This paper discusses the analytical simulations employed by Columbus Div. of North American Aviation to analyze the landing gear and associated vehicle response for A-5 aircraft, Apollo, and OV-10A. A brief development of the mathematical simulations with the basic equations of motion is included, along with methods used to predict the loads due to running over arresting cables or deck lights. The method of obtaining internal load distributions of the vehicle structure is also given. Where available, results of the analyses are compared with experimentally measured data. Finally, a discussion of the validity and applicability of the methods together with the conclusions based on the results are presented.
