Computer program for solving gains required for steady-state decoupling of elements of longitudinal mode of an airplane
National Aeronautics and Space Administration, 1974 - Science - 36 pages
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03IiddUs airplane approximately decoupled attain those steady-state blown flap closed-loop gain matrix commanded pilot input compute the feedback computer program computes the prefilter CONTINUE SUPPLIED CALL control matrix control vector decoupled control DIMENSION dummy variable ENCODE equations of motion equilibrium feedback gain matrix feedback gains required flaps forward velocity four control elements fourth row horizontal tail IEEE Trans IMAX JMAX Kleinman's iterative technique Langley Research Center Laplace transform linear regulator problem listing for subroutine LLvp longitudinal mode matrix F matrix Riccati equation mioaX Multivariable Systems NASA NOISSV nondimensional obtain the prefilter optimal control performance index pitch angle prefilter gain matrix prefilter gains necessary Program RTOPSI provide steady-state decoupling pseudoinverse radians REQUIRED FOR STEADY-STATE RETURN END Subroutine RLAMDA solution solve the matrix stabilizing matrix steady-state conditions STOL Subroutine INTT subroutine LINEQ2 Subroutine MATINV subroutine NEWT2 subroutine OPTIFP Subroutine STABLE three control elements throttle time-invariant X 4 MATRIX