What does the future hold for India regarding solar energy? Well, in this powerpoint presentation you'll get your answers.

1. FEASIBILITY REPORT ON SOLAR
PLANE

2. OBJECTIVE
• The amount of energy the sun sends towards our planet is 35000 times more
than we currently produce and consume.
• This energy can be easily harnessed for practical purposes.
• The objective of our report is to contribute to the cause of renewable energies to
demonstrate the importance of clean technologies for sustainable development.
• Solar impulse wants to mobilize this enthusiasm in favour of technologies that
will allow decrease demand.
• Our endeavour try to deal with the current state of art of empower the aviation
industry with solar power and the shortcomings and the future aspects.
• The aim is to study the possibility of solar powered aircrafts in the atmosphere
more efficiently.

3. INTRODUCTION
• A solar aircraft is the one which collects energy from the sun by the means of
photovoltaic solar cells.
• The energy may be used to drive the electric motor to power the aircraft.
• Our basic principle is use solar power by means of aircraft and this thing can be
done by solar panels which covers the whole surface of wing.
• During the night, the only energy available comes from the battery.
• Our project is based on the solar power utilisation.

4. HISTORY OF SOLAR POWERED VEHICLES
• The first Silicon photovoltaic cells capable of converting enough of the sun’s
energy into power to run electrical equipment.
• UNMANNED SOLAR POWERED FLIGHT
• Sunrise I
• Solaris
• Solar Excel
• Centurion
• MANNED SOLAR FLIGHT
• Solar Riser
• Solar Challenger
• Helinet
• Solar Impuse And Solar Impuse 2

5. BASIC PRINCIPLE OF OPERATION
• Solar power conversion into electric energy by means of aircraft.
• It can be done by solar panels which covers the definite surface area of wings.
• A convertor ensures that the solar panels are working at their maximum power
point.
• The electric energy is used to charge battery which drives electric motor.
• Propeller is mounted on motor shaft produces thrust continuously.

6. AERODYNAMICS OF WINGS
• The design and analysis of wings of aircraft is principle application of science of
aerodynamics.
• Once a plane leaves the ground, it is acted upon by four aerodynamic forces.
• Thrust
• Drag
• Weight
• Lift
• The lift maintains the airplane airborne compensating the weight.
• The drag that is compensated by the thrust of the propeller.

7. BERNOULLI’S PRINCIPLE
• P+½ρv2 +gρh=k
Where, P=Pressure (Pa)
ρ=Density (kg/m3)
v=Velocity (m/s)
g=Acceleration (m/s2)
h=Distance from reference, measured in opposite direction of the gravitational
force (m)
k=constant (kg/m2)
• If density, height and acceleration are fixed the pressure will be inversely
proportional to velocity.
• It means area under high velocity will have lower pressure and vice versa.

8. CONCEPT OF LIFT
• The basic concept of lift is simple and is based on the Bernoulli’s equation.
• The air flow meeting the leading edge of the object is forced to split over and
under the object.
• Due to the pressure gradient and the viscosity of the fluid, the flow over the
object is accelerated down along the upper surface of the object.
• The two sections of the fluid each leave the trailing edge of the object with a
downward component of momentum, producing lift.

9. AIRFOIL
• An airfoil is any surface producing more lift than drag when passing through the
air at a suitable angle.
• Airfoils are most often associated with production of lift. Airfoils are also used for
stability (fin), control (elevator), and thrust or propulsion (propeller or rotor).
• The main and tail rotor blades are airfoils, and air is forced to pass around the
blades by mechanically powered rotation.
• Airfoils are carefully structured a specific set of flight characteristics.

10. AIRFOIL TERMINOLOGY
• Blade Span
• Chord Line
• Chord
• Mean Camber Line
• Leading Edge
• Flight Path Velocity
• Relative Wind And Resultant Relative Wind
• Angle Of Attack
• Angle Of Incidence
• Center Of Pressure

11. AIRFOIL TYPES
• Symmetrical Airfoil -
The symmetrical airfoil is distinguished by having identical upper and lower
surfaces.
The mean camber line and chord line are the same on a symmetrical airfoil, and it
produces no lift at zero AOA.
• Nonsymmetrical Airfoil (Cambered) -
The nonsymmetrical airfoil has different upper and lower surfaces, with a greater
curvature of the airfoil above the chord line than below.
The mean camber line and chord line are different.
The nonsymmetrical airfoil design can produce useful lift at zero AOA.

12. LIFT AND DRAG
• The circulation of the airflow creates a different pressure distribution on the
upper and lower side.
• The section that once integrated can be represented as two forces, the lift and
the drag.
INCLINATION EFFECT ON LIFT

13. ANGLE OF ATTACK
• It is the angle between the wing chord and the relative wind. We have used
software to create airfoil.
• By putting proper angles of attack related values of other parameters like
coefficient off lift, coefficient of drag, Reynolds number etc. can be generated.
SOLAR CELLS
• A solar cell or photovoltaic cell is a device that converts solar energy into
electricity by the photovoltaic effect.
• It is very widely used in space application because it allows a clean and long-
duration source of energy requiring almost no maintenance.
• Solar cells are composed of various semiconducting materials, constituting one or
more layers.

14. SOLAR IRRADIANCE
• Solar Irradiance is a measure of the irradiance (power per unit area on the Earth's
surface) produced by the Sun in the form of electromagnetic radiation.
CURRENT AND VOLTAGE OF SOLAR CELL
• When the cell pads are not connected, no current produced and the voltage
equals VOC, the open circuit voltage.
• When it is short circuited, the voltage is zero but the current equals ISC.
• In between these two points where in both cases the power retrieved is zero,
there is working point, called the maximum power point.
• The current of a solar cell is proportional to its area and varies almost linearly
with the light intensity

15. POWER STORAGE
• When the energy production is not constant and continuous, a good energy
storage method is necessary.
• Different ways to store energy:
• Chemical (hydrogen, biofuels)
• Electrochemical (batteries, fuel cells)
• Electrical (capacitor, super capacitor, superconducting magnetic
energy storage or SMES)
• Mechanical (compressed air, flywheel)
• Thermal
• In the case of a solar airplane, the gravimetric energy density also called specific
energy.
• The peak power are the most crucial parameters that determine the choice of the
energy storage method.
• In present case, the electrochemical batteries and the fuel cells are the two best
candidates.

16. ELECTROCHEMICAL BATTERIES
• Electrochemical batteries are energy storage devices, which are able to convert
chemically stored energy into electrical energy during discharging.
• They are composed of a cathode and an anode, made of two dissimilar metals
that are in contact with an electrolyte.
• When all elements are in contact with each other, a flow of electron is produced.

17. FUEL CELLS
• A fuel cell is a system where the chemical energy of reactants, often a gaseous
fuel and the oxygen.
• The fuel cell consists of two electrodes, known as the anode and cathode that are
separated by an electrolyte.
• A fuel cell on a solar airplane to store the energy during the day and reuse it
during the night.

18. MAXIMUM POWERPOINT TRACKER
• A solar cell has a working point on its current to voltage curve where the power
retrieved is maximal.
• The constantly changing irradiance conditions, and thus get the highest amount
of energy, a so called Maximum Power Point Tracker (MPPT) is required.
• An MPPT is basically DC/DC converter with variable and adjustable gain between
the input and the output voltage.
• The input being the solar panels and the output the battery.
• It contains electronics that monitor both the current and the voltage on each
side.

19. PROPELLER
• The propeller is a device consisting of a set of two or more twisted, airfoil shaped
blades
• The blades are mounted around a shaft and spun to provide propulsion of a
vehicle through a fluid.
• It accelerates incoming air particles creating a reaction force called thrust.
BLADE ELEMENT THEORY
• In this theory the blade is assumed to be composed of numerous, infinitesimal
strips with width ’dr’ that are connected from tip to tip.
• The lift and drag are estimated at the strip using the 2-Dairfoil characteristics of
the section.
• Also, the local flow characteristics are accounted for in terms of climb speed,
inflow velocity, and angular velocity.
• The section lift and drag may be calculated and integrated over the blade span.

20. 1. BLADE ELEMENT SUBDIVISION
• A propeller blade can be subdivided as shown into a discrete number of sections.
• For each section the flow can be analyzed independently.
• If the assumption is made that for each there are only axial and angular velocity
components.
• The induced flow input from other sections is negligible.

21. 2. INFLOW FACTORS
• The induced flow components can be defined as factors increasing or decreasing
the major flow components.
3. AXIAL AND ANGULAR CONSERVATION OF MOMENTUM
• The governing principle of conservation of flow momentum can be applied for
both axial and circumferencial directions.
• For the axial direction, the change in flow momentum along a stream-tube
starting upstream, passing through the propeller.
• Then moving off into the slipstream, must equal the thrust produced by this
element of the blade.

22. 4. PROPELLER THRUST AND TORQUE COEFFICIENTS AND EFFICIENCY
• So designing an efficient propeller comes to the same challenges as for an
airplane wing.
• Find the best airfoil, chord and incidence angle that minimize the resistance
torque and maximize the thrust for a given axial speed.
• This optimum varies along the blade, from the hub to the tip, due to the
increasing radius and thus airspeed, explaining the twisting shape of propellers.
• Good propeller designed for a specific flight domain should have an efficiency of
at least 80 %, 85 % being an excellent value that is difficult to surpass.

23. SCALING DOWN: - SOLAR MICRO AERIAL VEHICLE
• The miniaturization of processors, sensors, communication chips, the
development of efficient robotic platforms is not only possible at the UAV size,
but also at the MAV size.
SCALING DOWN:- ADVANTAGES AND DRAWBACKS
• Airframe
• Low Reynolds Number Airfoil And Propeller
• Actuators
• Solar Cells
• Maximum Power Point Tracker
• Energy Storage
• Control

24. METHODOLOGY ADAPTATION:-DAY FLIGHT ONLY
• The methodology can be slightly modified to design an airplane that flies only
during the day.
• For this purpose, we can set Tnight = 0 and give Tday any value higher than zero.
• A quick look at the influence of this modification shows that no battery will be
considered and that the area of solar cells will be lower,
• As logically no battery needs to be charged during the flight.
• We consider a mean irradiance, the value of Imax has to be multiplied by α/2
because it was divided by the same value to obtain the mean irradiance on an
entire day.

25. SCALING UP: - MANNED SOLAR AIRPLANE
• The feasibility at a much reduced size, we will now go in the other direction and
consider the case of a manned solar airplane at low altitude.
• A body mass of 80 kg is assumed to which we add 40 kg of additional
equipment’s, i.e. a seat, a parachute, food, beverages, etc., yielding a total
payload of 120 kg.
• We will also consider 20 kg for the avionics system, including navigation
instruments and communication means that require an electrical power of
100W.
SCALING UP: - ADVANTAGES AND DRAWBACKS
• Aerodynamics and Efficiencies
• Solar Cells and MPPT
• Airframe Structure

26. CONCLUSION
• This thesis presented a new methodology for the conceptual design of solar
airplanes.
• It has the advantage to be very versatile and usable for a large range of
dimension, from UAVs with less than one meter wingspan to manned airplanes.
• The models are used for efficiency or weight prediction and constitute a key part
of such design method.
• The design methodology consists of a simple routine that takes 5 parameters
linked to the mission and 25 to the technologies used as inputs.
• It allows the designer to output the layout of a solar airplane rapidly, with size,
weight and power information.

27. POTENTIAL APPLICATIONS AND THE FUTURE OF SOLAR AVIATION
• Airports and hangars with solar panels and use this energy to hydrolyze water
into hydrogen and oxygen.
• The hydrogen would then be stored and used on the airplane in a fuel cell.
• To summarize, what makes solar airplane not so ideal is that they have to embed
the whole factory that converts the few energy coming from the sun in real-time,
which is, as we saw, a heavy and not so efficient undertaking.
• Thus, the better idea is to let this heavy factory none the ground, concentrate the
energy, and then only use it on a fast airplane with reasonable dimensions and
thus a correct maneuverability.
• One part of the wing could still be covered by solar panels, but to cover only a
small percentage of the electrical power consumption.