AN ENGINEERING EVALUATION OF AIRPLANE GUST LOAD ANALYSIS METHODS. VOLUME 1. THEORETICAL DEVELOPMENT
Abstract
Airplane longitudinal motion is described by a linear, multi-degree- of-freedom system of forced response equations in terms of normal modes, where the basic inputs to the system are the generalized aerodynamic forces due to motion and gust. The modes considered in the analysis are two symmetric rigid- body modes (vertical translation and pitch) and an arbitrary number of symmetric vibration modes of the wing and fuselage with the stabilizer assumed jigid. In formulating the generalized forces, strip theory, appropriately modified to yield experimental complete-airplane steady-state stability derivatives, is used. The lifting elements (strips) of the airplane are an arbitrary number of wing and tail panels per side. Aerodynamic loading of the fuselage is assumed to be acting on the wing sections obtained by extending the wing to the centerline of the airplane.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1963
- Accession Number
- AD0444436
Entities
People
- Dino George
- George R. Schriro
- John B. Smedfield
Organizations
- Grumman