1. Final Readiness Review
York College of Pennsylvania
NASA Student Launch

2. Vehicle Dimensions
Overall length: 138 inches  Bottom body tube: 48 inches  Middle body tube: 38 inches  Top body tube: 26 inches  Diameter: 6 inches  CG: inches from nose  CP: inches from nose  SSM: 2.77 cal  Fin Dimensions : Chord Root: 36 cm Chord Tip: 25 cm Height: 15 cm

3. Motor Motor Designation: Aerotech L-1150R
Max average thrust: 1150 Newtons
Impulse of 3517 Newton-seconds over a burn time of 3.10 seconds
MOTOR FLOWN FOR MAIN LAUNCH: K-560 W-PS
Impulse of 2417 Newton-seconds over a burn time of 4.10 seconds

4. Design Features
CO2 ejection system used to separate the nose cone from the payload tube
Gear crank used for payload ejection
Gear and motor are assembled to make the fully functioning dispensing payload mechanism
3D printed fin can will be used

5. Major Calculations Thrust to weight ratio 9.07:1
Rail exit velocity: ft/s
Maximum Velocity: ft/s VS.
Maximum Mach Number: 0.67 Mach
Maximum Acceleration: (ft/s)^2
Predicted Apogee (From Sim.): 5,400 ft

6. Mass Statement Total Mass: 29.50 lbs (28.50 lbs @CDR)
Component
Weight (lb)
Nose Cone with CO2 Ejection System
2.50
Upper Body Tube
1.76
Payload
3.50
U-Bolts in Upper Body
0.18
Middle Body Tube
2.58
Coupler
0.65
Electronics Bay
1.50
Main parachute
1.02
U-Bolts in Middle Body
Shock Cord in Middle Body
0.30
Lower Body Tube
3.25
Motor Tube
0.60
Drogue Parachute
0.194
Shock Cord in Lower Body
U-Bolts in Lower Body
Motor
8.099
Fins
1.22
Gear System
0.50
Total Weight
28.513
Simulation Mass
28.499
Mass Statement
Total Mass: lbs (28.50
Based on our design we have planned for an increase in weight of the rocket by 2%, due to added supports and epoxy weight.
Given this weight increase, our projected 5,400 feet height drops to 5,292 feet which is just over the target (CDR).

7. Recovery Subsystem
Drogue: 15 inches in diameter made by ParaMedichutes
Main Parachute: 120 inches in diameter made by ParaMediChutes
Recovery harness: 3/8” Kevlar
Recovery harness length for drogue: 30 ft
Recovery harness length for main: 30 ft
Terminal velocity for drogue: 147 ft/s
Terminal velocity for main: 12.7 ft/s

8. Kinetic Energy Findings
Kinetic Energy of Each Section (Ft-lbs)
Bottom Section : 21.74
Middle Section : 16.39
Payload Section and Nose-Cone: *

9. Drift Calculations Predicted drift with 5-mph wind: 616.0 ft

10. Test Plan and Procedures (Recovery Included)
Shear Pin Testing – Between nose-cone and payload tube
CO2 Ejection Testing – To ensure that nose-cone does not travel further than 10 feet away from launch vehicle
Electronics Bay Ejection Testing (Staged Recovery Test) – To ensure the correct amount of black powder charge mass for drogue and main parachute deployment
Fin Can Testing – Additional CFD and Wind-Tunnel Testing
Wireless Control Testing – In order to make sure that our gear system motor receives signals from a maximum distance
CO2 Ejection Testing/ Shear Pin Testing: To ensure that nose-cone has the correct number of shear pins and ejects properly using the CO2 ejection system
Additional testing will be performed on the shock cord

11. Full-Scale Flight Data
Flight altitude: 3134 feet
Launch Conditions
Temperature = 41 Fahrenheit
Humidity = 71%
Wind Speeds = 10 mph / mph
Motor Characteristics
Aerotech K560
Aerotech L1150
Impulse (N*s)
2417
3517
Average Thrust (N)
560
1150
Burn Time (s)
4.1
3.1
Peak Thrust (N)
753.7
1346
OpenRocket Simulation
Actual Flight Data
3,579 ft
3,134 ft
Rail Exit: 50.2 ft/s
Rail Exit: 54 ft/s

12. Launch Vehicle Verifications
SOW 2.1 – Apogee
SOW – Altimeter Requirements
SOW 2.6 – Rocket is able to be reused
SOW 2.7 – Maximum of 4 independent sections
SOW 2.8 – Single Stage
SOW Prepped in less than 3 hours
SOW 2.10 – Able to stay on pad for up to 1 hour
SOW – Related to Rocket Motor and Firing
SOW 2.14 – No pressure vessels
SOW 2.15 – Greater than 2.0 stability
SOW 2.16 – 2.17 – Calculations
SOW – Subscale and Full-Scale Flight

13. Final Payload Design Overall dimensions: Length: 10.000 inches
Max width: inches
Max height: inches
Arduino programmed
Two D/C powered electric motors
Can operate upside down

14. Payload Design Microcontroller: Arduino Nano Sensors: Motor(s):
Ultrasonic Sensor
GPS Unit
Motor(s):
D/C Hobby motor 4.5-9v
Power System:

15. Payload Design

16. Payload Integration
Payload housed within the payload tube at the front of the rocket
Payload Deployment System: After ejection of the nose cone off the front payload tube, the gear mechanism will push the payload out.
Integration: To integrate the gear housing and motor it will be riveted to the coupler tubing. Once the gear housing has been attached the coupler tubing will be epoxied to the body tube.

17. Nose-Cone Ejection System
CO2 ejection system integrated within the nose-cone to eject the nose-cone and to break the shear pins that were holding the payload tube and nose-cone together during launch
Peregrine Exhaustless CO2 Ejection System

18. Interfaces
Wireless Communication for Gear System: HC-12 Wireless Serial Port Communications Module with communication distance of 1000m in open space
Nose-Cone Deployment:
PerfectFlite Altimeter in the nose cone for the CO2 ejection system
We will use a FeatherWeight Magnetic Switch which we can wire directly to our PerfectFlite Altimeter
The altimeter itself will be programmed to have a delay of 65 seconds from the time that the rocket lands until the nose-cone is ejected off.

19. Status of Requirements Verification
PDR completed, CDR completed, successfully launched the sub- scale twice, main rocket one launched
Completed testing: Quick-Link testing, U-Bolt testing, Shock cord testing, Wireless signal testing, Ejection, Shear pins
Additional testing required: Shock cord, CO2 ejection
Educational Engagement:
York Vo-Tech
Dallastown Middle School
Hereford High School
Activities Fair