Preliminary Design Review Presentation Launch Vehicle Dimensions Size and mass Length 110 Diameter 55 Mass Without Motor 23636 oz Mass With Motor 31144 oz Stability Margin CP from nose 7703 in ID: 465420 Download Presentation
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..
Download Presentation - The PPT/PDF document "PHS Student Launch Team 2" is the property of its rightful owner. Permission is granted to download and print the materials on this web site for personal, non-commercial use only, and to display it on your personal computer provided you do not modify the materials and that you retain all copyright notices contained in the materials. By downloading content from our website, you accept the terms of this agreement.
Presentation on theme: "PHS Student Launch Team 2"— Presentation transcript:
Slide1
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.
V
ehicle
will use a 12 volt firing system to initiate launch
.Slide12
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
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
Drogue
Main
Coupler
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
