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Accession Number N20120014568
Title Flight Dynamics Modeling and Simulation of a Damaged Transport Aircraft.
Publication Date Aug 2012
Media Count 12p
Personal Author G. H. Shah M. A. Hill
Abstract 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.
Keywords 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


 
Source Agency National Aeronautics and Space Administration
NTIS Subject Category 51C - Aircraft
51F - Test Facilities & Equipment
Corporate Author National Aeronautics and Space Administration, Hampton, VA. Langley Research Center.
Document Type Conference proceedings
Title Note N/A
NTIS Issue Number 1308
Contract Number N/A

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