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VORTEX Spring Final Review

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VORTEX Spring Final Review VORTEX Vertically Optimized Research, Testing, & EXploration Spring Final Review Team Mohamed Aichiouene Stephen Albert Joseph Buescher Bill Chabot Customer: Steve Borenstein Colton Cline Brandon Cummings Advisor: Donna Gerren Roland Ilyes Delaney Jones Project Manager: Bill Chabot Cameron Kratt Michael Patterson Joseph Rooney Justin Troche Project Purpose Design Solution CPE’s Requirements Risks Validation Project Planning Backup Slides 2 Project Overview Mission Statement 3 VORTEX In order to expand the capabilities of the IRISS center and TORUS project in gathering meteorological data and understanding the formation of supercell thunderstorms, the VORTEX team will bring Vertical Takeoff and Landing (VTOL) functionality and extended endurance to the RiteWing Drak airframe. Design Systems Project Project Overview Testing Backup Slides Description Engineering Management Mission CONOPS 4 Design Systems Project Project Overview Testing Backup Slides Description Engineering Management Summary of Results 5 Level 1 Level 2 Level 3 All motors and actuators shall be successfully integrated with the flight All external (non-native) sensors are Avionics & controller. The telemetry link shall be successfully integrated with the avionics - Electronics maintained with less than 50% packet loss system. within 2 km of the ground station. Both the VTOL and fixed-wing modes have valid dynamic models to ensure active The aircraft shall autonomously execute a stabilization is possible. Ensure that the The aircraft can autonomously execute a full mission profile, transitioning between Autonomy chosen avionics package interfaces takeoff and landing. flight modes, and land within a 1.5 meter successfully with propulsion system, radius of a target location. sensors, and connectivity with ground station. The aircraft shall have an autonomous return to loiter function if telemetry is lost for Safety an extended period (90 seconds) as well as - - capability to terminate the flight immediately upon command from the GSE Design Systems Project Project Overview Testing Backup Slides Description Engineering Management Summary of Results 6 Level 1 Level 2 Level 3 Show on a static test stand that the Maintain tethered hover at 2 m of altitude for 30 Aircraft shall demonstrate takeoff ability via propulsion system is capable of producing seconds as well as demonstrate capability to RAP-Cat launch system as well as Flight enough thrust to provide a TWR greater transition to horizontal flight while aircraft is demonstrate full transition from vertical to than 1 mounted to a test stand horizontal flight modes. The aircraft shall cost no more than The aircraft shall cost no more than $900, The aircraft shall cost no more than $1000, not Budget $1250, not including IRISS avionics not including IRISS avionics package or including IRISS avionics package or batteries package or batteries batteries The propulsion system shall maintain required thrust output for the equivalent of 1 hour cruise and 2 takeoffs and landings Demonstrate 1 hour of flight cruise as well Endurance (approximately 1hr 16 minutes) on a static - as 2 takeoffs and landings test stand in simulated freestream conditions of 18 m/s with >15% battery remaining A finite element analysis of the modified The aircraft will have full integration capabilities air-frame will be performed to The airframe shall withstand axial and Airframe with RAPCat launch system, and show that it demonstrate that it can withstand the lateral forces up to 10G. can withstand the forces due to acceleration. required forces with a FOS of 1.7 Design Systems Project Project Overview Testing Backup Slides Description Engineering Management 7 Design Description Critical Project Elements 8 Element Justification Vertical Takeoff and Landing Primary deliverable of project. (VTOL) Structure Structure must withstand forces of takeoff, flight, and (STR) landing. Endurance Aircraft must be able to maintain flight for the required (END) duration of 1 hour plus takeoffs and landings. Aircraft must autonomously perform mission flight Automation profile as well as controlling takeoff, landing, and (AUT) transitions. Design Systems Project Project Overview Testing Backup Slides Description Engineering Management Functional Requirements 9 FR1 VTOL The aircraft shall be a VTOL conversion of the COTS Ritewing RC “Drak” airplane kit FR2 END The aircraft shall have an endurance of 1 hour with 2 takeoffs and landings The aircraft shall be able to autonomously execute all aspects of its mission from first FR3 AUT takeoff through final landing FR4 AUT The aircraft shall maintain communication with the ground station up to a distance of 2km FR5 STR The aircraft shall be capable of carrying a 0.5kg payload FR6 STR The aircraft shall be capable of taking off from existing RAPCat launch system The airframe, propulsion system, and required mounting hardware shall cost no more FR7 VTOL than $1000 per aircraft Design Systems Project Project Overview Testing Backup Slides Description Engineering Management Final Design 10 Empennage Rear Vertical Motor Pitot Probe Key Parameters Dimensions: ● Wingspan: 1.55m ● Tip-to-Tail: 1.10m Weight: GPS Navigation ● 6.0kg Forward Tilting Motors Design Systems Project Project Overview Testing Backup Slides Description Engineering Management Final Design 11 Reinforced Stabilizer Landing Skids Cutout for LiDAR RAPCat Bracket and Landing Leg Design Systems Project Project Overview Testing Backup Slides Description Engineering Management Final Design 12 Elevon Servos Custom Li-Ion Battery Pack Power Module RC Receiver LiDAR IRISS Avionics Board 0.5kg Payload Design Systems Project Project Overview Testing Backup Slides Description Engineering Management System Functional Block Diagram 13 Design Systems Project Project Overview Testing Backup Slides Description Engineering Management Changes Since TRR 14 Electronics ● Upgraded tilt servos for higher torque ● Airspeed sensor protocol changed to I2C Structures TRR ● Mass of tilt rotor wing mount reduced ● Reduced characteristic drag ● Increased structural support in rear motor mount Aerodynamics ● Designed and manufactured empennage Automation ● Initial aircraft tuning in hover ● Integrated LiDAR SFR Design Systems Project Project Overview Testing Backup Slides Description Engineering Management Elements Critical for Project Success 15 Vertical Takeoff and Landing ● Tricopter configuration with tilting front motors ● High discharge custom battery Structures ● Forward tilt motor mounts ● Rear vertical motor mount Endurance ● Empennage for better stability and horizontal cruise ● High voltage custom battery Automation ● Rangefinding lidar ● ArduPilot parameters tuned to match aircraft configuration ● Various flight mode settings and autonomous mission profiles Design Systems Project Project Overview Testing Backup Slides Description Engineering Management 16 Test Overview Test Overview 17 Functional Element Test Description Status Requirement Wing Motor Verification of FEM model and testing 1 FR6 STR Complete Mount Stress structural limits of wing motor mounts Battery Verify and prove the assembled battery meets 2 FR2 END Complete Endurance modeled capacity performance Testing thrust and power draw in static 3 FR1 VTOL Static Motor Complete conditions 4 FR3 AUT Controls Verify that control surfaces actuate properly Complete 5 FR3 AUT LiDAR Testing LiDAR system for accuracy Complete Verify/test avionics package and 6 FR4 AUT Telemetry Complete communications Design Systems Project Project Overview Testing Backup Slides Description Engineering Management Test Overview 18 Functional Element Test Description Status Requirement Dynamic Testing thrust and power draw in flight 7 FR2 END Complete Motor conditions Car Top 8 FR2 END Obtain aerodynamic forces to validate CFD Complete Aerodynamic RAPCat Validate that Drak fits into existing RAPCAT Planned 9 FR6 STR Integration bracket and test launch procedure 4/19-4/23 10 FR1 VTOL Hover Verify stability in hover Complete 11 FR2 END Full Flight Verify that Drak can execute the mission Planned 4/21 Design Systems Project Project Overview Testing Backup Slides Description Engineering Management Wing Motor Stress Testing 19 What and Why: ● Verification of FEM simulations; ensuring requirements met ● Increasing load applied to end of motor arm / wing assembly ● Removes risk of failure during maximum loading in flight Testing Procedure: ● Wing spars clamped to table ● Weight incrementally added to the end of the motor arm in 0.5kg increments Requirement Description FR 6 RAPCat Compatibility Motor mount Withstand 5G acceleration DR 6.2 Complete structural test during RAPCat launch Withstand 10G during takeoff DR 6.5 and landing operations Design Systems Project Project Overview Testing Backup Slides Description Engineering Management Battery Endurance Testing 20 What and Why: ● Verification of custom battery assembly functionality ● Reduces the risk of power capabilities for the aircraft Static Test Thrust Testing Procedure: Stand ● Verify battery cell balanced voltage ● Maintained a cruise condition current draw until battery voltage drops below 18V Test Board RC Power benchmark Meter Static Test Setup (in-action) Exposed battery view Software Complete Battery Test Overview Design Systems Project Project Overview Testing Backup Slides Description Engineering Management Static Propulsion Test Stand 21 What and Why: Propulsion test stand setup ● Test for thrust, power, and endurance requirements for the propulsion subsystem ● Using RC Benchmark
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