Development and Wind Tunnel Evaluation of a SMA Based Trim Tab Actuator for a Civil Aircraft

Senthil Kumar, P and Jayasankar, S and Kamaleshiah, MS and Prashanth, N.S. and Paulsingh, Alfred and Dayananda, GN (2011) Development and Wind Tunnel Evaluation of a SMA Based Trim Tab Actuator for a Civil Aircraft. In: Symposium on Applied Aerodynamics and Design of Aerospace Vehicle (SAROD 2011), November 16-18, 2011, Bangalore, India.

Full text available as:
[img] PDF
Download (465Kb)

    Abstract

    This paper presents about the development and wind tunnel evaluation of an SMA based smart trim tab for a typical 2 seater civil aircraft. SMA actuator was housed in the port side of the elevator for actuating the trim tab. Wind tunnel tests were conducted on a full scale Horizontal Tail model with Elevator and Trim Tab at free stream speeds of 25, 35 & 45 m/sec and also for a number of deflections of the elevator (30° up, 0° neutral & 25° down) and trim-tab 11° & 21° up and 15° & 31° down). To measure the hinge moment experienced by the trim-tab at various test conditions, two miniaturized balances were designed and fabricated. Gain scheduled proportional integral controller was developed to control the SMA actuated smart trim tab. It was confirmed during the tests that the trim-tab could be controlled at the desired position against the aerodynamic loads acting on it for the various test conditions.

    Item Type: Conference or Workshop Item (Paper)
    Subjects: AERONAUTICS > Aeronautics (General)
    Division/Department: Advanced Composites Division, Advanced Composites Division, Centre for Civil Aircraft Design and Development, CSMST, CSMST, Advanced Composites Division
    Depositing User: Mrs Manoranjitha M D
    Date Deposited: 16 Dec 2011 14:14
    Last Modified: 16 Dec 2011 14:14
    URI: http://nal-ir.nal.res.in/id/eprint/10159

    Actions (login required)

    View Item