Project TARTAN: Preliminary Design Review (PDR) Vehicle Summary: - - PowerPoint PPT Presentation

Project TARTAN: Preliminary Design Review (PDR)

Vehicle Summary: Dimensions and Materials

Parameter Value Length 121” Outer Diameter 6.112” Inner Diameter 6” Materials Carbon Fiber / G12 Fiberglass Mass Dry: 454 oz Wet: 584 oz

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Vehicle Summary: Stability Margin

Parameter Value Static Stability Margin 2.63 CP (from Nose Cone) 93.874” CG (from Nose Cone) Dry: 73.076” Wet: 77.797”

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Vehicle Summary: Motor & Launch Considerations

Motor: Aerotech L830W Apogee with L850W: 5,762 ft

• Bring down to 5,280 using

Apogee Targeting System Rationale:

• Apogee with ballast within

range of ATS correction ○ 5,400-6,000ft

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Launch Vehicle Overview

1. Nose Cone and Airframe 2. Payload and Payload Deployment 3. Recovery 4. ATS & Motor Retention

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Launch Vehicle Schematic

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Nose Cone Payload & Payload Deployment Recovery

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ATS & Motor Mount System

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Vehicle Alternative Designs: Nose Cone

• Fiberglass vs. Carbon Fiber
• Public Missiles vs. Madcow
• Considerations

○ Size ○ Price ○ Compatability with Electronics ○ Unintentional RF Shielding

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Vehicle Alternative Designs: Airframe

• Materials

○ G10/G12 Fiberglass vs Carbon Fiber

• Benefits to Carbon Fiber

○ Stronger → Thinner Airframe → Lighter

• Drawbacks to Carbon Fiber

○ Expensive ○ Difficult to work with

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Launch Vehicle Schematic

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Nose Cone Payload & Payload Deployment Recovery

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ATS & Motor Mount System

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Payload: Rover

Two-Wheeled Option With Auger Four-Wheeled Option With Reversible Scoop

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Payload: Deployment

Payload with spring loaded deployment mechanism Locking Mechanism to prevent premature firing

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Launch Vehicle Schematic

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Nose Cone Payload & Payload Deployment Recovery

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ATS & Motor Mount System

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Recovery: Recovery Bay

• Recovery Bay

○ RF Shielding: Aluminum Shield Tape ○ Additive Aerospace Sled vs Made-In-House ■ Materials: PLA vs. Acrylic vs. Aluminum ○ Electronics ■ Leading Altimeter: PerfectFlite Stratologger CF ■ Independent Systems ■ Duracell 9V Battery

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Recovery: Redundant Systems

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Recovery: Parachutes

• Drogue

○ SkyAngle Classic I 24” ○ Terminal Velocity: 94.1 ft/s

• Main

○ FruityChute Iris Ultra 96” ○ Terminal Velocity: 16.4 ft/s ○ Maximum Landing Kinetic Energy: 65.28 ft-lbs

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Recovery: GPS Telemetry

• Location: Payload Deployment Bay (Fiberglass)

○ 19” away from nearest e-match in main parachute bay ○ Will use RF shielding to prevent premature deployment of main parachute

• Model: BigRedBee 70cm 100mW GPS/APRS Transmitter

○ Can transmit on any frequency in 125 Hz steps

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Launch Vehicle Schematic

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Nose Cone Payload & Payload Deployment Recovery

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ATS & Motor Mount System

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Apogee Targeting System (ATS) Overview

• The ATS is an airbrake system designed to regulate the velocity of

the rocket in flight.

• It consists of a set of four motor flaps that extend from the sides of

the rocket to generate drag, slowing the rocket to ensure that it achieves the target apogee of 5280 ft.

• The extension of the flaps is determined by a control algorithm that

uses data from an altimeter system and an inertial measurement unit.

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ATS Physical Design

• The air brake deployment system consists
• f a central rotation hub, the attached

rotation piece, 4 connecting arms, 4 flaps, and 4 flap guides.

• Our current flap design is a rectangular

shaped flap with a curved outer edge.

• While similar to our first flap design, this

flap has the key advantage of having extra surface area and endure more force.

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ATS Algorithm Design

• The algorithm begins collecting data after motor burnout.
• The system will average measurements of multiple sensors or utilize

a Kalman filter to clean the data.

• Drag force is calculated based on measured velocity and current flap

extension.

• Based on the drag force, the current altitude, and the velocity the

system will predict the estimated apogee.

• After apogee calculation, the system adjusts flap extension

accordingly, feeds back the data, and repeats the process.

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Motor Retention System

• Thrust Plate

○ 6061 vs 7075 ○ Thickness ○ Easy to manufacture ○ CNC Capabilities

• 75mm flanged motor retainer and

cap ○ Very hard to manufacture ○ Reliable

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Mission Performance Predictions

1. Apogee 2. Kinetic Energy & Descent 3. Drift

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Apogee

• Overall goal: 5,280 ft
• Current Apogee w/ L850W & no ballast: 5,762 ft

○ Ballast to bring apogee within a few hundred feet of goal ○ ATS brings it down to actual goal

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Kinetic Energy & Descent

• Landing Kinetic Energy

○ Upper: 44.5 ft-lbs ○ Middle: 51.87 ft-lbs ○ Lower: 65.28 ft-lbs

• RasAero Simulation:

○ Descent Time: 83s

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Drift

• OpenRocket Simulations

○ Max 1,790ft ○ 20mph launching downwind

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Requirements Verification

Quick update:

• Most requirements pertain

to design of rocket and its design process.

• Requirements are kept in

mind during design process

• Internal design stop:

December 6th

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Questions?