Student Launch Project Flight Readiness Review

April 21, 2014

Team Structure

Presentation Overview

• Final Launch Vehicle• Final Motor Selection• Static Stability/ Mass Margin• Recovery System• Full Scale Test Flight• Verifications• Integrated Research Payload

Final Launch Vehicle Design and Dimensions

Key Design Features• Launch Vehicle Sections

• Voltmeter/ CubeSat, Hazard Detection, Multi-Staging• Fin Style• Launch Vehicle Separations

• Booster Section, Drogue Bay/ Detachable Bulkhead

Forward Section - CubeSat• Nose Cone• Voltmeter• CubeSat

Avionics/Payload Section - Hazard Detection

• Avionics/ Payload components• Hazard Detection System• Drogue bay disengagement

Booster/Sustainer Section - Multi-Staging

• Booster section disengagement• Fin Style and attachment• Positive Motor Retention

Motor Description

Motor Brand Engine Code

Diameter Length Burn Time Total Impulse

Maximum Thrust

Main Cesaroni K1620 - Vmax

98mm 9.3307 in 1.53s 2432Ns 996 N

Sustainer Cesaroni L985TT 54mm 19.33 in 2.7s 2678 Ns 1589 N

Thrust Curve of Motors

Table of Motor Events

Event Time (s) Altitude (ft) Velocity (ft/s)

Motor Ignites 0 0 0

Main Motor Burnout 1.53 230 290

Main Motor Separation 2 360 275

Sustainer Ignites if within critical angle off

of the Z-axis

2.5 550 270

Sustainer Burn Out 5.2 2000 700

Apogee 24 7000 <20

Static Stability MarginStability Margin

  Stability Margin Center of Gravity Center of Pressure

With Booster 1.68 87.6 in 98.0 in

Without Booster 1.14 65.8 in 72.8 in

Thrust-to-Weight Ratio and Rail Exit

Ascent Analysis With Booster Section Without Booster Section

Rail exit velocity (ft/s) 64 -

Max velocity (ft/s) 290 690

Max Mach number 0.26 0.61

Max acceleration (ft/s2) 260 262

Peak altitude (ft) 1350 7000

Thrust-to-Weight Ratio 7:1 6:1

Mass Statement and Mass MarginSubsystem Mass (lbs) Mass Limit (lbs)

Propulsion (Including: motor mounts and centering rings)

12.0 15.0

Structure (Including: body tube, coupling tubes, bulkheads, nose cones, fin sets)

21.4 26.5

Recovery (Including: main parachute, drogue parachute, detachable components parachutes)

5.0 6.3

Payload (Including: avionics bays, electrical components)

13.0 16.3

Miscellaneous (Including: Paint scheme, dressings/coatings)

1.0 1.4

Total 52.4 65.5

Propulsion23%

Structure41%

Recovery10%

Payload25%

Miscellaneous2%

Mass Distribution

Propulsion Structure RecoveryPayload Miscellaneous

Parachute Sizes and Descent Rates

Parameter Drogue Main Booster

Diameter (in) 85 120 60

Deployment Altitude (ft) 7000 1200 1350

Velocity at Deployment (ft/s)

>20 54 >20

Descent Rate (ft/s) 17.5 15 23

Harness Length (ft) 20 30 10

Shroud Line Length (in) 93.5 132 66

Kinetic EnergiesParachute Parachute

SizeVehicle Section

Mass of Section

Descent Rate

Kinetic Energy

Booster 60 inches Booster Section

6 lbs 22.6 ft/s 50 ft-lbs

Mini Avionics Bay

3 lbs 22.6 ft/s 24 ft-lbs

Drogue 85 inches Drogue & Main Bay

29.5 lbs 54 ft/s --

Drogue Bay

11 lbs 17.5 ft/s 52.6 ft-lbs

Main 120 inches Avionics Bay

8 lbs 15 ft/s 28 ft-lbs

Main Section

8.5 lbs 15 ft/s 30 ft-lbs

Predicted Drift from Launch Pad0 mph 5 mph 10 mph 15 mph 20 mph

0 ft. 1050ft. 2284ft. 3654ft. 4515 ft.

Predicted Altitude

0 mph 5 mph 10 mph 15 mph 20 mph

7089ft. 7078ft. 7043ft. 6981ft. 6888ft.

Test Plans and ProceduresTest Purpose Test Status

Full-Scale Test Flight

To ensure safe stage separation and sustainer motor ignition during flight

In Progress

Smart Ignition Device

To ensure that the sustainer ignition charge will be inhibited if the rocket off of the vertical.

Completed

Booster Section Separation Ground

Test

To ensure booster section can separate from main bay with attachment scheme

Complete

Airstart Test To ensure Raven3 has appropriate output current to airstart sustainer

Complete

Full Scale Flight – 1st Test

Full Scale Flight Test Data

Recovery System TestingTest Purpose Test 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

Completed – Successful

To test static ejection charges of full scale parachutes

Completed – Successful

To demonstrate durability of bulkhead attachment scheme within the rocket.

Completed – Successful

Electrical Component TestingComponent Test Purpose Test Status

Microcontrollers including the Raspberry pi and Arduinos

To test functionality and programming logic

Completed

RockeTiltometer and Raven 3 altimeters

To test functionality and accuracy

Completed

Voltmeter To test functionality and accuracy

Completed

XBee Pro 900 To test functionality and communication between systems

Completed

GPS units for separable sections

To test functionality and accuracy

Completed

Summary of Requirements VerificationLaunch Vehicle

Requirement StatusRocket must not fly higher than 20,000 ft. AGL CompleteRocket must carry a scientific payload CompleteRocket must have dual altimeters CompleteRocket must have dual deploy recovery system CompleteRocket must be reusable on the day of recovery CompleteRocket must land within 5000 ft. of the launch pad assuming 20 mph wind

Complete

Students must do all critical design and fabrication CompleteTeam must use a launch and safety checklist CompleteRocket 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 between 6500-7500 ft.

Complete

Drogue parachute successfully deploys at apogee and main at 1200 ft.

Complete

Rocket must be compatible with a 1.5’’ launch rail Complete

Key Design Features of the Payload• Hazard Detection System• Lateral Vibrations In line System (LVIS)• Tesseract

Payload Design and DimensionsHazard Detection/Avionics Bay

Payload Design and DimensionsLVIS

Motor Brand Engine Code

Diameter Length Burn Time Total Impulse

Maximum Thrust

Main Cesaroni K1620 - Vmax

98mm 9.3307 in 1.53s 2432Ns 996 N

Sustainer Cesaroni L985TT 54mm 19.33 in 2.7s 2678 Ns 1589 N

Payload Design and Dimensions• Designed to measure the magnitude of accumulated

triboelectric charge on the surface of the nose cone at carious altitudes

• Time stamp all altitudes and charge measurements to assist in post flight analysis

Tesseract

Tesseract Payload Overview• The system can be broken down into three separate subsystems:

• Voltmeter• CubeSat• Ground Station

• The nose cone will be coated with MGM Chemicals 838 Total Ground Carbon Conductive Coating

Payload IntegrationHazard Detection/Avionics Bay

Payload IntegrationLVIS

• Locations of Raven3 • Avionics Bay• Above the Sustainer• Mini-Avionics Bay

Raven3 diagram from manufacturer’s website

Raven3 on payload sled

Payload IntegrationLVIS

• Electrical schematic of RockeTiltometer2 with Raven3

Image of RockeTiltometer2 with connections

Payload IntegrationTesseract

1

2

3

45

6

Interfaces with Ground Systems• 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 (x2 for each section)

• External Interfaces• 1515 rail buttons

Summary of Requirements VerificationPayload

Payload Requirement StatusHazard Detection Bulkhead covering camera must be detachable CompleteHazard Detection Payload must be capable of detecting landing hazards CompleteHazard Detection Data must be transmitted to the ground in real time IncompleteLVIS Motor staging must perform properly CompleteLVIS Payload must record lateral vibrations in the airframe CompleteLVIS Data must be recoverable CompleteTesseract Payload must be able to record a potential difference CompleteTesseract Payload must record altitude CompleteTesseract Data must be stored and recoverable Complete

Questions?