The basic understanding of the significance of aircraft loads and their relationship to aeroelasticity will be elaborated comprehensively. The estimation of loads acting on an aircraft structure is an indispensable task ranging from conceptual, preliminary and detailed design to loads flight testing and the manufacturing and operation of aircrafts, when an aircraft is already in service, there are a large range of topics that need to be elaborated and proven, analytically as well as by experiments. Much of these problems can be understood and mastered, by looking into selected topic which can be classified into those related to (a) stability (e.g. flutter), (b) static deformation (e.g. static aeroelastic effects, steady flight maneuvers) and (c) dynamic response (e.g. maneuvers, gusts, turbulence). Once the response deformations and accelerations are obtained, the loads and stresses generated in the aircraft must also be determined so that the strength and fatigue/damage tolerance behavior may be assessed. Structural loads are the major reason for degradation of structures. Loads is a general term that incorporates both forces and moments. Various basic concepts relevant to loads in general will be introduced, including Newton’s laws of motion for a particle and their generalization to a body, as well as D’Alembert’s principle as sources of externally applied/reactive loads, which will further generate internal load within a structure. Basic analysis using the principles of mechanics, strength of materials, aerodynamics and flight mechanics will be elaborated. The determination of loads together with the qualification for static strength and fatigue by calculation and test for all important structural components is a main prerequisite for successful design and safe operation of any aircraft.
Introduction to Aircraft Loads
Introduction to Aeroelasticity ; Kapitel : 13 ; 591-619
2023-09-04
29 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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