CONCEPTUAL DESIGN REVIEW ROCKSAT-C

downtownbeeMechanics

Nov 18, 2013 (3 years and 7 months ago)

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October 5, 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


CONCEPTUAL DESIGN REVIEW

ROCKSAT
-
C


ROCKSAT
-
C 2013

1

MCC Aerospace Engineering & Technology

Goal Statement
:


The goal of Mitchell Community College’s
aerospace engineering and technology team is to
educate and prepare students for careers based in
science, technology, engineering, or math related
occupations. Through contextual and collaborative
projects, individuals will develop their teamwork and
organizational skills. These projects will foster
innovative thought through hands
-
on research and
development activities which will lead to improved
opportunities for success in the workforce.

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C 2013

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C 2013

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Mission

Overview

Mission Overview

Minimum

Success Criteria

Theory and Concepts

Concepts of Operations

Mission

Requirements

Expected Results


Systems Requirements

Conceptual

Design Overview

Mechanical

Shared Can Logistics

Electrical

RockSat
-
C User’s

Guide Compliance


Testing

Management

Team Organization

Budget

Mentors

Facilities

Schedule

Legacy

Plan

Conclusions

Mission Overview


PEGASIS

II

ROCKSAT
-
C 2013

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Mission Overview


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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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

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Mission Overview

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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.

Mission
Requirements

O
bjectives:


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

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System
Requirements


Energy generators


Data collection & retention


Electronic operation control


Control & experiments (sensing board)


Simplified structure design

Mission Overview

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Minimum Success


Voltages are successfully read from
each transducer and recorded to
memory


Control sensing board records data of
various environmental aspects


Concepts of
Operations


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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.



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Conceptual Design
Overview


PEGASIS

II

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Mechanical Design Overview

PEGASIS

II

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Design Overview

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Major Components



SUBSYSTEM DEFINITIONS


“EM Pendulum”

Magnet suspended on a pendulum over
multiple copper coils will use horizontal
vibrations and angular velocity


Aubade


Photovoltaic panel

“Jerk”

Magnet surrounded by a copper coil will use
vertical vibrations

“Bristol”

Magnets in a circular track will use angular
velocity

“Diving Board”

Piezoelectric cantilever will use horizontal
vibrations

Design Overview

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C 2013

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Mechanical

-

Major Components


Will have a pendulum mounted that rotates
with the rocket from the center rotation
surrounded by semispherical wire coils.

Design Overview

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C 2013

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Mechanical
-

Major Components


Photovoltaic
panel that will be constructed of
efficient solar cells

Solar Rays

N
-

type

P

-

type

Junction

Design Overview

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Mechanical
-

Major Components


Will create energy through a copper wire coil
wrapped around a cylinder with a magnet
between two springs using the R axis.

Design Overview

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C 2013

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Mechanical
-

Major Components


Design based on idea of circular motion resembling
a race track where the magnet travels 360 degrees
inside a tube surrounded by coil wire

Design Overview

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Mechanical
-

Major Components


Will vibrate vertically on the z axis of the rocket;
composed of a piezoelectric cantilever

Design Overview

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Mechanical
-

Major Components



Other past transducers will receive further testing for
possible inclusion


New transducer designs are being considered and will be
tested


Other producers of energy will be considered for the
payload

Design Overview

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C 2013

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Mechanical
-

Structure



2
Makrolon

Plates, top & bottom


Circular to match canister


Components mounted on either the top of the bottom plate or the
bottom of the top plate.


Aluminum hex standoffs, 4 or 5


Components made of plastic using rapid prototype or of aluminum
using CNC machines


Design Overview

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-
C 2013

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Mechanical
-

Structure


Green:
Electronics Package


Data Collection


Data Retention


Sensing Board (Controlled)

Grey

Box
: Battery

Grey

Cylinder
: Jerk

Blue

& Red

unit
: EM Pendulum

Gold
: Bristol

Yellow
:
Aubade

Purple
: Diving Board

Pink
: Sensing Board (Experiment)



Design Overview

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C 2013

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Mechanical
-

Summary




Electrical Design
Overview


PEGASIS

II

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C 2013

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Design Overview

Electrical
-

Major Components



The electrical system will use 1.SYS.1 activation
system at approximately T
-
5mins.


An internal counter will begin for further on board
control.


An Arduino will be used for main processing work and
data acquisition.


Data will be collected until power is disconnected.

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Design Overview

Electrical
-

Major Components



Sensing board(SB) design form the 2012 mission will
be improved for the 2013 mission.


Dual SB’s will be used for comparative data.


One SB will be powered from battery, the control.


One SB will be powered directly from transducers, the
experiment.


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Design Overview

Electrical
-

Major Components



Openlogs

will be used for data retention.


2012 mission showed no flaws in operation.


Open
-
source licensing will allow


For full integration into SB


design instead of using


daughter cards.


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Design Overview

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Transducer

#1

#2

#3

#4

#5

Processor

Sensing Board


Control

Battery

Sensing Board



Experiment

Design Overview

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Electrical
-

Summary




Test Design
Overview


PEGASIS

II

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Design Overview

Testing



The
goal of our testing plan is to ensure the payload
will perform to design and improve the efficiencies from
Pegasis 2012 transducers. Each test will be used to verify
the payload can withstand high G forces and strong
vibrational forces. Hardware mounts, electrical connectors,
circuit boards and transducers will need to remain
functional after testing.

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Design Overview

Will
c
onsist of :

Vibration analysis


Via shake
-
table

Simulation Testing


Component test rocket


Complete payload
test rocket

Plans to include:

Temperature functionality


In design process

Electrical System testing


In design process

Further tests will be designed as
needs arise

Testing

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Design Overview

Testing


Shake Table Specs


Frequency: 200
-
3000Hz


0.1 inch amplitude


200
-
1750 RPM


Functional spin table: 0
-
500RPM

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Design Overview

Testing


Component
Rocket Specs


Length


42 inches


Diameter


4 inches


Cesaroni


H 400 Motor


Max Acceleration


26 (gees) (approx.)


Max Altitude


1600 ft (approx.)


Equipment from last year


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Design Overview

Testing


Full Scale Rocket Specs


Length


93 inches


Diameter


10 inches


Cesaroni



J 1520 Motor


Max Acceleration


25 (gees) (approx.)


Max Altitude


1900 ft (approx.)


Equipment from last year.


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C 2013

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Shared can logistics


Project
PEGASIS II
will use half a canister and require a
partner.


The
optic port will be used, but
atmospheric port
shall
will not
be needed.


Center of mass and all other requirements shall be fulfilled in
compliance with
RockSat
-
C
2012
-
2013
Payload Canister
User’s Guide.


Communication will be done via email


Solidworks

files will be shared with canister partner using
D
ropbox


Aluminum hex standoffs will be used to integrate with canister
partner

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C 2013

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RockSat
-
C user's guide compliance


Project PEGASIS will use half a canister and require a partner.


Useable payload space = 9.3


Diameter x 4.75


high.


Center of gravity


Payloads must conform to a center of gravity that lies within a 1x1x1
inch envelope of the geometric centroid of the integrated RockSat
payload canister.


Approximate weight <
5
lbs without cap head screws.


Total weight of canister = 20+/
-

0.2 lb.


Cannot modify canister.


Must be able to pass vibration test.


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Design Overview

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Testing
-

Summary




Management


Pegasis

II

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http://www.mitchellcc.edu/programs/rocket
-
projects/team2.html

Faculty Advisor


Sharon Rouse


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C 2013

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1987 Diploma Machining Technology


A.A.S. Manufacturing Engineering Technology

1999 A.S. Associate of Science

2003 CAD Drafting Certificate

2004 B.S.I.T. Industrial Systems minor in Manufacturing

2007 M.S.I.T. Technology Systems minor in Manufacturing

2013 Ph.D. Technology Management minor in
Manufacturing


Manual and CNC machining, quality assurance, product
engineering, blueprint reading, engineering materials.


Management

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C 2013

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Doug Knight
Ph.D.

Clint Halsted

Shawn
Fraver

Ron
Davis



Mentors

S
chedule


10/8


RockSat
-
C meeting


10/15


RockSat
-
C meeting


10/17


Payment and online progress report due


10/26
-
10/27


PDR and PDR teleconference


10/29


RockSat
-
C meeting


11/1


Small scale test flights begin


11/5


RockSat
-
C meeting 11/14


Online progress report due


11/18


RockSat
-
C meeting


11/16 or 11/30


CDR Due
-

discuses with team based on finals schedules


11/28


CDR and then CDR teleconference


12/3


RockSat
-
C meeting, begin legacy equipment testing


12/10


RockSat
-
C meeting


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C 2013

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C 2013

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Facilities

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Electronics Lab

Machine Shop

Rapid Prototyping Printer

Management

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A Safety
officer will train team members on safe guidelines and
practices.


A test will be administered to each team member to certify that each
member understands the proper procedure.


Rocket test flights


Materials
-

use non
-
flammable material.


Motors
-

use certified motors.


We will strictly follow the TRIPOLI HIGH POWER SAFETY CODES
.

Safety


Management

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Legacy Plan

It is a goal of this team to set up a plan to
where new members will join each year and
be taught by experienced members. Also, we
wish to create a long term financial plan to
support the team projects.

Further considerations


Software development


Selection of transducers


Individual or group voltage measurement


Battery selection


Possible replacement of
Arduino

with in
-
house built data
collection device


Coil design


Develop test methods as conditions change

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C 2013

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CONCLUSION


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C 2013

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October 5, 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