Linear theory of active control of pressure oscillations in combustion chambers
Abstract
Active control of longitudinal pressure oscillations in combustion chambers has been studied theoretically using a digital state-feedback control technique. The formulation is based on a generalized wave equation which accommodates various influences on combustion, mean flow, unsteady motions, and contol actions. After a procedure equivalent to the Galerkin method, a system of ordinary differential equation governing the amplitude of each oscillatory mode is derived, serving as a basis for the controller design. The control actions is provided by a finite number of point acutators, with the instantaneous chamber conditions monitored by a few sensors. Several important control aspects such as sampling period, locations of sensors and controllers, controllability and observabi1ity have been investigated. As a specific example, the case involving two controlled and two residual (uncontrolled) modes is studied. The control and observation spillover phenomena due to the residual modes are clearly demonstrated.
Additional Information
© 1988, American Institute of Aeronautics and Astronautics.Attached Files
Published - 302_Yang_v_1988.pdf
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Additional details
- Eprint ID
- 21128
- Resolver ID
- CaltechAUTHORS:20101202-115230138
- Created
-
2010-12-04Created from EPrint's datestamp field
- Updated
-
2020-03-09Created from EPrint's last_modified field
- Caltech groups
- Guggenheim Jet Propulsion Center
- Series Name
- AIAA Papers
- Series Volume or Issue Number
- AIAA-88-2944
- Other Numbering System Name
- AIAA
- Other Numbering System Identifier
- 88-2944