SIX-DEGREE-OF-FREEDOM FLIGHT PATH STUDY GENERALIZED COMPUTER PROGRAM. PART 1. VOLUME 2. STRUCTURAL LOADS FORMULATION
Rept. for June 1962-Dec 1963
MCDONNELL AIRCRAFT CORP ST LOUIS MO
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The equations of motion applicable to the Six-Degree-of-Freedom Structural Loads Program SLP are derived in this report. These equations are written for the determination of vehicle structural loads and response due to aerodynamic loads, loads due to control surface deflections, and environmental disturbances. Arbitrary elastic degrees of freedom wing bending, wing torsion, body bending, etc. and fuel slosh equations are incorporated into the overall analysis. Newtonian flow theory is used for obtaining idealized aerodynamic pressure distributions since it is the simplest aerodynamic theory that offers sufficient generality. Accelerations, deflections, shear forces and bending moments at arbitrary stations can be computed.
- Military Aircraft Operations