SIMULATED ALTITUDE TESTING IN THE USAF ENGINE TEST FACILITY

1956 ◽  
Author(s):  
Joel Ferrell ◽  
Ray W. Harvey
Keyword(s):  
Test Facility ◽  
Engine Test ◽  
Simulated Altitude

Modeling and HIL Simulation of Flight Conditions Simulating Control System for the Altitude Test Facility

2016 ◽  
Vol 33 (4) ◽  
Author(s):  
Jun Zhou ◽  
Li Shen ◽  
Tianhong Zhang
Keyword(s):  
Control System ◽  
Wind Tunnel Test ◽  
Control Valve ◽  
Simulation System ◽  
Test Facility ◽  
Engine Test ◽  
Simulated Altitude ◽  
Free Jet ◽  
Aero Engine ◽  
Hil Simulation

AbstractSimulated altitude test is an essential exploring, debugging, verification and validation means during the development of aero-engine. Free-jet engine test can simulate actual working conditions of aero-engine more realistically than direct-connect engine test but with relatively lower cost compared to propulsion wind tunnel test, thus becoming an important developing area of simulated altitude test technology. The Flight Conditions Simulating Control System (FCSCS) is of great importance to the Altitude Test Facility (ATF) but the development of that is a huge challenge. Aiming at improving the design efficiency and reducing risks during the development of FCSCS for ATFs, a Hardware- in-the-Loop (HIL) simulation system was designed and the mathematical models of key components such as the pressure stabilizing chamber, free-jet nozzle, control valve and aero-engine were built in this paper. Moreover, some HIL simulation experiments were carried out. The results show that the HIL simulation system designed and established in this paper is reasonable and effective, which can be used to adjust control parameters conveniently and assess the software and hardware in the control system immediately.

Development status of the NAL Ramjet Engine Test Facility and sub-scale scramjet engine

1992 ◽  
Author(s):  
HIROSHI MIYAJIMA ◽  
NOBUO CHINZEI ◽  
TOHRU MITANI ◽  
YOSHIO WAKAMATSU ◽  
MASATAKA MAITA
Keyword(s):  
Test Facility ◽  
Engine Test ◽  
Development Status ◽  
Ramjet Engine ◽  
Scramjet Engine

Comparison and Synthesis of Performance and Aerodynamic Modeling of a Pass-Off Turbofan Engine Test Cell

2015 ◽  
Author(s):  
Martin Marx ◽  
Michael Kotulla ◽  
André Kando ◽  
Stephan Staudacher
Keyword(s):  
Research Effort ◽  
Engine Performance ◽  
Cell System ◽  
Performance Model ◽  
Test Cell ◽  
Test Facility ◽  
Engine Test ◽  
Combined System ◽  
Installation Effects ◽  
Engine Testing

To ensure the quality standards in engine testing, a growing research effort is put into the modeling of full engine test cell systems. A detailed understanding of the performance of the combined system, engine and test cell, is necessary e.g. to assess test cell modifications or to identify the influence of test cell installation effects on engine performance. This study aims to give solutions on how such a combined engine and test cell system can be effectively modeled and validated in the light of maximized test cell observability with minimum instrumentation and computational requirements. An aero-thermodynamic performance model and a CFD model are created for the Fan-Engine Pass-Off Test Facility at MTU Maintenance Berlin-Brandenburg GmbH, representing a W-shape configuration, indoor Fan-Engine test cell. Both models are adjusted and validated against each other and against test cell instrumentation. A fast-computing performance model is delivering global parameters, whereas a highly-detailed aerodynamic simulation is established for modeling component characteristics. A multi-disciplinary synthesis of both approaches can be used to optimize each of the specific models by calibration, optimized boundary conditions etc. This will result in optimized models, which, in combination, can be used to assess the respective design and operational requirements.

A Low Cost Computer Controlled IC Engine Test Facility

1998 ◽  
Vol 31 (4) ◽  
pp. 105-109
Author(s):  
Z. Ren ◽  
T. Campbell ◽  
J. B. Yang
Keyword(s):  
Low Cost ◽  
Test Facility ◽  
Engine Test ◽  
Ic Engine ◽  
Computer Controlled

Design and Implementation of a Digital Multimode H∞ Controller for the Spey Turbofan Engine

2009 ◽  
Vol 132 (1) ◽  
Author(s):  
Raza Samar ◽  
Ian Postlethwaite
Keyword(s):  
Degrees Of Freedom ◽  
Structural Integrity ◽  
Controller Design ◽  
Reference Model ◽  
Test Facility ◽  
Engine Test ◽  
Control Logic ◽  
Turbofan Engine ◽  
Simple Strategy ◽  
Bumpless Transfer

In this paper, a 2 degrees-of-freedom multimode controller design for the Rolls Royce Spey turbofan engine is presented. The controller is designed via discrete time H∞-optimization; it provides robust stability against coprime factor uncertainty, and a degree of robust performance in the sense of making the closed-loop system match a prespecified reference model. Multimode control logic is developed to preserve structural integrity of the engine by limiting engine variables to specified safe values. A simple strategy for antiwindup and bumpless transfer between controllers, based on the Hanus anti-windup scheme (1987, “Conditioning Technique, A General Anti-Windup and Bumpless Transfer Method,” Automatica, 23(6), pp. 729–739) and the observer-based structure of the controller, is presented. The structure of the overall switched controller is described. Actual engine test results using the Spey engine test facility at Pyestock are presented. The controller is shown to perform a variety of tasks, its multimode operation is illustrated and improvements offered on existing engine control systems are discussed.

Two-stage heater for a Mach 0 to 8 free-jet engine test facility

1998 ◽  
Author(s):  
Robert Engers ◽  
John Erdos ◽  
William Swartwout ◽  
Nicholas Tilakos
Keyword(s):  
Test Facility ◽  
Engine Test ◽  
Two Stage ◽  
Jet Engine ◽  
Free Jet

Liquid rocket engine test facility engineering challenges

2006 ◽  
Vol 59 (12) ◽  
pp. 1123-1134 ◽  
Author(s):  
Hartwig Ellerbrock ◽  
Stefan Ziegenhagen
Keyword(s):  
Rocket Engine ◽  
Test Facility ◽  
Liquid Rocket Engine ◽  
Engine Test ◽  
Liquid Rocket
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