Accession Number : ADA469919


Title :   Optimal Spacecraft Attitude Control Using Aerodynamic Torques


Descriptive Note : Master's thesis


Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT


Personal Author(s) : Gargasz, Michael L


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a469919.pdf


Report Date : Mar 2007


Pagination or Media Count : 91


Abstract : This thesis introduces a method of three-axis spacecraft attitude control using only aerodynamic torques. Attitude actuation is achieved using four control panels mounted on the rear of a cubical spacecraft bus. The controller consists of an outer loop using linear state feedback to determine desired control torque and an inner loop to choose appropriate control panel angles. The inner loop uses a Jacobian-based approach to invert the nonlinear relationship between panel angles and generated torque. Controller performance is evaluated via simulations, which show that three-axis control is possible over a range of initial angles and angular rates. The analysis used partial accommodation theory as the basis for aerodynamic torque calculations and assumed a rotating atmosphere with an exponential density profile.


Descriptors :   *ATTITUDE CONTROL SYSTEMS , *AERODYNAMIC DRAG , *TORQUE , *CONTROL PANELS , STABILITY , THESES , ATTITUDE(INCLINATION) , ACTUATION , AERODYNAMIC FORCES , NONLINEAR SYSTEMS , CONTROL SYSTEMS


Subject Categories : Flight Control and Instrumentation
      Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE