Design, development and flight testing of control laws for the Indian Light Combat Aircraft AIAA Paper 2002-4649

Chetty, Shyam (2002) Design, development and flight testing of control laws for the Indian Light Combat Aircraft AIAA Paper 2002-4649. In: AIAA Guidance, Navigation, and Control Conference and Exhibit, Aug. 5-8, 2002, Monterey, CA.

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    Abstract

    The Light Combat Aircraft (LCA) is a single engine, tailless delta wing supersonic fighter aircraft, which is designed to be aerodynamically unstable in the longitudinal axis. In order to stabilize the airframe and achieve the desired performance over the entire flight envelope, the aircraft is equipped with a quad-redundant full-authority fly-by-wire (FBW) flight control system (FCS). The control laws resident in the sophisticated-electronics FBW-FCS, in addition to guaranteeing stability, optimize the aircraft performance and piloted handling qualities over the entire flight envelope for all aircraft external store configurations. This paper gives an overview of the design, development, and testing of the flight control laws for the indigenously developed LCA. The LCA has successfully completed the first block of 12 test flights. These flights were carried out basically to calibrate the air data system and identify the aerodynamic stability and control characteristics. The pilots have rated the aircraft as Level 1 in all the tasks performed during these flights. The paper concludes by presenting typical flight test results.

    Item Type: Conference or Workshop Item (Paper)
    Uncontrolled Keywords: Flight Control System and Avionics;LCA Programme;Flight Control Laws;Control law design philosophy;CLAW Performance and Stability Requirements
    Subjects: AERONAUTICS > Aeronautics (General)
    Division/Department: Aerospace Electronics and Controls Division
    Depositing User: Mr. N A
    Date Deposited: 02 Feb 2006
    Last Modified: 24 May 2010 09:40
    URI: http://nal-ir.nal.res.in/id/eprint/1016

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