UAV- A MANNED VEHICLE IN ADVERSE ENVIRONMENTS

INTERNATIONAL JOURNAL OF RESEARCH IN AERONAUTICAL AND MECHANICAL ENGINEERING ISSN (ONLINE): 2321-3051 Vol.3 Issue.1, January 2015. Pgs: 128-142 UAV- A MANNED VEHICLE IN ADVERSE ENVIRONMENTS Sriram.R1, Nandhini.S2 1 PG- 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 128 Sriram.R, Nandhini.S INTERNATIONAL JOURNAL OF RESEARCH IN AERONAUTICAL AND MECHANICAL ENGINEERING ISSN (ONLINE): 2321-3051 Vol.3 Issue.1, January 2015. Pgs: 128-142 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). 129 Sriram.R, Nandhini.S INTERNATIONAL JOURNAL OF RESEARCH IN AERONAUTICAL AND MECHANICAL ENGINEERING ISSN (ONLINE): 2321-3051 Vol.3 Issue.1, January 2015. Pgs: 128-142 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 Continuous current 1 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 IBM Global Positioning System (GPS) 2205-14 Input voltage 110V-240V. Max charge current 3*700mA Pepersistent current 5A 130 Sriram.R, Nandhini.S INTERNATIONAL JOURNAL OF RESEARCH IN AERONAUTICAL AND MECHANICAL ENGINEERING ISSN (ONLINE): 2321-3051 Vol.3 Issue.1, January 2015. Pgs: 128-142 Propeller- Double blade (6*4E) Receiver- 2.4HZ Servos - 9gms. Transmitter Weight Y Connector Channel 2.4 GHz, Battery needed of 1.5V, Model no: FS-R6A 4 Channels FS T4A, Channel 4, 100% Digital proportional radio control system. Model no: H700183 180g 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. 131 Sriram.R, Nandhini.S INTERNATIONAL JOURNAL OF RESEARCH IN AERONAUTICAL AND MECHANICAL ENGINEERING ISSN (ONLINE): 2321-3051 Vol.3 Issue.1, January 2015. Pgs: 128-142 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 AR = b2/s Table 2: Formula used for designing Modified UAV model 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) AR - Aspect ratio s - Wing planform area (cm2) Wo - Overall weight (gm) b = sqrt (AR*s) = wcrew + wpayload + wfuel + wempty 4.2 Design Calculation Table 3: Design dimensions of UAV model General Characteristics Weight Configuration Performance Calculation 132 Sriram.R, Nandhini.S INTERNATIONAL JOURNAL OF RESEARCH IN AERONAUTICAL AND MECHANICAL ENGINEERING ISSN (ONLINE): 2321-3051 Vol.3 Issue.1, January 2015. Pgs: 128-142 Wing loading - 0.340 kg/cm2 Length - 77cm Wing span - 135cm Overall weight Wing area - 600gm - 1764cm2 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 133 Sriram.R, Nandhini.S INTERNATIONAL JOURNAL OF RESEARCH IN AERONAUTICAL AND MECHANICAL ENGINEERING ISSN (ONLINE): 2321-3051 Vol.3 Issue.1, January 2015. Pgs: 128-142 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 134 Sriram.R, Nandhini.S INTERNATIONAL JOURNAL OF RESEARCH IN AERONAUTICAL AND MECHANICAL ENGINEERING ISSN (ONLINE): 2321-3051 Vol.3 Issue.1, January 2015. Pgs: 128-142 4.5 Fabricating Diagram of Aerosonde UAV Figure 8: Modified Aerosonde UAV model Figure 9: Modified Aerosonde UAV Wing Design 135 Sriram.R, Nandhini.S INTERNATIONAL JOURNAL OF RESEARCH IN AERONAUTICAL AND MECHANICAL ENGINEERING ISSN (ONLINE): 2321-3051 Vol.3 Issue.1, January 2015. Pgs: 128-142 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 136 Sriram.R, Nandhini.S INTERNATIONAL JOURNAL OF RESEARCH IN AERONAUTICAL AND MECHANICAL ENGINEERING ISSN (ONLINE): 2321-3051 Vol.3 Issue.1, January 2015. Pgs: 128-142 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. 137 Sriram.R, Nandhini.S INTERNATIONAL JOURNAL OF RESEARCH IN AERONAUTICAL AND MECHANICAL ENGINEERING ISSN (ONLINE): 2321-3051 Vol.3 Issue.1, January 2015. Pgs: 128-142 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. 138 Sriram.R, Nandhini.S INTERNATIONAL JOURNAL OF RESEARCH IN AERONAUTICAL AND MECHANICAL ENGINEERING ISSN (ONLINE): 2321-3051 Vol.3 Issue.1, January 2015. Pgs: 128-142 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 139 Sriram.R, Nandhini.S INTERNATIONAL JOURNAL OF RESEARCH IN AERONAUTICAL AND MECHANICAL ENGINEERING ISSN (ONLINE): 2321-3051 Vol.3 Issue.1, January 2015. Pgs: 128-142 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. 140 Sriram.R, Nandhini.S INTERNATIONAL JOURNAL OF RESEARCH IN AERONAUTICAL AND MECHANICAL ENGINEERING ISSN (ONLINE): 2321-3051 Vol.3 Issue.1, January 2015. Pgs: 128-142 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. 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