CDR PresentationPLANTATION HIGH TEAM 2
2015-2016
Launch Vehicle Dimensions
Diameter: 5.5” (OD), 5.346” (ID)
Length: 110”
Payload Dimensions
Length: 20”
Diameter: 5.346”
Mass: 24 Oz.
Design Features
BlueTube airframes, motor mount and coupler
Fiberglass bulkheads, centering rings and fins
Plastic nosecone
3D printed payload plates
Final Motor Choice
Aerotech K1050 WL
Total Impulse: 2426.4 Ns
Average Thrust 1132.9 N
Flight Stability
Stability (No Motor): 5.32 Calibers
Stability (Motor): 3.16 Calibers
Simulation Data
Thrust to Weight Ratio: 9.6/1
Rail-exit velocity: 84.48 ft/s.
Predicted Altitude: 5233 feet.
Mass and Mass Margin
Predicted altitude drops to 5100 ft. if mass increase by 30 oz.
This gives the vehicle about a 10% mass margin.
Section Mass (Oz)
Upper Airframe 111.1
Coupler 48.9
Lower Airframe 151.7
Total (With Motor): 311.6
Total (Without Motor): 236.6
Recovery
Main Parachute: 84”
Drogue Parachute: 24”
Harness: 80’ of ½” Tubular Kevlar
Drogue Terminal Velocity: 87.4 ft/s.
Main Terminal Velocity: 22.4 ft/s.
Kinetic Energy
Kinetic energy for each tethered section is less than 75 ft-lbs at
landing.
Stage Upper Airframe Coupler Lower Airframe
Rail-Exit 769.5 339.0 1018.6
Motor Burnout 62273.0 27434.0 58173.0
Drogue Ejection 26.9 15.2 32.8
Main Ejection 648.4 360.3 788.6
Landing 42.9 23.8 48.4
Predicted Drift
Wind Speed (MPH) Drift (Ft.)
5 350.3
10 703.0
15 1074.2
20 1878.4
Test Plans and Procedures
A subscale test flight and payload ground test have been
conducted.
Ground ejection tests will be conducted for the recovery system.
The fully integrated payload system will be ground tested.
The full-scale vehicle will be tested on February 13th.
Procedures for this launch can be found in the Operations of the
CDR.
Subscale Flight
The subscale test flight was
conducted on January 2nd.
The vehicle reached an altitude of ‘
946 feet.
Flight Data
Vehicle reached an apogee of 946 feet.
Main and drogue parachutes successfully ejected.
Recovery Tests
During the test launch, the drogue chute ejected at altitude and
the main ejected at 300 feet.
Ejection charge masses have been calculated.
A ground ejection test will be conducted with the full-scale vehicle prior to test launch.
Tug and ejection test
Final Payload Design
The payload will consist of an
Arduino Uno, antenna and SD card.
Two of these will be flown in the vehicle,
one with a shield on the Arduino,
and the other without.
Extra space and mass is accounted
for because of outreach payloads.
Payload Schematics
Payload Integration
External Interfaces
Rail buttons to launch rail
Ignitor to alligator clips
GPS transmitting to receiver
Internal Interfaces
U-bolt to recovery harness
Recovery harness to eyebolts on coupler
Recovery harness to engine case
Parachutes to barrel swivels
U-bolts and eyebolts to bulkheads
Bulkheads to airframe and coupler
Centering rings to airframe and motor mount
Internal Interfaces of Coupler Recovery harness attached to eyebolts on coupler.
Attachment
points
Lower body tube interface
Recovery harness attached to engine case.
Requirements
Plans for the verification of requirements are outlined in the CDR.
Payload requirements will be verified when it is functional tested.
Vehicle requirements will be verified as the vehicle is constructed
and tested.
Recovery requirements will be verified with ground tests and a test
launch.
The safety officer will remain responsible for the verification of all requirements.
Outreach
Night launch events
Rocket building
Open lap night
EMF construction
Thank you