Integrated simulation model for preliminary aerodynamic, structural, and control-law design of aircraft

1999 ◽  
Author(s):  
Mark Drela
Keyword(s):  
Simulation Model ◽  
Control Law ◽  
Integrated Simulation ◽  
And Control

Multi-Mode Flight Control Simulation of UAV Based on Stateflow and GUI

2012 ◽  
Vol 241-244 ◽  
pp. 1545-1549
Author(s):  
Ning Zhang ◽  
Hua Wei Chen ◽  
Kai Yu Qin
Keyword(s):  
Remote Control ◽  
Simulation Model ◽  
Flight Control ◽  
Control Law ◽  
Control Logic ◽  
Control Instruction ◽  
And Control ◽  
Designing Method ◽  
Multi Mode ◽  
Navigation Strategies

Considering a UAV has different flight control modes, such as remote control instruction flight and auto-navigation flight, this paper uses modular designing method to describe the overall structure of simulation model, and based on the way of loading waypoint, focuses on discussing the control logic of auto-navigation flight. Furthermore, according to the flight control logic of UAV, the simulation model was built by using Stateflow, and combining with Matlab GUI, the remote control instruction was realized. The simulation results in the auto-navigation flight can effectually verify the correctness of the design of flight navigation strategies and control law. It is practical to build the simulation environment by using Stateflow and GUI technology.

Integrated Simulation Model of Rotor/Propeller Powered Aerobot in Steady Flight

2016 ◽  
Author(s):  
Wei Zhao ◽  
Zhenguo Wang
Keyword(s):  
Simulation Model ◽  
Cost Effective ◽  
Control Law ◽  
Integrated Simulation ◽  
Aerodynamic Interaction ◽  
Wake Model ◽  
Free Wake ◽  
Predictor Corrector ◽  
Coaxial Rotors ◽  
Good Agreement

In this paper, a cost-effective integrated simulation model for rotor/propeller driven aerobot is proposed based on the free wake model. It is helpful to provide aerodynamic input for preliminary control law design, especially for conceptual design at the beginning of a project. Apart from the computational efficient, the model proposed has two more advantages, grid-free and containing the aerodynamic interaction. The governing equation is the Laplacian Equation with the assumption of invisid, incompressible flow. The solver used is inspired by the well-known Pseudo-Implicit Predictor Corrector (PIPC) for the rotors. Two validation cases are carried out. Firstly, the simulation results for the Harrington coaxial rotors and the Hamilton coaxial propellers show good agreement with the experiment. The simulation of a 45° swept-back wing also goes well with the corresponding experiment. Before the end, a simulation for a transition state with 0° tilt angle for the Eagle Eye is used to show the aerodynamic interaction, which has more influence on the wings.

Research on Dynamic Characteristics and Control Method of Propelling Nozzle Based on MATLAB/AMESim Integrated Simulation

2020 ◽  
Author(s):  
Zhitao Wang ◽  
Shuoshuo Liu ◽  
Tielei Li ◽  
Shuying Li
Keyword(s):  
Simulation Model ◽  
Dynamic Characteristics ◽  
Control Method ◽  
Aerodynamic Force ◽  
Pi Controller ◽  
Adjustment Process ◽  
Hydraulic Actuator ◽  
Integrated Simulation ◽  
Self Tuning ◽  
And Control

Abstract In this paper, the integrated simulation method is used to study the dynamic characteristics and control methods of propelling nozzle when it is coupled with the gas generator. The overall simulation model of the double-shaft hybrid exhaust turbofan engine was established by the volume inertia method under MATLAB/Simulink platform. A simulation model of the propelling nozzle hydraulic actuator was established under the AMESim platform. These two models are transmitted through the “Propelling Nozzle Throat Kinematics Simulation Module”, thus achieving the construction of the integrated simulation model. Then, based on the integrated model, a fuzzy self-tuning PI controller is developed. The quantization factor is obtained through optimization to further optimize the coupled dynamic response of the propelling nozzle. The simulation results show that the integrated simulation model captures the special change of aerodynamic force during the nozzle area adjustment process, which can more realistically show the working condition of the actuator. Controller design based on integrated simulation model is more reasonable. The fuzzy self-tuning PI controller used in this paper corrects the PI parameters online according to the fuzzy control rules, so that the hydraulic actuator of the nozzle formed by numerical simulation has faster response, and good dynamic characteristics. It has certain guiding significance for follow-up research.

A Mathematical Model Including Mechanical Structure, Hydraulic and Control of LHDS

Robotica ◽  
2021 ◽  
pp. 1-16
Author(s):  
Guoliang Ma ◽  
Kaixian Ba ◽  
Zhiwu Han ◽  
Zhengguo Jin ◽  
Bin Yu ◽  
...  
Keyword(s):  
Simulation Model ◽  
Hydraulic System ◽  
Inverse Dynamics ◽  
Hydraulic Drive ◽  
Operation Time ◽  
Variable Load ◽  
Mechanical Structure ◽  
Load Characteristics ◽  
Common Problems ◽  
And Control

SUMMARY In this paper, mathematical models of kinematics, statics and inverse dynamics are derived firstly according to the mechanical structure of leg hydraulic drive system (LHDS). Then, all the above models are integrated with MATLAB/Simulink to build the LHDS simulation model, the model not only considers influence of leg dynamic characteristics on hydraulic system but also takes into account nonlinearity, variable load characteristics and other common problems brought by hydraulic system, and solves compatibility and operation time which brought by using multiple software simultaneously. The experimental results show the simulation model built in this paper can accurately express characteristics of the system.

Rotorcraft Lateral-Directional Oscillations: The Anatomy of a Nuisance Mode

2021 ◽  
Author(s):  
Dheeraj Agarwal ◽  
Linghai Lu ◽  
Gareth D. Padfield ◽  
Mark D. White ◽  
Neil Cameron
Keyword(s):  
Simulation Model ◽  
Simulation Models ◽  
Flight Test ◽  
Flight Simulation ◽  
Stability And Control ◽  
Systems Research ◽  
Control Derivatives ◽  
Research Aircraft ◽  
Level Of Understanding ◽  
And Control

High-fidelity rotorcraft flight simulation relies on the availability of a quality flight model that further demands a good level of understanding of the complexities arising from aerodynamic couplings and interference effects. One such example is the difficulty in the prediction of the characteristics of the rotorcraft lateral-directional oscillation (LDO) mode in simulation. Achieving an acceptable level of the damping of this mode is a design challenge requiring simulation models with sufficient fidelity that reveal sources of destabilizing effects. This paper is focused on using System Identification to highlight such fidelity issues using Liverpool's FLIGHTLAB Bell 412 simulation model and in-flight LDO measurements from the bare airframe National Research Council's (Canada) Advanced Systems Research Aircraft. The simulation model was renovated to improve the fidelity of the model. The results show a close match between the identified models and flight test for the LDO mode frequency and damping. Comparison of identified stability and control derivatives with those predicted by the simulation model highlight areas of good and poor fidelity.

Integrative Modeling Platform for Design and Control of an Adaptive Wind Turbine Blade

2018 ◽  
Author(s):  
Hamid Khakpour Nejadkhaki ◽  
John F. Hall ◽  
Minghui Zheng ◽  
Teng Wu
Keyword(s):  
Simulation Model ◽  
Wind Turbine ◽  
Real Time ◽  
Turbine Blade ◽  
Design Tool ◽  
Real Time Control ◽  
Time Control ◽  
Partial Load ◽  
And Control

A platform for the engineering design, performance, and control of an adaptive wind turbine blade is presented. This environment includes a simulation model, integrative design tool, and control framework. The authors are currently developing a novel blade with an adaptive twist angle distribution (TAD). The TAD influences the aerodynamic loads and thus, system dynamics. The modeling platform facilitates the use of an integrative design tool that establishes the TAD in relation to wind speed. The outcome of this design enables the transformation of the TAD during operation. Still, a robust control method is required to realize the benefits of the adaptive TAD. Moreover, simulation of the TAD is computationally expensive. It also requires a unique approach for both partial and full-load operation. A framework is currently being developed to relate the TAD to the wind turbine and its components. Understanding the relationship between the TAD and the dynamic system is crucial in the establishment of real-time control. This capability is necessary to improve wind capture and reduce system loads. In the current state of development, the platform is capable of maximizing wind capture during partial-load operation. However, the control tasks related to Region 3 and load mitigation are more complex. Our framework will require high-fidelity modeling and reduced-order models that support real-time control. The paper outlines the components of this framework that is being developed. The proposed platform will facilitate expansion and the use of these required modeling techniques. A case study of a 20 kW system is presented based upon the partial-load operation. The study demonstrates how the platform is used to design and control the blade. A low-dimensional aerodynamic model characterizes the blade performance. This interacts with the simulation model to predict the power production. The design tool establishes actuator locations and stiffness properties required for the blade shape to achieve a range of TAD configurations. A supervisory control model is implemented and used to demonstrate how the simulation model blade performs in the case study.

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