Papers by Keyword: Flight Simulation

Abstract: As flying wing aircraft has no tail and adopts blended-wing-body design, most of flying wing aircrafts are directional unstable. Pitching moment couples seriously with rolling and yawing moment when control surfaces are deflected, bringing insecurity to landing stage. Numerical simulation method and semi-empirical equation estimate method were combined to obtain a high aspect ratio flying wing aircraft’s aerodynamic coefficients. Modeling and simulation of landing stage were established by MATLAB/Simulink. The control coupling effect on lift and drag characteristics and anti-crosswind landing capability was studied. The calculation results show that when the high aspect ratio flying wing aircraft was falling into the deceleration phase, appropriate to increase the opening angle of split drag rudder can reduce the trimming pitching moment deflection of pitch flap, thereby reduce the loss of lift caused by the deflection of pitch flaps. Flying wing aircraft can be rounded out successfully by using the pitch flap gently and steady. Both side-slip method and crabbed method can be applied to the landing of high aspect ratio flying wing aircraft in crosswind, the flying wing aircraft’s anti-crosswind landing capability was weakened by the control coupling effect of split drag rudder and elevon. Sideslip method was recommended in the crosswind landing of flying wing aircraft after calculation and analysis.

Abstract: This paper presents the development of a flight simulator for a fixed-wing propeller-driven UAV. A new architecture for UAV low-level functional units is presented. The work involves modeling main low-level units of the UAV, which includes modeling of aircraft lateral and longitudinal dynamics and controlling of flight-path states holding. Key characteristics for aerodynamics and propulsion properties are calculated. A nested PID loops are used to provide a low-level control necessary for intelligent control and mission planning and execution. Simulation results are demonstrated in order to validate the effectiveness of the flight simulator and thereby providing an infrastructure low-level abstraction platform that can be used for various multi-level algorithms testing.

Abstract: The flight process often in turbulence. Atmospheric turbulence causes flight bump, long time will cause damage to the aircraft structure fatigue. This paper establishes a model for atmospheric disturbance, flight simulation. Based on the aircraft through all kinds of atmospheric disturbance is studied. The use of embedded database and real-time simulation platform, built a run, in the PC machine can be used for dynamic model for real-time simulation of flight simulator.

Abstract: Based on analysis for characteristic of the motion configuration, the control strategy and control law used on the motion control system are presented. The controller in velocity tracking loop and location loop are respectively designed by frequency correcting method and normal control method which belongs to classical control theory. The problem of location control loop low velocity creeping is solved. A simulating experimentation demonstrates the effectiveness of the proposed approach.

Abstract: The servo control methods of 6-DOF motion configuration are researched. Based on analysis for characteristic of the motion configuration, the control strategy and control law used on the motion control system are presented. The controller in velocity tracking loop and location loop are respectively designed by frequency correcting method and normal control method which belongs to classical control theory. Sliding mode variable structure control method is presented for location control law designing, against the super low velocity creep caused by friction disturbance, so that the problem of location control loop low velocity creeping is solved, and a simulating experimentation demonstrate the effectiveness of the proposed approach.

Abstract: This paper introduces a new approach for the identification of linear state-space models of dynamical systems of arbitrary complexity. The identification procedure is described and applied for modeling aeroelastic response of helicopter main rotors. With the aim of developing a tool that might be conveniently applied for real-time simulations of helicopter flight dynamics, the state-space model considered is a reduced-order description of loads transmitted to the airframe due to hub motion and blade pitch controls. In order to validate the proposed approach, loads from the state-space, reduced-order model are compared with those predicted by the complete full-state, nonlinear rotor model for prescribed helicopter maneuvers.

Abstract: The servo control methods of motion configuration are researched. Based on analysis for characteristic of the motion configuration, the control strategy and control law used on the motion control system are presented. The controllers are respectively designed by frequency correcting method and normal control method which belongs to classical control theory. Sliding mode variable structure control method is presented for location control law designing, so that the problem of location control loop low velocity creeping is solved, and a simulating experimentation demonstrate the effectiveness of the proposed approach.

Abstract: Quadrocopter is an aerial vehicle platform which has become very popular among researchers in the recent past due to the advantages it offers over conventional helicopters. Quadrocopter is very simple structure, but it is inherently unstable from aerodynamics point of view. The first step before the control stage is presenting the adequate modeling of the system dynamic. This paper presents the dynamic model of quadrocopter as regarding to Newtons Laws with kinematic equations. Presented model is simulated with Matlab-Simulink for testing translational and rotational situations. And it is figured out that; presented model is acting like a real quadrocopter. Finally a PID controller designed for stabilize the altitude of modeled quadrocopter.

Abstract: The method to set up visual environment of flight simulation was studied with Open Scene Graph (OSG) technology, and it includes the method and steps to build three dimensional digital earth, the method to read out airport and aircraft model, the method to simulate meters in the cockpit of an aircraft, and the method to simulate an aircraft fly in the visual digital earth environment, etc. Then software was written in VC++ based on the methods and steps given in this paper. The running results of the software in a personal computer shows that OSG technology can build up realistic simulation environment of flight visualization, and it is very helpful to realize realistic feeling and immersion of flight vision simulation of an aircraft in three dimensional digital earth.

Abstract: The research of data model is a key technology in engineering flight simulation platform. This work analyses the engineering flight simulation platform’s present research situation and specific demands. Then we propose a data model in engineering flight simulation platform based on meta-data. The model shields the heterogeneity of system data and can build association between system data. At last, we finished the data management module in engineering flight simulation platform based on the model mentioned above, which proved that this data model has greater significance in realizing generality and expandability in engineering flight simulation platform.