scholarly journals Analysis Of Aircraft Control Input To Produce 3D Continuous Descent Approach (CDA) Trajectory With PY-FME

2021 ◽  
Vol 6 (1) ◽  
Author(s):  
Ronald Andryando ◽  
Neno Ruseno
Keyword(s):  
Fuel Consumption ◽  
Three Dimensional ◽  
Control Input ◽  
Aircraft Control ◽  
Descent Trajectory ◽  
Aircraft Controls ◽  
Python Programming ◽  
Time And Energy ◽  
Aircraft Data

One of proposed solutions to decrease the fuel consumption of a flight is by optimizing descent trajectory using Continuous Descent Approach (CDA). The focus of this research is to analyze the aircraft inputs used in CDA with several types of trajectories (straight and turning) in 3D (Three Dimensional). The CDA concept used is based on Time and Energy Managed Operation concept where the use of idle thrust is the key point. The research will also analyze the fuel consumption of aircraft in CDA trajectory and compare it with conventional descent trajectory. The methodology on this research is simulation using a Python programming module called Py-FME with Cessna-172 aircraft data. The result concluded that thrust and elevator input have significant effect on aircraft controls to achieved CDA. The research also found that CDA could reduce the fuel consumption by 67.6%.

Three-dimensional adaptive fixed-time guidance law against maneuvering targets with impact angle constraints and control input saturation

2021 ◽  
pp. 014233122110598
Author(s):  
Fei Ma ◽  
Yunjie Wu ◽  
Siqi Wang ◽  
Xiaofei Yang ◽  
Yueyang Hua
Keyword(s):  
Sliding Mode ◽  
Input Saturation ◽  
Three Dimensional ◽  
Fixed Time ◽  
Impact Angle ◽  
Guidance System ◽  
Control Input ◽  
Guidance Law ◽  
The Stability ◽  
And Control

This paper presents an adaptive fixed-time guidance law for the three-dimensional interception guidance problem with impact angle constraints and control input saturation against a maneuvering target. First, a coupled guidance model formulated by the relative motion equation is established. On this basis, a fixed-time disturbance observer is employed to estimate the lumped disturbances. With the help of this estimation technique, the adaptive fixed-time sliding mode guidance law is designed to accomplish accurate interception. The stability of the closed-loop guidance system is proven by the Lyapunov method. Simulation results of different scenarios are executed to validate the effectiveness and superiority of the proposed guidance law.

Research on the Application of Cellular Algorithm in 3D Modeling of Cartoon Characters

2014 ◽  
Vol 513-517 ◽  
pp. 1744-1747
Author(s):  
Feng Liu
Keyword(s):  
Design Method ◽  
Three Dimensional ◽  
Production Costs ◽  
3D Animation ◽  
Design Concepts ◽  
Three Dimensional Modeling ◽  
Modeling Software ◽  
High Production ◽  
Cartoon Characters ◽  
Time And Energy

The traditional design method of 3D animation modelings, by which can obtain attractive and precise 3D animation modelings, is to use three-dimensional modeling software such as Maya or 3D Max to draw directly. However, this method is faced with many problems, for instance, the lack of creativity, long design circle, high production costs, etc. For the problem of the lack of creativity, the reason is that animation designers are often subject to the limitation of the existing modelings and design concepts in the design process, therefore, they can not design creative modelings which are attractive and unforgettable enough. [For the problem of long design circle and high production costs, the reason is that although the 3D animation software are powerful, to skillfully master them not only requires users to have knowledge of computer technology and aesthetics at the same time, but also need a long learning process of modeling. Moreover, it takes the designers a lot of time and energy to design, draw and complete each modeling, and this will undoubtedly extend the design circle and increase the costs to some extent. Therefore, how to quickly and automatically generate creative 3D animation modelings has become a research focus of the present computer-aided creative design.

scholarly journals Mission Performance Simulation of Integrated Helicopter–Engine Systems Using an Aeroelastic Rotor Model

2013 ◽  
Vol 135 (9) ◽  
Author(s):  
Ioannis Goulos ◽  
Panagiotis Giannakakis ◽  
Vassilios Pachidis ◽  
Pericles Pilidis
Keyword(s):  
Fuel Consumption ◽  
Three Dimensional ◽  
Numerical Procedure ◽  
Engine Performance ◽  
Flight Dynamics ◽  
Flight Test ◽  
Integrated Approach ◽  
Operating Conditions ◽  
Main Rotor ◽  
Engine Systems

This paper presents an integrated approach, targeting the comprehensive assessment of combined helicopter engine designs within designated operations. The developed methodology comprises a series of individual modeling theories, each applicable to a different aspect of helicopter flight dynamics and performance. These relate to rotor blade modal analysis, three-dimensional flight path definition, flight dynamics trim solution, aeroelasticity, and engine performance. The individual mathematical models are elaborately integrated within a numerical procedure, solving for the total mission fuel consumption. The overall simulation framework is applied to the performance analysis of the Aérospatiale SA330 helicopter within two generic, twin-engine medium helicopter missions. An extensive comparison with flight test data on main rotor trim controls, power requirements, and unsteady blade structural loads is presented. It is shown that, for the typical range of operating conditions encountered by modern twin-engine medium civil helicopters, the effect of operational altitude on fuel consumption is predominantly influenced by the corresponding effects induced on the engine rather than on airframe rotor performance. The implications associated with the implicit coupling between aircraft and engine performance are discussed in the context of mission analysis. The potential to comprehensively evaluate integrated helicopter engine systems within complete three-dimensional operations using modeling fidelity designated for main rotor design applications is demonstrated. The proposed method essentially constitutes an enabler in terms of focusing the rotorcraft design process on designated operation types rather than on specific sets of flight conditions.

scholarly journals Optimal Control of Diesel Engines: Numerical Methods, Applications, and Experimental Validation

2014 ◽  
Vol 2014 ◽  
pp. 1-21 ◽  
Author(s):  
Jonas Asprion ◽  
Oscar Chinellato ◽  
Lino Guzzella
Keyword(s):  
Optimal Control ◽  
Numerical Methods ◽  
Fuel Consumption ◽  
Diesel Engines ◽  
Large Scale ◽  
Experimental Validation ◽  
Control Unit ◽  
Pollutant Emissions ◽  
Control Input ◽  
Dynamic Optimisation

In response to the increasingly stringent emission regulations and a demand for ever lower fuel consumption, diesel engines have become complex systems. The exploitation of any leftover potential during transient operation is crucial. However, even an experienced calibration engineer cannot conceive all the dynamic cross couplings between the many actuators. Therefore, a highly iterative procedure is required to obtain a single engine calibration, which in turn causes a high demand for test-bench time. Physics-based mathematical models and a dynamic optimisation are the tools to alleviate this dilemma. This paper presents the methods required to implement such an approach. The optimisation-oriented modelling of diesel engines is summarised, and the numerical methods required to solve the corresponding large-scale optimal control problems are presented. The resulting optimal control input trajectories over long driving profiles are shown to provide enough information to allow conclusions to be drawn for causal control strategies. Ways of utilising this data are illustrated, which indicate that a fully automated dynamic calibration of the engine control unit is conceivable. An experimental validation demonstrates the meaningfulness of these results. The measurement results show that the optimisation predicts the reduction of the fuel consumption and the cumulative pollutant emissions with a relative error of around 10% on highly transient driving cycles.

scholarly journals Mission Performance Simulation of Integrated Helicopter–Engine Systems Using an Aeroelastic Rotor Model

2013 ◽  
Author(s):  
Ioannis Goulos ◽  
Panos Giannakakis ◽  
Vassilios Pachidis ◽  
Pericles Pilidis
Keyword(s):  
Fuel Consumption ◽  
Three Dimensional ◽  
Numerical Procedure ◽  
Engine Performance ◽  
Flight Dynamics ◽  
Flight Test ◽  
Integrated Approach ◽  
Operating Conditions ◽  
Main Rotor ◽  
Engine Systems

This paper presents an integrated approach, targeting the comprehensive assessment of combined helicopter–engine designs, within designated operations. The developed methodology comprises a series of individual modeling theories, each applicable to a different aspect of helicopter flight dynamics and performance. These relate to rotor blade modal analysis, three-dimensional flight path definition, flight dynamics trim solution, aeroelasticity and engine performance. The individual mathematical models are elaborately integrated within a numerical procedure, solving for the total mission fuel consumption. The overall simulation framework is applied to the performance analysis of the Aérospatiale SA330 helicopter within two generic, twin-engine medium helicopter missions. An extensive comparison with flight test data on main rotor trim controls, power requirements and unsteady blade structural loads is presented. It is shown that, for the typical range of operating conditions encountered by modern twin-engine medium civil helicopters, the effect of operational altitude on fuel consumption is predominantly influenced by the corresponding effects induced on the engine, rather than on airframe–rotor performance. The implications associated with the implicit coupling between aircraft and engine performance, are discussed in the context of mission analysis. The potential to comprehensively evaluate integrated helicopter–engine systems within complete three-dimensional operations, using modeling fidelity designated for main rotor design applications, is demonstrated. The proposed method essentially constitutes an enabler in terms of focusing the rotorcraft design process on designated operation types, rather than on specific sets of flight conditions.

Takagi–Sugeno Fuzzy Predictive Control for a Class of Nonlinear System With Constrains and Disturbances

2015 ◽  
Vol 10 (5) ◽  
Author(s):  
Bin Wang ◽  
Jianwei Zhang ◽  
Delan Zhu ◽  
Diyi Chen
Keyword(s):  
Nonlinear System ◽  
Nonlinear Systems ◽  
Predictive Control ◽  
Three Dimensional ◽  
Fuzzy Model ◽  
Control Input ◽  
Chen System ◽  
External Disturbances ◽  
Takagi Sugeno ◽  
Fuzzy Predictive Control

This paper investigates the fuzzy predictive control for a class of nonlinear system with constrains under the condition of noise. Based on the fuzzy linearization theory, a class of nonlinear systems can be described by the Takagi–Sugeno (T–S) fuzzy model. The T–S fuzzy model and predictive control are combined to stabilize the proposed class of nonlinear system, and the detailed mathematical derivation is given. Moreover, the designed controller has been optimized even if the system is constrained by output and control input, or perturbed by external disturbances. Finally, numerical simulations including three-dimensional Lorenz system, four-dimensional Chen system and five-dimensional nonlinear system with external disturbances are presented to demonstrate the universality and effectiveness of the proposed scheme. The approach proposed in this paper is simple and easy to implement and also provides reference for relevant nonlinear systems.

Perceptual and motor learning underlies human stick-balancing skill

2015 ◽  
Vol 113 (1) ◽  
pp. 156-171 ◽  
Author(s):  
Kwee-Yum Lee ◽  
Nicholas O'Dwyer ◽  
Mark Halaki ◽  
Richard Smith
Keyword(s):  
Motor Learning ◽  
Input Parameter ◽  
Center Of Mass ◽  
Three Dimensional ◽  
Fine Motor ◽  
Radius Of Gyration ◽  
Visual Localization ◽  
Control Input ◽  
Fine Motor Skill ◽  
Finger Movements

We investigated the acquisition of skill in balancing a stick (52 cm, 34 g) on the fingertip in nine participants using three-dimensional motion analysis. After 3.5 h of practice over 6 wk, the participants could more consistently balance the stick for longer durations with greatly reduced magnitude and speed of stick and finger movements. Irrespective of level of skill, the balanced stick behaved like a normal noninverted pendulum oscillating under greater-than-gravity torque with simple harmonic motion about a virtual pivot located at the radius of gyration above the center of mass. The control input parameter was the magnitude ratio between the torque applied on the stick by the participant and the torque due to gravity. The participants utilized only a narrow range of this parameter, which did not change with practice, to rotate the stick like a linear mass-spring system. With increased skill, the stick therefore maintained the same period of oscillation but showed marked reductions in magnitude of both oscillation and horizontal translation. Better balancing was associated with 1) more accurate visual localization of the stick and proprioceptive localization of the finger and 2) reduced cross-coupling errors between finger and stick movements in orthogonal directions; i.e., finger movements in the anteroposterior plane became less coupled with stick tip movements in the mediolateral plane, and vice versa. Development of this fine motor skill therefore depended on perceptual and motor learning to provide improved estimation of sensorimotor state and precision of motor commands to an unchanging internal model of the rotational dynamics.

Enhancement of performance of three-dimensional fiber metal laminates under low velocity impact – A coupled numerical and experimental investigation

2017 ◽  
Vol 21 (6) ◽  
pp. 2127-2153 ◽  
Author(s):  
Zohreh Asaee ◽  
Farid Taheri
Keyword(s):  
Three Dimensional ◽  
Absorption Capacity ◽  
Low Velocity Impact ◽  
Low Velocity ◽  
Fiber Metal Laminates ◽  
Velocity Impact ◽  
Finite Element Software ◽  
Fiber Metal ◽  
Time And Energy ◽  
The Impact

The main objective of the present study is to examine the level of enhancement in performance of three-dimensional fiber metal laminates (3DFML) under low velocity impact, when reinforced by different types of reinforcing face-sheets (i.e. fiberglass or carbon). Three layup configurations of the fabrics are considered in this investigation. The impact response of each of these configurations is assessed numerically using ABAQUS/Explicit, a commercially available finite element software. Specifically, each configuration’s impact capacity, deformation, contact time, and energy absorption capacity are evaluated. The numerical results are validated by comparison against experimental results. Moreover, a semi-empirical equation is developed for evaluating the impact capacity of such panels, as a function of impact energy, capable of accounting the influence of any type of reinforcement. Finally, the most efficient reinforced three-dimensional fiber metal laminates are identified based on their impact strength with respect to their overall weight and cost.

scholarly journals Boundary Control of A Flexible Rotatable Manipulator in Three-Dimensional Space With Input Constraints and Actuator Faults

2021 ◽  
Author(s):  
Jiacheng Wang ◽  
Jinkun Liu ◽  
Fangfei Cao
Keyword(s):  
Boundary Control ◽  
Dimensional Space ◽  
Three Dimensional ◽  
Flexible Manipulator ◽  
Control Input ◽  
Input Constraints ◽  
Actuator Faults ◽  
Flexible System ◽  
Actuator Failures ◽  
Three Dimensional Space

Abstract In this paper, the boundary control problem of a flexible rotatable manipulator in Three-Dimensional space with input constraints and actuator faults is taken into account. The Hamilton principle is introduced to derive the dynamic model represented by partial differential equations (PDEs), which can accurately reflect the characteristics of the distributed parameters of the flexible system. The hyperbolic tangent function is adopted to ensure that the control input is within a bounded range, and the projection-based adaptive laws are designed to estimate the degree of unknown actuator failures. Satisfying the input constraints, the system can still remain stable when the actuator failures ensue. The flexible manipulator can track the required angle, and both the elastic deformation and the deformation rate are effectively suppressed simultaneously. The numerical simulation results further illustrate the effectiveness of the proposed controller.

scholarly journals The Design of Compact Robotic-Assisted Needle Position System with MPC-Based Remote Control

Complexity ◽  
2020 ◽  
Vol 2020 ◽  
pp. 1-13
Author(s):  
Jing Guo ◽  
Yi Liu ◽  
Jin Wang ◽  
Chao Zeng ◽  
Jie Huang ◽  
...  
Keyword(s):  
Control Method ◽  
Kinematic Model ◽  
Three Dimensional ◽  
Percutaneous Biopsy ◽  
Target Point ◽  
Model Parameters ◽  
Control Input ◽  
Control Performance ◽  
Robot System ◽  
Needle Position

This article introduces the design and control performance of a lightweight, flexible, 4-degree-of-freedom (DOF) parallel robot for percutaneous biopsy guided by computed tomography (CT). At present, the CT guidance method allows surgeons to quickly locate the lesion area; however, it is necessary to manually adjust the position of the puncture needle for insertion. In this paper, a three-dimensional assisted method is used to infer the control input required to reach the target point through the kinematic model of the robot. A Kalman filter is designed to estimate model parameters and obtain a more accurate model. To further improve the control performance of the robot system, a model-based control method—the model predictive control (MPC) controller—is used to increase the accuracy of the needle position in the developed robot system. In this way, medical efficiency is improved while reducing the burden on the surgeon.

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