Transcript SolarSat

CSU RocketSAT
Conceptual Design Review
Colorado State University
Project Advisor: Dr. Azer Yalin
Graduate Advisor: Grant Rhoads
Matt Lyon
Wesley Munoz
Ryan Sullenberger
Kenny Vogel
October 14, 2009
Mission Overview
• Objective
– Space exploration missions are challenged with the ability
to measure the amount of fluid (specifically a cryogenic
fluid) that remains in a tank without the assistance of
gravity. The RocketSat payload will consist of an optical
mass gauging system that will demonstrate accurate
measurements of the amount of fluid in a tank exposed to
any gravitational environment. Two tanks with different
volumes of liquid will be independently opened and closed
from the system to show the volume difference between
the two, simulating the loss (or usage) of liquids.
Mission Overview
The overall goal of the CSU RocketSat Team for the 2009 –
2010 academic year is to design and flight test a system that
could be used as a mass gauge for cryogenic (liquid) fuel
systems. The team will develop a methodology for measuring
the change in volume of a liquid sample due to the change in
density of an enclosed gas. This system is designed to
measure fluid volumes in any gravitational environment, but
has specific application to orbital rockets and space vehicles.
An interferometer will be used to obtain the fringe pattern of
an enclosed gas.
Mission Overview
• Previous Research:
– A mass gauging demonstrator for any gravitational conditions was
studied and constructed by Bill Witherow, Kevin Pedersen and Valentin
Korman in the 2006 IRAD Review.
– The objectives of this experiment was to develop a sensor and
measurement technique to accurately determine liquid volume in a
tank in any gravitational environment, and demonstrate its accuracy
and reliability in a relevant cryogenic environment.
– The mass gauging system used a modified Michelson interferometer
to detect subtle changes via the index of refraction.
Mission Overview
• Michelson Interferometer used for IRAD 2006.
Mission Overview
• Working laboratory experiment at MSFC; limit
of successful data
Fringe Count
Optics
Tank 1
Tank 2
Mission Requirements
Requirement :
Method:
Status:
Payload must not exceed a mass of 3.17 kg
Design
Pending
Payload must survive the duration of the mission under
intense vibration and acceleration.
Design, Test,
Analysis
Pending
Batteries must be able to provide sufficient power
through the duration of the mission.
Design, Test,
Analysis
Pending
The center of gravity for the payload must be within one
inch of flight string.
Design
Pending
An adequate system must be made to integrate both the
CSU and UNC payloads in one canister.
Design
Pending
Gas must not escape from the optics chamber.
Design, Test,
Analysis
Pending
A redundant system must be created in case accidental
spillage of water from the liquid tanks occurs.
Design, Test
Pending
Success Criteria
•
Minimum:
– To construct a functional Optical Mass Gage within the size and weight
constraints
– Accurately and precisely measure differences in liquid volumes while on the
earth (1G levels)
– Pass all of Wallops’ testing requirements and be eligible to fly on launch day
– Stay under budget
•
Maximum:
– Accurately and precisely measure differences in liquid volumes throughout the
entire flight envelope
– Have all data be successfully recorded to the micro-SD card throughout the
entire flight envelope
– All minimum criteria
Scientific Benefits
• Future space missions are severely limited by the inability to
determine the amount of fluid that remains in a tank without the
assistance of gravity.
• The sensor would enable future mission concepts dependant on
mass gauging.
• The sensor design is simple with minimal intrusion or modification to
the tank.
• Optical mass gauging system with piston would only require a
compression device of a few cubic centimeters to determine volumes
of 100 liter tanks. The same system would require a compression of
roughly the same size of 1/3 of a soda can to allow for complete
detection of 1000 liter volumes. This result far exceeds any current
compression system.
Ref: W. Witherow, Kevin Pedersen. Mass Gauging Demonstrator for Any Gravitational Conditions. IRAD 2006.
Design
• Design will consist of a
Michelson-Morley or MachZehnder interferometer, two
liquid tanks containing
different volumes of water,
and a piston for compression.
• Interference from the laser
beam will be recorded by a
data logger.
Conceptual Payload
Design
Mach-Zehdner
Interferometer
Expected Results
It is expected that the Mach-Zehnder
Interferometer will detect the change in the
index of refraction for a noble gas (argon)
within a contained volume during a launch on
a sounding rocket, due to the difference in
volume of a contained fluid.
Payload Canister User’s Guide Compliance
– Mass and Volume
• Expected to require ½ of a full-size can (9.3in dia. x 4.75in height)
• Mass is expected to be under 7 lb
– Payload activation
• Playload will be activated by a G-switch
• All power and electronics will be provided by a power source and
electronics system flown on the CSU RocketSat project in July 2009.
• G-switch will be redesigned from last year to prevent accidental triggering
during integration
– Rocket Interface
• Shorting wires and interface with the rocket will be that same as those
from 2009.
Shared Can Logistics Plan
• Canister is shared with University of Northern Colorado
• Northern Colorado Mission:
– Studying the dynamics of a vessel containing a known liquid to study slosh affects that
could be applicable to payloads attached to the spend final stage of a booster.
• Colorado State Mission:
– Innovative method for measuring gas volume with possible application to cryogenics
using fringe patterns.
• The CSU RocketSAT team would STRONGLY prefer to occupy the bottom
half of the can due to the nature of vibrations on the experiment
• The bottom bulkhead will be mounted to using the standard 5-bolt
pattern, but it is preferable to use a different mounting pattern to UNC
that does not have a standoff directly in the center
Management
• Team Members:
– Matt Lyon
– Wesley Munoz
– Ryan Sullenberger
– Kenny Vogel
Budget
Item
Category
Vendor
Qty.
RocketSat Canister
Laser
Optics
Beam Splitter
Mirrors
Mounts
Linear Actuator
Nickel Mesh (6x6)
Piston
Raw Piston Material (Aluminum)
Valves
Copper Tubing
Swagelok
Swagelok Sleeve
Photo-Diode Detector
Xenon/Argon Xenon/Argon Tank
Raw Material optical chamber (Aluminum)
Liquid Tanks 1 and 2
Raw Tank Material (Aluminum)
Data Acquisition Software
Travel Costs to WFF for Launch
Registration
Tangible Item
N/A
WickedLasers
1
1
$7,000.00
$97.97
Tangible Item
Tangible Item
Tangible Item
Tangible Item
Tangible Item
Scientific Online
Thorlabs
2
4
Firgelli
Industrial Netting
1
1
$59.85
$32.00
$0.00
$65.00
$236.00
Raw Material
Tangible Item
Tangible Item
Tangible Item
Tangible Item
Tangible Item
Tangible Item
Colorado Iron and Metal
McMaster - Carr
McMaster - Carr
McMaster - Carr
McMaster - Carr
Thorlabs
Airgas
N/A
2
N/A
2
2
2
1
$20.00
$145.78
$4.10
$1.20
$1.68
$84.20
$300.00
Raw Material
Colorado Iron and Metal
1
$20.00
Raw Material
Intangible
Travel
Colorado Iron and Metal
N/A
N/A
1
1
5
$20.00
N/A
$2,000.00
Total Required
Total
$10,087.78
Conclusions
• The apparatus will be a functioning Mach-Zehnder Optical
Mass Gauging system capable of measuring the change in
volume of water between two separate tanks, to simulate a
loss in mass. The most challenging endeavors involved with
this project will be maintaining optical alignment throughout
the mission, especially due to severe vibrations and
accelerations, as well as the limited budget. Limited resources
force us to design around looser tolerances that could be
achieved with higher quality parts. Another challenge will be
miniaturizing the device to fit within half a RocketSat canister.
Our device will require an innovative approach to problem
solving.