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.

scholarly journals Impacts of Deflection Nose on Ballistic Trajectory Control Law

2014 ◽  
Vol 2014 ◽  
pp. 1-6 ◽  
Author(s):  
Bo Zhang ◽  
Shushan Wang ◽  
Mengyu Cao ◽  
Yuxin Xu
Keyword(s):  
Control System ◽  
Motion Control ◽  
Flight Control ◽  
Calculation Model ◽  
Trajectory Control ◽  
Control Law ◽  
Flight Control System ◽  
Theory Of Motion ◽  
Ballistic Trajectory ◽  
Exterior Ballistics

The deflection of projectile nose is aimed at changing the motion of the projectile in flight with the theory of motion control and changing the exterior ballistics so as to change its range and increase its accuracy. The law of external ballistics with the deflectable nose is considered as the basis of the design of a flight control system and an important part in the process of projectile development. Based on the existing rigid external ballistic model, this paper establishes an external ballistic calculation model for deflectable nose projectile and further establishes the solving programs accordingly. Different angle of attack, velocity, coefficients of lift, resistance, and moment under the deflection can be obtained in this paper based on the previous experiments and emulation researches. In the end, the author pointed out the laws on the impaction of external ballistic trajectory by the deflection of nose of the missile.

Special issue “Flight control law design”

1999 ◽  
Vol 3 (3) ◽  
pp. 111-113
Author(s):  
Georg Grübel ◽  
Jean-François Magni
Keyword(s):  
Flight Control ◽  
Control Law ◽  
Special Issue

Design of sliding mode flight control system for a flexible aircraft

2021 ◽  
pp. 095441002110455
Author(s):  
Majeed Mohamed ◽  
Madhavan Gopakumar
Keyword(s):  
Control System ◽  
Rigid Body ◽  
Flight Control ◽  
High Speed ◽  
Sliding Mode ◽  
Flight Mechanics ◽  
Frequency Separation ◽  
Flight Control System ◽  
Flexible Aircraft ◽  
Aircraft Dynamics

The evolution of large transport aircraft is characterized by longer fuselages and larger wingspans, while efforts to decrease the structural weight reduce the structural stiffness. Both effects lead to more flexible aircraft structures with significant aeroelastic coupling between flight mechanics and structural dynamics, especially at high speed, high altitude cruise. The lesser frequency separation between rigid body and flexible modes of flexible aircraft results in a stronger interaction between the flight control system and its structural modes, with higher flexibility effects on aircraft dynamics. Therefore, the design of a flight control law based on the assumption that the aircraft dynamics are rigid is no longer valid for the flexible aircraft. This paper focuses on the design of a flight control system for flexible aircraft described in terms of a rigid body mode and four flexible body modes and whose parameters are assumed to be varying. In this paper, a conditional integral based sliding mode control (SMC) is used for robust tracking control of the pitch angle of the flexible aircraft. The performance of the proposed nonlinear flight control system has been shown through the numerical simulations of the flexible aircraft. Good transient and steady-state performance of a control system are also ensured without suffering from the drawback of control chattering in SMC.

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