Ask Question, Ask an Expert

+1-415-315-9853

info@mywordsolution.com

Ask Mechanical Engineering Expert

Assignment: Isolation and Fault Detection for Lateral Flight of an UAV
 
Introduction:

Fault tolerance is very significant for aircraft flight control.  The majority of the faults take place in the actuators and sensors onboard the aircraft.  Once a fault has occurred the aircraft could become uncontrollable and be hazardous to passengers and crew.  This assignment is to examine the effects of sensor faults on the lateral dynamics of an Unmanned Aerial Vehicle.

Background
Lateral Dynamics

The Lateral Dynamics of any aircraft are defined in terms of the Body-fixed velocities and corresponding Earth-fixed orientation (see Figure).

226_figure lateral dynamics.png

 

In this specific case the velocities are roll rate (p) and yaw rate (r).  All other Body-fixed dynamics are regarded as constant (e.g. surge velocity) or zero.  The effects of such velocities on to the initially fixed Earth-fixed axes are represented through the orientation of the aircraft.

These are the roll angle (φ) and yaw angle (ψ).  In addition, the affect of sideslip on the aircraft is included in the form of the sideslip angle (β).

The corresponding inputs to the lateral dynamics of the aircraft are the aileron deflection (δa) and the rudder deflection (δr).  The ailerons control the roll motion and the rudder controls the heading or yaw. The Lateral Dynamics of an UAV can be represented by the following differential equations:

520_equation.png

 

Here the translational velocities are find outd in m/s, rotational velocities in rad/s and the angles in radians.  The constant value for the surge velocity is taken to be U0 = 30 m/s.

In addition to the flight dynamics, this aircraft representation also consists of the dynamics of the aileron and rudder actuators.  Both actuators have a maximum amplitude deflection of 25 degrees and a maximum rate limit of 5 degrees/second.

Faults in Lateral Dynamics

The faults in the Lateral Dynamics of an aircraft can be either multiplicative or additive. The multiplicative faults occur in the dynamics of the aircraft and can be caused by changes to the aircraft itself throughout flight.   These types of faults are not considered here. Instead, additive faults caused by the sensors in the system will be the main focus of this assignment.  In particular faults which occur on the heading channel which are added to the sensed dynamics from the aircraft shall be the subject of this study.

Problem Specification

The following stages are expected to be performed in this assignment:

problem1.  Construct a continuous time simulation of the Lateral Dynamics of the UAV using zero initial conditions.

problem2.  Simulate a suitable man oeuvre where changes in heading can be observed (e.g. zig-zag).

problem3.  Simulate three separate stepwise faults in the heading channel of magnitudes 2, 5 and 10 degrees.

problem4.  Simulate a separate drift wise fault in the heading channel.

problem5.  Analyses the effect of these separate faults.

problem6.  Using a suitable limit checking method, detect these faults in the system.

problem7.  Using a suitable fault diagnosis method, diagnose these faults.

problem8.  Repeat this investigation with simulated white noise of amplitude ±5degree included in the heading output of the system.

problem9.  describe how the FDI system has to be altered to accommodate the existence of noise.

problem10. Comment on the influence of the faults and the FDI system on the Lateral Dynamics if a heading control system was employed.

Mechanical Engineering, Engineering

  • Category:- Mechanical Engineering
  • Reference No.:- M9547

Have any Question? 


Related Questions in Mechanical Engineering

Determine the tip deflection of a beam with linear varying

Determine the tip deflection of a beam with linear varying width b(x), constant height h, length L, and elastic modulus E due to tip load P. Write the answer in terms of the maximum width b L = b(L). Also determine the n ...

A rosette composed of three strain gages measures strain at

A rosette composed of three strain gages measures strain at a point on the surface of a flat sheet of annealed stainless steel loaded in plane stress. The strains measured (numbers correspond to strain gages in the figur ...

The force applied to a nut in a nutcracker is larger than

The force applied to a nut in a nutcracker is larger than the force P applied to the handles. Model the top element of the nutcracker as a beam as shown, and find the forcce on the nut as a function of P and lengths a an ...

Part 1- heat1 the is used to express absolute temperatures

Part 1- Heat 1. The _______ is used to express absolute temperatures in the English system of measurement. A. Rankine scale B. Celsius scale C. Kelvin scale D. Fahrenheit scale 2. A silver bar 0.125 meter long is subject ...

You need a reort if 10 pages and above the report about

You need a reort if 10 pages and above. the report about colorimeter specificly measuring spesific heat. anything you need will be provided. format sample has been will be provided. and a report sapmle will be provided t ...

I need research paper of 3 pages about any topics in

I need research paper of 3 pages about any topics in Thermodynamics. 1. Benedictine Orphanage and a new medical building in Tanzania are in need of power supply.  Please design a system which provides power economically ...

Projectdesign a tube bank that will increase the

Project Design a tube bank that will increase the temperature of a 1200 CFM flow of air from 35°F to 100°F. Assume a constant pressure of 1atm. Each tube will have a diameter of 0.5in and a length of 24in. The tube confi ...

Design design all members of the 6 span truss each span is

Design: Design all members of the 6 span truss each span is 12 ft long, the height of the truss is 16 feet shown if w = 10,000 pounds. The allowable maximum tensile stress P/A is 1000 psi where P is the force in the memb ...

Determine the effective moment and vertical shear force

Determine the effective moment and vertical shear force that would be required to replicate the effect of the three bar forces in Problem 1.15. Problem 1.15: For the truss shown, find the bar forces at the section indica ...

A simply supported beam 5 m long is loaded with a 20 n

A simply supported beam 5 m long is loaded with a 20 N downward force at a point 4 m from the left support. The second moment of area of the cross-section of the beam is 4I 1 for segment AB and I 1 for the remainder of t ...

  • 4,153,160 Questions Asked
  • 13,132 Experts
  • 2,558,936 Questions Answered

Ask Experts for help!!

Looking for Assignment Help?

Start excelling in your Courses, Get help with Assignment

Write us your full requirement for evaluation and you will receive response within 20 minutes turnaround time.

Ask Now Help with Problems, Get a Best Answer

WalMart Identification of theory and critical discussion

Drawing on the prescribed text and/or relevant academic literature, produce a paper which discusses the nature of group

Section onea in an atwood machine suppose two objects of

SECTION ONE (a) In an Atwood Machine, suppose two objects of unequal mass are hung vertically over a frictionless

Part 1you work in hr for a company that operates a factory

Part 1: You work in HR for a company that operates a factory manufacturing fiberglass. There are several hundred empl

Details on advanced accounting paperthis paper is intended

DETAILS ON ADVANCED ACCOUNTING PAPER This paper is intended for students to apply the theoretical knowledge around ac

Create a provider database and related reports and queries

Create a provider database and related reports and queries to capture contact information for potential PC component pro