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RC PLANE WITH SLATS AND FLAPS AEROMODELLING CLUB IIT ...

RC PLANE WITH SLATS AND FLAPS AEROMODELLING CLUB IIT ...

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<strong>RC</strong> <strong>PLANE</strong> <strong>WITH</strong><br />

<strong>SLATS</strong> <strong>AND</strong> <strong>FLAPS</strong><br />

SCIENCE <strong>AND</strong> TECHNOLOGY COUNCIL<br />

<strong>AEROMODELLING</strong> <strong>CLUB</strong><br />

<strong>IIT</strong> KANPUR<br />

PROJECT BY –<br />

ARPIT KHUNTETA<br />

S<strong>AND</strong>EEP SINGH<br />

POONAM RAUT<br />

ANSHITA AGRAWAL


INSPIRATION :<br />

WE WERE THINKING ABOUT INCREASING THE LIFT OF THE <strong>PLANE</strong>. BY<br />

INCREASING THE ANGLE OF ATTACK LIFT CAN BE INCREASED. SO WE<br />

THOUGHT THAT IF WE COULD MAKE MOVABLE <strong>SLATS</strong> THEN IT WILL SERVE<br />

OUR PURPOSE. HENCE WE DECIDED TO MAKE MOVABLE <strong>SLATS</strong> <strong>AND</strong><br />

SEA<strong>RC</strong>HED DIFFERENT MECHANISMS OF MOVABLE <strong>SLATS</strong> <strong>AND</strong> FINALLY<br />

DESIGNED OUR OWN MECHANISM!.<br />

WE ARE PLANNING IF WE CAN GET SOME STASICAL DATA USING SOME<br />

SENSORS, DURING ITS FLIGHT, SO AS TO SEE HOW PRACTICALLY SLATES ARE<br />

USEFUL.<br />

DETAILS ABOUT THE <strong>PLANE</strong><br />

1. WING :<br />

<br />

WE USED DESIGNFOIL SOFTWARE TO DECIDE THE AIRFOIL<br />

SHAPE OF THE WING. AIRFOIL IS SHAPE OF THE CROSS SECTION<br />

OF THE WING.<br />

WE CHOSE NACA 3415 WHERE<br />

# 3 IS MAX HEIGHT AS A PE<strong>RC</strong>ENTAGE OF CHORD.<br />

# 40 IS MAX CAMBER LOCATION AS A PE<strong>RC</strong>ENTAGE OF CHORD.<br />

AN AIRFOIL WHICH IS IS NOT SYMMETRIC IS CALLED CAMBER.<br />

# 15 IS MAX AIRFOIL THICKNESS AS A PE<strong>RC</strong>ENTAGE OF CHORD.<br />

CHORD LENGTH OF AIRFOIL : 25 cm<br />

TOTAL WING SPAN : 150 cm<br />

TOTAL AIRFOILS USED 14 <strong>WITH</strong> EQUAL SPACING.<br />

WE USED 3 mm BALSA FOR AIRFOILS.


WE CONNECTED ALL AIRFOILS THROUGH CONNECTING RODS.<br />

TWO CONNECTING RODS WERE THERE AT LEADING <strong>AND</strong><br />

TRAILING EDGES <strong>AND</strong> ‘T’ & ‘I’ SHAPED CONNECTING RODS<br />

<strong>WITH</strong>IN THE AIRFOIL.<br />

WE MADE THE WINGS IN TWO PARTS <strong>AND</strong> THEN JOINT THE<br />

THEM BY LAYERS OF BALSA TO GIVE IT PROPER STRENGH. WE<br />

USED 6 SHEETS OF 3 mm BALSA TO MAKE THESE JOINTS.


WE JOINT TWO ROUND STYROFORM AT EITHER ENDS OF THE<br />

WING TO GIVE IT PROPER SHAPE <strong>AND</strong> USED TAPES TO GIVE IT<br />

STRENGTH.<br />

WE COVERED THE <strong>PLANE</strong> BY PLASTIC COVER.<br />

2.<strong>SLATS</strong> :<br />

# WE MADE <strong>SLATS</strong> BY USING STYROFORM <strong>AND</strong> USED TAPING TO<br />

GIVE IT STENGTH. IT WAS A FREE H<strong>AND</strong> SHAPING BY S<strong>AND</strong> PAPER.<br />

# THE SHAPE OF THE <strong>SLATS</strong> ACCORDING TO MEASUREMENTS OF<br />

AIRFOIL.


SLAT MECHANISM:<br />

WE USED A SMALL PIECE OF PLYWOOD <strong>AND</strong> HINGED IT TO THE LEADING<br />

EDGE OF WING THROUGH CLIPS SO THAT IT CAN MOVE INDEPENDENT OF<br />

OTHER PART OF WING.<br />

WE ATTACHED THIS ROD TO A SERVO SO THAT IT CAN CONTROL ITS<br />

MOVEMENT .


USES OF MOVABLE <strong>SLATS</strong> :<br />

1. <strong>SLATS</strong> INCREASE THE EFFECTIVE CHORD LENGTH OF <strong>AND</strong> THUS<br />

INCREASE THE LIFT COEFFICIENT. The lift coefficient is equal to<br />

• is the lift force,<br />

• is fluid density<br />

• is true airspeed( speed of the body relative to a static point on the<br />

earth's surface)<br />

• is dynamic pressure, and<br />

• is planform area.


2. <strong>SLATS</strong> ALSO HELP IN DELAYING FLOW SEPERATION.<br />

3. THE LEADING EDGE <strong>SLATS</strong> ALLOW THE STEEP CLIMB ANGLE UPTO<br />

30 – DEGEES.


<strong>FLAPS</strong>:<br />

# WE MADE <strong>FLAPS</strong> BY USING STYROFORM <strong>AND</strong> FREE H<strong>AND</strong> SHAPING <strong>WITH</strong><br />

S<strong>AND</strong> PAPER. WE USED TAPING TO GIVE IT PROPER STRENGH. WE MADE IT<br />

CONTINUOUS FOR STABILITY.<br />

# WE JOINED THE FALPS TO THE WING BY PLASTIC HINGES.<br />

USES OF <strong>FLAPS</strong>:<br />

1. <strong>FLAPS</strong> INCREASE THE SWEPT AREA <strong>AND</strong> HENCE THE LIFT<br />

GENERATED IS INCREASED.


2. EXTENDED <strong>FLAPS</strong> INCREASE THE DRAG COEFFICIENT WHICH<br />

HELPS IN DECREASING THE SPEED OF THE <strong>PLANE</strong> DURING<br />

L<strong>AND</strong>ING.<br />

THE FUSELAGE OF THE <strong>PLANE</strong>:<br />

WE USED CORO FOR FUSELAGE CONSTRUCTION <strong>AND</strong> STRENGTHENED IT BY<br />

DOUBLING THE LAYERS AT THE BASE.THE SPECIFICATIONS ARE AS FOLLOWS-<br />

Width-10cm<br />

Max. Height-10cm


THE SHAPE OF THE FUSELAGE WAS MADE SUCH THAT IT CAN SUPPORT<br />

WEIGHT OF THE WING PROPERLY .<br />

SO WE GAVE ANGLES TO LATER PORTION OF FUSELAGE . THE FUSELAGE WAS<br />

DIVIDED INTO THREE PARTS .THE LATER PART WAS STRENGHTHENED BY FILLING<br />

IT <strong>WITH</strong> STYROFORM.<br />

FOR THE FORMER PART WE USED PLY WOOD TO FIX THE MOTOR <strong>AND</strong><br />

ATTATCHED IT BY USING MOLTEN PLASTIC.<br />

WE ALSO USED PLY IN INNER PARTS OF FUSELAGE.<br />

<strong>AND</strong> TO PROVIDE PROPER SUPPORT TO THE HORIZONTAL <strong>AND</strong> VERTICAL<br />

STABILIZER WE SUPPORTED CORO BY BALSA WOOD.<br />

THE L<strong>AND</strong>ING GEAR WAS PLACED IN SAME LINE AS OF WING NEAR THE CENRE<br />

OF GRAVITY OF THE <strong>PLANE</strong>.<br />

WE PROVIDED REQUIRED STRENGH AT THE L<strong>AND</strong>ING GEAR POSITION BY<br />

USING PLY ON BOTH INSIDE <strong>AND</strong> OUTSIDE OF THE FUSELAGE WHICH<br />

HELPED IN DISTRIBUTION<br />

OF LOAD UNIFORMLY.


HORIZONTAL <strong>AND</strong> VERTICAL STABILIZERS :<br />

WE USED 6mm BALSA WOOD FOR VERTICAL <strong>AND</strong> HORIZONTAL STABILIZER .<br />

STABILIZERS WERE SHAPED <strong>WITH</strong> INNER PART BROADER <strong>AND</strong> OUTER PART<br />

NARROWER.<br />

THE STABILIZERS WERE MADE HOLLOW TO REDUCE WEIGHT AS MUCH AS<br />

POSSIBLE.<br />

WE FIXED THEM INTO THE SLOTS MADE IN REAR PART OF FUSELAGE .<br />

TO PREVENT AIR FLOW THROUGH THE STABILIZERS , WE COVERED THEM<br />

<strong>WITH</strong> PLASTIC SHEETS <strong>AND</strong> TIGHTENED IT USING AIR BLOWER.<br />

ELEVATOR:<br />

ELEVATORS WERE MADE IN RHOMBUS SHAPE <strong>AND</strong> WAS MOVED BY<br />

ATTATCHING IT VIA PLASTIC HINGES TO THE HORIZONTAL STABILIZER.THEY WERE<br />

MOVED TO PROVIDE PROPER DIRECTION TO <strong>PLANE</strong> .


RUDDER:<br />

RUDDER WAS ALSO MADE IN RHOMBUS SHAPE BUT WAS CONNECTED TO<br />

VERTICAL STABILIZER.IT WORKED IN SAME WAY AS ELEVATOR.RUDDER USED TO<br />

MOVE LEFT <strong>AND</strong> RIGHT MOTION.


SERVOS:<br />

WE USED 6 SERVOS IN THIS <strong>PLANE</strong>. TWO SERVOS EACH FOR RUDDER<br />

<strong>AND</strong> ELEVATOR, TWO FOR <strong>SLATS</strong> ,<strong>AND</strong> TWO FOR <strong>FLAPS</strong>. WE USED HINGES<br />

<strong>AND</strong> RODS TO CONNECT IT TO THE RESPECTIVE PARTS <strong>AND</strong> CONTROL THE<br />

MOVEMENTS.<br />

WE USED ‘Y’ CONNECTOR FOR THE MOVEMENT OF <strong>FLAPS</strong> SO THAT<br />

IT CAN ACT BOTH AS <strong>FLAPS</strong> <strong>AND</strong> ALLERONS.<br />

WE USED MOLTEN PLASTIC TO CONNECT SERVOS TO <strong>PLANE</strong>.


ELECTRONICS IN THE <strong>PLANE</strong>:<br />

2600mah lipo battery<br />

9gm servo<br />

NTM electric motor 1100kv<br />

30amp ESC<br />

11X6 propeller<br />

connectors<br />

PROBLEMS FACED:<br />

1. DECIDING SLAT MECHANISM :<br />

FIRSTLY WE THOUGHT OF A DIFFERENT MECHANISM BUT IT DIDN’T<br />

WORKED OUT PROPERLY . SO WE SWITCHED TO ANOTHER<br />

MECHANISM.<br />

2. MINIMIZING WEIGHT:<br />

WE FACED THE MAJOR PROBLEM IN MINIMIZING THE WEIGHT OF<br />

<strong>PLANE</strong>. SO WE AVOIDED MAKING MOST OF THE PARTS SOLID<br />

3. STRENGTHNING OF FUSELAGE:<br />

IT TOOK A LOT OF TIME IN DECIDING WHERE TO GIVE MORE<br />

STRENGH.<br />

4. IN ASSEMBLY OF HORIZONTAL <strong>AND</strong> VERTICAL STABILIZER:<br />

HINGES WERE NOT SUFFICIENTLY STRONG SO WE USED TO REPLACE<br />

IT REPEATEDLY.


SOU<strong>RC</strong>ES OF INFORMATION:<br />

*GOOGLE<br />

*<strong>RC</strong> GROUP FORUM<br />

*OUR COORDINATORS

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