Intelligent Pitch Controller Identification And Design

Torabi, Amir; Ahari, Amin Adine; Karsaz, Ali; Kazemi, Seyyed Hossin

doi:10.22436/jmcs.08.02.03

Cited by 12 publications

(11 citation statements)

References 16 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…This section provides a brief description on the modeling of pitch control longitudinal equation of aircraft, as a basis of a simulation environment for development and performance evaluation of the proposed controller technique [8][9]. The pitch control system considered in this work is shown in Fig.…”

Section: IImentioning

confidence: 99%

Performance Analysis of Aircraft Pitch Control By Linear Quadratic Regulator and Fuzzy Controller

Singh¹

2017

IJRASET

View full text Add to dashboard Cite

Today's aircraft consist of number of automatic controller that helps the airplane crew in airplane management and piloting the aircraft. Usually, the control strategies of aircraft can be grouped into two categories as follows: lateral and longitudinal control. In longitudinal control, the pitch angle has been employed for an aircraft system. Pitch of an aircraft may be described as a rotation around the lateral axis. An elevator is used to control pitch of aircraft which is located at the back of an airplane. So in this paper, a pitch control of an aircraft has been implemented by using Fuzzy controller. The stability of aircraft system is of major concern in real interface system. Thus, aircraft system must be accurate having stable response of aircraft system and should approaches to reference over a certain interval of time i.e. it should not oscillate over a long time. So this work exhibits the design of fuzzy control strategy for controlling the pitch angle of an aircraft. Two control strategies: Linear quadratic regulator (LQR) control and Fuzzy control strategies have been employed and compared. After that a comparative analysis of these control strategies has been done. The whole system has been implemented in MATLAB SIMULINK environment. Keywords: Pitch control, longitudinal l control, Lateral control, Fuzzy controller, linear quadratic regulator (LQR). I.INTRODUCTION Pitch control is a longitudinal control; therefore longitudinal model of an aircraft is used to design the pitch angle controller of an aircraft. Roll control is a lateral control. Therefore lateral model of an aircraft is required to design the roll angle controller of an aircraft. The roll angle is used to control the rolling motion of an aircraft. Elevator is used to control pitch of an aircraft and ailerons are used to control roll of an aircraft. The ultimate aim is to follow the elevator and ailerons command with minimum delay and maximum accuracy. To reduce the complexity of system, assume aircraft as a rigid body and aircraft's motion consist of a small deviation from its equilibrium flight condition [1]. In addition, the aircraft control system can be divided into two parts, namely longitudinal and lateral control [2]. In longitudinal control, the elevator controls pitch or the longitudinal motion of aircraft system whereas in lateral control lateral motion (roll and yaw) of aircraft system is controlled. Pitch of an aircraft may be described as a rotation around the lateral axis. It might be calculated as the angle between the direction of speed in a horizontal line and vertical plane Pitch of aircraft is control by elevator which usually situated at the rear of the airplane running parallel to the wing that houses the ailerons [3]. Elevator is used to control pitch or to control the tail planes of an aircraft which is located at the back of an airplane. The elevator pivoted at the rear of an aircraft work in pairs; when the right elevator goes up, the left elevator also goes up. The linear zed mathematical model is o...

show abstract

Section: IImentioning

confidence: 99%

Performance Analysis of Aircraft Pitch Control By Linear Quadratic Regulator and Fuzzy Controller

Singh¹

2017

IJRASET

View full text Add to dashboard Cite

show abstract

“…The model can be used to study the performance impact of different modes and/or configuration alternatives under different workloads, leading to advice for improving the system and software algorithm. Performance evaluation of a model may be done by simulating the model and collecting results [6][7][8][9].…”

Section: Validating the Approachmentioning

confidence: 99%

“…Outputs of the simulation are shown in display and scope. Outputs also in the form of discrete (1-warning and 0-no warning) [3][4][5][6][7].…”

Section: Top Level Modelmentioning

confidence: 99%

See 1 more Smart Citation

Optimization of Aircraft Pitch Trim Rate of Movement Using Model Based Approach and Improving the Software Algorithm

Rathinakumar¹,

Nanda²

2015

J Aeronaut Aerospace Eng

View full text Add to dashboard Cite

In safety critical systems such as aerospace, it becomes more important since the non-performance of the system as per the requirement may lead to a catastrophe. Also, the work-around to modify the design as per the requirements, generate code, obtain safety clearance from the authorized agency before porting to the target is very time consuming and a cumbersome approach.In this paper, we propose a model-based approach to improve the performance of the software algorithm and optimize the pitch trim movement before porting the code to the target. The effectiveness of the approach is demonstrated with a case study of aerospace domain. The approach encompasses the aircraft sub-system dynamics and the software which operates the sub-system. The analysis of the functionality with performance provides a high level of confidence in the software that is to be ported on to the target. The test crew can provide feedback on the overall functionality and performance of the software at the model-level. The proposed approach not only increases the efficacy of the process but also provides higher safety assurance earlier in the process.Pitch-trim is a critical sub-system of the aircraft which is modeled and the improved software algorithm is incorporated into the model for analyzing the overall functionality and performance of the sub-system. Based on the model simulation and analysis result, the changes in the algorithm were made and finally ported onto the target. The performance and functionality of the pitch-trim sub-system on the aircraft was as per the simulation analysis results indicating the correctness of the model and the proposed approach.

show abstract

“…Pitch control is a longitudinal control, therefore longitudinal model of an aircraft is used to design the pitch angle controller of an aircraft. In the past many researcher has done work to control the pitch, roll and yaw of an aircraft to stabilize an aircraft and this topic even now remains a challenging issue for present and future works [1], [3], [4], [5] and [9]. This work exhibits the design of control strategies for controlling pitch angle of an aircraft.…”

Section: Introductionmentioning

confidence: 99%

GA tuned LQR and PID controller for aircraft pitch control

Vishal

Ohri

2014

2014 IEEE 6th India International Conference on Power Electronics (IICPE)

View full text Add to dashboard Cite

In this paper linear quadratic Regulator (LQR) and Proportional integral derivative (PID) controllers are designed for pitch control system of an aircraft. Genetic Algorithm (GA) is used for tuning the parameter LQR and PID controllers. The controller design begins with the appropriate mathematical model to account the longitudinal motion of an aircraft. Simulation is done within the MATLAB and results for the pitch angle response of an aircraft are represented in step's response. LQR and PID controllers are associated with their parameters which can either be tuned manually or by optimized methods like genetic algorithms to get better control and enhancement in the performance. GA is the powerful tool in the field of global optimization to various problems. Here genetic algorithm is successfully applied for Pitch control of an aircraft using MATLAB simulation for tuning of LQR and PID controllers and thus optimized parameters values for the LQR and PID controllers are derived.

show abstract

Intelligent Pitch Controller Identification And Design

Cited by 12 publications

References 16 publications

Performance Analysis of Aircraft Pitch Control By Linear Quadratic Regulator and Fuzzy Controller

Performance Analysis of Aircraft Pitch Control By Linear Quadratic Regulator and Fuzzy Controller

Optimization of Aircraft Pitch Trim Rate of Movement Using Model Based Approach and Improving the Software Algorithm

GA tuned LQR and PID controller for aircraft pitch control

Contact Info

Product

Resources

About