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PHS Student Launch Team 2

Preliminary Design . Review Presentation. Launch Vehicle Dimensions. Size and mass. Length: 110”. Diameter: 5.5”. Mass Without Motor: 236.36 oz. Mass With Motor: 311.44 oz. Stability Margin. CP (from nose): 77.03 in..

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PHS Student Launch Team 2

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PHS Student Launch Team 2

Preliminary Design

Review PresentationSlide2

Launch Vehicle Dimensions

Size and mass

Length: 110”

Diameter: 5.5”Mass Without Motor: 236.36 ozMass With Motor: 311.44 ozSlide3

Stability Margin

CP (from nose): 77.03 in.

CG (without motor): 48.37 in.

CG (with motor): 60.14 in.Slide4

Launch Vehicle Materials

Blue Tube Airframes

Fiberglass Bulkheads, Fins, and Centering Rings

3D Printed ABS Plastic Payload Plates

½” Tubular Kevlar Recovery Harness

84” and 24” Nylon Parachutes

Plastic, 13” Nosecone Slide5

Material Justifications

½” Kevlar has a test strength of 7200 lbs.

ABS is stronger than PLA, and can be used with adhesives.

Blue Tube is durable and has high resistance to abrasion and cracking.Fiberglass is a strong composite material, with lower cost than alternatives such as carbon fiber.Parachutes minimize descent rate to 22.2 ft/s, while decreasing drift.

The nosecone reduces drag on the vehicle and secures the payload.Slide6

The team will follow all safety precautions in the NAR safety handbook.

The safety officer will oversee all construction and launch procedures.

The team will follow the Launch and Assembly checklist detailed in the PDR.

All material, tool and environmental hazards have been analyzed, and mitigations have been planned.

Vehicle Safety VerificationSlide7

Vehicle Safety Test Plan

Ground ejection tests will be run to test the recovery system.

Fins, bulkheads and other epoxied components will be stress tested.

D-Links will be wrenched tight.Entire rocket assembly will be functionally tested during test flight.Slide8

Motor Selection and Justification

Aerotech K1050 White Lightning

Total Impulse: 2426.4 Ns

Average Thrust: 1132.9 NMaximum Thrust: 2172.0 NSlide9

Simulation Data

Predicted Altitude: 5539 ft.

Thrust to Weight Ratio: 14/1.

Rail Exit Velocity: 95.71 f/s.Slide10

Flight ProfilesSlide11

Launch Vehicle Verification

The team will use detailed simulations to ensure the vehicle reaches a maximum altitude of 5280 ft.

The launch vehicle will use only one K1050WL motor.

The use of two parachutes will ensure that the vehicle is recoverable.Vehicle will comprise only three sections.Drag will be hand calculated to ensure proper simulation data.



will use a 12 volt firing system to initiate launch


Vehicle Test Plan

A sub-scale launch vehicle will be flown in December.

Data from this flight will be used to adjust the full-scale, as necessary.

The full-scale vehicle will be flown in February with NEFAR, an affiliate of NAR and TRA.Slide13

Discussion of Subsystems


84“ main and 24” drogue parachutes

½” D-Links ¼” Eyebolts½” Tubular Kevlar Recovery Harness

2 PerfectFlite Stratologger Altimeters

Upper Body Tube:

48” long, 5.5” wide Blue Tube Airframe

5.34” Fiberglass Bulkhead


Discussion of Subsystems (Cont.)


Plastic, Ogive

13in” long, 4in” shoulderCoupler:12in” long, 5.34in”OD Blue Tube coupler

2in” long, 5.5in”OD Blue Tube band

two 5.19in”OD, ¼in” thick Fiberglass Bulkheads

Altimeter Bay and AltimetersSlide15

Discussion of Subsystems (Cont.)

Lower Body Tube 46” long, 5.5” wide Blue Tube Airframe

5.34” wide, ¼” thick Centering Ring and Thrust Plate

25” long, 54mm wide Blue Tube Motor Mount4 Half Parabolic Fiberglass FinsSlide16

Dimensional Drawing




Lower stage

Upper stage and payloadSlide17

Recovery SchematicSlide18

Payload Design

5.3”, 3D printed base plates.

2 T-rails.

Arduino UNO

Antenna, made of solid core wire and Mega-Ohm resistor.

Power provided by 9V batteries and Trail fixtures.Slide19

Payload Schematic Slide20

Payload Verification

The team’s payload will collect data on the voltage of residual EMI in the atmosphere. No part of the payload will be jettisoned, and no UAVs will be used. The payload will be secured by T-rail and plates between a bulkhead and nose cone, ensuring its safe recovery. Slide21

Payload Test Plan

Ground Test - Test of the payload within the work area.

Functional Test - Test of the payload during the test launch.

Prior to launch, all payload systems will be checked to ensure functionality. Slide22


Payload Design

EMF Detectors

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