Spectral Gust Response for an Airplane with Vertical Motion and Pitch
Abstract
Gust response analysis based upon power spectral techniques is made for an airplane having the two degree of freedom of vertical motion and pitch. A rather unique formulation of the equations of motion is made, wherein the aerodynamic loads are treated as dependent variables, as are the vertical and pitching motions. Nonsteady lift effects, finite span effects, tail downwash effects, and gust lag effects are all taken into account over the complete frequency range of concern. It is found that the inclusion of pitch considerably alters the response from that found for the case of vertical motion alone. In general, pitch is found to cause a significant attenuation of the response at low frequencies. One of the important findings of the study is the fact that the gust response for the two-degree-of-freedom case can be expressed in a form which is essentially independent of the integral scale of turbulence. Variations in geometric parameters of the airplane, such as tail moment arm, or radius of gyration in pitch, are considered to obtain an idea of the sensitivity of the gust response to these parameters.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1975
- Accession Number
- ADA021713
Entities
People
- Guy G. Williamson
- John C. Houbolt