PAPERS AND CONFERENCE PROCEEDINGS

Paper Title

Preliminary Sizing of an Agricultural Aircraft

Authors

Ismail Abdelrahman. Yousif^{1}and Mohammed Elhadi A. E.^{2}

Affiliation

1Researcher, Aeronautical Research Center, Sudan.
2 General Manager of Aeronautical Research Center, Associate Professor, Aeronautics Dept., College of Engineering, Karary University Sudan.

Contacts Details

1email This email address is being protected from spambots. You need JavaScript enabled to view it.
2e mailThis email address is being protected from spambots. You need JavaScript enabled to view it.

Conference Name

14^{th}International Conference on AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT  14– May 28  30, 2011, Military Technical College, Egypt.

No. of pages

8

Paper Abstract

This paper aims to preliminary size an agricultural aircraft that meets the agricultural requirements in Sudan and could be manufactured locally and be equipped with an engine that works with cheaper type of fuel (JetA1). The specifications have been obtained from existing similar aircraft designs working in Sudan then the standard design procedure has been reproduced. The aerodynamic parameters have been obtained using FLUENT. The primary results were found qualitatively acceptable but need extensive verification. Finally a UAV downscaled model has been constructed and a flight test has been carried out and the aircraft taxed, took off and landed safely. That indicated a good aircraft configuration.

Keywords

Agricultural aircraft, aircraft sizing, FLUENT, Scaledown model.


Paper Title

Preliminary Sizing of an Agricultural Aircraft

Authors

Ismail Abdelrahman. Yousif^{1}and Mohammed Elhadi A. E.^{2}

Affiliation

1Researcher, Aeronautical Research Center, Sudan.
2 General Manager of Aeronautical Research Center, Associate Professor, Aeronautics Dept., College of Engineering, Karary University Sudan.

Contacts Details

1email This email address is being protected from spambots. You need JavaScript enabled to view it.
2e mailThis email address is being protected from spambots. You need JavaScript enabled to view it.

Conference Name

14^{th}International Conference on AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT  14– May 28  30, 2011, Military Technical College, Egypt.

No. of pages

8

Paper Abstract

This paper aims to preliminary size an agricultural aircraft that meets the agricultural requirements in Sudan and could be manufactured locally and be equipped with an engine that works with cheaper type of fuel (JetA1). The specifications have been obtained from existing similar aircraft designs working in Sudan then the standard design procedure has been reproduced. The aerodynamic parameters have been obtained using FLUENT. The primary results were found qualitatively acceptable but need extensive verification. Finally a UAV downscaled model has been constructed and a flight test has been carried out and the aircraft taxed, took off and landed safely. That indicated a good aircraft configuration.

Keywords

Agricultural aircraft, aircraft sizing, FLUENT, Scaledown model.


Paper Title

Preliminary Design of the Tail Unit of a Newly Designed Agricultural Aircraft

Authors

Ahmed M. Jubartalla^{1}, M. Elhadi A. E.^{2}

Affiliation

1 Researcher, Aeronautical Research Center, Sudan.
2 General Manager of Aeronautical Research Center, Associate Professor, Aeronautics Dept., College of Engineering, Karary University Sudan.

Contacts Details

1 email This email address is being protected from spambots. You need JavaScript enabled to view it.
2 email This email address is being protected from spambots. You need JavaScript enabled to view it.

Conference Name

14^{th}International Conference on AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT  14– May 28  30, 2011, Military Technical College, Egypt.

No. of pages

14

Paper Abstract

This project work undertakes the task of analyzing stresses and preliminary designing of the tail structure members of a newly designed light agricultural aircraft. Schrenk’s method has been used for estimating the spanwise lift distribution, while the tail weight was assumed to be uniformly distribution along the span. Hence, the shear force and bending moment diagrams have been obtained. Accordingly, the working shear and bending stresses within the flight envelope have been calculated. The design has been based on the limit load while the maximum bending and shear values are encountered at the tail root, with the gust load being neglected. The bending and shear margins are found to be positive along the semispan/height, which shows good enough strength.

Keywords

Agricultural aircraft, Preliminary design, tail unit, Schrenk’s method.


Paper Title

Stability Analysis of a Light Aircraft Configuration using ComputationalFluid Dynamics

Authors

Mohammed Mahdi^{1}, Yasser A. Elhassan^{2}

Affiliation

1,2  Researcher, Aeronautical Research Center, Sudan.

Contacts Details

(1) email This email address is being protected from spambots. You need JavaScript enabled to view it.
Tel:+249123404305,
(2) e mailThis email address is being protected from spambots. You need JavaScript enabled to view it.

Conference Name

AEROTECHIV, Recent Advanced in Aerospace Technologies, Published in Journal of Applied Mechanics and Materials, Vol 225, pp 391396.Malaysia.

No. of pages

6

Paper Abstract

This work aims to simulate and study the flow field around SAFAT01 aircraft using numerical solution based on solving Reynolds Averaged NavierStokes equations coupled with Kω SST turbulent model.
The aerodynamics behavior of SAFAT01 aircraft developed at SAFAT aviation complex were calculated at different angles of attack and side slip angles. The x,y and z forces and moments were calculated at flight speed 50m/s and at sea level condition. Lift and drag curves for different angles of attack were plotted. The maximum lift coefficient for SAFAT01 was 1.67 which occurred at angle of attack 16^{o} and Maximum lift to drag ratio (L/D) was 14 which occurred at α=3^{o}, and the zero lift drag coefficient was 0.0342. Also the yawing moment coefficient was plotted for different side slip angles as well as rolling moment.
The longitudinal stability derivatives with respect to angle of attack, speed variation (u), rate of pitch (q) and time rate of change of angle of attack were calculated using obtained CFD results. Concerning lateral stability only side slips derivatives were calculated.
To validate this numerical simulation USAF Digital DATCOM is used to analyze this aircraft; a comparison between predicted results for this aircraft and Digital DATCOM indicated that this numerical simulation has high ability for predicting the aerodynamics characteristics

Keywords

Stability Derivatives, CFD, Control, Longitudinal Stability, Lateral Stability

Paper Title

Structural Analysis of Light Aircraft Wing Components

Authors

Abdelmunem Bushra^{1}, Mohammed Mahdi^{2} and Dr. Mohammed Elhadi^{3}

Affiliation

1 ,2–Researcher, Aeronautical Research Center, Sudan.
3 General Manager of Aeronautical Research Center, Associate Professor, Aeronautics Dept., College of Engineering, Karary University Sudan.

Contacts Details

(1) email This email address is being protected from spambots. You need JavaScript enabled to view it.
,
(2)emailThis email address is being protected from spambots. You need JavaScript enabled to view it.
,
(3) e mailThis email address is being protected from spambots. You need JavaScript enabled to view it.

Conference Name

AEROTECHIV, Recent Advanced in Aerospace Technologies, Published in Journal of Applied Mechanics and Materials, Vol 225, pp 201206. Malaysia.

No. of pages

6

Paper Abstract

The paper aims to demonstrate the structure analysis of StrutBraced wing for a typical manufactured LightAircraft by using FEM software (MSC.PATRAN/NASTRAN) and determine the safety margin in all of the wing components, which are useful to determine the structure strength requirements.
After creating the finite element model for all parts; the elements and materials properties were assigned and the model was fixed at spar root edge and strut brace end, then loaded by distributed inertia load and aerodynamic load, calculated using (CFD), acting at the ribs edge. Then, the model was submitted to NASTRAN for linear static analysis.
The obtained Stress Results and Safety Margin of each part were calculated and found to be acceptable.

Keywords

Structure analysis; strutbraced wing; FEM; PATRAN/NASTRAN

Paper Title

Computational Analysis of a truss type fuselage

Authors

Ismail Abderahman Yousif^{1}, Mohamed Abdelmageed M. Zein^{2} and Dr. Mohammedelhadi Ahmed Elsayed^{3}

Affiliation

1 Researcher, Aeronautical Research Center, Sudan.
2Coresearcher, Aeronautical Research Center, Sudan
3 General Manager of Aeronautical Research Center, Associate Professor, Aeronautics Dept., College of Engineering, Karary University Sudan.

Contacts Details

(1)email This email address is being protected from spambots. You need JavaScript enabled to view it.
,
(2)email,
(3) e mailThis email address is being protected from spambots. You need JavaScript enabled to view it.

Conference Name

AEROTECHIV, Recent Advanced in Aerospace Technologies, Published in Journal of Applied Mechanics and Materials, Vol 225, pp 183188. Malaysia.

No. of pages

6

Paper Abstract

This study was conducted to analyze the fuselage structure of safat 01, the fuselage geometry was modeled using a CAD (Computer Aided Design) program, the main dimensions were taken from 2D drawings related to the aircraft and some missing dimensions were extracted experimentally from a built aircraft, then a static analysis was conducted using FEM (Finite Element Method).
Principle stresses were found acceptable except for small region near the attachment between wing and fuselage, this region were subjected to some changes. Accordingly, the fuselage was reanalyzed and then principle stresses became acceptable. At the end it was recommended to design new attachment fittings between the fuselage and the wing. However, these results need extensive static test

Keywords

Structural analysis, static analysis, welded truss,, fuselage.

Paper Title

Computational Aerodynamics Analysis of a Light Aircraft

Authors

Mohammed Mahdi

Affiliation

Researcher, Aeronautical Research Center, Sudan,

Contacts Details

This email address is being protected from spambots. You need JavaScript enabled to view it.
Tel:+249915193162

Conference Name

15^{th}International Conference on AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT  15 – May 28  30, 2013, Military Technical College, Egypt.

No. of pages

8

Paper Abstract

This work aims to study and simulate the flow field around light a/c usingnumerical solution based on solving Reynolds Averaged NavierStokes equations coupledwith Kω SST turbulence model.
Solution strategy began by analyzing wing alone then analyzing the whole a/c configuration.This strategy allows studying the wing flow field carefully and analyzing the vortices whichoccur over the wing and capture their effective regions at critical design conditions like stallcondition. These regions were captured by plotting pressure contours and flow pathlines.
The aerodynamic behavior of this aircraft was investigated at different angles of attack andside slip angles. The x, y and z forces and moments were calculated at flight speed of 50m/sand at sea level conditions. Lift and drag curves for different angles of attack were plotted.
The maximum lift coefficient for this a/c was 1.67 which occurred at angle of attack 16o , themaximum lift to drag ratio (L/D) found to be 14 which occurred at α=3o, and the zero lift dragcoefficient was 0.0342. Also the yawing moment coefficient was plotted for different side slipangles as well as rolling moment.The longitudinal stability derivatives with respect to angle of attack, speed variation (u), pitchrate (q) and time rate of change of angle of attack were calculated using obtained CFD results.Regarding lateral stability only side slip derivatives were calculated.

Keywords

Aerodynamics analysis, CFD, static stability.

Paper Title

Structural Design of Agricultural Aircraft Fuselage

Authors

Ahmed M. Jubartalla&Isamil A. Yousif

Affiliation

1,2 Researcher, Aeronautical Research Center, Sudan,

Contacts Details

1 email This email address is being protected from spambots. You need JavaScript enabled to view it.
2email This email address is being protected from spambots. You need JavaScript enabled to view it.

Conference Name

15^{th}International Conference on AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT  15 – May 28  30, 2013, Military Technical College, Egypt.

No. of pages


Paper Abstract

This paper aims to calculate the fuselage loads, and analyzing the structure to determine the margin of safety.
Configuration of the aircraft was completed and frozen as addressed in a previous publication [1]. However, the aircraft should meet the agricultural requirements in Sudan. It could be manufactured locally and equipped with an engine that works with cheaper type of fuel (JetA1). Preliminary arrangement of structural component of fuselage has been done. Preliminary sizing for bulkhead, frames, longerons, stiffeners and skin has been conducted with great consideration for crew and systems integrated within fuselage such as agricultural and control systems.
FEM software of ABAQUS® used for structure modeling and analysis, hence the shear forces and bending moment diagrams have been obtained. Accordingly, the working shear and bending stresses within the flight envelope have been calculated.
The margin of safety is found to be positive along the fuselage structural parts, which shows good enough strength.

Keywords

Agricultural aircraft, Preliminary Design, Sizing, Fuselage, Structure, Hopper, Loading, Margin of safety, Numerical analysis and strength calculation
