A Description of the Air Force Real-Time Nephanalysis Model

1992 ◽  
Vol 7 (2) ◽  
pp. 288-306 ◽  
Author(s):  
Thomas M. Hamill ◽  
Robert P. D'Entremont ◽  
James T. Buntin
Keyword(s):  
Real Time ◽  
Air Force

Organizational Knowledge and Innovation

2015 ◽  
pp. 510-530
Author(s):  
Carlos Páscoa ◽  
José Tribolet
Keyword(s):  
Real Time ◽  
Air Force ◽  
External Environment ◽  
Organizational Knowledge ◽  
Self Awareness ◽  
Flight Plan ◽  
Knowledge Based ◽  
Complete Knowledge ◽  
Informed Decisions ◽  
New Instrument

Having the necessary instruments to steer the organization, allowing constant knowledge informed changes, is extremely important for an organizations, while adapting, in an agile way, to the external environment. Like an aircraft, the organization must have a flight plan and instruments that provide an update of what is happening in real time. As an organization, the Portuguese Air Force needs to make good planning and possessing instruments for assessing, considering innovative manners, the progress made, allowing for a greater self-awareness. Every organization has key elements, essential for its operational success, and vital to plan controlled transformations. The objective of the research described in this chapter is to create a new instrument that provides complete knowledge about an organizational key element, in this case the Organizational Cost per Flight Hour that allows coping with transformation projects, by allowing innovative, knowledge-based, informed decisions.

Integrated Flight/Propulsion Control for Flight Critical Applications: A Propulsion System Perspective

1992 ◽  
Vol 114 (4) ◽  
pp. 755-762 ◽  
Author(s):  
K. D. Tillman ◽  
T. J. Ikeler
Keyword(s):  
Control System ◽  
Real Time ◽  
Air Force ◽  
Flight Control ◽  
Closed Loop ◽  
Fault Tolerant ◽  
Lessons Learned ◽  
System Perspective ◽  
Propulsion Control ◽  
Development Center

The Pratt & Whitney and Northrop companies together, under the Air Force Wright Research and Development Center (WRDC) sponsored Integrated Reliable Fault-Tolerant Control for Large Engines (INTERFACE II) Program [1, 2], designed and demonstrated an advanced real-time Integrated Flight and Propulsion Control (IFPC) system. This IFPC system was based upon the development of physically distinctive, functionally integrated, flight and propulsion controls that managed the Northrop twin engine, statically unstable, P700 airplane. Digital flight control and digital engine control hardware were combined with cockpit control hardware and computer simulations of the airplane and engines to provide a real-time, closed-loop, piloted IFPC system. As part of a follow-on effort, lessons learned during the INTERFACE II program are being applied to the design of a flight critical propulsion control system. This paper will present both the results of the INTERFACE II IFPC program and approaches toward definition and development of an integrated propulsion control system for flight critical applications.

Ground Test Data Validation Using a Subscale F/A-22 Engine Inlet Empirical Model

2006 ◽  
Author(s):  
Randall L. Bickford ◽  
Donald J. Malloy ◽  
Jeffrey F. Monaco ◽  
David S. Kidman
Keyword(s):  
Parameter Estimation ◽  
Real Time ◽  
Air Force ◽  
Model Updating ◽  
Integrated Approach ◽  
Data Validation ◽  
Time Data ◽  
Simulation Tools ◽  
Real Time Data ◽  
Identification Parameter

The US Air Force’s two main aeropropulsion test centers, Arnold Engineering Development Center and the Air Force Flight Test Center, are developing a common suite of modeling and simulation tools employing advanced predictive modeling technologies. These modeling and simulation tools incorporate real-time data validation, system identification, parameter estimation, model calibration, and automated model updating as new test results or operational data become available. The expected benefit is improved efficiency and accuracy for online diagnostic monitoring of Air Force assets. This paper describes the integrated approach to real-time data validation. Implementation of a software package to enable efficient model handoff between test groups and centers and extension of the capability to aeropropulsion models is discussed. An F/A-22 inlet model is used to demonstrate the approach. Compact polynomial function models of the distortion and recovery flow descriptors and 40-probe pressure values are derived from quasi-steady and instantaneous subscale wind tunnel data. The total-pressure inlet distortion and recovery models are integrated in a real-time equipment health monitoring system designed to support test operations, and preliminary results are given. A companion paper describes the integrated approach to system identification, parameter estimation, and model updating.

scholarly journals Development of Real-Time Maneuver Library Generation Technique for Implementing Tactical Maneuvers of Fixed-Wing Aircraft

2020 ◽  
Vol 2020 ◽  
pp. 1-12
Author(s):  
Do hyeon Lee ◽  
Chang-Joo Kim ◽  
Man Jung Heo ◽  
Joo Wan Hwang ◽  
Hee Gyeong Lyu ◽  
...  
Keyword(s):  
Control System ◽  
Real Time ◽  
Air Force ◽  
Flight Control ◽  
Pid Control ◽  
Control Technique ◽  
Proportional Integral Derivative ◽  
Flight Control System ◽  
Generation Technique ◽  
Flight Simulations

This study develops the real-time maneuver library generation technique for performing aggressive maneuvers of fixed-wing aircraft. Firstly, the general maneuver libraries are defined, and then 7th-order polynomials are used to create the maneuver libraries. The attitude command attitude hold (ACAH) system, the rate command rate hold (RCRH) system, and the speed command speed hold (SCSH) system using the proportional-integral-derivative (PID) control technique are designed to minimize the complexity of the flight control system (FCS) and to reduce the weight and volume of the payload. Moreover, the FCS is used for implementing tactical maneuvers. Finally, flight simulations are implemented for the longitudinal loop and Immelmann-turn maneuvers to check the usefulness of the proposed maneuver library generation technique. This study can affect the development of flight techniques for aircraft tactical maneuvers and the modification of air force operational manuals.

Real-Time Monitoring of a United States Air Force Topcoat/Mg-Rich Primer System in ASTM B117 Exposure by Embedded Electrodes

CORROSION ◽  
2010 ◽  
Vol 66 (7) ◽  
pp. 075003-075003-11 ◽  
Author(s):  
K. N. Allahar ◽  
D. Wang ◽  
D. Battocchi ◽  
G. P. Bierwagen ◽  
S. Balbyshev
Keyword(s):  
United States ◽  
Real Time ◽  
Air Force ◽  
United States Air Force ◽  
Real Time Monitoring

Calibration of a Subscale F/A-22 Engine Inlet Empirical Model Using Ground and Flight Test Data

2006 ◽  
Author(s):  
Jeffrey F. Monaco ◽  
David S. Kidman ◽  
Randall L. Bickford ◽  
Donald J. Malloy
Keyword(s):  
Parameter Estimation ◽  
System Identification ◽  
Modeling And Simulation ◽  
Real Time ◽  
Air Force ◽  
Test Data ◽  
Model Updating ◽  
Flight Test ◽  
Simulation Tools ◽  
Identification Parameter

The US Air Force’s two main aeropropulsion test centers, Arnold Engineering Development Center and the Air Force Flight Test Center, are developing a common suite of modeling and simulation tools employing advanced predictive modeling technologies. This common set of modeling and simulation tools incorporates real-time data validation, system identification, parameter estimation model calibration, and automated model updating as new test results or operational data become available. The expected benefit is improved efficiency and accuracy for online diagnostic monitoring of Air Force assets. These resultant models could also be used for flight manual development, determining compliance to specifications, or to aid in real-time equipment monitoring. This paper describes the integrated approach to system identification, parameter estimation, and model updating. Implementation of a software package to enable efficient model handoff between test groups and centers is discussed. An F/A-22 inlet model is used to demonstrate the approach. Compact polynomial function models of the distortion and recovery flow descriptors and 40-probe pressure values are derived from quasi-steady and instantaneous subscale wind tunnel data. The model parameters are then calibrated with F/A-22 flight test data. Results show that the modeling algorithm captures the relevant nonlinear physics of the application, and the calibration and updating procedure improves the model match to flight data. A companion paper provides preliminary results from integrating the calibrated total-pressure inlet distortion and recovery models into a real-time equipment health monitoring system to support test operations.

Integrated Flight/Propulsion Control for Flight Critical Applications: A Propulsion System Perspective

1991 ◽  
Author(s):  
Kenneth D. Tillman ◽  
Timothy J. Ikeler
Keyword(s):  
Control System ◽  
Real Time ◽  
Air Force ◽  
Flight Control ◽  
Closed Loop ◽  
Fault Tolerant ◽  
Lessons Learned ◽  
System Perspective ◽  
Propulsion Control ◽  
Development Center

The Pratt & Whitney and Northrop companies together, under the Air Force Wright Research and Development Center (WRDC) sponsored Integrated Reliable Fault-Tolerant Control for Large Engines (INTERFACE II) Program[1,2], designed and demonstrated an advanced real-time Integrated Flight and Propulsion Control (IFPC) system. This IFPC system was based upon the development of physically distinctive, functionally integrated, flight and propulsion controls that managed the Northrop twin engine, statically unstable, P700 airplane. Digital flight control and digital engine control hardware were combined with cockpit control hardware and computer simulations of the airplane and engines to provide a real-time, closed loop, piloted IFPC system. As part of a follow on effort, lessons learned during the INTERFACE II program are being applied to the design of a flight critical propulsion control system. This paper will present both the results of the INTERFACE II IFPC program and approaches toward definition and development of an integrated propulsion control system for flight critical applications.

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