In this study, a velocity measuring instrument has been designed to measure velocities for slow-flying unmanned aerial vehicles or VTOLs during transition; measuring such low velocities with good resolution is difficult to measure with a pitot static tube and electronic pressure sensors used with flight controllers. This instrument described in this study uses a curved surface for accelerating the flow, resulting in a higher difference in pressure compared to the conventional pitot static tube. These instruments can also be used in drones and flapping wings UAVs, which fly at a speed of around 10 m/s or less. The pressure sensors, which are currently available to measure the pressure difference with conventional pitot static tubes, are highly inaccurate in this range. These are some available venturi effects on airspeed, which are also effective and give good results at lower air speeds (10 m/s or less). However, due to their bulky size and shape, they are not easily mountable on the respective UAV and also compromise the aerodynamics of the vehicle. So, in this study, we have done a numerical investigation over varying Reynolds numbers to find the relationship between velocity and pressure difference using which the electronic air pressure sensor can be calibrated to measure the airspeed. The effects of scalability also indicate the size of the instrument can be made small enough while giving higher pressure difference at lower airspeeds.


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    Title :

    Design of a Low-Velocity Measuring Pitot Static Tube


    Additional title:

    Advances in Science, Technology & Innovation


    Contributors:

    Conference:

    International Conference on Advances in Aerospace and Navigation Systems ; 2024 ; Bangalore, India August 22, 2024 - August 23, 2024



    Publication date :

    2025-05-21


    Size :

    5 pages





    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English




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