Accession Number : ADA266186


Title :   Pulse Response Based Control for Minimum Time Maneuver of Flexible Spacecraft


Descriptive Note : Final rept. 1 Jul-30 Nov 1992


Corporate Author : TEXAS UNIV AT AUSTIN DEPT OF AEROSPACE ENGINEERING AND ENGINEERING MECHANICS


Personal Author(s) : Bennighof, Jeffrey K


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a266186.pdf


Report Date : 10 May 1993


Pagination or Media Count : 98


Abstract : The pulse response based control method for minimum time maneuver of flexible spacecraft is described. This method makes it possible to obtain minimum time control profiles for linear systems solely on the basis of measured response to pulses in control inputs and gross inertial properties of the system, such as total mass or total mass moment of inertia. The accuracy with which the final state of the system can be specified is shown to be related to the observability of the system with the given outputs. A special algorithm is developed for solving the numerical optimization problem arising in this approach. For maneuver problems, nonlinear behavior is handled by explicitly modeling the deviation from linear behavior in those few modes in which it is significant. A feedback control scheme to complement pulse response based control, which is stable in the presence of nonlinear rotational stiffening effects and input bounds, is presented. Also, a near minimum time method which requires virtually no real time computation is described. Numerical examples illustrate the method and its features and extensions.


Descriptors :   *SPACECRAFT , *FLIGHT MANEUVERS , *FLEXIBLE STRUCTURES , ALGORITHMS , LINEAR SYSTEMS , CONTROL , INERTIA , INTERACTIONS , STIFFENING , MOMENTS , PULSES , APPROACH , MOMENT OF INERTIA , SLEWING , FEEDBACK , RESPONSE , PROFILES , ACCURACY , MASS , REAL TIME , COMPUTATIONS , SPACE TECHNOLOGY , OPTIMIZATION


Subject Categories : Astronautics
      Spacecraft Trajectories and Reentry


Distribution Statement : APPROVED FOR PUBLIC RELEASE