final report

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PROJECT DEGINE BY:

VYAS TAJAGNA

MANUFACTURED BY:

PATEL JAIMIN

PRAJAPATI MEHUL

ASSEMBLED BY:

DHOLARIA DHARMESH

GHAJERA CHINTAN

GHAJERA TUSHAR

THE THIRD EYE

REMOTE CONTROLLED HOVERCRAFT

A PROJECT REPORT

Submitted in partial fulfillment of the requirements for the award of the certificate

Of

DIPLOMA

IN

MECHANICAL ENGINEERING

BY

VYAS TAJAGNA PARTHESHKUMAR 106750319015

PATEL JAIMIN BHARATBHAI 106750319002

PRAJAPATI MEHUL RAMESHBHAI 106750319034

GAJERA CHINTAN PARSHOTTAMBHAI 106750319030

GAJERA TUSHAR JAYSUKHBHAI 106750319018

DHOLARIA DHRMESH LAXMANBHAI 106750319023

UNDER THE GUIDENCE OF

MR R.P.PRAJAPATI

MR D.M.RASAMIYA

MR N.K.TRIPATHI

MR.HARDIP PANDYA

MR.NILESH DOSHI

DEPARTMENT OF MECHANICAL ENGINEERING

F.D.(MUBIN) INSTITUTE OF ENGINEERING AND TECHNOLOGY,DAHEGAM

PIN-382308, GANDHINAGAR, GUJARAT, INDIA

CERTIFICATE

This is to certify that,

Mr. VYAS TAJAGNA PARTHESHKUMAR

From F.D.( MUBIN) Institute of engineering & Technology college

having Enrollment no.106750319015 has completed Report on the

Semester –VI Project Report having title Remote Control Hovercraft.

In a group consisting of 6 persons under the guidance of the

Mr.NileshTripathi , Mr.DipakRasamiya and Mr.RakeshPrajapati.

Institute Guide- UDP Head of Department

DATE

The purpose of our project is to construct a functioning hovercraft designed through fundamental

principles. Through this design project, we explore the process of engineering from initial design to

product construction. We were forced plan around material limitations and me constraints. We

produced a vehicle capable of hovering and forward motion.

Hovercrafts are multi-purpose vehicles which can travel across various types of terrain with no

alteration. The overall purpose for this design project is to build a hovercraft which can carry various

payloads, across land and water. This air cushioned vehicle (ACV) can be used for numerous different

applications including military, aid, transportation of building supplies, etc. This report will outline the

design process as well as the final selected design. It also includes sections on fabrication and testing of

the hovercraft and all its components. Also included in this report are detailed design drawings, detailed

budget, a list of calculations done for the project.

We place on record and warmly acknowledge the continuous encouragement, invaluable supervision,

timely suggestions and inspired guidance offered by our guide MR. RAKESH PRAJAPATI, Professor,

Department of Mechanical Engineering, in bringing this project to a successful completion.

We are grateful to MR. DEEPAK RASAMIYA, Head of the Department of Mechanical engineering, for

permitting us to make use of the facilities available in the department to carry out the project

successfully. Last but not the least we express our sincere thanks to all of our friends who have

patiently extended all sorts of help for accomplishing this undertaking.

We are thankful to MR. NILESH TRIPATHI and MR. LALBHAI THAKORE for their support for electric

equipment’s and also thanks to MR. HARDIP PANDYA for technical advice.

We are thankful to MR. NILESH DOSHI for guiding us in purchasing equipment’s and also thankful to

MR. SHAILESH AMIN, MR. KAMLESH PATEL, MR. KALPESH NAI.

Finally we express our gratefulness to those who are directly or indirectly responsible for successful

completion of this project.

I). ABSTRACT……………………………………………………………………………………..………………………………………………………………...I

II). ACKNOWLEDGMENT……………………………………………………………………………………………………………………………………….II

III). TABLE OF CONTENTS……………………………………………………………………………………………………………………………………..III

IV). LIST OF FIGURES……………………………………………………………………………..…………………………………………………………….IV

V). LIST OF TABLES………………………………………………………………………………………………………………………………………………..V

VI). NOMECLATURE

1). ACRONYMS………………………………………………………………………………………………………………………………………………VI

2). LIST OF SYMBOLS……………………………………………………………………………………………………………………………........VII

1 HISTORY…………….…………………………………………………………………………………………………………………………………………..002

2 ABOUT PROJECT

2.1 INTRODUCTION…………………………………………………………………………………………………………………………………….004

2.2 OBJECTIVE…………………………………………………………………………………………………………………………………………….005

3 SELECTION OF EQUIPMENT

3.1 PROPULSION EQUIPMENT..…………………………………………………………………………………………………………………..007

3.2 LIFT EQUIPMENT…………………………………………………………………………………………………………………………………..008

3.3 BODY MATERIAL…….…………………………………………………………………………………………………………………………….009

3.4 SKIRT MATERIAL….……………………………………………………………………………………………………………………………….009

3.5 POWER SOURCE….……………………………………………………………………………………………………………………………….010

3.6 BODY DESIGN……………………………………………………………………………………………………………………………………….010

4 DETAIL DESIGN

4.1 LIFT…………………………………………………………………….……………………….……………………………………………………….012

4.2 PROPULSION……………………………………………………………………………….……………………………………………………….014

4.3 PLATFORM & SKIRT……………………………………………………………………..……………………………………………………….016

5 MANUFACTURING…..……………………………………………………………………………..……………………………………………………..019

6 CONTROLLING……………………………………………………………………………………………………………………………..………………..023

7 TESTING………………………………………………………………………………………………………….……………………………………………..026

8 CONCLUSION AND REFERANCES

8.1 CONCLUSION………………………………………………………………………………………………………………………………………..030

8.2 REFERANCES………………………………………………………………………………………….……………………………………………..030

VII) BILL OF MATERIAL………………………………………………………………………………………………….…………………………………..VIII

VIII) PROJECT SCHEDULE………………………………………………………………………………………………………………………………………X

IX) CPM AND PERT ANALYSIS…………………………………………………………………………………………………………………………….XI

X) BUDGET………………………………………………………………………………………………………………………………………….……………XII

XI) CALCULATION………….……………………………………………………………………………………………..……………………….…………XIII

XII) DESIGN……………………….……………………………………………………………………………………………………..………….…………..XIV

XIII) MOMENTS AT WORK……………………………………….……………………………………………………………………………………….XXII

1 HOVERCRAFT PRINCIPAL DESIGN………….…………………………………………………………………………………………………..…..004

2 SELECTED PROPELLER ………………………………………………………………………………………………………………………….………..012

3 LIFT MOUNTING DESIGN ……………………………………………………………………………………………………………………..………..013

4 SELECTED MOTOR …………………………………………………………………………………………………………………………………………014

5 MOTOR SUPPORT ………………………………………………………………………………………………………………………………………….015

6 FAN DUCT ……………………………………………………………………………………………………………………………………………..………016

7 PLATFORM DESIGN …………………………………………………………………………………………………………………………………......017

8 SKIRT DESIGN ………………………………………………………………………………………………………………………………………….......018

9 PLATFORM CONSTRUCTION ……………………………………………………………………………………………………………………......020

10 LIFT MOUNTING CONSTRUCTION………………………………………………………………………………………………………………..020

11FAN DUCT CONSTRUCTION……………………………………………………………………………………………………………..…………..020

12 MOTOR SUPPORT……………………………………………………………………………………………………………………………….……….021

13 SKIRT CONSTRUCTION…………………………………………………………………………………………………………………………..…….021

14 ASSEMBLY……..…………………………………………………………………………………………………………………………………………….021

15 FINAL CONSTRUCTION…………………………………………………………………………………………………………………………………022

16CIRCUIT DESIGN……………………………………………………………………………………………………………………………………….....024

17REMOTE AND RECIEVER……………………………………………………………………………………………………………………………….024

18 BATTERY………………………………………………………………………………………………………………………………………………………025

19 MOTOR………………………………………………………………………………………………………………………………………………………..025

20 SERVOMOTOR……………………………………………………………………………………………………………………………………………..025

1 PROPULSION EQUIPMENT SELECTION MATRIX.……………………………………………………………………………………………..007

2 LIFT EQUIPMENT SELECTION MATRIX…..………………………………………………………………………………………………………..008

3 BODY MATERIAL SELECTION MATRIX……………………………………………………………………………………………………………..009

4 SKIRT MATERIAL SELECTION MATRIX……………………………………………………………………………………………………………..009

5 POWER SOURCE SELECTION MATRIX……………………………………………………………………………………………………………..010

6 BODY DESIGN SELECTION MATRIX…..…………………………………………………………………………………………………………….010

7 TERRAIN TESTING RESULT……………………………………………………………………………………………………………………………..028

8 BILL OF MATERIAL………………………………………………………………………………………………………………………………………….VIII

9 PROJECT SCHEDULE…………………………………………………………………………………………………………………………………………..X

10 CRITICAL PATH METHOD ANALYSIS………………………………………………………………………………………………………………..XI

11 BUDGET…………………………………………………………………………………………………………………………………………………………XII

1).ACRONYMS

ACV = AIR CUSHION VEHICAL

UFO = UNDENTIFIED FLYING OBJECT

ESC = ELECTRONIC SPEED CONTROLLER

BOM = BILL OF MATERIAL

LI-PO= LITHIUM POLYMER

CPM = CRITICAL PATH METHOD

BEC = BATTERY ELLIMINATOR CIRCUIT

There have been many attempts to understand the principles of high air pressure below hulls and

wings. To a great extent, the majority of these can be termed "ground effect" or "water effect" vehicles

rather than hovercraft. The principal difference is that a hovercraft can lift itself while still, whereas the

majority of other designs require forward motion to create lift. These active-motion "surface effect

vehicles" are known in specific cases as ekranoplan and hydrofoils.

The first mention in the historical record of the concepts behind surface-effect vehicles that used the

term hovering was by Swedish scientist Emanuel Swedenborg in 1716 In 1915, Austrian Dagobert Müller

(1880 - 1956) built the world's first "water effect" vehicle. Shaped like a section of a large aero foil (this

creates a low pressure area above the wing much like an aircraft), the craft was propelled by four aero

engines driving two submerged marine propellers, with a fifth engine that blew air under the front of

the craft to increase the air pressure under it. Only when in motion could the craft trap air under the

front, increasing lift. The vessel also required a depth of water to operate and could not transition to

land or other surfaces. Designed as a fast torpedo boat, the Versuchsgleitboot had a top speed over 32

knots (59 km/h). It was thoroughly tested and even armed with torpedoes and machine guns for

operation in the Adriatic. It never saw actual combat, however, and as the war progressed it was

eventually scrapped due to lack of interest and perceived need, and its engines returned to the Air

Force.

In 1931, Finnish aero engineer Toivo J. Kaario began designing a developed version of a vessel using an

air cushion and built a prototype Pintaliitäjä (Surface Soarer), in 1937.[4] Kaario's design included the

modern features of a lift engine blowing air into a flexible envelope for lift. Kaario never received

funding to build his design, however.[citation needed] Kaario's efforts were followed closely in the

Soviet Union by Vladimir Levkov, who returned to the solid-sided design of the Versuchsgleitboot.

Levkov designed and built a number of similar craft during the 1930s, and his L-5 fast-attack boat

reached 70 kn (130 km/h) in testing. However, the start of World War II put an end to Levkov's

development work.

During World War II, an engineer in the United States of America, Charles Fletcher, invented a walled

air cushion vehicle. Because the project was classified by the U.S. government, Fletcher could not file a

patent.

A hovercraft is a vehicle capable of traveling over most surfaces on a cushion of air trapped under the

body for lift. Air propellers, water propellers, or water jets usually provide forward propulsion. Air-

cushion vehicles can attain higher speeds than can either ships or most land vehicles due to lower

frictional forces and use much less power than helicopters of the same weight. Figure 1 above illustrates

the operational principles and basic components of a typical hovercraft.

Specifically for our hovercraft, there are three main design groups: the lift, thrust, and steering

systems. The arrangement of the hovercraft is similar to that shown in Figure 1. The propeller shown

must be designed for a vehicle as typical fans act by creating vortices to mix the air, reducing the

ejected air’s translational kinetic energy and significantly reducing efficiency. We outline key features of

the three main groups below.

Lift System

The hovercraft relies on a stable cushion of air to maintain sufficient lift. The air ejected from the

propeller is separated by a horizontal divider into pressurized air utilized for the aircushion and

momentum used for thrust. The weight distribution on top of the deck is arranged so that the air is

distributed the air from the rear of the deck throughout the cushion volume in an approximately even

fashion to provide the necessary support. The skirt extending below the deck provides containment,

Figure 1 HOVER CRAFT PRINCIPAL DESIGN

improves balance, and allows the craft to traverse more varied terrain. We maintain the rigidity of the

skirt by filling the air-tight skirt with the same pressurized air diverted towards lift.

Thrust System

The air not directed to the cushion and skirt is propelled backwards, providing forward thrust to the

craft. The size of the propeller, rpm output of the engine, and height of the lift/thrust divider are the

determining parameters for the thrust force. A thrust duct channeling the air into the propeller can

provide up to a 15% increase in efficiency [Universal Hovercraft]. The limiting factor for the thrust is the

air flow available to direct backwards since our primary concern is providing pressurized air for air

cushion and lift. As a result, our forward speed is limited but maintainable.

Steering System

Since a hovercraft lacks the same frictional and drag effects as boats or cars, steering must be

approached without precise control in mind. This is especially true in our case as the power supply is

limited. Rudders are a main source of steering and are attached to the rear of the duct to direct the flow

of air and the direction of the subsequent momentum transfer from the air to the craft. The driver

controls the movement of the rudders through a joystick located in the front of the craft. A throttle on

the engine situated next to the driver allows him to vary the speed of the craft, allowing for a smaller

radius of turning once proper driving techniques are mastered. Because of the air cushion effect, the

driver may influence the steering by shifting his weight nearer to any of the four sides of the deck. For

example, a shift right turns the hovercraft to the right. In the remainder of the report, we discuss our

design and construction processes, the results from testing the craft, the problems associated to our

design and construction, and possible improvements.

Our goal is to present a clear description of hovercraft history, design concepts, and fundamentals, and

to incorporate these into a well thought out design to be considered for manufacturing. We expect that

our hovercraft will successfully complete the course, will achieve maximum top speed with minimal

cost, will be aesthetically pleasing to the client and spectators, will be reliable and durable for use in

multiple runs and will be safe for all concerned.

Once our list of concepts was completed we created a screening matrix from them. The matrix was

used to evaluate each concept against each client need. The evaluation system we employed was: for

each concept and client need a −, 0 or + was assigned to indicate a negative response, a neutral

response and a positive response respectively. This evaluation was done by each team member

individually. Once the individual screening was completed, we assembled as a team to compare our

results, and form a master screening matrix, with which are all in agreement - this is what is presented

beginning on the following tables.

TABLE 1 : PROPULSION EQUIPMENT SELECTION MATRIX

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THRUST POWER

Single rocket - - - - - 0 - -

Double rocket - - - - - 0 - -

Single motor + + + + + + + +

Double motor + + + + 0 + + +

Diesel engine 0 + 0 0 0 0 - 0

Petrol engine 0 + 0 0 0 0 - 0

POWER SOURCE

Single fan – single battery + + + + + + + +

Double fan – double battery + + + + 0 + 0 +

FAN TYPE

Turbo fan - 0 - - 0 0 - 0

Propeller – glass - - 0 - - 0 - 0

Propeller – polycarbonate + + + + + + + +

Propeller – wood + + + 0 0 + + +

STEERING SYSTEM

Mounting table - - - - - - - -

Rudder system + + + + + + + +

TABLE 2 : LIFT EQUIPMENT SELECTION MATRIX

Equipment sa

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Easy

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man

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Easy

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Mar

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LIFT POWER

Single motor + + + + + + + +

Double motor + + + + + + 0 +

Diesel engine 0 + 0 0 0 0 - 0

Petrol engine 0 + 0 0 0 0 - 0

Leaf blower + + - - - 0 - 0

Vacuum cleaner + + - - - - - +

POWER SOURCE

Single fan – single battery + + + + + + + +

Double fan – double battery + + + + 0 + 0 +

PROPELLER TYPE

Turbo fan - 0 - - 0 0 - 0

Propeller – glass - - 0 - - 0 - 0

Propeller –poly carbonate + + + + + + + +

Propeller – wood + + + 0 0 + + +

TABLE 3 : BODY MATERIAL SELECTION MATRIX

Equipment sa

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Easy

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Carbon fiber + + + - - + - -

Cardboard + - + + + + 0 +

Aluminium + + 0 0 0 + 0 +

Fiberglass + + 0 0 0 + - 0

Glass - 0 0 0 0 + - +

Paper + - + + + + + +

Steel + + - 0 0 + 0 +

Light weight wood + + 0 + 0 + 0 +

Heavy weight wood + + 0 0 0 + 0 +

Plastic + + + + + + 0 +

Sheet metal + + - 0 0 + - +

Waterproof wood + + - 0 0 + - +

Foam + + + + + + + +

TABLE 4 : SKIRT MATERIAL SELECTION MATRIX

Equipment sa

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du

rab

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Ligh

t w

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Easy

to

man

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re

Easy

to

des

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Mar

ket

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ility

Rubber + 0 + + + + + +

Plastic + + + + + + + +

Paper + - + + + + + +

Cloth + + + + + + 0 +

Neoprene + 0 + 0 + + + 0

Cushion + + + + + + 0 +

Nylon + + + + + + 0 +

Oiled paper + - + + + + + +

polyethylene + + + 0 + + + +

TABLE 5 : POWER SOURCE SELECTION MATRIX

Equipment sa

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du

rab

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Ligh

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Easy

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Battery + + + + + + + +

Storage battery + + - 0 0 + - +

Chemical - - + 0 0 - + 0

Solar power + - + 0 0 + - 0

Wind power from lift fan + 0 + 0 0 + - 0

TABLE 6 : BODY DESIGN SELECTION MATRIX

Equipment sa

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Ellipse + + + 0 0 + 0 0 - -

Square + + + + + + + + + 0

Rectangle + 0 + + + + + + + 0

Triangle + + + 0 0 + + - + -

Saucer + + + 0 - + 0 0 - 0

Circular (like a UFO) + + + - - + 0 - - 0

Rectangle (rounded corner)

+ + + + + + + + + +

Aerodynamic + + + - - + - 0 0 +

Life boat + + + + + + + + + +

4.1.1 Design Specifications

The lift system was designed to supply airflow to the air cushion in order to lift the weight of the

hovercraft, including the desired payload, giving a total lifting weight capacity of 100 kilograms to allow

for battery weight and additional mounted devices. The system itself was required to meet a set of

requirements, as detailed below.

It was to be of light weight, as this was one of the general requirements for all components.

The system should be small given the special restraints present on the platform.

The design should be simple, as a complex design would lead to further complications with the

potential to increase the overall size of the system.

4.1.2 Propeller Design

Propellers are best when a low flow rate and high static pressure is required. Given that a high flow rate

and comparatively low static pressure was required in order to achieve lift, an axial flow fan was

selected as the most suitable fan type for this application. A detailed analysis of the variables present in

axial fan design was carried out to determine which characteristics best suited this application. There

are two main parameters in fan design which influence the characteristics of a fan; the blade pitch, and

the number of blades. In general, the rotational speed, diameter, flow rate and static pressure are all

specified prior to selecting a fan.

SELECTED PROPELLER AS PER THE TABLE 1

4.1.3 Mounting structure design

As seen in Figure 3 raising the motor vertically upwards a height of 6 inches gives this design two major

advantages. First it removes the risk of the fan damaging the skirt during deflation, because the skirt

cannot deflate in close proximity to the blades. The main reason for this selection is the ability to funnel

the air flow into a smaller cross section as well as keeping the skirt Fan material out of the vicinity of the

fan blades.

Figure 2 SELECTED PROPELLER

SELECTED MOUNTING FOR LIFTING SYSTEM

Figure 3 LIFT MOUNTING DESIGN

In order to provide cushion, flow of air must be guided properly towards the base. As shown in the

figure 3 the mounting has been kept on the raised platform so that air coming from the outside can be

guided through narrow region to the base.

4.1.4 Motor design

The propulsion motors are used to drive the propellers, providing thrust to accelerate the hovercraft.

The motors required a high degree of controllability, the ability to turn on/off quickly and operate over

a variety of operational speeds. To achieve this an electric motor was required, as no other engine can

achieve the high degree of controllability needed.

Due to the rotational properties of the vectored thrust design, a motor was required with a high

power to weight ratio. Able to provide high power levels, whilst remaining light weight, so not to

restrict the rotation of the propulsion system. Further the motor size must remain small enough not

to restrict the flow into the propeller, in a direct drive configuration. Based on this it was determined

A brushless electric motor was required over a brushed motor, able to provide more power and lower

Electromagnetic interference. Size restrictions further limited selection to an in-runner motor over an

out runner, being significantly smaller, allowing for higher flow and thrust efficiencies.

SELECTED BRUSHLESS MOTOR AS PER THE TABLE 2

Propulsion is defined as the forces required to cause motion over a given terrain. The basic principle

of hovercraft propulsion is momentum theory. Momentum theory in principle, describes motion of the

platform based on a reactive force to the change in momentum of airflow accelerated via a propulsion

system. Using dimensionless coefficients of thrust and power, a propeller and power house have been

selected based on these principles.

4.2.1 Design Specifications

Several design criteria were identified for the propulsion system. The main requirement was the need

to maintain maneuverability of the craft by providing the ability to apply forces in the forward, back and

sideward directions. This ensures sufficient maneuverability to control the hovercraft in accordance

with operational scenarios identified for mine detection regimes. Additional requirements, beyond

providing thrust, include obtaining the highest efficiency system at the lowest weight and power costs.

As the special limitations of the platform are significant this also becomes an important criteria for

selection. The design specifications are summarized below:

Propulsion systems must be independent of the lift system

Provide thrust forces to overcome the inertial and drag loadings on the craft

The platform must have the capacity to DE accelerate to rest in the same time

Maintain a constant velocity at operational of 5 m/s

Figure 4 SELECTED MOTOR

Provide thrust forcing in all directions outward of the platform to ensure sufficient maneuver-

ability for autonomy

Be of high efficiency, and fit within the spatial bounds of the platform

4.2.2 Propeller Design

Propeller which can be used in lift system same like it is used in propulsion system.

4.2.3 Mounting structure design

There were several requirements determined for the design of the propulsion mount. These included

limitlessly rotate the thrust vector 360 degrees, the ability to resist deflection as a result of thrusting,

and simple and easy manufacture and assembly. Furthermore, with safety was an important

consideration due to the rotation of a fast moving propeller. It was to be ensured that the rotation of

the two propulsion mounts could be achieved independently without interference.

The air not directed to the cushion and skirt is propelled backwards, providing forward thrust to the

craft. The size of the propeller, rpm output of the engine, and height of the lift/thrust divider are the

determining parameters for the thrust force. A thrust duct channeling the air into the propeller can

provide up to a 15% increase in efficiency [Universal Hovercraft]. The limiting factor for the thrust is the

air flow available to direct backwards since our primary concern is providing pressurized air for air

cushion and lift. As a result, our forward speed is limited but maintainable.

SELECTED MOUNTING FOR PROPULSION SYSTEM

Propulsion motor has been placed on the base through triangular shaped extruded support as shown in

the figure. In order to introduce steering effect flat panels have been placed just behind the motor. The

panels are movable through servo motor.

Figure 5 MOTOR SUPPORT

4.2.4 Motor design

Motor which can be used in lift system same like it is used in propulsion system.

4.2.5 Fan duct design

Similar to the lifting motor, air flow from propulsion has to be directed through guide walls as shown in

the figure. This panels provide support to the steering panels as well.

SELECTED FAN DUCT DESIGN

4.3.1 Top plate design

The top plates primary function is to house and support all sub systems as well as form the top seal

of the pressure chamber, and hence requires a high level flexural rigidity to avoid undue deflection

with the potential of damaging the lift fan which is mounted within the pressure chamber. Moreover

a high compressive modulus is required to endure repetitive application of torque on the bolts which

hold the primary engine mounts, safety tether points and sealing ring. Reliability; in particular the

ability to replace and the ability to modify mounting points were assigned the greatest priority in

the design considerations, given the high probability of modification of the position of subsystems

being mounted on the top plate. A sandwiched structure was specifically chosen to ensure a marginal

Figure 6 FAN DUCT

penalty in weight for exponential gains in stiffness and strength.

SELECTED PLATFORM DESIGN

4.3.2 Skirt design

Skirts were first implemented in hovercraft designs in the 1960's to assist with containment of the

air cushion. By acting as a flexible sidewall to the air cushion, skirts led

to a decrease in the horsepower requirements of hovercrafts and an increase in several performance

parameters, namely; air cushion performance, stability and obstacle clearance. Skirts have been

implemented in several different configurations, each offering different advantages to the ACV's

performance. There are many considerations to undertake when choosing the configuration

suitable for a crafts application, including drag, stability and maneuverability requirements of the

craft.

4.3.2.1 Design Specification

Skirt configuration is an area of ongoing research in industry and different skirt designs over varying

performance characteristics. Benchmarking of small hovercraft under two meters has been done to

obtain empirical data on the most common configurations used for small craft. Four main configu-

rations were identified; the segmented skirt (22%), open-loop bag skirt (74%), the bag and segment

combination and the pericell or jupe skirt. Furthermore, combinations of these sets could be used to

splice performance characteristics of differing configurations.

Figure 7 PLATFORM DESIGN

A set of design criteria were generated for skirt configuration selection:

The drag association of the skirt should be minimized due to the application of the hovercraft.

This is to ensure that the probability of landmine detonation through skirt contact is minimized.

As active control of the hovercraft in pitch and roll is not being attempted inherent stability of

the platform is of high importance. The skirt must therefore control stability of the platform to

maximum disturbances in pitch or roll.

The skirt must be adaptable to the platform shape and able to be both fastened and shaped to

the preceding hull design.

The hover height of a hovercraft is achieved through obtaining the correct skirt depth and

cushion pressure. The skirt must therefore achieve a hover height clearance of 50 mm to the

bottom of the hull.

SELECTED SKIRT DESIGN AS PER THE TABLE 4

Figure 8 SKIRT DESIGN

Below is the detailed outline of the construction process we used. Each section is accompanied by a

detailed schematic diagram detailing the dimensions of the materials used as well as pictures taken

during construction. A listing of the materials used, their costs and sources can be found in the

appendix.

First of all we made deck as shown in figure, which

is made of 2 foam plates- one in blue and second

in white foam. The blue plate is for mounting

equipment’s and the other, from these two plates-

while foam plate is so made that the air may not

leak from the skirt. By cutting with iron coil and by

cutter as shown in figure, it was cut in half circle of

10" radius in both plates. Now from the center of

the half circle, a circular hole is made in center of

the second plate. After cutting the circle, a fillet is

made of 2" radius on the corner.

Idea was left for making lift mounting on base plate to

support the motor it was decided to mount the motor so as

to give proper direction to the air. For making mounting

foam was cut in size of 2" high x 1" thickness for mounting

of 9"diameter. Aluminum strip provided on foam to support

the motor. After mounting glue is used on base plate

i.e. deck, as shown in figure. After making this mounting, it

was decided to make fan duct, which is made in rectangular size

most commonly. This fan duct is 5" away from the edge but in

center. This fan duct is made by blue foam, as shown in figure.

Three plates were cut from fan duct in size of 4"x9"x1" two plates

and one plate in 4"x11"x1". After that these three plates were

joined with each other by glue. After that this glue was completed

Figure 9 PLATFORM CONSTRUCTION

Figure 11 LIFT MOUNTING CONSTRUCTION

Figure 10 FAN DUCT CONSTRUCTION

assembly. This fan duct is shown in the figure.

After making this fan duct motor mounting was made as shown in

figure which is in triangular shape so that it may not be stressed by

the vibration of the motor and can remain stable. This mounting is

done in size of 2"x10"x12". After mounting, fan duct was stick at

the proper distance.

After making complete base plate and mounting structure

it was decided to make skirt. For making skirt it was desired to use plastic in which from too base plate,

only one plate was made of white foam, and joint was made

on it. This skirt is made in dimension shown in the figure to

make joint of base plate glue tape is used.

After skirt joint, the base plate i.e. white plate and blue plate

were joined. so that skirt be tightly packed between two

plates and air may not be leaked. For joining these two

plates with each other, aluminum clamp was used. After joining these two plates, the look of both

plates and the look of skirt can remain clear. We have used black color plastic.

After completing structure of hovercraft we fixed the

electrical equipment’s at the proper place. After assembling

the electrical equipment, testing of the project was done.

the aim of testing is that to know, that to keep the

hovercraft in proper balance:1. Where and how much

weight is required over it? 2. Whether there is any leakage

of air? 3. And what effect is getting on air of atmosphere

and how much it is? So that we can solve the problem if any, in making the body. Now we start the

work, after making the body. Complete body is made of blue foam. We have used two vertical shades so

that there is no adverse effect of outer air, propulsion system, (as this has been shown in figure). So that

the specific path may get the air and while lifting air may pass inside, so a net with frame is fixed.

Figure 12 MOTOR SUPPORT

Figure 13 SKIRT CONSTRUCTION

Figure 14 ASSAMBLY

After completing the body we have fixed the camera on the front side, as shown in figure.

Figure 15 FINAL CONSTRUCTION

6.1 Remote and receiver

Four channels were the minimum required to manually control each actuator on the craft: lift system,

Thrust vector, differential thrust. The remote and receiver selected was a spare unit held by the

University, which had a total of six channels. In particular the remote, or radio, was a FLY SKY CT6B.

6.2 Electronic speed controller (ESC)

The electronic speed controller is used as an electrical isolator between the motor and the MCU,

Whilst acting as a controller for the electric motor. An Electronic Speed Controller (ESC) is required

in order to provide a high degree of controllability and protect the motor from incorrect signals and

interference levels. Manufacturers recommendations suggest a 25 A ESC and based on this we selected

an available Constant Current: 25A -Max. Current: 30A (for 10 seconds) WAIGHT 16 GM , BEC-2 AMP.

Lower rated ESC's were available, however are undesirable due to incompatibility warnings with high

powered motors operating near maximum performance limitations and known reliability issues.

The selected ESC can operate with up to a 2 cell Lithium Ion Polymer (LiPo), providing automatic

Figure 16 CIRCUIT DESIGN

Figure 17 REMOTE AND RECIEVER

brake settings, battery type recognition, low voltage cut-off protection, startup modes and variable

signal timing.

6.3 Battery

Due to high costs of a 6 cell battery, a 3 cell LiPo was used, in

particular a Hacker 20C with a charge capacity of 2200 mAh.

This gives a minimum battery life of 2.7 minutes when motor is

run at calculated power of 975 W . It is expected that the

endurance of the propulsion system will far exceed this

however, as motors will not need to be run at full power for

the entire time.

6.4 Motor

The propulsion motors are used to drive the propellers,

providing thrust to accelerate the hovercraft.

Two identical motors are required for a dual vector

thrust design. The motors required a high degree of

controllability, the ability to turn on/off quickly and

operate over a variety of operational speeds. To

achieve this an electric motor was required. a brushless

electric motor was required over a brushed motor, able

to provide more power and lower electromagnetic interference, which reduced landmine detection

interference. Size restrictions further limited selection to an in-runner motor over an out runner, being

significantly smaller, allowing for higher flow and thrust efficiencies.

6.5 Servomotor

Servo motor is used for a changing a direction of rudder

and also used for controlling a camera direction. we used

a two ball bearing servo for camera controlling and one

servo motor used for rudder controlling.

Figure 18 BATTERY

Figure 19 MOTOR

Figure 20 SERVO MOTOR

The design criteria for a minimum speed of 5 m/s (18 km/h) was established in order to have an overall

better performance than the hovercraft built in 2008-2009 at Dalhousie University.

The testing of the speed test was conducted on pavement terrain as it is the best for performance

hence why it was selected for the test. If time is adequate speed test will be completed on other

surfaces.

1. Hovercraft was placed on a flat surface with adequate room to open full throttle.

2. Controller was turned on, battery plugged in.

3. Lift motor was started.

4. Thrust motor was then throttled up to full throttle.

5. Once hovercraft meets what is perceived as max speed, the throttle was released.

The following are the results of the speed test on the hovercraft. Each measurement was repeated

twice to ensure accuracy.

Results of the speed test were mostly successful. The hovercraft performed really well on pavement

and exceeded our design requirement of 5 m/s. Although on the gravel the craft did not meet the 5

m/s, the team believes that the craft performed effectively. The run which was used for the gravel test

was less than 100 m in length and therefore the craft was not able to reach maximum speed. Given a

longer run of gravel the team believes that the craft could meet the requirement of 5 m/s.

Performance on grass was not admirable as there was too much friction which restricted the craft from

travelling up to speed. This is usual as it is the toughest surface for hovercrafts to hover. Overall, the

speed test was deemed a success.

One of the main capabilities of the hovercraft is established that it must be able to work on various

types of terrain. This has been established through many other tests but is a simple pass or fail scale

whether the hovercraft worked or didn’t on these types of terrain.

1. Hovercraft was placed on the various surfaces.

2. Both engines were turned on.

3. Hovercraft was driven around and if performance was satisfactory a pass grade given.

Terrain tests were deemed a large success as the hovercraft was capable of operating on all smooth

services, while grass provided it much difficulty to thrust. However literature available online shows

that grass is one of the hardest surfaces for a hovercraft to traverse because the craft does not get

good lift separation between the ground, grass, and skirt. On all other surfaces (cement, gravel, water,

and sand) the hovercraft was able to both lift and thrust and steer adequately to provide control of

operation.

This test was also deemed a success, as in almost all cases the hovercraft was able to perform as

desired. With respect to the low performance on grass, this could be solved through a more powerful

motor in either lift, thrust, or both. This would allow the craft to lift higher and gain more separation,

power through the separation which is already occurring, or both, respectively.

TABLE 7 : TERRAIN TESTING RESULTS

TERRAIN TEST # PASS FAIL

Cement 1

2

3

Gravel 1

2

3

Grass 1

2

3

Water 1

2

3

Sand 1

2

3

8.1 Conclusion

To date, the authors of this report has successfully designed and manufactured an operational hover-

craft. Remote control of this hovercraft has been achieved and a comprehensive set of performance

tests implemented, confirming the design specification under ideal operating conditions. While the

autonomous functionality of the hovercraft, including active yaw control and way point navigation,

hasn't reached the final stage of testing and troubleshooting due to time constraints, the extensive

design effort applied to these systems provides a solid foundation for further work in this area.

8.2 References

http://www.rqriley.com/hc-calc.html

http://www.hovercraft.com/content/

http://en.wikipedia.org/wiki/Hovercraft

https://sites.google.com/site/kearnsbryan/HoverCalculations-ShaftSizing.xls

https://sites.google.com/site/kearnsbryan/HovercraftDesignToolsrev3-20-08.xls

http://www.model-hovercraft.com/calculator.html

http://4wings.com.phtemp.com/tip/bag.html

Theory & Design of Air Cushion Craft By Liang Yun, Alan Bliault

Principles of hovercraft By Dr TOM margerisom

Hovercraft design and construction Gordon H. Elsley, Anthony John Devereux

The Bill of Materials (BOM) is a comprehensive list of all the components on the hovercraft. The

BOM is separated into the main systems of the platform for which each is numbered. The numbering

system is summarized as follows:

115-XX-YY-ZZ(D)(T)(A)(V)

1. 115 - the project number

2. XX - The System Number

(a) 01 - Deck

(b) 02 - Lift

(c) 03 - Skirt

(d) 04 - Propulsion

(e) 05 - Electronics/Mechatronics

(f) 06 - Body

(g) 07 - Assembly

3. YY - The System Subassembly Number

4. ZZ - The Item Number

5. D - The item number should be followed with a D if design is required

6. V - The item number should be followed with a V if it's a vendor item

Drawing Numbers follow the same convention.

TABLE 8 : BILL OF MATERIAL

ID

NUMBER

SECTION ITEM VENDOR

OR

DESIGN

AMOUNT DESIGN NO

DECK

115-01-01-01D DECK TOP BASE PLATE DESIGN 1

115-01-01-01 115-01-01-02D DECK BOTTOM BASE PLATE DESIGN 1

115-01-02-01V DECK U CLAMP (ALLUMINUM) VENDOR 7

115-01-03-01V DECK GLUE TAPE VENDOR 20 ft

115-01-04-01V DECK PLASTIC STRIPE (BLACK) VENDOR 12 ft

LIFT

115-02-01-01D LIFT LIFT MOUNT DESIGN 1 115-02-01-01

115-02-02-01D LIFT MOTOR SUPPORT STRIPE (ALLUMINUM) VENDOR 1

115-02-03-01V LIFT 2 x 3cm SCREW VENDOR 2

115-02-04-01V LIFT FEVICOL VENDOR 50 ml

115-02-05-01V LIFT 4 x 8mm SCREW VENDOR 4

SKIRT

115-03-01-01V SKIRT PLASTIC SQUARE VENDOR 2.5 x 4 ft

115-03-01-02D SKIRT PLASTIC (CUT IN SHAPE) DESIGN 1 115-03-01-02

115-03-02-01V SKIRT GLUE TAPE VENDOR 15 ft

PROPULSION

115-04-01-01D PROPULSION FAN DUCT DESIGN 1

115-04-01-01 115-04-01-02D PROPULSION RUDDER DESIGN 3

115-04-02-02V PROPULSION CYCLE SPOKE VENDOR 4

115-04-03-01D PROPULSION MOTOR SUPPORT DESIGN 1 115-04-03-01

115-04-03-02V PROPULSION 4 x 8mm SCREW VENDOR 4

115-04-04-01V PROPULSION FEVICOL VENDOR 50 mL

ELECTRONICS / MECHATRONICS

115-05-01-01V ELECTRONICS BRUSHLESS MOTOR VENDOR 2

115-05-01-02V ELECTRONICS ELECTRONIC SPEED CONTROLLER (ESC) VENDOR 2

115-05-02-01V ELECTRONICS 11.1 V LI-PO BATTERY VENDOR 1

115-05-03-01V ELECTRONICS SERVO MOTOR VENDOR 3

115-05-04-01V ELECTRONICS CAMERA VENDOR 1

115-05-04-02V ELECTRONICS CAMERA MOUNTING VENDOR 1

115-05-04-03V ELECTRONICS CAMERA BATTERY (9V) VENDOR 1

115-05-05-01V ELECTRONICS RECIEVER VENDOR 1

115-05-05-01V ELECTRONICS REMOTE VENDOR 1

115-05-01-03V ELECTRONICS PROPELLER VENDOR 2

BODY

115-06-01-01D BODY CABINE DESIGN 1 115-06-01-01

115-06-02-01D BODY SPOILER DESIGN 1 115-06-02-01

115-06-03-01D BODY AIR VANE DESIGN 1

ASSEMBLY

115-01-00-00AS DECK DECK DESIGN 1

115-AS-00-00

115-02-00-00AS LIFT LIFT DESIGN 1

115-03-00-00AS SKIRT SKIRT DESIGN 1

115-04-00-00AS PROPULSION PROPPULSION DESIGN 1

115-06-00-00AS BODY BODY DESIGN 1

TABLE 9 : PROJECT SHEDULE

SR NO TASK NAME DURATION START DATE FINISH DATE

1 Define project 2 days 01-02-13 02-02-13

2 Project planning 5 days 04-02-13 08-02-13

3 Prepare a simple design 8 days 09-02-13 17-02-13

4 Market survey 4 days 18-02-13 22-02-13

5 Prepare a final design 11 days 25-02-13 10-03-13

6 Purchase a equipment from market 7 days 11-03-13 19-03-13

7 Manufacturing 4 days 18-03-13 01-04-13

8 Assembly 7 days 02-04-13 10-04-13

9 Testing 5 days 11-04-13 17-04-13

10 Problem solving or rework 5 days 18-04-13 24-04-13

11 Prepare a final report 8 days 25-04-13 04-05-13

The following section outlines a detailed budget of all the necessary parts which were purchased in order

to build the hovercraft. The final budget can be seen in Table 9. The budget is within the allotted budget

which the Department of Mechanical Engineering at Ahmedabad gave to My team.

TABLE 11 : BUDGET

SR.NO ITEM RATE QUANTITY TOTAL RATE

IN RS

ROBOKITS INDIA , JUDGES BUNGLOW , AHMEDABAD

1 11.1 V LI-PO BATTERY 2500/- 1 2500/-

2 BATTERY CHARGER 1000/- 1 1000/-

3 BRUSHLESS MOTOR 950/- 2 1900/-

4 CAMERA MOUNTING 1500/- 1 1500/-

5 CAMERA WITH DVR 3550/- 1 3550/-

6 CHARGER SMPS 180/- 1 180/-

SPHERE HOBBIES , PALDI , AHMEDABAD

7 REMOTE WITH RECIEVER 2900/- 1 2900/-

8 PROPELLER (PAIR) 250/- 2 500/-

9 SERVO MOTOR 820/- 1 820/-

10 SERVO EXTENSION 320/- 2 640/-

SHIVCO HOBBEY CENTRE , SHIVRANJANI CROSS ROAD , AHMEDABAD

11 ELECTRONIC SPEED CONTROLER (ESC) 975/- 2 1950/-

12 T CONNECTOR 55/- 4 220/-

13 GOLD CONNECTOR 50/- 6 300/-

14 WIRE 58/- 1 ft 58/-

EXTRA

15 SCREW,NUT AND BOLT, PLASTIC,GLUE,FOAM ETC

SERVICE TAX 5%

500/-

16 900/-

TOTAL 18918/-

WE ARE USE HOVERCRAFT CALCULATOR FROM FOLLOWING LINKS :

(I) https://sites.google.com/site/kearnsbryan/HovercraftDesignToolsrev3-20-08.xls

(II) https://sites.google.com/site/kearnsbryan/HoverCalculations-ShaftSizing.xls

(III) http://www.rqriley.com/hc-calc.html

(IV) http://www.model-hovercraft.com/calculator.html

PROJECTION

PROJECT 115 :- REMOTE CONTROLES HOVERCRAFT PART NO 115-01-01-01 PART DESCRIPTION DECK (PLATEFORM)

DRAWN BY VYAS TAJAGNA .P. MATERIAL FOAM ALL DIMENSIONS ARE IN INCH

DATE QUANTITY 2 SCALE NA INSTITUTE NAME F.D. (MUBIN) INSTITUTE OF ENGINEERING AND TECHNOLOGY

PROJECTION

PROJECT 115 :- REMOTE CONTROLES HOVERCRAFT PART NO 115-02-01-01 PART DESCRIPTION LIFT MOUNTING



PROJECTION

PROJECT 115 :- REMOTE CONTROLES HOVERCRAFT

PART NO 115-03-01-02 PART DESCRIPTION SKIRT

DRAWN BY VYAS TAJAGNA .P. MATERIAL PLASTIC ALL DIMENSIONS ARE IN INCH


PROJECTION

PROJECT 115 :- REMOTE CONTROLES HOVERCRAFT PART NO 115-04-01-01 PART DESCRIPTION FAN DUCT WITH RUDDER

DRAWN BY VYAS TAJAGNA .P. MATERIAL FOAM / ACRYLIC ALL DIMENSIONS ARE IN INCH

DATE QUANTITY SCALE NA INSTITUTE NAME F.D. (MUBIN) INSTITUTE OF ENGINEERING AND TECHNOLOGY

PROJECTION

PROJECT 115 :- REMOTE CONTROLES HOVERCRAFT PART NO 115-04-03-01 PART DESCRIPTION MOTOR SUPPORT FOR PROPULSION



PROJECTION

PROJECT 115 :- REMOTE CONTROLES HOVERCRAFT PART NO 115-06-01-01 PART DESCRIPTION CABIN



PROJECTION

PROJECT 115 :- REMOTE CONTROLES HOVERCRAFT PART NO 115-06-02-01 PART DESCRIPTION SPOILER



PROJECTION

PROJECT 115 :- REMOTE CONTROLES HOVERCRAFT PART NO 115-AS-00-00 PART DESCRIPTION FINAL ASSEMBLY

DRAWN BY VYAS TAJAGNA .P. MATERIAL NA ALL DIMENSIONS ARE IN INCH

DATE QUANTITY NA SCALE NA INSTITUTE NAME F.D. (MUBIN) INSTITUTE OF ENGINEERING AND TECHNOLOGY

final report

Education

design project

process of engineering

initial design

functioning hovercraft

detailed design drawings

final selected design

kamlesh patel

testing ofthe hovercraft