A digital 3-D automatic control law was developed to achieve an optimal transition of a B-737 aircraft between various initial glid slope conditions and the desired final touchdown condition. A discrete, time-invariant, optimal, closed-loop control law presented for a linear regulator problem, was extended to include a system being acted upon by a constant disturbance. Two forms of control laws were derived to solve this problem. One method utilized the feedback of integral states defined appropriately and augmented with the original system equations. The second method formulated the problem as a control variable constraint, and the control variables were augmented with the original system. The control variable constraint control law yielded a better performance compared to feedback control law for the integral states chosen.

  • Corporate Authors:

    Old Dominion University

    Norfolk, VA  United States  23529
  • Authors:
    • Nadkarni, A A
    • Breedlove, WJJ
  • Publication Date: 1979-2

Media Info

  • Pagination: 73 p.

Subject/Index Terms

Filing Info

  • Accession Number: 00192006
  • Record Type: Publication
  • Source Agency: National Technical Information Service
  • Report/Paper Numbers: NASA-CR-158114 Prog Rpt.
  • Contract Numbers: NSG-1480
  • Files: TRIS
  • Created Date: Jul 11 1979 12:00AM