University of Colorado Boulder NASA Student Launch Critical Design Review

Table of Contents ●Vehicle Design ●Subscale Results ●Recovery System Design ●Hazard Camera ●Liquid Sloshing ●Aerodynamic Analysis ●Schedule ●Budget ●Questions

Vehicle Design Overview

Vehicle Name: HYDRA (HYdrodynamics, hazard Detection, Research for Aerodynamics) Carbon Fiber Airframe – High stiffness to weight ratio Total Length: 154in Diameter: 3.9” Wet Mass: 32.1 lb Static Stability Margin: 6.4 Target Altitude: 6,000 ft

Final Motor Selection Final Motor Selection: Cessaroni L1720-WT – Max/Avg.Thrust: 473/398 lbf – T/W Ratio: 12.4 – Rail size: 12 ft 1515 rail – Rail Exit Velocity: 93.1 ft/s

Stability Margin Static Stability Margin: ~6-8

Mass Statement ComponentMass (lbs) Nosecone2.750 Hazard Camera Payload0.124 GPS and Radio Transmitter0.222 Aerodynamic Analysis Payload Total3.960 Upper Body Tube1.920 Drogue Parachute Liquid Sloshing Payload and Electronics5.000 Avionics Bay and Electronics2.050 Lower Body Tube1.360 Main Parachute1.200 Complete Motor Assembly and Fin Can Motor Casing3.496 Propellant3.869 Total32.063

Mass Statement Current Wet Mass: 32.1 lb Potential mass growth: ~2.5 lb Expected Weight: 33 lb Mass Margin: +/- 2.5lb –This will keep the team near their target altitude of 6000ft.

Subscale Results

Total Length: 99.5 in Diameter: 54 mm Wet Mass: 9 lb Static Stability Margin: 6.4 Motor: Cesaroni K-360 Projected Altitude: 9216 ft

Subscale Results Static Stability Margin: ~6-10

Subscale Results

Recovery System

Parachute Design Elliptical cupped –Simple design 8 ft. diameter main parachute –Descent Rate: 18 ft/s 3 ft. diameter drogue parachute –Descent Rate: 50 ft/s Example of elliptical cupped parachute

Manufacturing Pattern cut from 1.9 ounce rip stop nylon Sewed with rolled hem seam and Dual Duty XP Heavy Nylon Thread Reinforced with 1” tubular nylon which continue to become shroud lines.

Chute Testing Chutes will be dropped off tall building with a small mass attached to determine drag coefficient. Strength test of seams will be done using a strength tester.

Parachute Placement/Deployment Main will deploy between first section and electronics bay Drogue will deploy between middle section and motor section –Trigged by two black powder charges each deployment First section Electronics Bay Middle section Motor section

Kinetic Energy (ft-lbf) Flight EventsMotor SectionMiddle SectionFirst Section Motor BurnoutN/A 261,683 Main Deployment Landing

Recovery attachments Two 25ft sections of 1” tubular Kevlar shock cord and one 1ft –One for each chute and one for payload integration Chutes attached by high strength (2,500 lbf) swivel and 3/8” quick link to shock cord Shock cord attached to bulkhead assemblies using quick links. Bulkheads are made of ¼” birch aircraft plywood.

Avionics Using Raven Featherweight altimeters 1 st event (drogue deployment) at apogee 2 nd event (main deployment) at 1,000 ft. AGL Redundant altimeter is also a Raven Wiring for Raven3 Featherweight

Vehicle Drift (0 mph)

Vehicle Drift (5 mph)

Vehicle Drift (10 mph)

Vehicle Drift (15 mph)

Vehicle Drift (20 mph)

Hazard Camera Payload

Hazard Camera (HazCam) Payload Overview Scans ground looking for Hazards Image is taken and sent to Raspberry Pi Raspberry Pi analyzes image and looks for Hazard When hazard is found, it is transmitted to ground station All footage is saved onboard for post-launch analysis Drawing of Nosecone-HazCam Assembly

HazCam Payload - Block Diagram HazCam connects to Comm System via USB to Arduino Board Uses cost effective and easy-to-use Raspberry Pi hardware

HazCam Payload - Design Used to process image Handles transmission to Xbee transmitter Built by makers of Raspberry Pi, comes with fully built library Capable of HD video

HazCam/GPS-Comm System Integration Placed within nosecone Mounted on Fiberglass Sled Secured in place with 8-32 all- thread Hazard Camera is at top of nosecone Clear acrylic lid on top of nosecone

HazCam Algorithm - Current State

HazCam Algorithm - Future Work Increase Speed Translate to C Reduce False Positives

Liquid Sloshing Payload

Liquid Sloshing Overview Tests a new method for mitigating liquid sloshing in fuel tank in microgravity Fuel contained in flexible bag in pressurized container Acceleration data and camera videos recorded by Raspberry Pi on SD card Data processed post-flight

Experiment Design and Analysis Control tank: water free to move about tank Experimental tank: water confined to flexible bag in pressurized tank Tanks isolated by electronics bay Acceleration data measured Data verified by video data Two launches: full scale and competition for greater sample size and less error

Liquid Sloshing Design Overall Dimensions: 17” long, 3.9” diameter Placed in middle body tube of rocket just above drogue parachute Bulkheads bolted into rocket body hold payload in place Two tanks: control and experiment, separated by electronics bay Accelerometer mounted to outside of experimental tanks LEDs light up coupler tubes for camera

Electronics Overview Data from camera and accelerometer processed by Raspberry Pi microcomputer Data stored on SD card for post-flight analysis Raspberry Pi powered by 5V USB charger, camera and accelerometer powered through Pi LEDs powered by 2x 9V batteries in electronics bay

Liquid Sloshing Integration Payload built utilizing coupler tubes and bulkheads that are similar to avionics bay Payload is bolted into rocket body tube through ½” bulkheads

Testing Plan Pressure test acrylic tank to ensure 4:1 pressurization safety factor Drop test to ensure payload survival in case of parachute failure Accelerometer test to confirm it can withstand 13g liftoff accelerations Systems integration testing to ensure proper component interfacing and wiring logic

Aerodynamic Analysis Payload

Aerodynamic Analysis Overview Payload to satisfy requirement – Aerodynamic analysis of protuberances during flight Goals: To determine drag of different shaped protuberances through pressure measurement To correlate and verify experimental data with CFD results

Aerodynamic Analysis Design Three mock “SRBs” are attached to the rear of the rocket Each SRB has a different geometry Pressure distribution over each SRB is measured

Scientific Overview

Electronics Isolation of systems Managed data flow Hardware filters of analog signals Pressure Velocity MultiplexerMicrocontrollerSD Card

Aerodynamic Analysis Integration Mounted to rocket utilizing a rail system Each SRB is an independent apparatus Easy to assemble and dissasemble

Aerodynamic Analysis Testing Structural testing Static pressure testing –Data recording –Circuit design –Sensor communication Dynamic pressure testing –Filtering –Noise levels –Leaks in pressure measurement system

Requirements Verification

Structures and Aerodynamics #RequirementSatisfying Design Feature Verified by: Status SA.1The airframe of the vehicle must be able to survive under all expected loads experienced during flight. Body Tubes and Couplers Analysis, Test Verified SA.1.1The airframe must survive a max longitudinal load of 400 lbf Body Tubes and Couplers Analysis, Test Verified SA.2The airframe must be able to integrate with all on board payloads, electronics, and recovery systems. Avionics Bay, Body Tubes InspectionVerified SA.3The airframe must integrate with the motor retention system. Motor Tube, Motor Retainer InspectionVerified

Propulsion and Guidance #RequirementSatisfying Design Feature Verified by: Status PG.1The motor must stay within the vehicle at all times during flight Motor RetainerAnalysis, test Verified PG.2The motor must supply enough thrust for the vehicle to obtain the target altitude of 6,000 feet MotorAnalysis, test Verified

Avionics and Recovery #RequirementSatisfying Design Feature Verified by: Status AR.1The recovery avionics must have a completely independent backup system Raven Featherweight Altimeters InspectionVerified AR.2The recovery avionics must fit within the allotted space in the avionics bay Avionics BayInspectionVerified AR.3The recovery system shall fit within the available tube space. Recovery System, Body Tubes Inspection Pending AR.4The recovery system shall be able to be deployed while the rocket is in its flight configuration Recovery SystemTestPending

Ground Ops # RequirementSatisfying Design Feature Verified by: Status GO.1 The wireless transmitters must be able to downlink all necessary data from the rocket in real time while in flight configuration. Transmitter, ground computer TestVerified GO.2 The range of the transmitter shall be more than two miles when installed in its flight configuration TransmitterTestVerified GO.3 The ground station must be able to store all downlinked data in real time. Ground computerTest Verified

Project Plan

Schedule

Budget CategoryCost Vehicle & Payloads$ Outreach$ Testing$ Travel$ Misc.$ TOTAL$

Educational Outreach Status Completed 1 Event – Reached over 90 middle-school students 2 more activities scheduled this month 1 scheduled in April On target to reach goal of working with 200 students

Questions?