2005, pp. KN3-1 - KN3-8; In English; See also 20060011579; Original contains color and black and white illustrations; Copyright; Avail.: CASI: A02, Hardcopy; Available from CASI on CD-ROM only as part of the entire parent document
From the beginnings of flight to the present, there have been international aircraft programs undertaken by most of the countries represented in this room. Those programs were frequently co-assembly or coproduction efforts in which the purchasing country manufactured an existing aircraft using production tools and techniques from the country of origin. In the last 40 years, we have seen a number of true collaborative efforts to design and develop an entirely new aircraft using the intellectual capital from two or more countries. Europe has been a key leader in these programs with the Jaguar, Tornado and Eurofighter on the military side and the spectacular success of the Airbus consortium on the civil side. While the USA has engaged in numerous co-assembly and co-production dating back to World War II, it has been only recently that we have engaged in co-development efforts similar to the European ventures of the 1960s and 70s. The F-35 Joint Strike Fighter is the largest single multi-company aircraft development program ever attempted in the U.S. and, indeed, in the world. At present, there are nine partner nations actively involved in the design and development of this next-generation fighter. This massive undertaking is not without it challenges a popular euphemism for difficult and perplexing but there are also some very bright spots and reasons for optimism. Let me show you the construct of this program, what we intend to build and, most importantly, what it promises for all of the partner countries sharing in this massive enterprise. Author
Fighter Aircraft; Aircraft Design; International Cooperation
20060011591 Saab Aerospace, Sweden
Flight Test Verification of a Wake Vortices Model
Lampe, thomas; Sedin, Yngve; Weinerfelt, Per; Flight Test: Sharing Knowledge and Experience; May 2005, pp. 4-1 - 4-16; In English; See also 20060011579; Original contains color and black and white illustrations; Copyright; Avail.: CASI: A03, Hardcopy; Available from CASI on CD-ROM only as part of the entire parent document
A simulation model for encounters of wake vortices has been developed at Saab in Link ping, Sweden. Distribution of incremental forces on the aircraft surfaces is calculated for different locations related to the vortices and also for different relative attitudes of the aircraft. Also, the response of the angle-of-attack and angle-of-sideslip vanes is calculated. For simulation, multidimensional tables are created describing the increments in forces, moments and vane angles as function of relative position and attitude. The model, represented by table lookup algorithms for these particular tables as well as some scaling algorithms, was in the year 2000 added to an experimental version of a 6-DOF Gripen simulator. The results seemed promising because the response of the aircraft flying through the vortices was, seen from a pilot s view, realistic. However, it was evident that the model also needed to be verified with and, most likely, adjusted (scaled) to flight test data. The need for accurate estimates of the aircraft s trajectory through the vortices requires special attention. Regardless of the ability to accomplish that accuracy in relative position between two aircraft, we still have to determine, also very accurately, where the vortices are, regarding cores and size. Local wind fluctuations and the self-induced motion of the vortices away from the flight path contribute with uncertainties in the range of a couple of meters. From that standpoint, we have too large uncertainties. Our best solution so far is to use a 'closed-loop' verification of the model where we use a subset of the output parameters to identify a two-dimensional position bias that gives us the most likely trajectory. We use the angle-of-attack and angle-of-sideslip vane signals for that purpose. The result is not only a method for verification of a trailing vortex simulation model but also a tool to map out in detail where we have been in wake vortex penetration tests.With respect to the simplifying assumptions used in the design of the current model, the agreement with flight test data is surprisingly good. Author
Vortices; Wakes; Flight Tests; Angle of Attack; Attitude (Inclination); Sideslip; Proving; Flight Paths
20060011595 Naval Air Warfare Center, Patuxent River, MD, USA
Ship Suitability Testing: Preparing for the Future
Harney, Ronald J.; Flight Test: Sharing Knowledge and Experience; May 2005, pp. 7-1 - 7-13; In English; See also 20060011579; Original contains color and black and white illustrations; Copyright; Avail.: CASI: A03, Hardcopy; Available from CASI on CD-ROM only as part of the entire parent document
In support of the USA Navy Sea Power 21 initiative, ship suitability test and evaluation personnel are preparing to support a large number of test and evaluation programs. The pillars of Sea Power 21, which include Sea Basing, Sea Shield, and Sea Strike call for a diverse set of new and modified aircraft and air capable ships. Ship compatibility testing may be required on aircraft ranging from the two variants of the Joint Strike Fighter to the Firescout unmanned helicopter; and from C-130 cargo aircraft to small unmanned seaplanes. Additionally, aircraft compatibility testing will be required on ships ranging from the Littoral Combat Ship to the DDX destroyer, and from a new amphibious assault ship to the latest in nuclear carrier technology, CVN-21, which will incorporate all new electric catapult and arresting gear equipment. The precision approach landing systems group is already testing enabling technologies for a new GPS-based Joint Precision Approach and Landing System, which will significantly change the air traffic control environment, enable all aircraft to have precision approach capability, and provide the means to operate fighter-sized Unmanned Combat Air Vehicles on aircraft carriers. These aircraft/ship test and evaluation programs will require the development of new methodology. They will also require the testers to research and modify test techniques that have not been used for decades. We are also challenged to seek methods to minimize testing requirements and manpower while still giving the Fleet operator the maximum possible safe operating envelope. From rotary wing to tilt rotor to fixed wing aircraft and from hydroplanes to catamarans to the super carriers, the ship suitability test and evaluation group will be responsible for testing aircraft/ship compatibility in a highly dynamic and challenging environment. This presentation will provide a brief overview of the upcoming programs and discuss the test and evaluation challenges. Author
Ships; Aircraft Configurations; System Effectiveness; Landing Aids; Global Positioning System; Cargo Aircraft; C-130 Aircraft; Helicopters; Seaplanes
20060011597 European Aeronautic Defence and Space Co., Germany
Introduction of a Workflow Tool in Support of Information Management within a Flight Test Organization
Oelker, Hans-Christoph; Flight Test: Sharing Knowledge and Experience; May 2005, pp. 24-1 - 24-16; In English; See also 20060011579; Original contains color and black and white illustrations; Copyright; Avail.: CASI: A03, Hardcopy; Available from CASI on CD-ROM only as part of the entire parent document
The challenges of changing markets have an impact on a flight test organization typically orientated at military aircraft as well. To cope with these challenges at EADS Military Aircraft Flight Test a workflow tool in support of process enhancements and refinements was introduced. In the present paper an overview about resulting activities at EADS Military Aircraft Flight Test Centre is given. The project was executed in a stepped approach with a process analysis through external consultancies in the beginning, introduction of a workflow tool for the flight test backbone process as second step, and possibilities to further integrate process elements as future options. Within the backbone process Test Task issue, Fight Test Programme, and Flight Card generation were considered. Flight Test specific aircraft configuration control was established as a necessary supporting process. The tool is realised with state of the art software technology (common data base system with WEB technology user interface) in order to provide maximum flexibility (incorporation of different engineering programmes, maintenance efficiency) and tool support independently of testing location. Overall process experience is positive. Process enhancements are clearly visible and transparency of process know-how will make past experiences easily accessible for future projects. It will be achieved through continuous utilisation of the workflow tool and continuous storing of facts and experience. Thus, powerful means of information management to share knowledge and experience are provided to a Flight Test organization. Author
Information Management; Configuration Management; Software Engineering; Flight Tests; Data Bases; Aircraft Control
20060012145 NASA Langley Research Center, Hampton, VA, USA
CFL3D Version 6.4-General Usage and Aeroelastic Analysis
Bartels, Robert E.; Rumsey, Christopher L.; Biedron, Robert T.; April 2006; 269 pp.; In English; Original contains color illustrations Contract(s)/Grant(s): 98-47-54 Report No.(s): NASA/TM-2006-214301; L-19247; No Copyright; Avail.: CASI: A12, Hardcopy
This document contains the course notes on the computational fluid dynamics code CFL3D version 6.4. It is intended to provide from basic to advanced users the information necessary to successfully use the code for a broad range of cases. Much of the course covers capability that has been a part of previous versions of the code, with material compiled from a CFL3D v5.0 manual and from the CFL3D v6 web site prior to the current release. This part of the material is presented to users of the code not familiar with computational fluid dynamics. There is new capability in CFL3D version 6.4 presented here that has not previously been published. There are also outdated features no longer used or recommended in recent releases of the code. The information offered here supersedes earlier manuals and updates outdated usage. Where current usage supersedes older versions, notation of that is made. These course notes also provides hints for usage, code installation and examples not found elsewhere. Author
Aeroelasticity; Computational Fluid Dynamics; User Manuals (Computer Programs)
Source: NASA
|
IHS sells products and services designed to meet the needs of today's aviation & aerospace engineers, including:
- Quick access to FAA, JAA, ICAO and UK-CAA information and regulations.
- Validated engineering methods, data, principles, worked examples, programs and related equations on over 1340 specific aerospace, process, structural and mechanical engineering topics.
- The IHS Fasteners eCatalog, providing decision support for the identification, specification and sourcing of aerospace & defense standard fasteners/hardware such as bolts, screws, nuts, washers, rivets, studs, etc.
- Standards documents and collections from the top aerospace & aviation standards development organizations, including SAE International, AIAA, AIA, FAA and NASA.
|