Automatic landing flight experiment flight simulation analysis and flight testing

1999 ◽  
Vol 36 (4) ◽  
pp. 554-560 ◽  
Author(s):  
Toshikazu Motoda ◽  
Yoshikazu Miyazawa ◽  
Kazutoshi Ishikawa ◽  
Tatsushi Izumi
Keyword(s):  
Simulation Analysis ◽  
Flight Simulation ◽  
Flight Testing ◽  
Flight Experiment ◽  
Automatic Landing

ALFLEX flight simulation analysis and flight testing

1998 ◽  
Author(s):  
Toshikazu Motoda ◽  
Yoshikazu Miyazawa ◽  
Kazutoshi Ishikawa ◽  
Tatsushi Izumi
Keyword(s):  
Simulation Analysis ◽  
Flight Simulation ◽  
Flight Testing

A Flight Simulation Vision for Aeropropulsion Altitude Ground Test Facilities

2005 ◽  
Vol 127 (1) ◽  
pp. 8-17 ◽  
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.

Robust flight control law design for an automatic landing flight experiment

1999 ◽  
Vol 7 (9) ◽  
pp. 1143-1151 ◽  
Author(s):  
Masahiro Ohno ◽  
Yasuhiro Yamaguchi ◽  
Takashi Hata ◽  
Morio Takahama ◽  
Yoshikazu Miyazawa ◽  
...  
Keyword(s):  
Flight Control ◽  
Control Law ◽  
Flight Experiment ◽  
Automatic Landing ◽  
Robust Flight Control

A Flight Simulation Vision for Aeropropulsion Altitude Ground Test Facilities

2002 ◽  
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.

Development of Digital Flight Motion Methodology Based on Aerodynamic Derivatives Approximation

2016 ◽  
Vol 28 (2) ◽  
pp. 215-225
Author(s):  
Norazila Othman ◽  
◽  
Masahiro Kanazaki
Keyword(s):  
Surrogate Model ◽  
Mean Squared Error ◽  
Simulation Analysis ◽  
Prediction Method ◽  
Solution Space ◽  
Latin Hypercube Sampling ◽  
Flight Simulation ◽  
Prediction Ability ◽  
Aerodynamic Derivatives ◽  
Exact Function

[abstFig src='/00280002/12.jpg' width=""300"" text='3D contour views of Cz [-0.4—1.05],Mach:0.6-1.4, Alpha:0°-30°' ]The accuracy of efficient flight simulation depends on the quality of the aerodynamic data used to simulate aircraft dynamic motion. The accuracy of such data prediction depends strongly on motion variables, aerodynamic derivatives, and the coefficients used when the complete global aerodynamic database is being building. A surrogate model applied as a prediction method based on several measured points (exact function) used to predict unknown points of interest helps reduce time taken by the experiment or computation. Latin hypercube sampling searches the solution space for aerodynamic data to optimize the experimental design, so the key objective is to develop an aircraft's efficient digital flight motion by solving equations of motion and predicting aerodynamic data using a surrogate model. To realize these goals, we use sample surrogate model data, acquired from empirical model USAF Stability and Control DATCOM. The database was built for two main variables, the angle of attack and the Mach number, along the longitudinal and lateral axes. Exact and predicted functions were compared by calculating the mean squared error (MSE). The digital flight was validated through mode motion analysis and a flight quality scale to prove flight mission capabilities. A comparison between results predicted by the surrogate model and the exact function showed that flight simulation analysis and prediction ability of the surrogate model are useful in future analyses.

Flight control system for the Automatic Landing Flight Experiment

1996 ◽  
Author(s):  
Yoshikazu Miyazawa ◽  
Kazutoshi Ishikawa ◽  
Toshikazu Motoda ◽  
Tatsushi Izumi ◽  
Masakazu Sagisaka ◽  
...  
Keyword(s):  
Control System ◽  
Flight Control ◽  
Flight Control System ◽  
Flight Experiment ◽  
Automatic Landing
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