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Safety and efficiency of carrier flight deck are two important factors that have great effects on the comprehensive performance of carrier. This paper studies on path planning algorithms for carrier aircraft on the deck in consideration of safety and efficiency requirements. Firstly, a kinematic model of the carrier aircraft, obstacle avoidance models and boundary constraints are proposed. Subsequently,...
Aircraft loss-of-control (LOC) is the major contributing factor to fatal accidents and is characterised by the manoeuvring of aircraft beyond the allowable flight envelopes. This paper proposes an online learning and inference based method for aircraft flight envelope estimation in order to prevent aircraft LOC. The lift and drag coefficients of the aircraft are identified online using an extended...
A sliding mode based active center of gravity control law is designed for the aircraft with center of gravity varying during flight. As the basis, the general scheme of the active center of gravity control system is proposed, and the mathematic model of aircraft center of gravity varying with fuel transfer is established. Then, the center of gravity control law based on sliding mode control theory...
Active center of gravity control can transfer fuel among many fuselage fuel tanks to effectively optimize aircraft center of gravity and gain the potential economic performance benefits. In-flight possible failures in the fuel system may generate direct influences on aircraft center of gravity control. The aim of this article is to investigate the influence of partial fuel transfer line leak on the...
Aircraft center of gravity control is an important technology to gain potential performance benefits. In-flight center of gravity control is usually based on a fuel transfer system which enables fuel to be transferred among fuselage fuel tanks and then adjust aircraft center of gravity. The aim of this article is to systematically investigate the influences of partial fuel pump failures on the CG...
Aircraft centre of gravity (C.G.) is important for aircraft safety and performance. This paper proposes the use of Gaussian process regression (GPR) models for the estimation of the C.G. location of fixed-wing aircraft. The major benefit of using a GPR model is that it is a data-based approach explicitly tackling uncertainties caused by the quality and quantity of the data as well as sensor measurement...
This paper discusses the scheme and design method for UCAV autonomous/semi-autonomous control system. According to the investigation of the traditional tactical flight maneuvers and the existing air combat simulators, a mission-oriented control scheme is proposed to fulfill the autonomous/semi-autonomous requirements. A library including 9 maneuvers is designed by which complex tasks could be formed...
Structural damage will cause a sudden variation of aircraft's quality, center of gravity and aerodynamic characteristics, as well as the destruction of longitudinal symmetry, thus bringing strong coupling. These pose serious threat to flight security. The present paper studies a kind of damaged aircrafts by presenting the nonlinear 6-DOF model of structural damaged aircraft and analyzing its dynamic...
Focusing on the abrupt parameter variation of the aircraft dynamic characteristics brought by the wing damage, an observer based multivariable reference adaptive control(O-MRAC) method is presented. Firstly, The Multivariable Model Reference Adaptive Control (M-MRAC) method is studied to compensate the abrupt variations in the state matrix, control matrix and the constant uncertainty. In order to...
The problem of designing transition flight controller via improved adaptive neural network dynamic inversion for Canard Rotor/Wing (CRW) UAV is studied. The transition control strategy from rotary-wing mode to fixed-wing mode is derived according to the flight characteristic analysis. The controller is composed of trajectory outer-loop and attitude inner-loop. The dynamic inversion method is used...
In this paper, a control method combining Active Disturbance Rejection Control (ADRC) and optimal control is discussed for large aircraft landing attitude control with disturbances, such as turbulence, gusts and modeling errors. On the basis of the extended state observer (ESO) inherited from ADRC, our design exploits the Linear Quadratic Regular (LQR) replacing the original Proportional-Derivation...
The accuracy of control allocation algorithms relies on control effectiveness matrix. To address this issue, this paper focuses on the robustness of control allocation. Several existing robust control allocation algorithms are analyzed at first. Then performance evaluation criteria for robust control allocation, which are designed for flight control, are proposed based on performance requirements...
Large scale variations in the mass or center of gravity (C.G.) pose serious problems for the control of aircraft in situations as heavy load airdrop on cargo aircraft, the airliners which employ the active C.G. control technology, aircraft with structural damages during the flight. To solve the problem of attitude control of such aircraft, a general model for the aircraft is established and a disturbance...
Active center of gravity (C.G.) control is a key technology of vehicle management system, which has been extensively used in various types of aircraft. With active C.G. control system, aircraft may deviate from its known dynamics due to the C.G. offset, thus bringing new problems to the existing flight control system. A new design approach of the attitude control system of aircraft with C.G. variations...
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