FRR Presentation

Aerostructure

Vehicle Dimensions

Nose Cone = 27.500”

Main Chute Bay = 35.875”

Payload Bay = 36.750”

Drogue Chute Bay = 16.414”

Engine Bay = 30.000”

Total Length ≈ 147.00” Tube I.D. = 5”

Tube O.D. = 5.125”

Wall Thickness = 0.625”

Vehicle Weight

Final Motor Choice

Aerotech L2200G-P

75mm High Powered Reloadable Motor

5104 N-s

Justification:

- Performed well in simulation (5477ft)

- Low cost ($249.99)

- Reloadable

Launch Vehicle Flight Stability

• Stability average = 3.5

• >1 throughout majority of flight

CG = 98.564”

CP = 118”

Flight Performance Data

Thrust/Weight Ratio = 11.58

Rail Exit Velocity = 92.8 ft/s

Apogee = 5447 ft

Max Velocity = 706 ft/s

Max Acceleration = 460 ft/s^2

Time to Apogee = 17.8 s

Flight Time = 104 s

Ground Hit Velocity = 13.9 ft/s

Flight Performance data (cont)

Flight Performance data (cont)

Sub-System Components: Nose Cone

• Von Karman Design

• 5:1 ratio

• Utilization of coupler space for recovery hardware

• Carbon Fiber construction

Sub-System Components: Avionics/Electronics Bays

• Peregrine Rapter CO2 Ejection

• 2 Separate Bays (dual deployment)

- Drogue Chute (23g)

- Main Chute (45g)

• Swivel Mount for chute tethering

Sub-System Components: Payload Bay

• Fragile Material Protection

• Encapsulates payload between two solid aluminum bulkheads

• Removable body tube section

Sub-System Components: Engine Bay & Fins

• Distributes force due to thrust

• Secures reusable motor canister

• Removable inner assembly

• Fins securely fastened to body

- Flush with body tube

Combined Rocket Assembly

Predicted Altitude

Simulation 1 Simulation 2 Simulation 3 Simulation 4 Simulation 5

Apogee 5442 ft 5383 ft 5358 ft 5324 ft 5313 ft

Velocity @ Launch Rod Clearance 92.8 ft/sec 92.8 ft/sec 92.8 ft/sec 92.8 ft/sec 92.8 ft/sec

Maximum Velocity 703.7 ft/sec 701.3 ft/sec 699.9 ft/sec 698.4 ft/sec 696.6 ft/sec

Maximum Drag Force 76.9 lbf 78.1 lbf 78.1 lbf 78.1 lbf 78.1 lbf

Maximum Vertical Acceleration 458.7 ft/sec2 458.7 ft/sec2 458.6 ft/sec2 458.5 ft/sec2 458.5 ft/sec2

Stability @ Launch Rod Clearance 3.57 2.25 1.61 0.84 0.26

Maximum Stability 4.39 4.39 4.39 4.39 4.39

0 MPH 5 MPH 10 MPH 15 MPH 20 MPH

GPS and Wireless Communication

• The Copernicus II GPS module will be used to track the location of the rocket.

• Two Xbee Pro 900 modules will be used to communicate GPS data from the rocket to a ground station (900 Mhz)

• Atmega2560 microprocessor will be used to interface with each sensor

Full Scale Flight Test

Launch Day Conditions

The conditions for the first test launch were 7 miles per hour winds with 12 miles per hour gusts. The temperature

was an average of 42 degrees Fahrenheit.

Full Scale Flight Test Analysis:

Fiberglass tube snapped during flight. Root cause is epoxy not absorbing entirely into

fiberglass.

Full Scale Flight Test Data from Flight

Full Scale Flight Test Data from Flight

Full Scale Flight Test Comparison

Payload

Full Model

Electronics Bay Bladder System

Quick Connect/Disconnect

Damper

Spring Assist Nested Spring

Assembly Towards Nose Cone

Nested Spring Design

• Designed to absorb multiple magnitudes of forces

• Main/Drogue Chute Deployment

• Launch

• Miscellaneous forces

• Allows damper to function without exposing it to full force of impulse

• Prevents damper from rupturing

Damper Configuration

• Added spring for damper protection and force absorption capability of the spring system

• One way compression damping • Only dampens when compressing

• Allows absorption of forces in springs and slows ascent of compressed springs

• Spring will be elevated to help protect damper when completely compressed

Electronics Bay

Main Components

• Parker CTS Diaphragm Air Pump

• Arduino Circuit Board

• Differential Pressure Sensor

• Lithium Battery (2)

The length of time till batteries run out with the pump running on max flow is two hours, and time to fill entire bladder area will be ~30 seconds

Electronics

• Electronics are used to regulate air pressure in the bladder • The main electrical components are:

• NPA-700B pressure sensor • Senses the differential air pressure between the bladder and the atmosphere

• Parker CTS diaphragm air pump • Fills the bladder with air, at 2.5 LPM

• Atmega328p microprocessor • Controls the pump (on/off)

Electronics

• To conserve power, the electronics will be able to draw power from an internal or external power source - external before launch, internal during launch

• Rotary switches will be used to toggle where the electronics are drawing power from, or if the electronics are powered at all

• Two 9V Lithium-ion batteries will be used, since they provide a constant voltage throughout lifespan

• At max load, batteries are expected to last over 2 hours

Payload circuit board

Retention System

• Comprised of 6 bags, or “bladders” filled with air fitted with 1”x 1”x 0.08” shock absorbent tiles (Alpha Gel)

• Works with 1psi intake and relief valves to control pressure inside bladder

• 0.5” thick, 4” diameter shock absorbent pads bottom and top of canister

Puncture Proofing

• Option 1: URSACK bag • “Bear Proof”

• Allows for an unspecified amount of protection

• Will protect bladder system from sharp edges of fragile material

• Option 2: Kevlar • Used if URSACK falls through

• Same price

Quick Connect/Disconnect

• Allows for pre-launch preparations without complete removal from rocket (hatch door)

• Two springs inside housing shuts plugs when no pressure applied (0.9 lbf per plug)

Sealing Plate T-bracket (attached

to canister)

Latch Housing (attached to

spring/damper system)

Plug

Retaining Spring

Event Sequence

Sequence Event Altitude

1 Drogue Chute deployed from mid-section

of rocket 5,280 ft

2 Main Chute deployed from nosecone of

rocket 850 ft

2

1

Diameter (in) 17

Area (ft2) 2.1

Design Elliptical

Material 1.9 oz/yd²

Drag Coefficient 1.33

Terminal Velocity 133 ft/s

Diameter (in) 130

Area (ft2) 88.5

Design Toroidal

Material 1.1 oz/yd²

Drag Coefficient 1.77

Terminal Velocity 15 ft/s

Drogue Parachute Main Parachute

Canopy Summary

A total of 2 Bulkhead Assemblies: • 1 for drogue parachute ejection and harness attachment • 1 for main parachute ejection and harness attachment

Bulkhead components: • 1 Pyro Housing • 1 Redundant Pyro Housing • 1 CO2 Cartridge • 1 Redundant CO2 Cartridge • 1 Hoist Ring

Bulkheads

Hardware Connections

Find Number Part Name Rated Force (lb) Force Received (lb) Factor of Safety

1 Hoist Ring Swivel (Airframe Interface) 1000 895 1.11

2 Large Carabineer 2400 895 2.68

3 Shock Cord 2375 895 2.65

4 Swivel 3000 895 3.35

5 Bridle 6000 895 6.7

6 Small Carabineer 1400 316 4.43

7 Shroud Lines 400 79 5.06

8 Connection Line to Inner Shroud Lines 1400 316 4.43

9 Connection Line to Nosecone 1400 55 25.45

10 Hoist Ring Swivel (Nosecone Interface) 800 55 14.55

Drift and Energy Calculations

Nosecone Upper Section Lower Section

Estimated Weight (lbs) 2.5 19.5 13.85

Impact Velocity (ft/s) 14.89 14.89 14.89

Kinetic Energy (ft-lbf) 8.6 67.1 47.7

0 mph Winds (ft) 0

5 mph Winds (ft) 657

10 mph Winds (ft) 1312

15 mph Winds (ft) 1976

20 mph Winds (ft) 2638

Drift Distances

Landing Kinetic Energy

Ejection System

Peregrine CO2 Cartridges

• A total of 4 ejection systems: • 1 System for Drogue ejection

• 1 System for Main ejection

• 1 Redundant system for Drogue ejection

• 1 Redundant system for Main ejection

• Ground tests were done to verify the following: • QTY (1) 23 g Peregrine CO2 will be used for the Drogue parachute

• QTY (1) 45 g Peregrine CO2 will be used for the Main parachute

Ejection Test

• A complete ground test of firing the CO2 charges to observe the separation of the rocket body

and nose cone occurred.

• A program called DataCap was used which allowed manual firing of both drogue and main chute

ignition systems from the StratologgerCF chips.

Results:

• Main parachute experiences full separation from the airframe with a single 45g CO2 cartridge.

• Drogue parachute experiences full separation from the airframe with a single 23g CO2 cartridge.

Altimeter Selection

PerfectFlite StratoLoggerCF:

A Total of 2 StratoLoggerCFs:

• 1 StratoLoggerCF to connect to main CO2 ejection systems for main and drogue parachutes

• 1 redundant StratoLoggerCF to connect to redundant CO2 ejection systems for main and drogue parachutes

GPS

• The Copernicus II GPS module will be used to track the location of the rocket.

• Two Xbee Pro 900 modules will be used to communicate GPS data from the rocket to a ground station (900 Mhz)

• Atmega2560 microprocessor will be used to interface with each sensor