Oculus Superne System Definition Review Mission Objectives Concept

Oculus Superne

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

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

Mission Statement 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. 4

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

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

Engineering Requirements 7

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

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 9

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

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 11

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Concept Generation Selection 13

Models from Pugh’s 14

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

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

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

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

Performance Constraints • Maneuvering • Altitude – 2 g max – Ceiling: 20, 000 ft MSL • Climb rates • Velocity – Terrain adjustment: 0. 9 ft/s – Minimum Climb Rate at Service Ceiling : 1. 67 ft/s 19 – Loiter: 100 kts – 2 g Turn: 87 kts

Constraint Diagram Constants 20

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

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

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

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

Current Estimates 25

Current Engine Estimate • UAV Engines ltd – Model AR 801 -50 26

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

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 28

Internal Layout • Aircraft Dimensions – – Fuselage Length = 6 ft 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 29

3 View Layout 30

Stability Analysis • Some basic stability Xcg analysis has been done for this aircraft. CLα 3. 649 • Current estimates of the static margin for a fully loaded aircraft are 20%. Xac, wing 3. 288 Xac, ht 8. 313 Cmα -. 029 • Current estimates of the static margin with no fuel are 18%. 31 . 14 Static Margin. 205

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. 32

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

Questions?