Accession Number:

AD0503306

Title:

Advanced Fluidic Controls for Integrated Propulsion Systems. Part I. Fluidic Sensing, Computation, and Logic Components.

Corporate Author:

HONEYWELL INC MINNEAPOLIS MINN AEROSPACE DIV

Report Date:

1968-09-01

Abstract:

An Integrated Propulsion Control System IPC was developed using hybrid computer techniques. The system consisted of an inlet control system, an engine control system, and an exhaust nozzle control system. The IPC was mechanized with fluidic subsystems and components. A J85-GE-5 engine was used as the test vehicle to demonstrate the feasibility and capability of the engine control and exhaust nozzle control system to control the engine from sea level static to Mach 2, 40,000 feet altitude inlet conditions. Steady state control is achieved through closed loop speed control acceleration through closed loop control of turbine inlet temperature. This volume of the final report discusses the development of the fluidic sensing, computation and logic components. These components include fluid amplifiers, computation circuits, compensation networks, both analog and pulse type speed sensors, temperature sensors, a pressure regulator, filters, a fuel valve, fuel pumps, fluid potentiometers, and the concepts and techniques for packaging the components and circuits into a control system. Author

Descriptive Note:

Final rept. Apr 65-Apr 68,

Supplementary Note:

See also Part 2, AD-503 307.

Pages:

0196

Contract Number:

AF 33(615)-2696

File Size:

0.00MB

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