scholarly journals Initial Flight Simulation Testing of a Gesture-Based Interface for Flight Control

2019 ◽  
Author(s):  
Manuel Alejandro Rodriguez Diaz ◽  
Emilia Villani ◽  
Diego Arjoni ◽  
Petter Krus
Keyword(s):  
Flight Control ◽  
Flight Simulation ◽  
Simulation Testing

Empirical Validation of the Prediction of Operator Performance (POP) Model

1996 ◽  
Vol 40 (2) ◽  
pp. 39-43
Author(s):  
CS. Jordan ◽  
E.W. Farmer ◽  
A.J. Belyavin ◽  
S.J. Selcon ◽  
A.J. Bunting ◽  
...  
Keyword(s):  
Flight Control ◽  
Human Performance ◽  
Threat Assessment ◽  
Flight Simulation ◽  
Performance Modelling ◽  
Operator Performance ◽  
Wide Range ◽  
Modelling Environment ◽  
And Performance ◽  
Task Conditions

This paper describes an experiment conducted to validate the Prediction of Operator Performance (POP) model in a flight simulation context. The POP model uses subjective ratings of the demand imposed by single tasks to predict both the demand and performance associated with concurrent tasks. Previous experiments on the POP model have investigated a wide range of experimental tasks including tracking and verbal reasoning. In this experiment eight subjects performed flight control, threat assessment and threat identification tasks singly and in combination. Performance measures and POP scores were collected at the completion of each task condition. The results demonstrated performance decrements in the dual task conditions that were consistent with the predictions. The implications for the POP model are discussed in terms of workload modelling and human performance modelling within the context of the Integrated Performance Modelling Environment (IPME) currently being developed within the Defence Evaluation and Research Agency

Flight simulator study on the influence of vortex curvature on wake encounter hazard using LES wind fields

2012 ◽  
Vol 116 (1177) ◽  
pp. 287-302 ◽  
Author(s):  
D. Vechtel
Keyword(s):  
Flight Control ◽  
Flight Simulation ◽  
Flight Simulator ◽  
Wind Fields ◽  
Wake Vortices ◽  
Large Eddy ◽  
Final Approach ◽  
Simulator Study ◽  
The Difference ◽  
Normal Law

Abstract A flight simulator study has been carried out to evaluate the performance of modern flight control systems encountering curved wake vortices. During the decay process the shape of wake vortices alters significantly which has an influence on the encounter characteristics and thus on the encounter hazard. To analyse most realistic wake encounters, flow fields of matured vortices have been generated with large-eddy-simulations. These were used for the determination of induced force and moment histories during the encounter. The force and moment histories have been implemented into the equations of motions of a 6 DoF flight simulation. For the sake of comparison encounters have also been simulated with straight vortices as they were mostly used for many other investigations. The most important goal of the study was to analyse the difference between these ideally straight vortices and vortices with a more realistic shape regarding encounter acceptance. The simulator study was conducted in an A330 motion-based full-flight simulator with pilots-in-the-loop. The analysed scenario was a wake encounter during final approach. The encounter conditions corresponded to a heavy-behind-heavy situation for Instrument Flight Rules (IFR) operations. The aircraft was flown either manually (in normal law) or with autopilot engaged. Altogether 93 encounters have been simulated, 38 with straight and 55 encounters with curved vortices. For encounters under manual control the simulator study revealed a potential risk of pilot induced oscillations (PIO) during encounters with curved vortices. With autopilot engaged not even one encounter with curved vortices was classified to be unacceptable. Although significant aircraft response was experienced the autopilot never disengaged automatically in any encounter. Altogether about 12 percent of the encounters were not accepted by the pilots. This is indeed a significant number, especially as the analysed scenarios can be regarded to be realistic situations which can occur in reality even if the applicable separation distances are applied.

scholarly journals Tunnel/Predictor Display for Trajectory Control in Hypersonic Flight

2018 ◽  
Vol 47 (2) ◽  
pp. 157-165
Author(s):  
Csaba Moravszki ◽  
József Rohács ◽  
Gottfried Sachs
Keyword(s):  
Flight Control ◽  
Research Effort ◽  
Trajectory Control ◽  
Flight Simulation ◽  
Flight Mechanics ◽  
Research Center ◽  
Control Law ◽  
3 Dimensional ◽  
Hypersonic Flight ◽  
Guidance Information

A tunnel/predictor display which presents guidance information in a 3-dimensional format is considered for improving trajectory control in hypersonic flight. The displayed 3-dimensional information comprises a tunnel image and a predictor for indicating the aircraft position at a specified time ahead. The 3-dimensional guidance information is introduced to support the pilot in controlling the flight path. It is considered that piloting problems can be avoided which exist with conventional trajectory control techniques due to path-attitude decoupling. A predictor control law is constructed which yields controlled element properties (predictor-aircraft system) requiring minimum pilot compensation. This predictor control law forms the basis of the trajectory control improvement goal. Results from hypersonic flight simulation tests at the NASA Dryden Flight Research Center are presented for experimental verification. This paper is an outcome of a joint research effort of the NASA Dryden Flight Research Center, and the Institute of Flight Mechanics and Flight Control of the Technische Universität München and the Department of Aeronautics, Naval Architecture and Railway Vehicles (former Department of Aircraft and Ships at the Budapest University of Technology and Economics.

Immunity-Based Abnormal Condition Accommodation of Aircraft Sub-System Failures

2014 ◽  
Author(s):  
Adil Togayev ◽  
Mario G. Perhinschi ◽  
Dia Al Azzawi ◽  
Hever Moncayo ◽  
Israel Moguel ◽  
...  
Keyword(s):  
Immune System ◽  
Artificial Immune System ◽  
Time Windows ◽  
Flight Simulation ◽  
The Self ◽  
Design Development ◽  
Artificial Immune ◽  
System Failures ◽  
Simulation Testing ◽  
System States

This paper describes the design, development, and flight-simulation testing of an artificial immune-system-based approach for accommodation of different aircraft sub-system failures/damages. The accommodation of abnormal flight conditions is regarded as part of a complex integrated artificial immune system scheme, which consists of four major components: detection, identification, evaluation, and accommodation. The accommodation part consists of providing compensatory commands under upset conditions for specific maneuvers. The approach is based on building an artificial memory, which represents the self (nominal conditions) and the non-self (abnormal conditions) within the artificial immune system paradigm. Self and non-self are structured as a set of memory cells consisting of measurement strings, over pre-defined time windows. Each string is a set of features values at each sample time of the flight including pilot inputs, system states, and other variables. The accommodation algorithm is based on the cell in the memory that is the most similar to the in-coming measurement. Once the best match is found, control commands corresponding to this match will be extracted from the memory and used for control purposes. The proposed methodology is illustrated through simulation of simple maneuvers at nominal flight conditions and under locked actuator. The results demonstrate the possibility of extracting pilot compensatory commands from the self/non-self structure and capability of the artificial-immune-system-based scheme to accommodate an actuator malfunction, maintain control, and complete the task.

Flight Simulation of Military Aircraft Systems

1993 ◽  
Vol 207 (2) ◽  
pp. 127-131
Author(s):  
J E Perrin
Keyword(s):  
Control System ◽  
Design Process ◽  
Flight Control ◽  
Early Stage ◽  
Flight Simulation ◽  
Flight Control System ◽  
Military Aircraft ◽  
System Operation ◽  
Aircraft Systems ◽  
Manned Flight

Manned flight simulation plays a key role in the design and development of modern aircraft systems where pilot interaction is an important consideration. Examples of the systems simulated during an aircraft project include the flight control system, the head-up display, the weapons system and the warnings system. Flight simulation allows the pilot to assess the system operation at an early stage in the design process, and modifications can be quickly implemented so that optimum system operation can be finalized. At British Aerospace (Military Aircraft Division), Warton, three differently configured simulators are currently utilized in the evaluation of aircraft systems.

Design, Flight Simulation, and Handling Qualities Evaluation of an LPV Gain-Scheduled Helicopter Flight Control System

2000 ◽  
Vol 6 (6) ◽  
pp. 553-566 ◽  
Author(s):  
Ian Postlethwaite ◽  
Ioannis K. Konstantopoulos ◽  
Xiao-Dong Sun ◽  
Daniel J. Walker ◽  
Adrian G. Alford
Keyword(s):  
Control System ◽  
Flight Control ◽  
Flight Simulation ◽  
Flight Control System ◽  
Handling Qualities ◽  
Helicopter Flight ◽  
Gain Scheduled

scholarly journals An Automatic Thrust Calculation Method in Case of Engine Gear Missing in Flight Control Simulation System

2018 ◽  
Vol 36 (6) ◽  
pp. 1116-1120
Author(s):  
Zeyu Kang ◽  
Yongmei Cheng ◽  
Xiaodan Cui ◽  
Hui Li ◽  
Huibin Wang
Keyword(s):  
Control System ◽  
Flight Control ◽  
Calculation Method ◽  
Speed Control ◽  
Weight Coefficient ◽  
Linearization Method ◽  
Flight Simulation ◽  
Control Mode ◽  
Control Simulation ◽  
Speed Control System

The paper proposes an automatic thrust calculation method in the case of engine gear missing. The trimmed linearization method is used to calculate the equivalent throttle opening between the two gears. An automatic thrust calculation method is presented which uses the equivalent throttle opening as weight coefficient. The speed control system which has introduced the equivalent throttle opening is designed, and the speed is controlled through the combination of the speed control system and the vertical speed control system. In this way, four basic modes are realized in flight simulation——climb, glide, given the yaw angle, given the roll angle, and the special speed control mode. It takes A320 aircraft for an example, the aerodynamic parameters and the Idletrust and Miltrust coefficients are obtained from JSBSim. Carry out flight control simulation on the above modes by building aircraft flight simulation model through Simulink. The results of the flight speed control show that the proposed method can achieve precise control of the speed in multi-flight modes.

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