A Closed Loop Analysis of POGO Instability.
Abstract
In this thesis, a generalized computer code for the simulation of POGO instability in liquid rockets was generated and verified. The term POGO refers to the out of phase motion of the ends of a liquid rocket, which can build to a dangerous magnitude due to propulsion feed back. The elimination of any POGO instability will be of great importance in the development of future liquid rocket systems such as orbital transfer and orbital maneuvering vehicles. The model detailed in this investigation is based on a method of characteristics solution of the simplified Navier-Stokes equations. The resulting non-linear differential equations were solved using first order finite difference methods. This solution was applied to the fluid lines of several liquid rocket systems. Boundary conditions, based on component models used generally throughout the literature were developed to link these fluid lines. The computer routines were verified by comparison with published results from several sources. The results of numerous runs agreed quite well with the published data, even in very non-linear systems with large disturbance amplitudes. As an aid to future investigators the routines developed in this thesis were applied to a typical bipropellant liquid rocket system. Additional keywords: Systems analysis; User manuals; POGO computer program.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1984
- Accession Number
- ADA153121
Entities
People
- D. A. Rosenberg
Organizations
- Air Force Institute of Technology