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In 2004 the FAA finalized the Sport Pilot/Light Sport Aircraft (LSA) category. This category of affordable aircraft makes owning an aircraft more accessible than ever. There are two airworthiness certification categories: 1 A special light-sport aircraft (S-LSA), sold ready-to-fly that maybe used for flight training, rental, or personal flight, including personal flight instruction. 2 An experimental light-sport aircraft (E-LS), sold in a kit form that may be used for personal recreational flight or personal flight training. This paper describes a design applicable to the first category: S-LSA. The aircraft will be primarily used for recreational purposes and a sport pilot may only operate this airplane during daylight hours. The occupants are seated in tandem. A three-surface design is chosen for its aerodynamic efficiency. The paper describes the design philosophy, design requirements, weight sizing, performance sizing, weight and balance, aerodynamics and stability and control.

Experience has shown that process and system level thinking enables significant reductions in design cycle time by avoiding technically correct but irrelevant calculations. Irrelevance often arises when the correct analysis is performed at the wrong stage in the product definition. Current iterative approaches to engineering design require considerable duplication of effort, much of which comes from modeling multiple design abstractions for varied levels and types of analyses. To ensure that appropriate domain knowledge is available at the appropriate time, skills and experience with tools that enable more robust trade studies for increasingly detailed design with inputs from increasingly diverse disciplines are required. Vehicle-focused efforts have broad appeal for attracting high quality, diverse students and facilitate strategic alignment of teaching and research.

A user-friendly method for analyzing longitudinal and lateral-directional trim problems for airplanes with all engines operating (AEO) and with one engine inoperative (OEI) is presented. The method allows for rapid evaluation of various critical handling qiality parameters, such as stick-force per ‘g’ and stick-force versus speed gradients. In addtion, the effect of failures in trim systems on cockpit control forces and on control surface and/or tab deflections can be assessed. Also, the method can be used for sizing of tab control systems, down-springs, bob-weights and interconnect springs. Finally, elevator hingemoment derivatives for rather arbitrary aerodynamic balance configurations can be quickly estimated.