Handling Qualities and Flight Safety Implications of Rudder Control Strategies and Systems in Transport Aircraft

2004 ◽  
Author(s):  
Ronald Hess
Keyword(s):  
Control Strategies ◽  
Flight Safety ◽  
Transport Aircraft ◽  
Handling Qualities

scholarly journals Development of a Multi-Directional Manoeuvre for Unified Handling Qualities Investigation

Aerospace ◽  
2019 ◽  
Vol 6 (6) ◽  
pp. 70
Author(s):  
Gaétan Dussart ◽  
Mudassir Lone ◽  
Roger Bailey
Keyword(s):  
Quantitative Data ◽  
Multiple Points ◽  
Transport Aircraft ◽  
Handling Qualities ◽  
Simple Set ◽  
Quantitative Data Analysis ◽  
Augmented Reality Technology ◽  
Test Flight ◽  
Aircraft Type ◽  
Potential Use

A slalom and alignment tracking manoeuvre was developed for multi-directional handling qualities analysis of large transport aircraft in simulation environments. The manoeuvre is defined and scaled as a function of aircraft characteristics, flight conditions using a simple set of mathematical models. Throughout the manoeuvre, the trajectory and overall performances are monitored at a set of gross position and alignment control checkpoints methodically distributed and sized to buoy the task and allow handling qualities analysis based on Cooper Harper Ratings and quantitative data analysis. Initial tests have shown that the manoeuvre sizing method led to feasible manoeuvres at multiple points of the flight envelope of a large civil transport aircraft. The manoeuvre capability to highlight desirable and undesirable handling qualities was also highlighted based on the initial findings for a couple of commercial large transport aircraft, a high aspect ratio wing and in-flight folding wingtip aircraft concepts. The relevance and applicability of the manoeuvre for multi-directional studies are discussed and compared against a more conventional offset landing manoeuvre. Finally, the potential use of the manoeuvre for different aircraft type and test flight is also suggested based on augmented reality technology.

On the Evaluation of Negative Altitude Requirement for Flutter Speed Boundary of Transport Aircraft and UAV

2012 ◽  
Vol 225 ◽  
pp. 397-402 ◽  
Author(s):  
Erwin Sulaeman
Keyword(s):  
Mach Number ◽  
Atmospheric Condition ◽  
Aircraft Design ◽  
Maximum Speed ◽  
Flight Safety ◽  
Transport Aircraft ◽  
Aeroelastic Instability ◽  
Flight Envelope ◽  
Constant Altitude ◽  
Standard Regulation

To maintain flight safety, all transport aircraft designs should satisfy airworthiness standard regulation. One fundamental issue of the aircraft design that relates directly to flight safety as well as commercial aspect of the aircraft is on the evaluation of the maximum speed within the designated flight envelope. In the present work, a study is performed to evaluate the negative altitude requirement related to aeroelastic instability analysis as one requirement that should be fulfilled to design the maximum speed. An analytical derivation to obtain the negative altitude is performed based on the airworthiness requirement that a transport airplane must be designed to be free from aeroelastic instability within the flight envelope encompassed by the dive speed or dive Mach number versus altitude envelope enlarged at all points by an increase of 15% in equivalent airspeed at both constant Mach number and constant altitude. To take into account variation in atmospheric condition as function of altitude, the international standard regulation is used as referenced. The analysis result shows that a single negative altitude can be obtained using these criteria regardless of the dive speed or dive Mach number. A further discussion on the application of the negative altitude concept to UAV (Unmanned Aerial Vehicle), in relation to UAV Standard Airworthiness Requirement STANAG 4671, is presented.

Supersonic transport aircraft longitudinal flight control law design

2004 ◽  
Vol 108 (1084) ◽  
pp. 319-329
Author(s):  
A. J. Steer
Keyword(s):  
Flight Control ◽  
Dynamic Inversion ◽  
Control Law ◽  
Transport Aircraft ◽  
Handling Qualities ◽  
Supersonic Transport ◽  
Linear Dynamic ◽  
Non Linear ◽  
Quality Design ◽  
Handling Quality

Abstract Modern civil transport aircraft utilise increasingly complex command and stability augmentation systems to restore stability, optimise aerodynamic performance and provide the pilot with the optimum handling qualities. Provided it has sufficient control power a second generation fly-by-wire supersonic transport aircraft should be capable of exhibiting similarly desirable low-speed handling qualities. However, successful flight control law design requires identification of the ideal command response type for a particular phase of flight, a set of valid handling quality design criteria and piloted simulation evaluation tasks and metrics. A non-linear mathematical model of the European supersonic transport aircraft has been synthesized on the final approach to land. Specific handling quality design criteria have been proposed to enable the non-linear dynamic inversion flight control laws to be designed, with piloted simulation used for validation. A pitch rate command system, with dynamics matched to the aircraft’s flight path response, will consistently provide Level 1 handling qualities. Nevertheless, pre-filtering the pilot’s input to provide a second order pitch rate response, using the author’s suggested revised constraints on the control anticipation parameter will generate the best handling qualities during the terminal phase of flight. The resulting pre-filter can be easily applied to non-linear dynamic inversion inner loop controllers and has simple and flight proven sensor requirements.

scholarly journals Propeller control strategy for coaxial compound helicopters

2018 ◽  
Vol 233 (10) ◽  
pp. 3775-3789 ◽  
Author(s):  
Ye Yuan ◽  
Douglas Thomson ◽  
Renliang Chen
Keyword(s):  
Control Strategy ◽  
High Speed ◽  
High Performance ◽  
Control Strategies ◽  
Flight Dynamics ◽  
Axial Thrust ◽  
Handling Qualities ◽  
Speed Range ◽  
Compound Helicopter ◽  
Flight Dynamics Model

The coaxial compound configuration has been proposed as a concept for future high-performance rotorcraft. The co-axial rotor system does not require an anti-torque device, and a propeller provides axial thrust. A well-designed control strategy for the propeller is necessary to improve the performance and the flight dynamics characteristics. A flight dynamics model of coaxial compound helicopter is developed to analyze these influences. The performance and the flight dynamics characteristics in different propeller strategies were first investigated. The results show that there is an improvement in the performance in high-speed flight when the propeller provides more propulsive forces. It also illustrates that a reasonable allocation of the rotor and the propeller in providing thrust can further reduce the power consumption in the mid speed range. In other words, the propeller control strategy can be an effective method to improve the cruise-efficiency. The flight dynamics analysis in this paper includes trim and handling qualities. The trim results prove that the propeller strategy can affect the collective pitch, longitudinal cyclic pitch, and the pitch attitude. If the control strategy is designed only to decrease the required power, it will result in a discontinuity in the trim characteristics. Handling qualities are investigated based on the ADS-33E-PRF requirement. The result demonstrates that the bandwidth and phase delay results and eigenvalue results in various speed at different propeller strategies are all satisfied. However, some propeller control strategies lead to severe inter-axis coupling in high-speed flight. Based on these results, this paper proposes the propeller control strategy for the coaxial compound helicopter. This strategy ensures good trim characteristics and handling qualities, which satisfy the related requirements, and improves the flight range or the performance in high-speed flight.

scholarly journals Cargo blocking failure analysis, simulation, and safety control of transport aircraft with continuous heavy airdrop

2018 ◽  
Vol 15 (1) ◽  
pp. 172988141875704
Author(s):  
Jie Chen ◽  
Cunbao Ma ◽  
Dong Song
Keyword(s):  
Robust Control ◽  
Uncertainty Analysis ◽  
Failure Analysis ◽  
Closed Loop ◽  
Drop Out ◽  
Flight Safety ◽  
Closed Loop System ◽  
Safety Control ◽  
Transport Aircraft ◽  
Delivery Channel

This article investigates the cargo’s blocking failure analysis, simulation, and safety control of transport aircraft with continuous heavy airdrop. As the cargos move backward and drop out, the continuous variation of center of gravity for the whole system will deteriorate flight quality dramatically. Furthermore, due to various mechanical reasons, if the cargo is blocked on the delivery channel and the airdrop process is suspended suddenly at this time, the flight safety may be threatened. In view of this, the blocking failure is analyzed based on the aircraft model in this article and then the simulation is completed to show the failure’s impact on aircraft’s flight quality. Next, based on the uncertainty analysis and introduction of interval robust control theory, the safety controller is designed to stable the closed-loop system. The final simulation shows the proposed safety control strategy’s effectiveness.

scholarly journals Review of modeling and control during transport airdrop process

2016 ◽  
Vol 13 (6) ◽  
pp. 172988141667814 ◽  
Author(s):  
Bin Xu ◽  
Jie Chen
Keyword(s):  
Control Problem ◽  
Flight Safety ◽  
Modeling And Control ◽  
Transport Aircraft ◽  
Potential Problems ◽  
History Of ◽  
Low Altitude ◽  
Future Direction ◽  
And Control ◽  
Landing Control

This article presents the review of modeling and control during the airdrop process of transport aircraft. According to the airdrop height, technology can be classified into high and low altitude airdrop and in this article, the research is reviewed based on the two scenarios. While high altitude airdrop is mainly focusing on the precise landing control of cargo, the low altitude flight airdrop is on the control of transport aircraft dynamics to ensure flight safety. The history of high precision airdrop system is introduced first, and then the modeling and control problem of the ultra low altitude airdrop in transport aircraft is presented. Finally, the potential problems and future direction of low altitude airdrop are discussed.

Control and handling qualities considerations for an advanced supersonic transport aircraft

1999 ◽  
Vol 103 (1024) ◽  
pp. 265-272
Author(s):  
A. J. Steer ◽  
M. V. Cook
Keyword(s):  
Flight Control ◽  
Fully Integrated ◽  
Transport Aircraft ◽  
Handling Qualities ◽  
Supersonic Transport ◽  
Handling Characteristics ◽  
Research Activities ◽  
Propulsion Control ◽  
And Performance ◽  
And Control

Abstract A future advanced supersonic transport aircraft (AST) has fundamental characteristics and problems inherent to supersonic cruise aircraft with corresponding unique control and handling characteristics. In order to optimise the aerodynamic performance across the full flight envelope a fully integrated flight and propulsion control system will be required. However, this will need to be designed from the outset within clearly defined flight control and performance guidelines. Relevant existing and AST specific handling qualities criteria will need to be developed if a successful commercial transport aircraft is to be produced. This paper begins by presenting an overview of existing supersonic transport (SST) aircraft operations and current second generation SST research activities and design considerations. This is followed by an analysis of the principal aerodynamic, dynamic and control characteristics of SST and AST aircraft and their effect on the aircraft’s handling qualities. Finally, some possible solutions to the control and handling issues are investigated, assessed and presented.

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