Critical Design Review February 2, 2015 University of North Dakota Frozen Fury Critical Design Review February 2, 2015

General Vehicle Dimensions Sofiane Center of Gravity: 57.579 inches Center of Pressure: 68.434 Safety Margin: 1.76 Length: 105 inches Diameter: 6.155 inches Mass: 26.2 lbs

Critical Flight and Payload Systems Different subsystems of the rocket

Materials and Justifications Airframe – carbon fiber Superior strength to weight ratio Ease of workability Fins – birch plywood in carbon fiber Combines the strength of both materials for a more rigid, strong, and lightweight fin Bulk-Head/Centering ring – 0.5 inch birch plywood Cabinet quality grain, few knots, and locally available In addition to having access to these materials, members of our team have experience with them

General Vehicle Dimensions Location of Launch Lugs (inches) Fin Dimensions (mm) Location of Centering Rings (inches)

Materials and Justifications Fins Symmetric shape and quantity allows for ease of construction, trapezoidal shape limits potential damage to fins upon landing Diameter 6” diameter allows for ease of assembly and plenty of workspace. Also allows for better utilization of scrap components, and expansion of internal components if necessary Fins below the bottom of the rocket typically take much more damage than the trapizoidal design.

General Vehicle Dimensions A simple, factory made, reliable nose cone Nose Cone Dimensions (mm)

Materials and Justifications Nosecone Will be purchased to insure proper functionality West Systems Epoxy Used to bind the above materials together as well as some hardware (bolts, nuts, threaded rods) Be

Parachute Attachment Bulkhead Mention about the black powder connection Bulkhead Dimensions (inch)

Parachutes Parachute type Parachute size Harness Type Harness Length Descent Rate Drogue 36 in ripstop nylon 5ft 62 ft/s Main 115 in 16.08 ft/s Payload 58 in 22.47 ft/s

Deployment of Parachutes

Flight Analysis Total motion vs. Time

Drift Analysis at 5 mph

Drift Analysis at 10 mph

Drift Analysis at 15 mph

Drift Analysis 20 mph

Drag Coefficient at 5 mph Drag Analysis Drag Coefficient at 5 mph

Rocket in Horizontal Position AGSE Design ElectricalBox Ignition Insertion System Linear Actuator Kyle Payload System Rocket in Horizontal Position

Lifted Rocket Position Rocket in 5° to vertical Position

Frame Square Tube Iron

Basic electrical schematic Electrical Box Basic electrical schematic Arduino board Jeff All components for the AGSE will be housed in the black box that is on the frame.

Claw With Pan/Tilt Bracket Servo to open and close claw Another servo to tilt claw Claw assembly (in) Claw assembled by the team

Belt/Slider Rail Slider with belt assembly (in)

Payload Acquisition System Payload acquisition assembly (in)

Belt/Slider Rail Slider assembled by the team

Linear actuator has stall torque of 240 lbs. Actuator Position Rocket actuator assembly (in) Linear actuator has stall torque of 240 lbs.

Ignition Insertion System Kyle Side view of the ignition system

Wire Funnel Mounted to the rail Will help guide the ignition wire into the rocket motor Ignition system funnel (in)

Wire Extension Assembly 1, 16 tooth gear is driven by 51 RPM motor 2, 32 tooth gears spin rubber wheels Steel housing Will be mounted on rail Ignition system gearbox (in)

Wire Spool Housing Steel housing for spool Ignition wire is coiled around spool Mounted to rail Ignition system wire spool (in)

Final Design Changes to be Made If the stability of the rocket on the rail becomes an issue, there will be guides added to the rail. A counter weight will be added to the end of the rail behind the wire spool to alleviate motor stress of the actuator.

Design Justifications Sofiane

Selection and Justification Baseline Motor Selection and Justification Manufacturer: AeroTech Mfr. Designation: K480W Motor Type: reload Diameter: 54.0 mm Length: 57.9 cm Total Weight: 2078 g Average Thrust: 528.67 N Maximum Thrust: 1017.8 N Total impulse: 2273.3 Ns Burn Time: 4.3s Justifications 54.0 mm diameter allows for easy downscaling Black Max Propellant provides the high visibility tracking of dense black exhaust

Motor Selection: Aerotech K480W Aerotech K480W Thrust per second

Thrust-to-Weight Ratio

Avionics Dual deployment system Two Perfect Flight altimeters used as a backup system Measures barometric pressure “Mach” delay for safety Deploys drogue parachute at apogee Deploys main parachute at 3000 ft AGL and payload parachute at 1000ft AGL

Avionics: Altimeter Bay

Altimeter Bay Schematics

Payload Securing Payload Compartment 3-D View Payload Compartment Rear View

Sequence Code Jeff

Sequence Code

Declaration of Switches and Pins Code Declaration of Switches and Pins

Initialization of Switches and Pins Sequence Code Initialization of Switches and Pins

Declaration of Switches and Pins Code Starting Positions Declaration of Switches and Pins

Code Claw Actions

Code More Claw Actions

Code AGSE Actions

Code AGSE Actions

Success Criteria for AGSE Payload acquisition Payload is in the launch vehicle and secured Rocket Erection Rocket is lifted to a position of 85 degrees from the horizontal Wire Insertion Wire is fully inserted in motor and no accidental charge ignites motor

Success Criteria for Launch Vehicle Rocket launch Reaching an altitude of 3000 feet at apogee. Rocket recovery The recovery system deploying properly at the appropriate altitude and recovering the rocket on the ground such that it is deemed reusable for future launches Payload The payload should be ejected from the rocket at 1,000 feet and return to the ground with its own parachute.

Rocket Flight Static Margin Rocket Flight Stability in Static Margin Diagram The center of gravity is forward of the center of pressure (closer to the nosecone) Rocket Flight Static Margin 10.855 Center of Pressure 68.434 in Center of Gravity 57.579 in Kinetic Energy ft-lbs Drogue 1562.95 Main Parachute 68.17 Payload Parachute 70.29 Jacob

Vehicle Safety The minimum rod speed that ensures a stable flight is generally between 30 fps (20 mph) to 45 fps (30 mph). Exit rail velocity: 69.5 ft/s A pair of rail beads will be used to ensure the rocket reaches adequate speed off of the rail while maintaining proper orientation

Plan for Vehicle Safety Verification and Testing Critique Score 1/5 1 = Bad 5 = Good Comments Is this design safe? 4 This design will allow for ease of construction and eliminate safety concerns associated with more complex construction methods Is this design limiting? Altitude is expected to be reached and the design will accommodate larger motors and payload components Does this design meet the requirements of the payload/rocket? This current rocket design satisfies the requirements for the projected payload. Will this design land safely? Parachute sizes, impact absorbing design? The current size rocket and parachutes have the rocket descending rapidly under drogue, but slowing to under 25 ft/s under main. Does this design maximize performance? 3 The rocket has been designed to accommodate the payload as well as larger motors as the design is refined. Are the materials selected the best for this scenario? Carbon fiber is a strong yet lightweight material that we have had success with in years prior. Past experience with phenolic tubing has yielded structural failure. Any additional comments? ------- Conduct additional tests and review plan to ensure continued safety

Educational Engagement Physics Day at UND - November 12, 2014 This is a program for local middle school to high school students to learn about the many different facets of physics. Gave a presentation about rocketry Introduced them to the USLI program and shared our past history with the competition 200 students attended

Educational Engagement Outreach at Grand Forks area middle school Our team is still in the process of scheduling a date to visit the local middle schools. Give a brief lecture about rocketry We will build and launch balloon rockets Have a Q & A session about rocketry Expect to reach about 30-80 students.

Educational Engagement UND Physics and Astronomy Talk -February 23rd. In an hour long talk, we will detail rocketry throughout the ages and hold a demonstration of our current AGSE. The average attendance for these talks is 30-50 students and other interested parties.

Vehicle Testing Two sub-scale launches were performed to verify the recovery system and the main design (fins, nosecone). There were minor complications in each of the launches. Nate

Length ratio of subscale I: Length ratio of subscale II : Scale Launches Length ratio of subscale I: 1:1.75 Length ratio of subscale II : 1:1.4 Fins ratio: 1:2.25 Diameter ratio: 1:2

Motor and parachutes Aerotech 1211W-M Parachutes: Total Impulse: 460 N/s Motor Diameter: 1.5 in Motor Length: 9.82 in Parachutes: Drogue: 30 inches Main parachute: 28 inches Payload Parachute: 36 inches

Subscale Launch I Rocket: Length: 60.875 inches Diameter: 3 inches Mass with motors: 28.2 ounces Stability Margin: 1.3

Subscale Launch I Simulation Apogee: 2815 ft Maximum velocity: 930 ft/s

Subscale Launch I Flight Apogee: 2811 ft. Deployment of Time (s) Altitude (ft) Velocity (mph) Drogue 13.65 2804 15 Main parachutes 71.90 600 35

Flight I Complications Lack of space Increased charge Weakened bond

Subscale Launch II Rocket: Length: 73.75 inches Diameter: 3 inches Mass with motors: 31.9 ounces Stability Margin: 2.37

Subscale Launch II Simulation Apogee: 2801 ft Maximum velocity: 881 ft/s

Subscale Launch II Flight Apogee: 2621 ft. Deployment of Time (s) Altitude (ft) Velocity (mph) Drogue 13.6 2619 18 Main parachutes 62.05 600 35

Flight II Complications Obstruction when preparing break pin’s holes Slight wobble during launch Parachute Complications

Near-Future Work In the coming weeks, the team will be working on: For the AGSE: Cutting the frame and welding it Building of Ignition and lifting system Finishing the payload acquisition system Positioning of the different switches Implementing the electrical system For the rocket: Ordering of the rocket cylinders Building of the Fins Building of the Payload securing Kyle

Questions?