Georgia Tech NASA Critical Design Review

TeleconferencePresented By:

Georgia Tech Team ARES

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Agenda

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1. Team Overview (1 Min)

2. Changes Since Proposal (1 Min)

3. Educational Outreach (1 Min)

4. Safety (2 Min)

5. Project Budget (2 Min)

6. Launch Vehicle (10 min)

7. AGSE& Flight Systems (13 Min)

8. Questions (15 Min)

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TEAM OVERVIEW

Project Hermes - CDR

Georgia Tech Team Overview

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• 19 person team composed of both undergraduate and graduate students

• Graduate Students: 2• Undergraduates: 17

• Highly Integrated team across several disciplines

Work Breakdown Structure

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CHANGES SINCE PDR

Project Hermes - CDR

Changes since PDR

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• Launch Vehicle• Asdadf

• Autonomous Ground Support Equipment• ASdfa

• Flight Systems• ASD

• Project Plan• 13rfa

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EDUCATIONAL OUTREACH

Project Hermes - CDR

Educational Outreach

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Status of Requirements Verification *

Project Hermes - CDR

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Status of Requirements Verification *

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SAFETY

Project Hermes - CDR

13

Risk Assessment & Launch Vehicle

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PROJECT BUDGET

Project Hermes - CDR

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Project Budget Summary

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LAUNCH VEHICLE

Project Hermes - CDR

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Launch Vehicle Summary• Predicted apogee: 5610 ft • Stability margin: 1.9 calibers• Motor: Cesaroni L1390• (Parachutes Used) *

• 47 fps at 60 inches up the rail• Max Mach 0.72• Total weight: ~41 lbs• Dual deployment

Solidworks PREFERED but OpenRocket is okay :/

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Fins

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Booster Section

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Apogee Targeting System (ATS)

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Motor Selection

Final Motor Selection *

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Avionics Bay

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Payload Bay

Payload Design Overview *

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Payload Bay – Dimension *

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Payload Bay – Integration *

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Recovery System

Test of the staged recovery system *

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Recovery System - Main

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Recovery System - Drogue

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Mass Breakdown

Mass Statement and Mass Margin *

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Thrust-to-Weight Ratio *

Equations and numbers *

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Rail Exit Velocity *

Equations and numbers*

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Rocket Flight Stability *

Rocket flight stability in static margin diagram *

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Stability Calculation

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Parachutes*

Explain choice of model *

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Parachutes - Specifications *

Explain sizes, recovery harness type, size, length,And descent rates *

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Mission Performance – Flight Profile

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Mission Performance - Drift Profile

Predicted drift from the launch pad with 5, 10, 15, and 20 mph wind *

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Launch Vehicle Kinetic Energy *

Explain kinetic energy at key phases of the mission, especially landing! *

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Test Plan Overview

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Final Launch Vehicle Product

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FLIGHT SYSTEMS

Project Hermes - CDR

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Flight System Responsibilities

Outline Mission Objectives

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Flight Systems: Avionics

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Flight Systems: Avionics

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Flight Systems: Ground Station

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Flight Systems: ATS Science

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Flight Systems: ATS System

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Flight Systems: ATS Power

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Flight Systems: Testing Overview

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AUTONOMOUS GROUND SUPPORT EQUIPMENT

Project Hermes - CDR

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AGSE: Initial Design

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AGSE: RPDS -

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AGSE: RES

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AGSE: MIS

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AGSE: Safety

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AGSE: Electronics

AGSE: Power

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AGSE: Test Plan Overview

Questions?

Questions

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