Landing gear

About: Landing gear is a research topic. Over the lifetime, 3403 publications have been published within this topic receiving 25370 citations. The topic is also known as: landing gear & gear.

Mathematical Model Research on Aircraft Landing Gear

Abstract: It is investigated the composition and the principle of the aircraft landing gears, and the model structure of it is set up. It is simulated in the MATLAB/SIMULINK, the result of the aircraft anti-skid system is also presented and the effect on the aircraft anti-skid system is analysed in details. The result shows that the aircraft landing gear system model established is basically rational andcorrect.Itishelpfultodesigntheaircraftanti-skidbrakingsystem,andtoimprovethebrakingefficiency andthebrakingperformance.

Vibration Response Aspects of a Main Landing Gear Composite Door Designed for High-Speed Rotorcraft

Abstract: One of the crucial issues affecting the structural safety of propeller vehicles is the propeller tonal excitation and related vibrations. Propeller rotation during flight generates vibrating sources depending upon its rotational angular velocity, number of blades, power at shaft generating aircraft thrust, and blade geometry. Generally, the higher energy levels generated are confined to 1st blade passing frequency (BPF) and its harmonics, while additional broadband components, mainly linked with the blade shape, the developed engine power, and the turbulent boundary layer (TBL), also contribute to the excitation levels. The vibrations problem takes on particular relevance in the case of composite structures. The laminates in fact could exert damping levels generally lower than metallic structures, where the greater amount of bolted joints allow for dissipating more vibration energy. The prediction and reduction of aircraft vibration levels are therefore significant considerations for conventional propeller aircrafts now entering the commercial market as well as for models currently being developed. In the Clean Sky 2 framework, the present study focuses on a practical case inherent to the AIRBUS-Racer program aiming to design and develop a multi-tasking fast rotorcraft. This paper defines a finite elements (FE)-based procedure for the characterization of the vibration levels of a main landing gear (MLG) composite door with respect to the expected operating tonal loads. A parametric assessment was carried out to evaluate the principal modal parameters (transfer functions and respective resonance frequencies, mode shapes, and damping coefficients) of the landing gear-door assembly in order to achieve reduced vibration levels. Based on the FE analysis results, the influence of the extra-damping, location, and number of ballast elements, the boundary conditions were investigated with respect to failure scenarios of the kinematic line opening the study towards aeroelastic evaluations. Further experimental ground test results serve as a validation database for the prediction numerical methods representative of the composite door dynamic response.

Aircraft braking system

Abstract: A method of braked pivot turning an aircraft (1) , the aircraft (1) comprising a fuselage (3) and a landing gear assembly (9, 10) located to one side thereof. The landing gear comprises a bogie (17) with wheels (19, 20) mounted thereon, at least one wheel being located on a first side of the bogie (17) and at least one wheel being located on a second side of the bogie (17) . The method includes the steps of applying thrust (7'') for moving or turning the aircraft, and via the braking of at least one wheel, applying a greater braking force to the first side of the bogie (17) than to the second side. The first side is located closer to the centre of turning (13) of the aircraft than the second side. The method thereby generates relatively low torque loads in the landing gear leg, reducing fatigue damage. A brake control system is also provided for selectively braking wheels during a turn.

High-reliability landing gear control system

Abstract: The invention relates to a high-reliability landing gear control system. The high-reliability landing gear control system comprises a control driving unit and an EMAC driving circuit, wherein the control driving circuit comprises a power supply transformation power distribution module, a 1553B bus interface module, a CPU processing unit, a steering motor driving circuit, a solenoid valve driving circuit and an analog quantity signal processing circuit, wherein the CPU processing unit comprises a taking-up and releasing control module, a front wheel steering control module and an anti-skid braking driving control module; the landing gear control system adopts a driving and control integrated design, the CPU processing unit can be used for achieving combined control on taking up and releasing of a landing gear and a cabin door, the steering of a front wheel, and the anti-skid braking of an electro-mechanical actuator of a main engine wheel, and the system is light in weight, low in power consumption, high in reliability and good in environment adaptation, and can be widely applied to novel spacecraft landing recovery systems and traditional aircraft landing gear systems.