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Accession Number
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N20120014568
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Title
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Flight Dynamics Modeling and Simulation of a Damaged Transport Aircraft.
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Publication Date
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Aug 2012
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Media Count
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12p
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Personal Author
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G. H. Shah M. A. Hill
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Abstract
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A study was undertaken at NASA Langley Research Center to establish, demonstrate, and apply methodology for modeling and implementing the aerodynamic effects of MANPADS damage to a transport aircraft into real-time flight simulation, and to demonstrate a preliminary capability of using such a simulation to conduct an assessment of aircraft survivability. Key findings from this study include: superpositioning of incremental aerodynamic characteristics to the baseline simulation aerodynamic model proved to be a simple and effective way of modeling damage effects; the primary effect of wing damage rolling moment asymmetry may limit minimum airspeed for adequate controllability, but this can be mitigated by the use of sideslip; combined effects of aerodynamics, control degradation, and thrust loss can result in significantly degraded controllability for a safe landing; and high landing speeds may be required to maintain adequate control if large excursions from the nominal approach path are allowed, but high-gain pilot control during landing can mitigate this risk.
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Keywords
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Air defense
Aircraft models
Airspeed
Controllability
Damage
Damping tests
Dynamic characteristics
Flight simulation
Landing speed
Portable equipment
Real time operation
Rolling moments
Sideslip
Transport aircraft
Wind tunnel tests
Wings
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Source Agency
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National Aeronautics and Space Administration
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NTIS Subject Category
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51C - Aircraft
51F - Test Facilities & Equipment
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Corporate Author
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National Aeronautics and Space Administration, Hampton, VA. Langley Research Center.
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Document Type
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Conference proceedings
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Title Note
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N/A
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NTIS Issue Number
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1308
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Contract Number
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N/A
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