Student Launch Project Critical Design Review February 28, 2014

Team Structure

Final Launch Vehicle Dimensions

Key Design Features  Launch Vehicle Sections  CubeSat/Electrometer, Camera System, Parallel Boosters  Fin Style  Launch Vehicle Separations  Parallel Boosters, Booster Section, Drogue Bay/Detachable Bulkhead

Forward Section-CubeSat  Nose Cone  Electrometer  CubeSat

Avionics/Payload Section-Hazard Detection  Avionics/Payload components  Hazard Detection System  Drogue Bay disengagement

Booster Section-Parallel Boosters  Parallel booster attachment/detachment  Booster section disengagement  Fin material and shape  Positive motor retention

Final Motor Choice (18,500 ft) MotorBrand Engine CodeDiameterLengthBurn TimeImpulseThrust BoostersCesaroniJ240 RL54 mm in3.35 s Ns N MainCesaroniL61098mm in8.13s Ns N SustainerCesaroni L3150 Vmax98mm in1.57 s Ns N

Thrust Curve of Motors (18,500ft)

Table of Motor Events (18,500ft) EventTime (s)Altitude (ft)Velocity (ft/s) Motors Ignite000 Parallel Motors Burnout Separation of Parallel Boosters Main Motor Burnout Main Motor Separation Sustainer Ignites if within 5 degrees of the Z-axis Sustainer Burn Out Apogee

Final Motor Choice (9,000 ft) MotorBrand Engine CodeDiameterLengthBurn TimeImpulseThrust BoostersAerotech I229T 54 mm in1.73 s Ns N MainAerotechL339N98mm in8.43 in Ns N SustainerAerotechK1999N98mm in1.40 s Ns N Aerotech Motors were chosen over Cesaroni because of the motor mount sizes, should the team use Aerotech motors, the integration would only require the change of the type of motor casings used.

Thrust Curve of Motors (9,000 ft)

Table of Motor Events (9,000 ft) EventTime (s)Altitude (ft)Velocity (ft/s) Motors Ignite000 Parallel Motors Burnout Separation of Parallel Boosters Main Motor Burnout Main Motor Separation Sustainer Ignites if within 5 degrees of the Z-axis Sustainer Burnout Apogee

Static Stability Margin Stability Analysis From nose coneWith Booster SectionWithout Booster Section Center of Pressure ’” ” Center of Gravity ” ” Static Stability Margin Rail Size/Length1.5” (1515) / 144”

Thrust-to-Weight Ratio and Rail Exit Ascent Analysis (18,500ft) With Booster SectionWithout Booster Section Rail exit velocity (ft/s) Max velocity (ft/s) Max Mach number Max acceleration (ft/s 2 ) Peak altitude (ft) Thrust-to-Weight Ratio5:119:1

Thrust-to-Weight Ratio and Rail Exit Ascent Analysis (9,000ft) With Booster SectionWithout Booster Section Rail exit velocity (ft/s) Max velocity (ft/s) Max Mach number Max acceleration (ft/s 2 ) Peak altitude (ft) Thrust-to-Weight Ratio4.38:113.5:1

Mass Statement and Mass Margin SubsystemMass (oz)Mass Limit (oz) Propulsion (Including: motor mounts and centering rings) Structure (Including: body tube, coupling tubes, bulkheads, nose cones, fin sets) Recovery (Including: main parachute, drogue parachute, detachable components parachutes) Payload (Including: avionics bays, electrical components) Miscellaneous (Including: Paint scheme, dressings/coatings) 1620 Total

Mass Statement and Mass Margin

Recovery Subsystem 6-sided parachutes with Cd=0.75 Ripstop nylon 80 – 120 CFM 1 inch tubular nylon 4000 lbs 3/16 inch flat braided Dacron 600 lbs 3/8 inch brass grommets No 69 size “E” nylon thread 8.5 lbs

Recovery Specifications ParameterDrogueMainParallelBooster Diameter (in) Deployment Altitude (ft) Velocity at Deployment (ft/s) Descent Rate (ft/s) Harness Length (ft) Shroud Line Length (in)

Kinetic Energies ParachuteSection Mass of Section (lbs) Terminal Velocity (ft/s) Kinetic Energy (ft-lbs) ParallelParallel Motor Booster Booster Section Mini Avionics Bay Drogue Drogue & Main Bay Drogue Bay Main Avionics Bay Main Section

Predicted Drift from Launch Pad 0 mph5 mph10 mph15 mph20 mph 0 ft ft ft ft ft. 18,500 ft. Flight

Predicted Drift from Launch Pad 0 mph5 mph10 mph15 mph20 mph 0 ft ft ft ft ft. 9,000 ft. Flight

Launch Vehicle Testing Test PurposeTest Status Subscale TestTo ensure safe stage separation is possible Completed Cluster Ignition Test To ensure parallel circuitry can cause simultaneous ignition Completed Nylon Tie- Downs To ensure rocket motors all ignite before rocket launches Planned Booster Section Separation Ground Test To ensure booster section can separate from main bay with attachment scheme Planned Airstart TestTo ensure Raven3 has appropriate output current to airstart sustainer Planned

Exploding Nylon Bolt Testing Test PurposeTest Status Exploding Nylon Bolt Test To ensure exploding nylon bolts can safely separate parallel boosters from the booster section Completed. 1.5 x 3/8 inch exploding nylon bolts with 1/8 inch wide cavity almost an inch deep. Kerf mark below head. Exploding Nylon Bolts Shearing Strength To ensure exploding nylon bolts have enough shear strength to withstand rocket launch. In progress

Recovery System Testing Test PurposeTest Status To ensure design of parachute can withstand forces Completed – Successful To determine velocity that the parachute will fly, and impact force of different rocket sections Planned To test static ejection charges of full scale parachutes Planned To demonstrate durability of bulkhead attachment scheme within the rocket. Planned

Electrical Components Testing Test PurposeTest Status Raspberry Pi Camera module To test functionality and accuracy Completed. Camera board communicated effectively with Raspberry Pi RockeTilTometerTo test functionalityPlanned ElectrometerTo test functionality and accuracy Planned Transceiver to Ground Station To test functionality and accuracy Planned Linx TM Series GPSTo test functionality and accuracy Planned

Scale Model Flight Test

Staged Recovery Test Deployment Testing o Static ground test for rocket separation and parachute deployment. Altimeter Testing o Ground testing barometric pressure sensor and accelerometer calibration

Hazard Detection System Overview Cancellation of the LiDAR System Cost Availability of Parts Eliminate moving parts Raspberry Pi Edge Detection Sobel Operator Minimal components Ease of integration

P.I.M.S. Payload Overview

Tesseract Payload Overview

Hazard Detection/Avionics Bay Integration

P.I.M.S. Payload Integration Raven3 integration Avionics Bay Above the Sustainer Mini-Avionics Bay Payload Sled Keeps Electronics upright throughout the flight Ease of payload retrieval Ease of manufacturing Raven3 diagram from manufacturer

P.I.M.S. Payload Integration RockeTiltometer Ignition Control System Ease of integration Compatible with Raven3 Image from manufacturer

Tesseract Payload Integration

Launch Vehicle Interfaces Internal Interfaces Nose cone and payload sections All-threads Bulkhead-like centering rings Nut locks Drogue bay, avionics bay, main bay, sustainer section, booster section and mini parachute bay. #2-56 nylon shear pins (x3 for each section) External Interfaces 1515 rail buttons Parallel booster attachment points

Payload Interfaces Structural Interfaces o All-thread rods o Aluminum chassis o Plywood sleds o Grid style pc board Electrical Connections USB Connections Raspberry Pi, Power Supply Arduino, GPS, Camera, Digital and Analog Connections Atmospheric Sensor Serial Connections Raspberry Pi ↔ Xbee, GPS Arduino ↔ Xbee, GPS

Status of Requirements Verification RequirementStatus Rocket must not fly higher than 20,000 ft. AGL.Complete Rocket must carry a scientific payload.Complete Rocket must have dual altimeters.Complete Rocket must have dual deploy recovery system.Complete Rocket must be reusable on the day of recovery.Complete Rocket must land within 5000 ft. of the launch pad assuming 20 mph wind.Complete Students must do all critical design and fabrication.Complete Team must use a launch and safety checklist.Complete Rocket must use a commercially available, certified motor.Complete Rocket must be capable of being prepped for launch in less than 2 h.Complete Rocket must be able to remain in a launch-ready configuration for at least 1 h.Complete Rocket must attain an altitude of 18,500 with 500 foot variance.Complete Drogue parachute successfully deploys at apogee and main at 1200 ft.Complete Rocket must be compatible with a 1.5’’ launch rail.Complete Sustainer motor will only ignite if angle of attack is between 0-5 degrees.Complete

Questions?