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Liping Zhao – One of the best experts on this subject based on the ideXlab platform.
A stereo vision-based attitude measurement system for Aircraft Model in wind tunnel2010 International Conference on Computer Application and System Modeling (ICCASM 2010), 2010Co-Authors: Jiechun Chen, Liping ZhaoAbstract:
Measuring the attitude of an Aircraft Model in wind tunnel accurately is one way to improve the accuracy of wind tunnel experiment results. This paper investigates a stereo vision-based attitude measurement system for Aircraft Model in wind tunnel. To measure the attitude of an Aircraft Model, a cooperative object mounted on the Aircraft Model is firstly used to generate two bidirectional collimated laser beams, and then the laser beams are projected onto the surfaces of two screens. A pair of binocular stereo vision measurement systems is used to measure the 3D coordinates of the laser spots on the wall surfaces. Once the 3D coordinates of the laser spots are measured accurately, the attitude of the Aircraft Model in wind tunnel can be determined. The method for attitude measurement is validated in a controlled laboratory environment, and some preliminary experimental results are presented in the paper.
Yuan Feng – One of the best experts on this subject based on the ideXlab platform.
Stereo vision based attitude measurement of Aircraft Model in wind tunnelJournal of Applied Optics, 2010Co-Authors: Yuan FengAbstract:
This paper investigates a stereo vision based method for Model attitude measurement in wind tunnel test. A cooperative object,which can generate two bidirectional collimated laser beams,is firstly mounted on the shell of an Aircraft Model,and then the Aircraft Model is placed between two screens. The laser beams,which are projected onto the screen surfaces,generate four laser spots. Once the 3D coordinates of the laser spots are measured accurately by means of stereo vision technique,the attitude of the Aircraft Model can be determined by the principle of coordinate transformation. The analytical expressions for determining the attitude of an Aircraft Model in wind tunnel are presented in the paper. In addition,the proposed method was validated in a controlled laboratory condition. The preliminary experimental results show that the maximal error of attitude measurement is less than 0.05° on condition that the distance between two screens is about 6m.
Suresh M. Joshi – One of the best experts on this subject based on the ideXlab platform.
Adaptive actuator failure compensation for a transport Aircraft ModelProceedings of the 2001 American Control Conference. (Cat. No.01CH37148), 2001Co-Authors: Shuhao Chen, Gang Tao, Suresh M. JoshiAbstract:
Adaptive actuator failure compensation schemes are developed for a class of multi-input and single-output plants with actuator failures characterized by certain inputs stuck at some unknown fixed value at unknown time instants. Conditions and controller structures for achieving state tracking and output tracking in the presence of actuator failures are derived. Adaptive laws are designed for updating some of the controller parameters when the actuator failure parameters are unknown. Simulation results for a linearized transport Aircraft Model with actuator failure show the desired system performance with adaptive failure compensation.