Landing gear

About: Landing gear is a(n) research topic. Over the lifetime, 3403 publication(s) have been published within this topic receiving 25370 citation(s). The topic is also known as: landing gear & gear.

Aircraft Design: A Conceptual Approach

Abstract: * Design - A Separate Discipline * Overview of the Design Process * Sizing from a Conceptual Sketch * Airfoil and Geometry Selection * Thrust-to-Weight Ratio and Wing Loading * Initial Sizing * Configuration Layout and Loft * Special Considerations in Configuration Layout * Crew Station, Passengers, and Payload * Propulsion and Fuel System Integration * Landing Gear and Subsystems * Intermission: Step-by-Step Development of a New Design * Aerodynamics * Propulsion * Structures and Loads * Weights * Stability, Control, and Handling Qualities * Performance and Flight Mechanics * Cost Analysis * Sizing and Trade Studies * Design of Unique Aircraft Concepts * Conceptual Design Examples * Appendix A: Unit Conversion * Appendix B: Standard Atmosphere.

Aircraft landing gear design principles and practices

Abstract: This text aims to lead students and engineers from the initial concepts of landing gear design through to the final detail design. It provides a link in landing gear technology from historical practices to modern design trends, also considering the necessary airfield interface with gear design.

Morphing Aircraft Technology - New Shapes for Aircraft Design

Abstract: : Morphing aircraft are multi-role aircraft that change their external shape substantially to adapt to a changing mission environment during flight. This creates superior system capabilities not possible without morphing shape changes. The objective of morphing activities is to develop high performance aircraft with wings designed to change shape and performance substantially during flight to create multiple-regime, aerodynamically-efficient, shape-changing aircraft. Compared to conventional aircraft, morphing aircraft become more competitive as more mission tasks or roles are added to their requirements. This paper will review the history of morphing aircraft, describe a recent DARPA program, recently completed, and identify critical technologies required to enable morphing. As indicated in Figure 1, designing and building aircraft shape changing components is not new. In the past, aircraft have used variable sweep, retractable landing gear, retractable flaps and slats, and variable incidence noses. However, recent work in smart materials and adaptive structures has led to a resurgence of interest in more substantial shape changes, particularly changes in wing surface area and controlled airfoil camber.

Vibration Control of a Landing Gear System Featuring Electrorheological/Magnetorheological Fluids

Abstract: The feasibility and effectiveness of electrorheological (ER) and magnetorheological (MR) fluid-based landing gear systems on attenuating dynamic load and vibration due to the landing impact are demonstrated. First, the theoretical model for ER/MR shock struts, which are the main components of the landing gear system,is developed based on experimental data. The analysis of a telescopic-type landing gear system using the ER/MR shock struts is theoretically constructed, and its governing equation is derived. A sliding mode controller, designed to be robust against parameter variations and external disturbances, is formulated, and controlled performance of the simulated ER/MR landing gear system is theoretically evaluated during touchdown of the aircraft.

Airframe Noise Prediction Method

Abstract: : A noise component method is presented for calculating airframe noise. Noise from clean wing and tail surface is represented as trailing edge noise caused by the turbulent boundary layer. Landing gear noise is given by an empirical representation of model data. Trailing edge flap noise is modeled as a lift dipole normal to the deflected flap, with amplitude and spectrum given by a correlation of flyover data. Measured flyover data for the Prue-2 sailplane, Aero Commander Shirke general aviation airplane, Lockheed JetStar business jet, Boeing 747 commerical jet, and Convair F-106B delta wing airplane are used as test cases. These spectra are compared with predictions by this method and the NASA ANOPP total aircraft method and drag element method. Methods for reducing various components of airframe noise are examined and evaluated.