Aileron Angle - Explore the Science & Experts | ideXlab

Scan Science and Technology

Contact Leading Edge Experts & Companies

Aileron Angle

The Experts below are selected from a list of 27 Experts worldwide ranked by ideXlab platform

Aileron Angle – Free Register to Access Experts & Abstracts

Wei Zhang – One of the best experts on this subject based on the ideXlab platform.

  • CSE – Failure Analysis and Improved Method of Batch Cracks for Certain Fighter Aircraft
    2014 IEEE 17th International Conference on Computational Science and Engineering, 2014
    Co-Authors: Wei Zhang
    Abstract:

    52 cracks of different length appeared around R corner of counterweight Angles were checked in 30 service fighter aircrafts, which affected the completion of the flight training seriously. Based on the parts inspection, strength check and stress of broken components, combined with the results of failure fracture about physicochemical analysis, analyzed cracks on the Aileron Angle. This paper concluded that the main cause of cracks which is the fatigue source cause of the structure details of the design defects and details of manufacturing defects, and proposed the strengthening scheme about this kind of cracks.

M Jouma'a – One of the best experts on this subject based on the ideXlab platform.

  • Lateral and Directional Stability and Control in Air-to-Air Refuelling:
    Proceedings of the Institution of Mechanical Engineers Part G: Journal of Aerospace Engineering, 1995
    Co-Authors: A W Bloy, M Jouma'a
    Abstract:

    Application of a wake roll-up method coupled with the vortex lattice method and approximate expressions for the receiver fuselage effect have been used to determine the induced loads on a Hercules receiver aircraft behind a KC10 tanker. The induced loads depend strongly on the vertical position of the receiver wing and fin relative to the tanker wing wake. In the case of steady sideslip there is a large decrease in the directional stability of the receiver as quantified by the gradient of the rudder Angle versus sideslip. This is due mainly to the combined effects of the yawing moments due to bank, yaw and side displacements. Minimum directional stability corresponds to the tip of the receiver fin intersecting the tanker wing wake. The associated Aileron Angle is two to three times the value in free air in agreement with flight test data. Solution of the linearized equations of motion gives three lateral characteristic oscillations for the air-to-air refuelling case. These include the usual Dutch roll osc…

Andrea Amerio – One of the best experts on this subject based on the ideXlab platform.

  • Evaluation of the Flying Qualities of a Half-Scale Unmanned Airplane via Flight Simulation
    , 2015
    Co-Authors: Pedro González J. R, Pedro J. Boschetti, Elsa M. Cárdenas, Andrea Amerio
    Abstract:

    The purpose of the present work is to evaluate the flying qualities of a half-scale radio controlled airplane based on the Unmanned Airplane for Ecological Conservation via flight simulation. The stability coefficients of the half-scale airplane were obtained by vortex lattice method using the code Tornado. The radio controlled aircraft simulator CRRCSim was used to perform the virtual flights. Aerodynamic, geometry, thrust and mass characteristics of the airplane were introduced to the simulator by a code written in C++. Virtual test flights were carried out and the flying qualities were obtained. It could be concluded that the half-scale airplane has excellent flying qualities, rating the aircraft in level 1. The simulator is recommended as a training tool for test pilots of the real model. Nomenclature CLq, CMq = variation of lift, and pitching moment coefficients with pitch rate CLα, CDα, CMα = lift, drag, and pitching moment slopes CLδe, CMδe = variation of lift, and pitching moment coefficients with elevator deflection Cℓp, Cnp, CYp = variation of rolling, yawing and side force coefficients with roll rate Cℓr, Cnr, CYr = variation of rolling, yawing and side force coefficients with yaw rate Cℓβ, Cnβ, CYβ = variation of rolling, yawing and side force coefficients with sideslip Angle Cℓδr, Cnδr, CYδr = variation of rolling, yawing and side force coefficients with rudder Angle Cℓδa, Cnδa, CYδa = variation of rolling, yawing and side force coefficients with Aileron Angle c = medium chord gx, gy, gz = components of gravity acceleration vector Ix, Iy, Iz = rolling, pitching and yawing moments of inerinertia Ixy, Iyz, Izx = products of inertia moments about x-y, y-z and z-x axes L, M, N = rolling, pitching and yawing moments acting on the aircraft m = mass p, q, r = roll, pitch and yaw rate u, v, w = longitudinal, lateral and vertical components of velocity X, Y, Z = components of resultant aerodynamic forces acting on the airplan

A W Bloy – One of the best experts on this subject based on the ideXlab platform.

  • Lateral and Directional Stability and Control in Air-to-Air Refuelling:
    Proceedings of the Institution of Mechanical Engineers Part G: Journal of Aerospace Engineering, 1995
    Co-Authors: A W Bloy, M Jouma'a
    Abstract:

    Application of a wake roll-up method coupled with the vortex lattice method and approximate expressions for the receiver fuselage effect have been used to determine the induced loads on a Hercules receiver aircraft behind a KC10 tanker. The induced loads depend strongly on the vertical position of the receiver wing and fin relative to the tanker wing wake. In the case of steady sideslip there is a large decrease in the directional stability of the receiver as quantified by the gradient of the rudder Angle versus sideslip. This is due mainly to the combined effects of the yawing moments due to bank, yaw and side displacements. Minimum directional stability corresponds to the tip of the receiver fin intersecting the tanker wing wake. The associated Aileron Angle is two to three times the value in free air in agreement with flight test data. Solution of the linearized equations of motion gives three lateral characteristic oscillations for the air-to-air refuelling case. These include the usual Dutch roll osc…

Pedro González J. R – One of the best experts on this subject based on the ideXlab platform.

  • Evaluation of the Flying Qualities of a Half-Scale Unmanned Airplane via Flight Simulation
    , 2015
    Co-Authors: Pedro González J. R, Pedro J. Boschetti, Elsa M. Cárdenas, Andrea Amerio
    Abstract:

    The purpose of the present work is to evaluate the flying qualities of a half-scale radio controlled airplane based on the Unmanned Airplane for Ecological Conservation via flight simulation. The stability coefficients of the half-scale airplane were obtained by vortex lattice method using the code Tornado. The radio controlled aircraft simulator CRRCSim was used to perform the virtual flights. Aerodynamic, geometry, thrust and mass characteristics of the airplane were introduced to the simulator by a code written in C++. Virtual test flights were carried out and the flying qualities were obtained. It could be concluded that the half-scale airplane has excellent flying qualities, rating the aircraft in level 1. The simulator is recommended as a training tool for test pilots of the real model. Nomenclature CLq, CMq = variation of lift, and pitching moment coefficients with pitch rate CLα, CDα, CMα = lift, drag, and pitching moment slopes CLδe, CMδe = variation of lift, and pitching moment coefficients with elevator deflection Cℓp, Cnp, CYp = variation of rolling, yawing and side force coefficients with roll rate Cℓr, Cnr, CYr = variation of rolling, yawing and side force coefficients with yaw rate Cℓβ, Cnβ, CYβ = variation of rolling, yawing and side force coefficients with sideslip Angle Cℓδr, Cnδr, CYδr = variation of rolling, yawing and side force coefficients with rudder Angle Cℓδa, Cnδa, CYδa = variation of rolling, yawing and side force coefficients with Aileron Angle c = medium chord gx, gy, gz = components of gravity acceleration vector Ix, Iy, Iz = rolling, pitching and yawing moments of inertia Ixy, Iyz, Izx = products of inertia moments about x-y, y-z and z-x axes L, M, N = rolling, pitching and yawing moments acting on the aircraft m = mass p, q, r = roll, pitch and yaw rate u, v, w = longitudinal, lateral and vertical components of velocity X, Y, Z = components of resultant aerodynamic forces acting on the airplan