scholarly journals Research on Air Flight Simulation Control Law of Large Aircraft

2020 ◽  
Vol 1678 ◽  
pp. 012032
Author(s):  
Junbin You
Keyword(s):  
Flight Simulation ◽  
Control Law ◽  
Simulation Control ◽  
Large Aircraft

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.

Coupled CFD/GNC Modeling for the Basic Finner Projectile with Closed Loop

2014 ◽  
Vol 541-542 ◽  
pp. 1478-1482
Author(s):  
Ke Xi ◽  
Chao Yan ◽  
Yu Huang ◽  
Wen Wang
Keyword(s):  
Closed Loop ◽  
Moving Boundary ◽  
Stokes Equations ◽  
Engineering Application ◽  
Flight Simulation ◽  
Navier Stokes ◽  
Control Law ◽  
Navier Stokes Equations ◽  
Motion Equations ◽  
Flow Solver

The virtual flight simulation of the Basic Finner projectile has been investigated through coupling solving unsteady Navier-Stokes equations, rigid-body six degree-of-freedom motion equations, guidance, navigation and control law. The flow solver uses a finite-volume method based on structure grid with dual time stepping, the chimera method is used to simulate relative motions, the fourth-order Runger-Kutta method is used to solve the motion equations. A closed loop feedback control law with PID control is required for the elevator to attain the commanded deflection. The predictions show that the PID parameters for the controller must be correctly selected to obtain the proper response. Simulation results show that the virtual flight simulation platform that we developed is capable of solving the complicated unsteady flows with moving boundary, has a strong applicability to engineering application.

Research on Technology of Thrust Asymmetry Lateral Compensation for Large Aircraft

2011 ◽  
Vol 383-390 ◽  
pp. 1256-1261 ◽  
Author(s):  
Meng Ji ◽  
Ju Jiang ◽  
Wen Xue ◽  
Zhuo Xun Lin
Keyword(s):  
Numerical Simulation ◽  
Dynamic Characteristics ◽  
New Technology ◽  
Mathematic Model ◽  
Control Law ◽  
Simulation Results ◽  
Controllability Conditions ◽  
Large Aircraft

Thrust asymmetry is dangerous for aircraft, especially in the phases of approach and landing. This paper proposes a new technology to compensate the thrust asymmetry in lateral of large aircraft. The dynamic characteristics of aircraft with asymmetric thrust are firstly analyzed in the paper. Then, the controllability conditions and balanced flight attitude in the case of thrust asymmetry are studied. Based on the mathematic model of Airbus 300, a thrust asymmetry lateral compensator is designed for the phases of approach and landing to ensure the safety of approach and landing. Numerical simulation results show that the designed compensator (control law) can compensate the asymmetric thrust very well.

Helicopter Maneuver Flight Simulation and Control Law Design

2012 ◽  
Vol 232 ◽  
pp. 517-520
Author(s):  
Jing Ying Wang
Keyword(s):  
Design Methodology ◽  
Flight Simulation ◽  
Control Law ◽  
Control Performance ◽  
Flying Qualities ◽  
Attitude Error ◽  
Model Helicopter ◽  
Acceleration Method ◽  
Simulation And Control ◽  
And Control

This paper presents a solution to helicopter maneuver flight simulation according to ADS33 flying qualities requirement standard. Associated with aerodynamics and control law design methodology, the proposed scheme achieved satisfactory control performance by analyzing helicopter attitude and control parameter variation law at certain operating condition. To level flight acceleration, method based on force and moment balance is analyzed. To pirouette maneuver, a segment linear approximated trajectory is developed for attitude and velocity stability. All objective function is based on minimizing position error and attitude error. For a single rotor four bladed model helicopter in pirouette maneuver, experimental results certified its efficiency.

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