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mods:
  schema location: http://www.loc.gov/mods/v3 http://www.loc.gov/standards/mods/v3/mods-3-2.xsd
  title info:
    title: Nonlinear attitude control of spacecraft and momentum management of control moment gyros
  name:
    name part: Oh, Hwa-Suk
    name part: 1956-
    role:
      role term: creator
  name:
    name part: Vadali, Srinivas R.
    role:
      role term: degree supervisor.
  name:
    name part: Huang, Garng, M.
    role:
      role term: degree committee member.
  name:
    name part: Junkins, John L.
    role:
      role term: degree committee member.
  name:
    name part: Zhou, Jianxin
    role:
      role term: degree committee member.
  name:
    name part: Texas A & M University
    role:
      role term: degree granting institution.
  type of resource: text
  genre: bibliography
  genre: Academic theses
  origin info:
    place:
      place term: xx
    date issued: 1992
    issuance: monographic
  language:
    language term: eng
  physical description:
    form: print
    extent: ix, 106 leaves : illustrations ; 29 cm
  abstract: Nonlinear design procedures are presented for obtaining attitude control and momentum management laws. These are based on the Liapunov stability theorems. The Work-Energy Rate(WER) principle is extended to cover general classes of systems. It is shown that the use of the W ER principle for obtaining control laws, can reduce the design efforts. The attitude control laws are designed for several types of missions, i.e., absolute attitude and relative attitude control. The momentum management as well as attitude control laws are designed for both stable and unstable spacecraft configurations which use Control Moment Gyros(CMGs) as active actuators. A large stability region is found around the local-vertical-local-horizontal(LVLH) equilibrium point, and so the designed control laws can be used even in the event of large initial attitude deviations from LVLH. In the presence of constant disturbance, the momentum is managed by seeking a Torque Equilibrium Attitude(TEA) where the disturbance torque is balanced by gravity gradient and gyroscopic torques. This is done by the use of integral feedback of the control torque, which is related to the angular momentum of the CMGs. It is shown that the unknown constant disturbance can be identified by the use of integral feedback. Cyclic disturbance rejection for the pitch axis is performed by successive stabilization and integral feedback. Theoretical results developed are verified using both experimental and numerical simulations. Experimental model of a flexible spacecraft is used to demonstrate the applicability of the WER principle and the fact that under certain conditions, a control law based on a rigid body model, can be applied to a flexible spacecraft. Using a mathematical model of the space station Freedom, several attitude/momentum management control laws are simulated and shown to work successfully with/without a constant disturbance torque. The control law for cyclic disturbance rejection of pitch axis attitude is exa…
  note: Typescript (photocopy).
  note: Vita.
  note: "Major subject: Aerospace Engineering."
  note: Ph. D. Texas A & M University 1992
  note: Includes bibliographical references.
  subject:
    topic: Space vehicles
    topic: Attitude control systems
  subject:
    topic: Momentum (Mechanics)
  subject:
    topic: Major aerospace engineering
  identifier: http://proxy.library.tamu.edu/login
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    location:
      url: http://proxy.library.tamu.edu/login
  record info:
    record content source: TXA
    record creation date: 931006
    record change date: 20200904152631.0
    record identifier: in00001160526
    language of cataloging:
      language term: eng