Linear optimum trim solution for aircraft with three longitudinal control effectorsA simple and fast linear optimum method for trimming aircraft with a combination of three longitudinal aerodynamic or propulsive control effectors is developed, with application to preliminary design or in-flight scheduling. A Lagrangian formulation is used to determine the longitudinal load distribution which minimizes trim drag. Trim drag results obtained with the linear optimum method are similar to those obtained with a nonlinear optimum method, and significant trim drag reductions are found using either optimum method, in comparison with results obtained using various ad hoc methods.
Document ID
19870063279
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Goodrich, Kenneth H. (NASA Langley Research Center Hampton, VA, United States)
Sliwa, Steven M. (NASA Langley Research Center Hampton, VA, United States)