Coordinate Stabilization for a Flexible Aircraft during Flight in a Turbulent Atmosphere,
Abstract
The problem is considered of automatically controlling aircraft altitude and pitch angle in the duck system. The aircraft dynamics is described by a system of linear differential equations with constant coefficients: three equations of motion of the center of gravity and rotation of the aircraft as a solid body, and a combination of equations for the flexible oscillations of an elastic fuselage in the plane of longitudinal symmetry. It is assumed that the autopilot acts on the flaps in changing the pitch and attack angles, the generalized coordinates characterizing the bending oscillations of the fuselage, and the nose controlling surface, as well as in changing the slope of the trajectory. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 08, 1972
- Accession Number
- AD0751148
Entities
People
- V. V. Udilov
Organizations
- National Air and Space Intelligence Center