Enhancing the Fidelity of Post-stall Flight Simulation Using Detailed Propulsion System Model

Testing of a gas turbine engine for aircraft propulsion applications may be conducted in the actual aircraft or in a ground-test environment. Ground test facilities simulate flight conditions by providing airflow at pressures and temperatures experienced during flight. Flight-testing of the full aircraft system provides the best means of obtaining the exact environment that the propulsion system must operate in but must deal with limitations in the amount and type of instrumentation that can be put on-board the aircraft. Due to this limitation, engine performance may not be fully characterized. On the other hand, ground-test simulation provides the ability to enhance the instrumentation set such that engine performance can be fully quantified. However, the current ground-test methodology only simulates the flight environment thus placing limitations on obtaining system performance in the real environment. Generally, a combination of ground and flight tests is necessary to quantify the propulsion system performance over the entire envelop of aircraft operation. To alleviate some of the dependence on flight-testing to obtain engine performance during maneuvers or transients that are not currently done during ground testing, a planned enhancement to ground-test facilities was investigated and reported in this paper that will allow certain categories of flight maneuvers to be conducted. Ground-test facility performance is simulated via a numerical model that duplicates the current facility capabilities and with proper modifications represents planned improvements that allow certain aircraft maneuvers. The vision presented in this paper includes using an aircraft simulator that uses pilot inputs to maneuver the aircraft engine. The aircraft simulator then drives the facility to provide the correct engine environmental conditions represented by the flight maneuver.

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A Flight Simulation Vision for Aeropropulsion Altitude Ground Test Facilities

Volume 1: Turbo Expo 2002 ◽

10.1115/gt2002-30003 ◽

2002 ◽

Cited By ~ 2

Author(s):

Milt Davis ◽

Peter Montgomery

Keyword(s):

System Performance ◽

Engine Performance ◽

Aircraft Engine ◽

Flight Simulation ◽

Propulsion System ◽

Test Facility ◽

Flight Testing ◽

Test Environment ◽

Ground Test ◽

Aircraft System

Testing of a gas turbine engine for aircraft propulsion applications may be conducted in the actual aircraft or in a ground-test environment. Ground test facilities simulate flight conditions by providing airflow at pressures and temperatures experienced during flight. Flight-testing of the full aircraft system provides the best means of obtaining the exact environment that the propulsion system must operate in but must deal with limitations in the amount and type of instrumentation that can be put on-board the aircraft. Due to this limitation, engine performance may not be fully characterized. On the other hand, ground-test simulation provides the ability to enhance the instrumentation set such that engine performance can be fully quantified. However, the current ground-test methodology only simulates the flight environment thus placing limitations on obtaining system performance in the real environment. Generally, a combination of ground and flight tests is necessary to quantify the propulsion system performance over the entire envelop of aircraft operation. To alleviate some of the dependence on flight-testing to obtain engine performance during maneuvers or transients that are not currently done during ground testing, a planned enhancement to ground-test facilities was investigated and reported in this paper that will allow certain categories of flight maneuvers to be conducted. Ground-test facility performance is simulated via a numerical model that duplicates the current facility capabilities and with proper modifications represents planned improvements that allow certain aircraft maneuvers. The vision presented in this paper includes using an aircraft simulator that uses pilot inputs to maneuver the aircraft engine. The aircraft simulator then drives the facility to provide the correct engine environmental conditions represented by the flight maneuver.

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Research on aero-engine steady model based on an improved compact propulsion system model

Proceedings of the Institution of Mechanical Engineers Part I Journal of Systems and Control Engineering ◽

10.1177/0959651819878527 ◽

2019 ◽

Vol 234 (6) ◽

pp. 726-733

Author(s):

Qiangang Zheng ◽

Yong Wang ◽

Fengyong Sun ◽

Juan Fang ◽

Haibo Zhang ◽

...

Keyword(s):

Control Method ◽

System Modeling ◽

Propulsion System ◽

System Model ◽

Testing Time ◽

Variable Model ◽

Output Vector ◽

State Variable ◽

Advanced Control ◽

Aero Engine

The aero-engine steady model is the basis of the modern advanced control method such as performance seeking control. An improved compact propulsion system model is proposed to improve the steady model accuracy. The improved compact propulsion system model mainly contains linear model, such as steady-state variable model, and physical-based models, such as inlet model, nonlinear model, and nozzle model. The improved compact propulsion system model applied to full envelop by parameter corrections. The basepoint control vector and basepoint output vector of improved compact propulsion system model are four-dimensional interpolation instead of two-dimensional interpolation as conventional compact propulsion system modeling does. The improved compact propulsion system model not only considers the change of engine state but also take the flight parameter into account. The simulations of the conventional compact propulsion system modeling and the improved compact propulsion system model are conducted in subsonic and transonic flight envelop. The simulations show that, compared with the conventional compact propulsion system modeling, the relative testing errors of the improved compact propulsion system model decrease greatly. Moreover, the testing time of the conventional compact propulsion system modeling and the improved compact propulsion system model are both almost equal to 0.027 ms.

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A real time Pegasus propulsion system model for VSTOL piloted simulation evaluation

10.2514/6.1981-2663 ◽

1981 ◽

Author(s):

J. MIHALOEW ◽

S. ROTH ◽

R. CREEKMORE

Keyword(s):

Real Time ◽

Propulsion System ◽

System Model ◽

Simulation Evaluation

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Research on Optimization of Water Jet Propulsion

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.380-384.205 ◽

2013 ◽

Vol 380-384 ◽

pp. 205-208

Author(s):

Chang Tao Wang ◽

Feng Long Kan ◽

Lan Guang Zhao ◽

Wei Wei

Keyword(s):

Water Jet ◽

Propulsion System ◽

Nozzle Diameter ◽

The Other ◽

System Model ◽

Jet Propulsion ◽

Pump Speed

Based on characteristic of water jet, there are two important factors to product the thrust. One factor is pump speed and the other is the nozzle diameter. So, The significant optimization be required in order to overcome the existing water jet propulsion problem. In this paper, the water jet propulsion system model be studied at first, and then pump and nozzle optimization be discussed. At last, the result shows that the thrust of water jet by controlling the nozzle diameter size and pump speed.

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