CONFIGURATION OF A HYDROSTATIC DRIVE SYSTEM FOR AN AERO GAS TURBINE FUEL CONTROL SYSTEM FACILITY

摘要

It is required to develop engine control system to meet the increasing demand of control requirements of fighter aircraft. It is also essential to develop test facilities to test and prove the control system in a simulated environment before actual engine trials. This will enable us not only to save time and money but, also will help us to study the effect of failures and malfunctioning of sub-systems. In this regard, a simulation facility is being setup with control system and its loading system in hardware form and the engine in software form. A high performance drive is required to be selected to drive the pumps of engine control system. In this paper, details of a hydrostatic drive system configured to meet the above requirements are presented. The important elements were modelled and analysed for various loading conditions using the software code developed. The stability of the drive was also checked.