1. Oculus Superne

2. 2 System Definition Review Mission Objectives Concept of Operations Aircraft Concept Selection Payload Constraint Analysis and Diagrams Sizing Studies to Date Aircraft Concept

3. 3 System Definition Review Mission Objectives Concept of Operations Aircraft Concept Selection Payload Constraint Analysis and Diagrams Sizing Studies to Date Aircraft Concept

4. 4 To provide a multi-service UAS which acts as the primary detection method and facilitates a rapid response in the event of a system failure or natural disaster. Mission Statement

5. 5 Target Market Mission Power Line Pipeline Forest Monitoring Business Plan Target Customers DOT NPS Private Oil/Gas Companies

6. 6 Customer Attributes Patrolling the Right-of- Way –Third Party Infringement Constant Coverage Cost Reduction Safety Factors

7. 7 Engineering Requirements

8. 8 System Definition Review Mission Objectives Concept of Operations Aircraft Concept Selection Payload Constraint Analysis and Diagrams Sizing Studies to Date Aircraft Concept

9. 9 Operation Profile Type of Equipment –Ground Stations –Relay Stations –UAV Takeoff/Landing on Rough Airfield Operate from 1000 ft (AGL) Observe & Transmit to Local Relay Stations Relay Stations Transmit Information Back to Operator Number and Frequency of UAV Flight Completely Customer Defined

10. 10 System Definition Review Mission Objectives Concept of Operations Aircraft Concept Selection Payload Constraint Analysis and Diagrams Sizing Studies to Date Aircraft Concept

11. 11 Pugh’s Method Concepts generated by individual group members Picked base line Aircraft Compared generated Aircraft to base line Narrowed Scope Performed method again, with new hybrid ideas

12. 12

13. 13 Concept Generation Selection

14. 14 Models from Pugh’s

15. 15 System Definition Review Mission Objectives Concept of Operations Aircraft Concept Selection Payload Constraint Analysis and Diagrams Sizing Studies to Date Aircraft Concept

16. 16 Sensors LIDAR (Laser Imaging Detection and Ranging) –Corridor Mapping –Land Surveying –Vegetation Growth / Density LiteMapper 5600 components Airborne Lidar Terrain Mapping System IR/Visual Camera - Thermal Imaging - Video Tracking - Detailed Pictures

17. 17 Payload Requirements Camera Resolutions At 1000 ft AGL –466 ft x 582 ft At 12x Zoom –34 ft x 43 ft

18. 18 System Definition Review Mission Objectives Concept of Operations Aircraft Concept Selection Payload Constraint Analysis and Diagrams Sizing Studies to Date Aircraft Concept

19. 19 Performance Constraints Maneuvering –2g max Climb rates –Terrain adjustment: 0.9ft/s –Minimum Climb Rate at Service Ceiling : 1.67ft/s Altitude –Ceiling: 20,000ft MSL Velocity –Loiter: 100kts –2g Turn: 87kts

20. 20 Constraint Diagram Constants

21. 21 Constraints Wing Loading = 16 lb/ft 2 Power to Weight =.08 hp/lb

22. 22 System Definition Review Mission Objectives Concept of Operations Aircraft Concept Selection Payload Constraint Analysis and Diagrams Sizing Studies to Date Aircraft Concept

23. 23 Aircraft Design Mission Low Cost Solution for Frequent Area Coverage Long Endurance Time Stable Observation Platform Designed to Pipeline Constraints

24. 24 Sizing Approach MATLAB –From Constraint Diagram Power to Weight Wing Loading ACS –Results Were Passed Into ACS –Currently Refining Inputs Engine Data Prop Data

25. 25 Current Estimates

26. 26 Current Engine Estimate UAV Engines ltd –Model AR801-50

27. 27 System Definition Review Mission Objectives Concept of Operations Aircraft Concept Selection Payload Constraint Analysis and Diagrams Sizing Studies to Date Aircraft Concept

28. 28 Aircraft Configuration Pusher –Decreased Vibration (payload) –Clean Air Over Fuselage –Visibility High AR –Increased L/D Boom Mounted Inverted ‘V’ Tail –Prop Position –Weight Savings –Lower Drag Pod Fuselage –Weight Savings

29. 29 Internal Layout Aircraft Dimensions –Fuselage Length = 6ft –Width = 1.8 ft –Height =.85 ft –Wingspan = 14 ft Payload Volume –1.5 ft 3 Engine Volume –.86 ft 3 Avionics –.24 ft 3 Wing Box / Extra Fuel –1.4 ft 3

30. 30 3 View Layout

31. 31 Stability Analysis X cg 3.649 CLαCLα.14 X ac,wing 3.288 X ac,ht 8.313 CmαCmα -.029 Static Margin.205 Some basic stability analysis has been done for this aircraft. Current estimates of the static margin for a fully loaded aircraft are 20%. Current estimates of the static margin with no fuel are 18%.

32. 32 Next Steps Find more accurate aircraft weights. Create a more accurate CATIA model of the aircraft. Possible testing of the aircraft shape in FLUENT. Final airfoil selection. Structural analysis.

33. 33 Summary Mission Objectives Concept of Operations Aircraft Concept Selection Payload Constraint Analysis and Diagrams Sizing Studies to Date Aircraft Concept

34. Questions?