UAV- A MANNED VEHICLE IN ADVERSE … fileDesign of the proposed system is sculpted by means of CATIA...

INTERNATIONAL JOURNAL OF RESEARCH IN AERONAUTICAL AND

MECHANICAL ENGINEERING

ISSN (ONLINE): 2321-3051

Vol.3 Issue.1,

January 2015.

Pgs: 128-142

Sriram.R, Nandhini.S

128

UAV- A MANNED VEHICLE IN ADVERSE

ENVIRONMENTS

Sriram.R1, Nandhini.S

2

1PG- SVCE, Sriperumbudur, [email protected] 2 PG- SVCE, Sriperumbudur, [email protected]

8/42 Salem mail road, Elavanasur Kottai, Ulundurpet TK, Villupuram, +8870595303

Abstract

Now a day plenty of amounts are being debilitated in defence sector. Gross Domestic Product (GDP) is an

indicator which reveals the prosperity of a nation. Nation with rising riches needs adequate physique in

protecting the country’s hard earned assets along with its dwellers. A Precinct which plays dominant role for the

triumph of these above stated devoir is the defence sector. Aviation industry earned a blossoming reputation

right from the opus of Unmanned Aerial Vehicle (UAV) which penetrates the areas where personage cannot.

The Aerosonde UAV is a small unmanned aerial vehicle (UAV) designed to collect weather data including

Temperature, atmospheric pressure, humidity and wind measurement over oceans and remote areas. This

research work address the disasters occurred when the UAV had maneuvered in adverse conditions. An

alternate approach to evade this failure is by employing control horns and positioning the on board for acquiring

values. Design of the proposed system is sculpted by means of CATIA V5 software which proves to be best

suited for reverse engineering. Fabrication of proposed model is accomplished and tested in adverse

environments. Proposed model proved to be a new resolution in the field of RC modeling during test flight.

Keywords: Aerosonde UAV, E-logger, Control horns

1. Introduction

UAV’s commonly find its application in defence and patrol in situations where the risk of sending a human

piloted aircraft found to be threatening, or the situation of employing piloted aircrafts proves to be impractical.

One of the predecessors of today’s completely automated Unmanned Aerial Vehicles was the “aerial

torpedoes”, designed and built during First World War.

Advanced UAV’s used radio waves for guidance, allowing them to fly missions and return. They were

constantly controlled by a human pilot, without deserving a place in cockpit. This made them much like today’s

RC model airplanes which many people fly as a hobby. It is interesting to note that the government consider all

aircraft UAV’s, if they are unmanned and used by a government or business. After the invention of the

integrated circuit, engineers were able to build sophisticated UAV’s, using electronic autopilots which

replicates the work of pilot.

It was at this stage of development that UAV’s became widely used in defence applications. UAV’s

could be deployed, fly themselves to a target location, to target the enemy with weapons or survey it with




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January 2015.

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cameras and other sensor equipment. Modern UAV’s are controlled with both autopilots, and human controllers

in ground stations. This allows them to have long flights, uneventfully flights under their own control, and fly

under the command of a human pilot during complicated phases of the mission.

2. Methodology

Figure 1: Methodology of our paper

3. Fabrication of Modified UAV Requirements

3.1 Materials used For Fabrication of RC model

Expanded polystyrene

Cyno glue

3.2 Equipment details of RC model of Aerosonde UAV

There are 3 main types of foams used for RC airplanes they are:

EPP (Expanded poly propylene).

EPO (Expanded poly olefin).

EPS (Expanded poly styrene).




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EPP foams are preferred because of its toughness and flexibility. It is light and used for Combat wings, durable

by demanding carbon rods for reinforcement. Density of the material varies from surface to core. It has a waxy

feel which requires spraying of 3M adhesive.

Table 1: Equipment required and its specification

Battery (B3 Pro Compact Charger)

Balance charge current 850mA

Bush Less Motor (2840kw) -20AMPS

Cable length 28cm

Case Plastic

Compliant with Lithium battery 1

Continuous current 3A

Control Horns Nylon control horns

Data Recorder Eagle Tree V4 eLogger

DC 5.6V-20V

Dimensions 90mm*55mm*35mm

Dimensions (L*W*H) 13*11*4mm

Display Green, Red.

Electronic Speed Controller-3AMPS

Global Positioning System (GPS)

IBM 2205-14

Input voltage 110V-240V.

Max charge current 3*700mA

Pepersistent current 5A




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Propeller- Double blade (6*4E)

Receiver- 2.4HZ

Channel 2.4 GHz, Battery needed

of 1.5V, Model no: FS-R6A

Servos - 9gms. 4 Channels

Transmitter

FS T4A, Channel 4, 100% Digital

proportional radio control system.

Model no: H700183

Weight 180g

Y Connector 3 Phase Y Connection

3.3 Software Used For Data Collection

Figure 2: Eagle Tree V3 eLogger.

It is an extremely portable unit that can be used in-flight or on the workbench for both gathering and

analyzing data via both Live mode in conjunction with a laptop or the Eagle Tree Power Panel. Data storage is

accomplished by employing eLogger’s internal memory and in turn could be downloaded to your computer via

USB.

Figure 3: Parameter measured using Eagle Tree eLogger V3.

Once the data is collected, it is extremely easy to extract. Plug the eLogger into the computer, bring up

the Data Recorder software and click download. Once the data is downloaded the maximum readings will all be

displayed. Next, it is either possible to watch the flight via the gauges displayed or go directly to the graphing

portion of the software. In order to watch the data you have just recorded via the gauges, hit Play. To begin

graphing, a quick click on Graph Data is all that is needed.




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Customizing the graphs is an easiest task. Parameters to graph, color, line thickness, 2D, 3D, axis

placement, etc. could be easily accessed. The length to which you can customize the graphs is limitless. It all

happens in the Edit menu, which could be accessed through the Graph page.

3.4 Fabrication Procedure

Equipments needed includes such as 4 Servos, ESC, GPS, Temperature sensor, Data recorder, Battery, Receiver

and other materials such as Y Connector, Control horns, Transmitter, Carbon rods, Foams and Adhesives.

Place two servo in each wing by using adhesives (Cyno glue) and place the push pull rods at the

wing portion in the respective space provided for yielding the strength characteristics.

Place other two servo inside the fuselage its gets connected with elevator and rudder for deflections

by using control rods.

Each Servo is attached with control horns using screws and control rods.

By using Y Connector and push pull rods connect the port and starboard wing to the fuselage.

Use the Bushless motor for mounting the propeller (2 bladed) it is connected with ESC which is

mounted on center of the fuselage portion.

At nose portion of UAV, GPS and temperature sensor is to be placed and inside of rear fuselage

portion battery, Eagle tree V4 and 6 channel receiver is mounted by using adhesives and tapes.

Receiver has 6 channels in that 4 servos and ESC gets connected with it.

For starting the operation Battery is used, it is connected to ESC and Eagle tree V4 data recorder

system by using cables.

Eagle tree v4 is connected with GPS, Temperature sensor, Battery and ESC.

4. Modelling and Fabrications of Modified Aerosonde UAV

4.1 Theoretical Background

Table 2: Formula used for designing Modified UAV model

AR = b2/s

AR - Aspect ratio

b - Wing span (cm)

s - Wing planform area (cm2)

(w/s) = weight/wing area (w/s) - Wing loading (kg/cm2)

s = b2/AR AR - Aspect ratio

b - Wing span (cm)

b = sqrt (AR*s) AR - Aspect ratio

s - Wing planform area (cm2)

Wo = wcrew + wpayload + wfuel + wempty Wo - Overall weight (gm)

4.2 Design Calculation

Table 3: Design dimensions of UAV model

General Characteristics Weight Configuration Performance Calculation




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Length - 77cm

Wing span - 135cm

Wing area - 1764cm2

Overall weight - 600gm

Wing loading - 0.340 kg/cm2

Range - up to 1km

Aspect ratio - AR = 10.3

Wing loading - 0.340 kg/cm2

Wing area - 1769cm2

Wing span - 134.98cm

4.3 Aerosonde UAV model in CATIA V5

Figure 4: Design of Aerosonde UAV




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4.4 Three View Diagram of Aerosonde UAV model

Figure 5: Front View of Modified UAV model

Figure 6: Side View of Modified UAV model

Figure 7: Top View of Modified UAV model




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4.5 Fabricating Diagram of Aerosonde UAV

Figure 8: Modified Aerosonde UAV model

Figure 9: Modified Aerosonde UAV Wing Design




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Figure 10: Modified Aerosonde UAV Empennage Design

5. Result and Discussion

TEST LOCATION 1

Test location : Annanji, Theni 625531, India.

Latitude : N 100 2’ 33.2038”

Longitude : E 77030 12.2223

Time : 9.30 – 11.00 AM




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Figure 11: Recorded Parameters for 1st test location.

Figure 12: 2D GPS Data Chart.

This graph describes the relationship between the longitude and latitude. The X axis contains the

longitude in east direction and the Y axis contains the latitude in north direction. The point at which the

overlapping occurs shows the location of testing, the individual line shows the point of intersections.




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Figure 13: 3D GPS Data Chart.

The above figure depicts the 3d view of the location of the testing place plotted using its longitude and latitude.

The black colour surface indicates the testing place whereas the yellow and white colour indicates the

extensions

Figure 14: Time (Min) Vs Temperature.

The variation of temperature at various times is plotted in this graph. Since temperature depend on the time. The

temperature increases with increase in time.




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Figure 15: Time (Min) Vs GPS Altitude.

The Global positioning system is used to measure the latitude,longitude of the UAV .this graph shows the gps

altitude of 800m for the first 25 minutes.then it gains an altitude of 1000m in the next 10 minutes of the UAV in

the cruising condition.

TEST LOCATION 2

Test location : Karur - 639001, Tamil Nadu.

Latitude : N 100 57’ 33.4664”

Longitude : E 78 4’47.8008”

Time : 4.00-5.15 PM




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Figure 16: Recorded Parameters for 2nd test location.

Figure 17: Temperature, Current, Voltage Vs Time (Min).

The variation of current used in the UAV with respect to time is shown in the graph in red colour. It is a

continuous varying curve similar to the cos curve. The blue colour describes the plot between the voltage and

time. Compare to current the voltage will be used at steady level in the range of 14 to 15.whereas the current in

the range of 5 to 50.since the temperature is noted in the noon time .from the graph the brown colour indicates

the temperature is directly proportional to the time.




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Figure 18: Current Vs Time (Min).

The usage of current will vary in a fraction of seconds. Hence the graph shows the sudden variation in the

current level with respect to time. During the landing condition it requires only less amount of current so the

graph descends at the final stage.

6. Conclusion

The recent meteoric rise of UAV development highlights an issue of the growing importance of UAVs in the

future and leads to the corollary issue of whether UAVs will replace manned aircraft's roles and missions. The

bottom line is that the Services still need an organic capability for a continuous, on-demand, all-weather

platform to provide intelligence on weather forecasting. In addition, the Services must execute these operations

quickly, safely, and cheaply. Due to the frequent change in weather conditions it is quite necessary to survey the

environment conditions for the survival of human and other living beings. In remote areas such as deep forest

regions and coastal areas predicting of weather conditions is possible only by UAVs. The UAV such as

Aerosonde, plays a Vitol role in weather forecasting. Although the recovery of the mission’s during system

failure is risk in those model. Our proposed model can provide both recovery of the mission in emergency

conditions and better in finding the environmental situations in reasonable time. With the aid of GPS system

tracing of mission is also possible. There is no doubt that the unmanned aerial vehicle can provide a great

contribution in Climatology in future.

References

1. Holland, G. J., and Coauthors, (2001) “The Aerosonde Robotic Aircraft: A New Paradigm for Environmental

Observations”, published in Bull. Amer. Meteor. Soc., Vol.82, pp.889–901.

2. J.A.Curry.., et al., (2004) “Applications of Aerosondes in the Arctic”, Bulletin of the American Meteorological Society,

Vol.85, No.12, pp.1855-1861.




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3. Tad Mcgeer.., (9 October 1998) “Regulatory Issues Involving Long-Range Weather Observation by Aerosonde

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4. Edward J patten.., et al., (12 June 1963) “Study for the Advancement of Unmanned Aircraft Systems in Southern”,

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5. Po-Hsiung Lin and Cheng-Shang Lee.., et al, (2005) “The Eyewall-Penetration Reconnaissance Observation of

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7. John Andrews, (2010) “System Reliability Assessment for Real-time UAV Mission Planning”, conference in

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8. Edward H. Teets.., et al., (1998) “Atmospheric Considerations for Uninhabited Aerial Vehicle (UAV) Flight Test

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9. Gloria Kulesa.., (2003) “Weather and Aviation: How Does Weather Affect the Safety and Operations of Airports and

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10. Randy J. Lefevre.., et al., (January 2004) “ Weather Forecast Uncertainty Management And Display”, Proceedings of

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11. Stuart M. Adams.., et al., (2010) “Unmanned Aerial Vehicle Data Acquisition for Damage Assessment in Hurricane

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12. Maryam kamgarpour.., et al., (15-17 December 2010) “Trajectory Generation for Aircraft Subject to Dynamic

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13. Anthony P.Tvaryanas.., (2004) “Visual Scan Patterns During Simulated Control of an Uninhabited Aerial Vehicle

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15. Dah-Jye Lee.., et al, (29 December 2004) “See and avoidance behaviors for autonomous navigation”, this paper

was published in SPIE Proceedings, Vol.5609, pp. 12.

http://trid.trb.org/results.aspx?q=&datein=all&serial=%22The%20Potential%20Impacts%20of%20Climate%20Change%20on%20Transportation%22

http://trid.trb.org/results.aspx?q=&datein=all&serial=%22The%20Potential%20Impacts%20of%20Climate%20Change%20on%20Transportation%22

http://researchr.org/publication/cdc-2010

http://researchr.org/publication/cdc-2010

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http://pubget.com/search?q=issn%3A0095-6562+vol%3A75+issue%3A6&from=15198280

UAV- A MANNED VEHICLE IN ADVERSE … fileDesign of the proposed system is sculpted by means of CATIA...

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