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Pegasis II. PDR RockSat-C . October 26, 2012 Mitchell Community College MCC Aerospace Engineering and Technology http:// www.mitchellcc.edu/programs/rocket-projects/index.html http://www.facebook.com/MCCA.E.T.team. Outline of Presentation . Pegasis II. Mission Overview

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pdr rocksat c

Pegasis

II

PDRRockSat-C

October 26, 2012

Mitchell Community College

MCC Aerospace Engineering and Technology

http://www.mitchellcc.edu/programs/rocket-projects/index.html

http://www.facebook.com/MCCA.E.T.team

RockSat-C 2013

pegasis ii

PegasisII

Mission Overview

Presented by: Patrick

RockSat-C 2013

mission overview
Mission Overview

Mission Statement

Our goal is to power space-based instrumentation systems by passively generating energy from transducers of a proprietary design. Energy will be harvested from the rocket flight, solar rays, and other sources. This will be accomplished by building a more robust and simplistic payload using transducers with increased efficiency and improved design characteristics. Results may lower cost and power requirements for space science by reducing the weight of electrical components.

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Mission Overview

MissionRequirements

  • Harvest electrical energy from various sources during flight.
  • Measure various environmental factors throughout flight such as humidity, magnetic field and acceleration.
  • Use energy harvested to power electronic device

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Mission Overview

What We Expect

We will show that mechanical devices can successfully power low energy consumption electronic devices. Thereby reducing the need of expensive and heavy one-time use batteries.

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Mission Overview

Future Benefits

  • The primary field of application is for deep space exploration. Weight and longevity is a key factor in deep space exploration and any increase in efficiency for either reduces budget cost greatly.
  • Another possible market is micro and nano satellites. Small transducers to power these small devices can eliminate the use of expensive and toxic materials in battery components.

RockSat-C 2013

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Mission Overview

Theory and Concepts:

  • Electromagnetic transducers will utilize Faraday’s Law.
  • Solar transducers will utilize Photoelectric effect.
  • Peltier coolers will use solar transducer to act as a heat sink for microprocessors
  • Piezoelectric effect

RockSat-C 2013

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Mission Overview

Past Research

  • Electrodynamic tethers tested with the Space Shuttle
  • MEMS based micro-engineered motion energy harvesting devices (Imperial College of London, 2007)
  • MIDE out of Boston, Ma., founded in 1989, develops vibration energy harvesting devices
  • PEGASIS II is a continuation of our 2012 RockSat-C Project, PEGASIS.

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Mission Overview

Concept of Operations

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mission overview7
Mission Overview

Concept of Operations

  • Event A
    • Ignition, spike in data, collection begins
  • Event B
    • Orion burn ends, spike in data, collection continues
  • Event C
    • Apogee, little to no voltage measured, collection continues
  • Event D
    • Chute deploys, spike in data, collection continues
  • Event E
    • Splash down, spike in data, collection continues until retrieval

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11

mission overview8
Mission Overview

Expected Results

CONTROL

A sensing board will be powered by a fixed battery. It will record and save data of different environmental variables.

EXPERIMENT

A sensing board will be powered by energy gathering devices. The energy used from both sensing boards will be recorded and saved for comparison. Energy produced by transducers will also be recorded and saved.

TRANSDUCERS

Transducers are expected to produce from 2V to 15V peak. Currents will vary depending on transducer design and coil development.

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PegasisII

Systems Overview

Presented by: Nathan

RockSat-C 2013

systems overview
Systems Overview

Requirement Verification

  • Weight required for both electronic and mechanical systems will be determined. Combined weight will be less than the maximum requirement of 20 lbs.
  • Center of mass will meet requirements of the RockSat-C Users Guide and not negatively effect partnered payload.
  • Mock up canister will meet specified requirements set by the RockSat-C Users Guide for accurately payload simulation.
  • Potential difference between plates will be zero will all plates electrically connected to a common ground.

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Systems Overview

Critical Interfaces

  • Minimum, identify critical interfaces
  • Chart
  • Interface name, brief description, potential solution

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Systems Overview

Risk Matrix

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Prototyping Plan

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Systems Overview

System Management

  • We have divided the System into three categories
    • Mechanical
    • Electrical
    • Software
  • Systems have been assessed individually

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PegasisII

Systems Overview

Mechanical

Presented by: Joseph

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Systems Overview

RockSat-C 2013

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Systems Overview

RockSat-C 2013

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PegasisII

Subsystem Design

Mechanical

Presented By: Joseph

RockSat-C 2013

subsystem design
Subsystem design

Jerk, Bristol, EM Pendulum, & Diving Board

  • All designs are based off the 2012 mission.
  • Mounting techniques are tested and proven.
  • All show recordable energy generation.
  • Coil design is being reconsidered for optimal energy production.
  • No drastic changes are currently planned for any of these transducers. Further testing may show flaws that lead to redesigns.

RockSat-C 2013

subsystem design1
Subsystem design

Aubade

  • The design from the 2012 mission is being kept at this time as it has been proven.
  • Smaller more efficient cells are being researched for use. This stems from experience of the 2012 mission and positioning/size of the optical port.

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Subsystem design

Jerk

RockSat-C 2013

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Subsystem design

Bristol

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Subsystem design

EM Pendulum’s Pendulum

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Subsystem design

EM Pendulum’s Base

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Subsystem design

Diving Board

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Subsystem design

Aubade

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PegasisII

Systems Overview

Electrical

Presented by: Tony

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Subsystem design

Electronics Package

  • Design one is based off of the 2012 mission. We saw what worked and didn’t work which requires little change to make it flight ready.
  • Design two takes the design from the 2012 mission and improves on it greatly. Each weak point is completely reworked instead of just being fixed. Minimization and efficiency are the main design factors.
  • The sensing board uses the idea from the 2012 mission with an upgraded processor and on-board programming capabilities.
  • Design one has very few risk as it is a tested system.
  • Design two and the sensing board are untested and functionality is unknown.

RockSat-C 2013

systems overview5
Systems Overview

RockSat-C 2013

systems overview6
Systems Overview

RockSat-C 2013

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Subsystem design

Arduino

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Subsystem design

Trade Studies

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Subsystem design

Trade Studies

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PegasisII

Systems Overview

Software

Presented by: Tony

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Systems Overview

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Systems Overview

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Systems Overview

System Concept of Operations

  • Please refer to the A/D conversion cycle and data recording software flowchart for the data recording processes.
  • Data will be transferred from the microcontroller to the OpenLog after every ADC cycle.
  • UART transmission will be used with a baud rate of 115200bps. Dropped characters are expected at this speed but will be offset by the increases number of data points we acquire.
  • The OpenLog writes data to the SD card in blocks of 512 characters. Some data from the last block may be lost on power disconnection.

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PegasisII

Project Management Plan

Presented by: Catherine

RockSat-C 2013

project management plan
Project Management Plan

User-Guide Compliance

  • Each plate will be grounded to a common ground, ensuring that no system is shorted to the RockSat canister.
  • Mitchell’s project will use the 1.SYS.1 payload activation scheme, allowing us to receive power before G-switch activation.
  • All wires will be tied and staked to prevent disconnects during flight.

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Project Management Plan

Shared-Can Logistics

  • Pegasis II will be partnering with the New Jersey Space Grant.
  • Planned communication will take place via teleconferences, Google Chat & Google Docs along with Skype.
  • Pegasis II will leave the top plate clear for the New Jersey Space Grant Team. Allowing for variable capability to move CG and adapt in z & theta without constraining our partner.

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Project Management Plan

Organizational Chart

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Project Management Plan

Fall Schedule

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Project Management Plan

Spring Schedule

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Project Management Plan

Work Breakdown Schedule

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project Management Plan

Test Total:

$876.25

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Conclusion

Main Action Items

  • Begin component testing
  • Make final decisions on any required parts
  • Work on additional fundraising

Questions

RockSat-C 2013

pdr rocksat c1

Pegasis

II

PDRRockSat-C

October 26, 2012

Mitchell Community College

MCC Aerospace Engineering and Technology

http://www.mitchellcc.edu/programs/rocket-projects/index.html

http://www.facebook.com/MCCA.E.T.team

RockSat-C 2013