3 edition of Design-of-experiments to reduce life-cycle costs in combat aircraft inlets found in the catalog.
Design-of-experiments to reduce life-cycle costs in combat aircraft inlets
2003 by National Aeronautics and Space Administration, Glenn Research Center, Available from NASA Center for AeroSpace Information in [Cleveland, Ohio], Hanover MD .
Written in English
|Other titles||Design of experiments to reduce life cycle costs in combat aircraft inlets.|
|Statement||Bernhard H. Anderson, Henry D. Baust, [and] Johan Agrell.|
|Series||NASA/TM -- 2003-212017., NASA technical memorandum -- 212017.|
|Contributions||Baust, Henry D., Agrell, Johan., NASA Glenn Research Center.|
|The Physical Object|
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Design-of-experiments to reduce life-cycle costs in combat aircraft inlets] (OCoLC) Online version: Anderson, Bernhard H. Design-of-experiments to reduce life-cycle costs in combat aircraft inlets (OCoLC) Material Type: Government publication, National government publication, Internet resource: Document Type: Book, Internet.
Design-of-experiments to reduce life-cycle costs in combat aircraft inlets] (OCoLC) Microfiche version: Anderson, Bernhard H.
Design-of-experiments to reduce life-cycle costs in combat aircraft inlets (OCoLC) Material Type: Document, Government publication, National government publication, Internet Design-of-experiments to reduce life-cycle costs in combat aircraft inlets book Document Type.
Considerations in the Measurement of Inlet Distortion for High Cycle Fatigue in Compact Inlet Diffusers Design-of-Experiments to Reduce Life-Cycle Costs in Combat Aircraft Inlets.
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Increasing performance requirements and economical pressure to reduce aircraft Direct Operational Costs can no longer be met by traditional design processes. In particular, the impact of aeroelastic effects on aircraft design demands the use of multidisciplinary design concepts and optimization (MDO.
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The CJ has a length of 98 ft, wingspan of feet, and a height of 39 ft. The aircraft has four turboprop engines and a service altitude of 28, ft. The aircraft features traditional built-up aluminum construction.
These per-plane costs, large though they may be, pale beside the development costs of a new aircraft. The recently-let System Design & Development contract for the F Joint Strike fighter is officially given as $19 bill and that does not include the billions spent on closely related technology developments in recent years.
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Decisions made at the early stages of the development life cycle will have a significant impact on the overall life cycle, including the cost incurred and the effectiveness of the system. Therefore, a disciplined approach to integrated design and the development of new systems is required.
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A parallel discussion of air platforms would highlight many of the same issues, or challenges, for flow and noise control Cited by: NR 1 TC 0 Z9 0 U1 0 U2 0 PU SOC MILITARY HISTORY PI LEXINGTON PA C/O VIRGINIA MILITARY INST, GEORGE C MARSHALL LIBRARY, LEXINGTON, VA USA SN J9 J MILITARY HIST JI J.
Mil. Hist. PD APR PY VL 77 IS 2 BP EP PG 2 WC History SC History GA GN UT WOS ER PT J AU Grau, LW AF. Advantages and disadvantages of the safety analysis techniques described are discussed.
Keywords: Qualitative analysis, quantitative analysis, safety analysis techniques. Introduction. Reliability and safety analyses are different concepts that have a 5/5(2).
Aeroelasticity Aeroelasticity is the science which studies the interaction among inertial, elastic, and aerodynamic forces. It was defined by Collar in as "the study of the mutual interaction that takes place within the triangle of the inertial, elastic, and aerodynamic forces acting on structural members exposed to an airstream, and the influence of this study on design.".
For a subsonic aircraft, the optimal design, that is the airframe-engine combination, is obtained by the simulation. The aircraft is powered by two high-bypass-ratio engines with a nominal thrust of ab lbf.
It is to carry passengers at a cruise speed of Mach over a range of n mi and to operate on a ft runway.1/5(1). While there are fewer commercial aircraft flying today with turbojet engines, supersonic aircraft including high performance military aircraft use engines with similar exhaust flow characteristics.
The Pratt & Whitney FPW, pictured in Figure la, is an example of an engine that powers the F and F fighter jets. Free essays, homework help, flashcards, research papers, book reports, term papers, history, science, politics.
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The capacity for such self-adjusting behavior means that aircraft wings, traditionally designed with high rigidity in order to withstand the normal stresses caused by wind gust, can be less inherently stiff.
Further, the use of GLA facilitates lighter wing structures and, in turn, reduced fuel consumption and increased range. The book begins with a discussion of the principles and design of TCP/IP Protocols from the data networks perspective and continues with a detailed look at the vulnerabilities thus introduced in the network design process and concludes with advanced level experiments that show how these vulnerabilities can be easily exploited and offers.
Advanced stress analysis methods applicable to turbine engine structures. NASA Technical Reports Server (NTRS) Pian, T.
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In this paper, the influence of printing process planning on the width of printed rods for a copper ink is analyzed by means of a Design of Experiments procedure to optimize the printing and equipment parameters and characterize the shrinkage after the sintering process TI - Analysis of printing parameters for metal additive manufactured parts.
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