Authors: None

Abstract:

Keywords:

Digital Object Identifier (DOI): 10.3182/20070625-5-FR-2916.90001

Conference: 17th IFAC Symposium on Automatic Control in Aerospace (2007)

Location: ICT, Universitas Studii Tolosana, France

Start Date: Mon Jun 25 2007 - End Date: Fri Jun 29 2007

Page Numbers: ---

Authors: None

Abstract:

Keywords:

Digital Object Identifier (DOI): 10.3182/20070625-5-FR-2916.90002

Conference: 17th IFAC Symposium on Automatic Control in Aerospace (2007)

Location: ICT, Universitas Studii Tolosana, France

Start Date: Mon Jun 25 2007 - End Date: Fri Jun 29 2007

Page Numbers: ---

Authors: None

Abstract:

Keywords:

Digital Object Identifier (DOI): 10.3182/20070625-5-FR-2916.90003

Conference: 17th IFAC Symposium on Automatic Control in Aerospace (2007)

Location: ICT, Universitas Studii Tolosana, France

Start Date: Mon Jun 25 2007 - End Date: Fri Jun 29 2007

Page Numbers: ---

Authors: Patton, Ron J.; Uppal, Faisal J.; Simani, Silvio; Polle, Bernard

Abstract: This paper addresses the problem of the detection and isolation of the faults affecting the thrusters of a satellite system, which is characterised by a nonlinear model, in the presence of measurement errors, uncertainty and disturbance. In particular, this work proposes a robust estimation approach to the problem of the design of residual generators in order to realise complete diagnosis schemes when realistic faults are present on the simulated system. This approach leads to dynamic observers that can achieve both good disturbance de-coupling and robustness properties with respect to linearisation error, uncertainty and measurement noise. The description of the satellite structure is provided in order to highlight the main sources of uncertainty and disturbance. The faulty behaviour of the satellite Mars Express (MEX) nonlinear model and a comparison with the existing fault diagnosis scheme implemented on-board are reported. Finally, suitable performances criteria are introduced together with the Monte Carlo analysis for assessing the robustness and performance evaluation of the suggested FDI design methodology.

Keywords: reliability analysis and evaluation,fault detection and isolation,satellite attitude control,Monte Carlo simulation,robust FDI

Digital Object Identifier (DOI): 10.3182/20070625-5-FR-2916.00002

Conference: 17th IFAC Symposium on Automatic Control in Aerospace (2007)

Location: ICT, Universitas Studii Tolosana, France

Start Date: Mon Jun 25 2007 - End Date: Fri Jun 29 2007

Page Numbers: 1-6

Authors: Nagashio, Tomoyuki; Kida, Takashi; Ohtani, Takashi; Hamada, Yoshiro

Abstract: This paper studies the robust attitude control of large Geosynchronous communication satellite ETS-VIII. After describing its model features and control issues, a candidate of robust controller design method is proposed. The controller has the form of two-degrees-of freedom control in order to satisfy both specifications of disturbance attenuation and attitude maneuver. The feedback control employs the symmetric controller having the salient robust stability property irrespective of the plant parameters. Its optimization scheme in the H∞ norm sense is discussed. Finally, the on-orbit control experiment plan is shown with some simulation results.

Keywords: flexible spacecraft,attitude control,robust control,H∞ control,symmetric structure

Digital Object Identifier (DOI): 10.3182/20070625-5-FR-2916.00003

Conference: 17th IFAC Symposium on Automatic Control in Aerospace (2007)

Location: ICT, Universitas Studii Tolosana, France

Start Date: Mon Jun 25 2007 - End Date: Fri Jun 29 2007

Page Numbers: 7-12

Authors: Vigano, Luca; Lovera, Marco

Abstract: The problem of orbit control for spacecraft on elliptical orbits is analysed and an approach to the design of optimal constant gain controllers for the periodic dynamics of relative motion is proposed. In particular, it is shown how the proposed approach can guarantee closed loop stability and optimal performance both in the case of circular and elliptical orbits.

Keywords: satellite control,time-varying systems,optimal control,output feedback

Digital Object Identifier (DOI): 10.3182/20070625-5-FR-2916.00004

Conference: 17th IFAC Symposium on Automatic Control in Aerospace (2007)

Location: ICT, Universitas Studii Tolosana, France

Start Date: Mon Jun 25 2007 - End Date: Fri Jun 29 2007

Page Numbers: 13-18

Authors: Tewari, Ashish; Renuganth, V.

Abstract: An optimal attitude control method based upon linear quadratic regulator is applied to a spacecraft in an inclined orbit, alternatively using magnetic torquers and reaction wheels. The design objective of multi-axis pointing accuracy of 0.1 deg. with magnetic torquers, and 0.002 deg. with reaction wheels is demonstrated in the presence of environmental torques, without the need of a time varying control law design. The selection of optimal weighting matrices duly takes into account the underactuated and time varying nature of the plant with magnetic torquers. It is demonstrated that a well designed, constant feedback gain matrix precludes the necessity of sophisticated nonlinear and time varying design methods that require onboard programming.

Keywords: attitude control,automatic control (closed-loop),LQR control method,magnetic dipole excitation,optimal regulation

Digital Object Identifier (DOI): 10.3182/20070625-5-FR-2916.00005

Conference: 17th IFAC Symposium on Automatic Control in Aerospace (2007)

Location: ICT, Universitas Studii Tolosana, France

Start Date: Mon Jun 25 2007 - End Date: Fri Jun 29 2007

Page Numbers: 19-24

Authors: Konrad, Alexej; Fischer, Horst-Dieter; Muller, Carsten; Oesterlin, Wilfried

Abstract: The Galileo In Orbit Verification (IOV) program, consisting of 4 spacecrafts, is the first step towards an European satellite-based navigation system. The main objective of the IOV phase is to verify the proper functioning of the overall system before starting the next step - Galileo Full Operational Capability (FOC) - where the full deployment of 30 Galileo satellites will be performed. This paper gives an overview of the Galileo IOV Attitude and Orbit Control (AOC) function with the focus being put on the spacecraft attitude control. The AOC is a part of the Avionics subsystem, manufacturing of which has been subcontracted to Astrium. The article also describes the overall requirements on the control system, the AOC hardware and operational architecture as well as selected details on the AOC algorithms with corresponding test results.

Keywords: satellite control,attitude control,attitude algorithms,control systems,closed-loop control,feedback control,control equipment,control algorithms,discrete digital dynamics control,estimation algorithms,extended Kalman filters,estimators,statespace formulas,systems concepts

Digital Object Identifier (DOI): 10.3182/20070625-5-FR-2916.00006

Conference: 17th IFAC Symposium on Automatic Control in Aerospace (2007)

Location: ICT, Universitas Studii Tolosana, France

Start Date: Mon Jun 25 2007 - End Date: Fri Jun 29 2007

Page Numbers: 25-30

Authors: Cordoba, G. Mario Andres

Abstract: The EFIGENIA EJ-1 is an advanced aerodynamics design vehicle and avionics autopilot system design in which a digital neural network combined with a fuzzy logic system performs the best flight guidance, navigation and flight control condition operation. This paper describes the EFIGENIA EJ-1 Short or Vertical take-off and Landing (S/VTOL) autonomous intelligent Unmanned Aerial Vehicle (UAV) embedded multiprocessor fuzzy logic flight guidance and control system scheme autopilot system designed.

Keywords:

Digital Object Identifier (DOI): 10.3182/20070625-5-FR-2916.00007

Conference: 17th IFAC Symposium on Automatic Control in Aerospace (2007)

Location: ICT, Universitas Studii Tolosana, France

Start Date: Mon Jun 25 2007 - End Date: Fri Jun 29 2007

Page Numbers: 31-36

Authors: Samar, R.; Ahmed, Shakil; Aftab, Faisal

Abstract: This paper presents conventional proportional and derivative lateral control law with some non-linear modifications which enhance tracking performance for a UAV in different flight conditions especially recovery from large cross track errors. The scheme was implemented in C/C++ and extensively tested in 6-DoF nonlinear simulation environment. The performance was also compared with recent nonlinear lateral control logic (Park, 2004) on straight and circular paths. Simulation results showed that proposed scheme gave comparable path tracking performance with nonlinear logic on circular trajectories along with improved performance on straight paths with smaller steady state errors.

Keywords: flight control,path control,PD controllers,integral actions

Digital Object Identifier (DOI): 10.3182/20070625-5-FR-2916.00008

Conference: 17th IFAC Symposium on Automatic Control in Aerospace (2007)

Location: ICT, Universitas Studii Tolosana, France

Start Date: Mon Jun 25 2007 - End Date: Fri Jun 29 2007

Page Numbers: 37-42

Authors: Han, Sang Sul; Jang, Sang Keun; Lee, Sang Jeong

Abstract: A radome aberration causes degradation of miss distance as well as system stability at high altitude and high maneuver missile with RF seeker. These kinds of effectiveness have been already known well and many counter compensation techniques have been investigated. In this paper, proposed adaptive Particle filter estimates LOS rate excluding the radome induced error. Adaptive concept is very efficient in this problem because the actual radome aberration error is time varied and would not have Gaussian distribution. Particles of this filter are propagated and re-sampled such as conventional Particle filter, however, parameter value is changed as filter step progresses. LOS rate is allocated in particles and radome aberration error is defined to unknown parameter in this paper. Simulation results show that an estimated LOS rate yielded by adaptive Particle filter permits enhanced stability and considerable reduction of miss distance. Moreover, estimated LOS rate rapidly converges for varying radome error with non-constant slope.

Keywords: radome,aberration,adaptive,particle filter,LOS rate,stability

Digital Object Identifier (DOI): 10.3182/20070625-5-FR-2916.00009

Conference: 17th IFAC Symposium on Automatic Control in Aerospace (2007)

Location: ICT, Universitas Studii Tolosana, France

Start Date: Mon Jun 25 2007 - End Date: Fri Jun 29 2007

Page Numbers: 43-48

Authors: Park, HeeYoung; Kim, KwangJin; Lee, Jang Gyu; Park, Chan Gook

Abstract: The roll angle is estimated only using the pitch and yaw rates for a gunlaunched smart munition with fast rolling of 1∼2 Hz. An extended Kalman filter is designed based on the roll, pitch, and yaw dynamics and two MEMS gyroscopes measuring pitch and yaw rates. It is simulated under a realistic condition with low-grade gyroscopes. The simulation results show that the roll angle is estimated with an accuracy of 1∼3 deg. (1-sigma error). The filter also exhibits that it is robust to the scale factor and bias errors of the MEMS gyroscopes. And the proposed algorithm is experimented using a two-axis rate table and a low grade MEMS IMU. The results show that the algorithm can be applied to an actual system.

Keywords: smart munition,inertial measurement unit,roll estimation,extended Kalman filter

Digital Object Identifier (DOI): 10.3182/20070625-5-FR-2916.00010

Conference: 17th IFAC Symposium on Automatic Control in Aerospace (2007)

Location: ICT, Universitas Studii Tolosana, France

Start Date: Mon Jun 25 2007 - End Date: Fri Jun 29 2007

Page Numbers: 49-54

Authors: Abedi, Mostafa; Bolandi, Hossein; Saberi, Farhad Fani

Abstract: This paper proposes an observer based adaptive Takagi-Sugeno fuzzy guidance law for a surface to air missile. An integrated guidance-control model is derived to consider target manoeuvre and missile uncertainties in the design process of the proposed guidance law, also use of adaptive intelligent system for approximation of unknown dynamic parts of the mentioned model and a high gain observer for estimation of required states caused that this approach, in contrast to guidance approaches introduced by now, use the minimum number of inputs for a robust missile guidance. Presented proofs and simulated results show the practical application and effective performance of designed guidance law.

Keywords: guidance,missile,adaptive,Takagi-Sugeno,fuzzy,target,uncertainty,robust

Digital Object Identifier (DOI): 10.3182/20070625-5-FR-2916.00011

Conference: 17th IFAC Symposium on Automatic Control in Aerospace (2007)

Location: ICT, Universitas Studii Tolosana, France

Start Date: Mon Jun 25 2007 - End Date: Fri Jun 29 2007

Page Numbers: 55-60

Authors: Mehrabian, Ali Reza; Nayebpanah, Nastaran

Abstract: Modern aircrafts and missiles with high manoeuvrability present an interesting challenge to autopilot design, which has activated new investigations in estimating the potential and applicability of recent theoretical control methods as well as how they can meet industrial demands. In this paper, a multi-objective approach for autopilot design is introduced. The design requirements are formulated using several integral criteria. A hybrid-genetic algorithm (GA) is employed to solve the nonlinear optimization problem. The obtained results are verified using nonlinear simulations in SIMULINK® which shows performance, stability and robustness of the designed flight controller.

Keywords: flight control,genetic algorithms,PID controllers,nonlinear systems

Digital Object Identifier (DOI): 10.3182/20070625-5-FR-2916.00012

Conference: 17th IFAC Symposium on Automatic Control in Aerospace (2007)

Location: ICT, Universitas Studii Tolosana, France

Start Date: Mon Jun 25 2007 - End Date: Fri Jun 29 2007

Page Numbers: 61-66

Authors: Schallert, Christian

Abstract: This paper consolidates advanced techniques for flight control law design with the sizing issues of new technology electrical flight control actuators. An automatic optimisation tool is adapted to modify the control laws for minimum actuator deflection rates, which can be turned into weight savings for the overall aircraft. Thus, the paper outlines a new and up-to-date trade-off study, which is motivated by the recent trend towards the more-electric aircraft concept.

Keywords: flight control,actuators,electrical power system,flight dynamics simulation,control laws,automatic multi-objective parameter optimisation

Digital Object Identifier (DOI): 10.3182/20070625-5-FR-2916.00013

Conference: 17th IFAC Symposium on Automatic Control in Aerospace (2007)

Location: ICT, Universitas Studii Tolosana, France

Start Date: Mon Jun 25 2007 - End Date: Fri Jun 29 2007

Page Numbers: 67-72

Authors: Ochi, Yoshimasa

Abstract: This paper proposes a design method of a flight control system for automatic refueling based on the line-of-sight (LOS) angle control in conjunction with range and airspeed control of the receiver aircraft. A model following control method is employed for design of the controllers. This control method is applied to a control configured vehicle (CCV) aircraft. The guidance and control performance has been investigated through three-dimensional computer simulation in the presence of turbulences and/or wake vortex of the tanker. The results are compared with those for the conventional aircraft that is the original aircraft of the CCV.

Keywords: flight control,model following control,position control,velocity control,disturbance rejection

Digital Object Identifier (DOI): 10.3182/20070625-5-FR-2916.00014

Conference: 17th IFAC Symposium on Automatic Control in Aerospace (2007)

Location: ICT, Universitas Studii Tolosana, France

Start Date: Mon Jun 25 2007 - End Date: Fri Jun 29 2007

Page Numbers: 73-78

Authors: Padhi, R.; Rao, P. N.; Goyal, S.; Balakrishnan, S. N.

Abstract: This paper proposes a new straight forward technique based on dynamic inversion, which is applied for tracking the pilot commands in high performance aircrafts. Pilot commands assumed in longitudinal mode are normal acceleration and total velocity (while roll angle and lateral acceleration are maintained at zero). In lateral mode, roll rate and total velocity are used as pilot commands (while climb rate and lateral acceleration are maintained at zero). Ensuring zero lateral acceleration leads to a better turn co-ordination. A six degree-of-freedom model of F-16 aircraft is used for both control design as well as simulation studies. Promising results are obtained which are found to be superior as compared to an existing approach (which is also based on dynamic inversion). The new approach has two potential benefits, namely reduced oscillatory response and reduced control magnitude. Another advantage of this approach is that it leads to a significant reduction of tuning parameters in the control design process.

Keywords: command tracking,dynamic inversion,aircraft control,longitudinal maneuver,lateral maneuver

Digital Object Identifier (DOI): 10.3182/20070625-5-FR-2916.00015

Conference: 17th IFAC Symposium on Automatic Control in Aerospace (2007)

Location: ICT, Universitas Studii Tolosana, France

Start Date: Mon Jun 25 2007 - End Date: Fri Jun 29 2007

Page Numbers: 79-84

Authors: Yamasaki, Takeshi; Takano, Hiroyuki; Sato, Yoichi; Baba, Yoriaki

Abstract: A guidance and control system for a "mouse-guided aircraft" is introduced. It can fly through waypoints that are designated by clicks of a pointing device. The guidance law is calculated using a trajectory-tracking approach for landing and the pure pursuit guidance law for take-off and waypoint flying. A dynamic inversion controller generates the guidance forces. This paper describes the guidance and control system of this "mouse-click guided aircraft" and simulation results.

Keywords: pure pursuit,waypoint,trajectory tracking,dynamic inversion

Digital Object Identifier (DOI): 10.3182/20070625-5-FR-2916.00016

Conference: 17th IFAC Symposium on Automatic Control in Aerospace (2007)

Location: ICT, Universitas Studii Tolosana, France

Start Date: Mon Jun 25 2007 - End Date: Fri Jun 29 2007

Page Numbers: 85-90

Authors: Simani, S.; Bonfe, M.; Castaldi, P.; Geri, W.

Abstract: In this work, a model-based procedure exploiting analytical redundancy for the detection and isolation of faults on a multivariable linear dynamic process is presented. The main point of the paper consists of exploiting a disturbance decoupling scheme in connection with dynamic filter design procedure for diagnostic purpose. It is shown that the suggested approach to fault diagnosis is in particular advantageous in terms of solution complexity and performance. Moreover, the presented method is especially useful when robust solutions are considered for minimising the effects of modelling errors and noise, while maximising fault sensitivity. In order to verify the robustness of the solution achieved, the proposed design has been experimented with the data of a simulated aircraft model in the presence of both measurement and modelling errors. Finally, extensive simulations of the test-bed process and Monte Carlo analysis are the tools used for assessing the overall capabilities of the developed FDI scheme, when compared also with different data-driven diagnosis methods.

Keywords: fault detection & isolation,input & output sensors,aerospace application,polynomial methods,filter design

Digital Object Identifier (DOI): 10.3182/20070625-5-FR-2916.00017

Conference: 17th IFAC Symposium on Automatic Control in Aerospace (2007)

Location: ICT, Universitas Studii Tolosana, France

Start Date: Mon Jun 25 2007 - End Date: Fri Jun 29 2007

Page Numbers: 91-96

Authors: Cieslak, J.; Henry, D.; Zolghadri, A.; Goupil, P.

Abstract: This paper presents a Fault Tolerant Control (FTC) strategy to provide a highly reliable reconfigurable control capacity for safety critical systems in faulty situations. The paper describes mainly the status of an on-going research work which is undertaken within GARTEUR FM-AG(16)2 Action Group. The developed techniques are applied to a faulty scenario of a realistic nonlinear benchmark of a large transport aircraft. The goal is to provide a "self-repairing" capability to enable the pilot to land the aircraft safely in the event of a stabilizer fault. Once the fault is detected by the Fault Detection and Isolation (FDI) unit, a fault compensation loop is activated. A key feature of the proposed strategy is that the design of FTC loop is done independently of the nominal autopilot and the nominal Flight Control System (FCS) in place. Nonlinear simulation results demonstrate the capability and viability of the proposed active FTC scheme.

Keywords: fault tolerant control,fault detection and isolation,flight control,nonlinear system

Digital Object Identifier (DOI): 10.3182/20070625-5-FR-2916.00018

Conference: 17th IFAC Symposium on Automatic Control in Aerospace (2007)

Location: ICT, Universitas Studii Tolosana, France

Start Date: Mon Jun 25 2007 - End Date: Fri Jun 29 2007

Page Numbers: 97-102

Authors: Delannoy, Stephane

Abstract: Despite its extreme measurements, the A380 sets the standard of piloting. To achieve the challenge, piloting tasks require dynamic roll control surfaces motions, which can excite strongly the flexible structure of the aircraft. Impact could be a bad level of comfort, for crew and passengers. The roll kinematics developed for the A380 ensures for dynamic orders without exciting the structure nor degrading performances. The principle is to use differently each aileron, according to its particular roll efficiency and ability to excite flexible modes. The result looks like an amazing ailerons waltz, which makes A380 extremely precise, in a very high level of comfort.

Keywords: aircraft,control laws,kinematics,structural properties

Digital Object Identifier (DOI): 10.3182/20070625-5-FR-2916.00019

Conference: 17th IFAC Symposium on Automatic Control in Aerospace (2007)

Location: ICT, Universitas Studii Tolosana, France

Start Date: Mon Jun 25 2007 - End Date: Fri Jun 29 2007

Page Numbers: 103-108

Authors: Muhammad, Hari; Sembiring, Javensius; Jenie, Said D.

Abstract: This paper will discuss the development of an automatic flight control system of Wing in Surface Effect Craft (WiSE). Since the vehicle must fly at very low altitude to gain an improved lift to drag ratio, the altitude-holding system is designed to hold the desired optimal altitude. The design for the altitude holding system is done by using the classical control law of gain scheduling. The gains of three different altitudes are determined by analysing the root locus diagram. Some simulation results are presented and evaluated in this paper.

Keywords: surface effect,automatic control system,longitudinal stability,simulation

Digital Object Identifier (DOI): 10.3182/20070625-5-FR-2916.00020

Conference: 17th IFAC Symposium on Automatic Control in Aerospace (2007)

Location: ICT, Universitas Studii Tolosana, France

Start Date: Mon Jun 25 2007 - End Date: Fri Jun 29 2007

Page Numbers: 109-114

Authors: Hillgren, Robert

Abstract: The JAS 39 Gripen is a light weight multirole combat fighter. It has delta canard configuration with all moving canards. It has negative inherent stability in the longitudinal axes for improved performance. It has a full time three channel digital fly by wire Flight Control System (FCS). The FCS uses angle of attack, pitch rate and normal acceleration to stabilize the aerodynamically unstable aircraft in the longitudinal axes. To provide the pilot with maximum aircraft performance in every situation, without extra attention to air intake/engine envelope limits, structural overloading or departure situations, the JAS 39 Gripen has inbuilt flight control system limit functions such as angle of attack-, normal load factor-, sideslip- and roll rate limit functions, which will make the JAS 39 Gripen carefree to manoeuvre. If the pilot by mistake ends up in a low speed situation with a high aircraft nose attitude and high angle of attack, the JAS 39 Gripen FCS will automatically return the aircraft from high attitude angles, high angle of attack back to the normal angle of attack flight envelope. In order to demonstrate the JAS 39 Gripen carefree and automatic return to normal flight envelope capabilities with all types of external store configurations, extensive simulations and flight test programs have been performed, divided in a phase using an aircraft with an anti stall chute mounted and a final verification flight test phase with a production aircraft from the Swedish Air Force. Furthermore a wake vortex detection and wake vortex transient reduction flight control system has been developed and flight tested.

Keywords: aircraft control,flight control

Digital Object Identifier (DOI): 10.3182/20070625-5-FR-2916.00021

Conference: 17th IFAC Symposium on Automatic Control in Aerospace (2007)

Location: ICT, Universitas Studii Tolosana, France

Start Date: Mon Jun 25 2007 - End Date: Fri Jun 29 2007

Page Numbers: 115-120

Authors: Schonhoff, A.; Friedrich, M.; Harth, K.; Jarasch, G.; Momberg, M.; Scharer, S.; Wetteborn, D.

Abstract: The JAS 39 Gripen is a light weight multirole combat fighter. It has delta canard configuration with all moving canards. It has negative inherent stability in the longitudinal axes for improved performance. It has a full time three channel digital fly by wire Flight Control System (FCS). The FCS uses angle of attack, pitch rate and normal acceleration to stabilize the aerodynamically unstable aircraft in the longitudinal axes. To provide the pilot with maximum aircraft performance in every situation, without extra attention to air intake/engine envelope limits, structural overloading or departure situations, the JAS 39 Gripen has inbuilt flight control system limit functions such as angle of attack-, normal load factor-, sideslip- and roll rate limit functions, which will make the JAS 39 Gripen carefree to manoeuvre. If the pilot by mistake ends up in a low speed situation with a high aircraft nose attitude and high angle of attack, the JAS 39 Gripen FCS will automatically return the aircraft from high attitude angles, high angle of attack back to the normal angle of attack flight envelope. In order to demonstrate the JAS 39 Gripen carefree and automatic return to normal flight envelope capabilities with all types of external store configurations, extensive simulations and flight test programs have been performed, divided in a phase using an aircraft with an anti stall chute mounted and a final verification flight test phase with a production aircraft from the Swedish Air Force. Furthermore a wake vortex detection and wake vortex transient reduction flight control system has been developed and flight tested.

Keywords:

Digital Object Identifier (DOI): 10.3182/20070625-5-FR-2916.00022

Conference: 17th IFAC Symposium on Automatic Control in Aerospace (2007)

Location: ICT, Universitas Studii Tolosana, France

Start Date: Mon Jun 25 2007 - End Date: Fri Jun 29 2007

Page Numbers: 121-128

Authors: Didenko, Yury; Dolotovsky, Alexander; Gorelov, Sergey; Ivakha, Valery; Motovilov, Vladimir; Tarasov, Alexey; Chochiev, Victor

Abstract: Optimization of handling qualities for all the flight conditions. Angle of attack and normal load factor limitation. Pitch and bank angle limitation. Maximum speed and Mach number limitation. Tail damage protection for take-off. Hands free attitude hold mode. Compensation of changes in aircraft configuration. Engine thrust compensation. Thrust asymmetry compensation. Auto turn coordination. Auto trimming. Rudder deflection limitation. Direct Mode particularities.

Keywords: aircraft control,control laws,astatic systems,static systems,controllability,compensation

Digital Object Identifier (DOI): 10.3182/20070625-5-FR-2916.00023

Conference: 17th IFAC Symposium on Automatic Control in Aerospace (2007)

Location: ICT, Universitas Studii Tolosana, France

Start Date: Mon Jun 25 2007 - End Date: Fri Jun 29 2007

Page Numbers: 129-134