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Osama Saaid Mohamady

NI Technology in Aerospace Applications

Personal Experiences “Using NI Technology”

• 10 years of LabVIEW and NI hardware experience.

• Participated in Ramses statue transportation.

• Developing of several acoustics and HIL control educational experiments

2:50 PM NIDays 2015

Personal Experiences “Using NI Technology”

• Academic research projects using NI Technology:

• Industrial projects using NI Technology: Building a mufflers transmission loss measurement system for

Caterpillar USA Sound power assessment of some fan cool units for EGAT group Building a Sound Transmission Loss measurement

system according to ASTM E90 for the Material Lab in Dubai. Developing of an Aircraft black box

2:50 PM NIDays 2015

Active Flow control

Aircraft Parameter Identification

UAV Autopilot

Wind Turbine

QRFR

Sound Tracking

Sonic Crystal

Smart Paint Sensor

AST Lab

• Aeronautical Systems Technology Laboratory in the aerospace engineering department that aims to design, manufacture, and test the aeronautical systems and subsystems.

• The AST Lab facilities:

Manufacture facilities

2:50 PM NIDays 2015

AST Lab

• The AST Lab facilities:

Measurements facilities

(Aeronautical sensors, Signal conditioners, NI PXI system)

Computational facilities

2:50 PM NIDays 2015

NI Technology in Aerospace Applications

• Sound Tracking and Intercepting a Moving Target “Using NI software”

• Variable Pitch Horizontal Axis Wind Turbine “Using NI software and hardware”

• Active Wing: The Smart Airfoil “Using NI software and hardware”

• Aircraft Parameters Identification “Using NI software and hardware”

• UAV Autopilot ”Using NI software and hardware”

2:50 PM NIDays 2015

Sound Tracking and Intercepting a Moving Target

“Using NI software”

• NI products: LabVIEW

• By: Prof, Gamal Mahmoud Sayed El-Bayoumi

Associate Prof, Mohammed Sayed Bayoumi

Associate Prof, Basman El-Hadidi

Assistant Lecturer, Osama Mohamady

2:50 PM NIDays 2015

NIDays 2015 2:50 PM



NIDays 2015 2:50 PM

Simulation

Experimental

Array of sensors design

Fourier transform parameters

Filtering

Pure Pursuit

Stationary source

Moving source

Intercept a stationary source

Intercept a moving source





• Supersonic target speed simulation

2:50 PM NIDays 2015



• Experimental

2:50 PM NIDays 2015

0 2 4 6 8 10 12 14 16 18 20-60

-40

-20

0

20

40

60

time (sec)

sourc

e a

ngle

(deg)

measurement of fixed source angle

measured angle

filtered angle with filtering parameters R=250, Q=0.5

4 6 8 10 12 14 16 18 20 -60

-40

-20

0

20

40

60

time (sec)

Tra

cked A

ngle

(deg)

Measured Angle

Filtered Angle

Actual Angle



• Control and guidance

2:50 PM NIDays 2015

using gain schedule PD controller

0 5 10 15 0

10

20

30

40

50

60

70

z=2 k=0.16

time (sec)

car

angle

(deg)

0 5 10 15 0

10

20

30

40

50

60

70

time (sec)

car

angle

(deg)

schedual gain z=2, 0.2 k=0.16, 0.016

0 5 10 15 0

10

20

30

40

50

60

70

time (sec)

car

angle

(deg)

0 1 2 3 4 5 6-1

0

1

2

3

4

5

6

7

x

y

Measured interceptor path 1



Theoretical interceptor path

Simulated interceptor path

Target path

Variable Pitch Horizontal Axis Wind Turbine

“Using NI software and hardware”

• Objectives: Design small variable pitch horizontal axis wind turbine Compare model results with experimental measurements Characterize the dynamic response Apply feedback control to regulate wind turbine rotary speed

• NI products: LabVIEW NI USB-6221

• By: Associate Prof, Basman El-Hadidi Assistant Lecturer, Islam ElQatary Assistant Lecturer, Osama Mohamady

2:50 PM NIDays 2015



2:50 PM NIDays 2015

2:50 PM NIDays 2015

15o Pitch change



Active Wing The Smart Airfoil


• Objectives: The technology developed is to

test a prototype “Smart Airfoil” that can detect flow separation, control the flow and postpone stall.

• NI products: LabVIEW NI PXI system

• By: Associate Prof, Basman El-Hadidi Assistant Lecturer, Islam ElQatary Assistant Lecturer, Osama Mohamady

2:50 PM NIDays 2015



2:50 PM NIDays 2015

• An active slat is developed to increase the lift and delay the separation for a DU96-W180 airfoil.

• The Lift was increased for all positive angles of attack.

• The direction and speed of actuator rotation can influence the aerodynamic performance.

Blowing

Suction Port

Actuator



2:50 PM NIDays 2015

• To control the actuator, an encoder was used as a feedback

• A total of 14 unsteady pressure measurements were taken (9 on upper surface)

α = 0o , black lines for 175 rpm

clockwise actuation



2:50 PM NIDays 2015

Pressure and normalized velocity measurements at Re=50,000

α = 15o , green lines for 350 rpm

clockwise actuation

α = 15o , green lines for 175 rpm

Anti-clockwise actuation

Aircraft Parameters Identification


• Objectives: Calculating the aircraft parameters and derivatives. Identification of the aircraft parameters to validate the

calculated parameters.

• NI products: LabVIEW NI PXI system

• By: Prof, Gamal Mahmoud El-Bayoumi Associate Prof, Basman El-Hadidi Assistant Lecturer, Osama Mohamady Assistant Lecturer, Mohannad Draz Assistant Lecturer, Ahmed Khalil

2:50 PM NIDays 2015



• Ground testing using wind tunnel

• Mantis UAV was tested

2:50 PM NIDays 2015

• Longitudinal Stability and control Derivatives



2:50 PM NIDays 2015

-10 -5 0 5 10 15 20-0.6

-0.4

-0.2

0

0.2

0.4

0.6

0.8

1

1.2

[deg]

CL

ANSYS

Wind-Tunnel, 4 m/s

Wind-Tunnel, 8 m/s

Wind-Tunnel, 16 m/s

-10 -5 0 5 10 15 20-0.4

-0.3

-0.2

-0.1

0

0.1

0.2

0.3

[deg]

Cm

ANSYS

Wind-Tunnel, 4 m/s

Wind-Tunnel, 8 m/s

Wind-Tunnel, 16 m/s

-10 -5 0 5 10 15 200

0.05

0.1

0.15

0.2

0.25

[deg]

CD

ANSYS

Wind-Tunnel, 4 m/s

Wind-Tunnel, 8 m/s

Wind-Tunnel, 16 m/s

-15 -10 -5 0 5 10 15-0.5

-0.4

-0.3

-0.2

-0.1

0

0.1

0.2

0.3

0.4

e [deg]

Cm

At 16 m/s

ANSYS, = 0 [deg]

Wind-Tunnel, = -8 [deg]

Wind-Tunnel, = -4 [deg]

Wind-Tunnel, = 0 [deg]







2:50 PM NIDays 2015

-4 -2 0 2 4 6 8 10 12-0.14

-0.12

-0.1

-0.08

-0.06

-0.04

-0.02

0

0.02

[deg]

CY

= 0 [deg]

ANSYS

Wind-Tunnel, 4 m/s

Wind-Tunnel, 8 m/s

Wind-Tunnel at 16 m/s

-4 -2 0 2 4 6 8 10 12-0.005

0

0.005

0.01

0.015

0.02

0.025

[deg]

Cn

= 0 [deg]

ANSYS

Wind-Tunnel, 4 m/s

Wind-Tunnel, 8 m/s


-4 -2 0 2 4 6 8 10 12-0.14

-0.12

-0.1

-0.08

-0.06

-0.04

-0.02

0

0.02

[deg]

CY

At 16 m/s

ANSYS, = 0 [deg]

ANSYS, = 8 [deg]

Wind-Tunnel, alpha = 0 [deg]

Wind-Tunnel, alpha = 8 [deg]

-4 -2 0 2 4 6 8 10 12-0.12

-0.1

-0.08

-0.06

-0.04

-0.02

0

0.02

0.04

[deg]

CY

= 8 [deg]

ANSYS

Wind-Tunnel, 4 m/s

Wind-Tunnel, 8 m/s


• Lateral Stability and control Derivatives

• Objectives: To make an UAV operate as a fully autonomous

system. Build a ground control station

• NI products: LabVIEW NI sbRIO

• By: Prof, Gamal Mahmoud El-Bayoumi Assistant Lecturer, Osama Mohamady Assistant Lecturer, Mohannad Draz

UAV Autopilot ”Using NI software and hardware”

2:50 PM NIDays 2015


2:50 PM NIDays 2015

• ground control station


2:50 PM NIDays 2015

Why Using NI Technology?

2:50 PM NIDays 2015

• Ability to reuse existing equipment investments

• Integration between LabVIEW and NI hardware

• Highly customizable user interfaces

• Target various architectures (Windows, real-time OS, FPGA) with the same graphical approach

2:50 PM NIDays 2015

Questions

osama saaid mohamady - niarabia.ni.com/sites/default/files/said- technology in aerospace...•10...

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