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