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Project STATIC � Star Tracker and Testing Interplanetary Concrete

�Subsystem Testing Review (STR)

Arapahoe and Red Rocks Community Colleges

Leighanne Bennett, Nicholas Betz, Ruth Ehler, Sebastian Gomez, Kye Jackson, Christian Mack, Mallory Shaloy, Antonino Piscitella

2/23/2024

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STR Presentation Outline

Section 0: Action Item Summary
Section 1: Mission Overview
Section 2: Systems Overview
Section 3: Subsystem Testing Results
Section 4: Plan for ISTR
Section 5: Summary Test Plan
Section 6: Initial Wallops Test Plan
Section 7: Project Management
Section 8: Next Steps & Conclusion

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Section 0: Action Item Summary�Presenter Name

Please add and provides details on an inhibit for your sintering experiment during Wallops ground testing (Slide 31)
Please show more mechanical design details in your subsystem section (Slide 33)
Please make sure you are using the updated template as you are missing sections (test plan, student/mentor plan, partnerships) (Slides 52-61)
Provide a detailed test plan (Slides 43-45)

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Section 1: Mission Overview�Ruth Ehler, Leighanne Bennett, Christian Mack, Nicholas Betz, and Antonino Piscitella

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Mission Statement

The STATIC project aims to evaluate how sintering lunar regolith simulant (LRS) in a microgravity environment affects the sintering process. As well as testing the structural integrity and durability of sintered LRS after exposure to a suborbital environment.

The STATIC project also aims to create a cost efficient star tracker for cheaper use on spacecraft in the future. The star tracker will utilize open source software running on a Raspberry Pi, and will use an official Raspberry Pi camera, lens, and filters, mounted on a swivel.

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Mission Objectives

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Mission Overview: Concept of Operations

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t ≈ 1.3 min

Altitude: 75 km

t ≈ 15 min

Splash Down

-All systems off

t ≈ 0.5 min

TE2- Switch on Sintering

-All systems on

-experiment computer activated

-sensor package activated

-GSE Power on at (T – 180)

t = 0 min

t ≈ 4.0 min

Altitude: 95 km

Deactivate Star Tracker, End on-board calculations, Begin power off sequence

Apogee

t ≈ 3.1 min

Altitude: ≈150 km

End of Malemute Burn

t ≈ 0.6 min

Altitude: 52 km

t ≈ 4.5 min

Altitude: 75 km

Altitude

t ≈ 7.5 min

Chute Deploys

t ≈ 2.3 min

Switch off Sintering, begin cooling time, begin star tracker imaging

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Ruth�At t-0, all systems will be on. The experiment computer will be activated as well as the sensor package. At just under half a minute and 52km altitude, the Malemute burn will occur per the timing events sheet provided to us. At 1.7 minutes, we will begin imaging for the star-tracker and tracking on-board data, and turn on the coils to begin the sintering process. Roughly a minute later .4 minutes before apogee, the sintering will be completed and the subsystem will begin cooling. At 4 minutes into the flight, the star tracker will turn off, we will stop recording data, and begin to turn off all systems. All systems will turn off at 15 minutes at splashdown and the mission will be complete. �Once the payloads from the rocket are recovered, we will analyze the data collected in-flight and

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Timer Events

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Event	Time On	Dwell	Event Description
GSE 2	T-180 sec	540 sec	3 minutes before launch. Power on the computer for the experiments.
TE-2	T+030 sec	360 sec	Activate the sintering experiment; begin internal timing sequence for star tracker

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Primary Mission Overview: Expected Results

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Differences are anticipated between lunar regolith simulants sintered in a microgravity environment and those sintered on Earth. These differences include:

Lack of unified sintering
Densification rate
Grain size distribution
Pore formation
Overall structural deformation

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Secondary Mission Overview: Expected Results

The star tracker will be expected to have accurately comparable data to data of which has been professionally analyzed and proven correct. The team aims to create a faster, more space and cost-efficient star tracker that is comparable to the ones currently in use.

Store and Process
Small Space Efficiency
Quick Image Calculations
Accurate Directional Data

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Mission Overview: Success Criteria (Primary)

Minimum Success Criteria:

Sintered LRS is collected

In the event the sample is not suitable for structural testing due to its condition, the sample will undergo detailed microscopic analysis.
In the event sintering is not achieved, analysis of conditions resulting in lack of success will be conducted.

Comprehensive Success Criteria:

The sample is in good condition and can be used for multiple kinds of testing including:

Mechanical/structural
Microscope
Etc..

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Mission Overview: Success Criteria (Secondary)

Minimum Success Criteria:

Confirmation that the star tracker module powered on and attempted to take pictures.

Comprehensive Success Criteria:

Confirmation that all aspects of the star tracker module powered on and accurately captured images.

Images stored correctly on internal hardware

Images processed in flight

Have accurately comparable directional data to similar images taken and analyzed by NASA.

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Section 2: Systems Overview � Kye Jackson, Nicholas Betz, Leighanne Bennett, Sebastian Gomez, Antonino Piscitella, Mallory Shaloy, Ruth Ehler, and Kye Jackson

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Systems Overview: Top Level Requirements

Primary Mission

Perform induction sintering experiments on Earth prior to flight.
Secure the crucible into the payload.
Thermally insulate the payload from the crucible.
Provide ample power for regolith sintering in our time limit.
Sinter lunar regolith simulant during flight.
Compare regolith samples made in-flight to the control back on Earth.
Put samples through structural tests (compressive, tensive, and shear) as well as compare under microscope.

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Kye

For our primary mission our main objective is to compare simulant sintered in microgravity to simulant sintered on earth. To compare with samples sintered on earth we first need to actual sinter on earth, we will then be doing structural analysis on the simulant sintered on earth to compare to the in flight sintered regolith.

To successfully sinter in microgravity we need to secure our crucible in the induction coil on our payload. To do this we have decided on ceramic screws to secure the crucible. As well as a ceramic fiber insulator acting as a cushion around the crucible.

This insulator will also thermally insolate the sealed box containing the coil from the rest of the payload, in order to not disrupt any of the other operations taking place. The insulator has no conductivity so it will have no effect on the electric field going through the crucible.

We need to provide ample power to run the induction coil at least 1600 watts for it to sinter in under 3 minutes. The power and time required have both gone up since the CDR because of the data gathered from recent testing. The power source we will be using is two batteries made for RC cars, they will provide 44.4V and 40 amps to get to 1776 watts.

After flight we will run structural tests on the microgravity regolith if it is proper condition, if we can not run structural tests on it we will analyze its structure under a microscope.

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Systems Overview: Top Level Requirements

Secondary Mission

Store and process in flight data corresponding to the direction the camera was pointed when that picture was taken.
Gain a larger field of view, for precise navigation.
Run inexpensive open-source software.
Return with accurate data processed in zero gravity.
Prove that it is possible to collect precise navigational images with a much smaller overall space and cost budget.

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Systems Overview: Design Overview

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Requirement	Verification Method	Description
The Star Tracker and Regolith modules shall be powered and run through software commands. Ensuring proper sequence of the experiment.	Demo / Test / Analysis	Mission simulations prior to launch shall occur to ensure that the modules function as intended. With the data being captured properly, to then be analyzed to determine mission success.
Both modules will run through the necessary software commands. Making sure data recording is working and stored properly.	Demo / Test / Inspection	Tests of the software commands and data capture will be run prior to launch for experiment accuracy and data collection.
The sensor packages shall operate for the full duration of flight and pull no more than 0.5 Ah.	Demo / Test / Analysis	Sensor simulations prior to launch will verify that all sensors are able to record, transfer, and store data to the computer housing unit. As well as keeping our power consumption below 0.5 Ah.
The system shall survive the vibration and electrical characteristics prescribed by the RockSat-X program.	Test / Analysis	The final payload will be subjected to these test during testing at Wallops Flight Facility. As we integrate our modules into one system, we shall periodically test the structure.

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Kye

We will be demonstrating testing and analyzing our power and software commands for the star tracker and regolith to ensure proper sequencing. This is to ensure during mission our software is properly telling our modules how to function so our experiments can run properly.

We will also be demonstrating testing and analyzing our data collection systems, like our sensors for regolith and our image capturing for star tracker.

Data collection is very important for the star tracker and therefor it is very important our software works so we will be verifying it works before launch.

We will also verify that the sensor package will be working properly the whole flight and pull the correct amount of current. We will be testing that the sensors can record transfer and store data to our computer housing unit without using more than .5 amp hours.

We also need to ensure that our whole payload can withstand the vibration and electrical characteristics required by rocksat-X. The Wallops-flight facility will test these characteristics on our payload and we need to ensure that it will not fail. As we implement modules onto our payload we will test our structure at various points to ensure it is still up to standard.

Many of these tests have been run which will be gone over in later slides.

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Systems Overview: Functional Block Diagrams

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Systems Overview: Design Overview

(Unit = Inches)

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Level 1

Level 2

**(Callouts on future slide)

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Kye

Here you can see the payload layout with the Regolith, Star tracker and programming subsystems.

Looking at the top left most image you can see the programming subsystem, housing all the brains of the payload, this subsystem is sitting on top of the induction coils circuit, the circuit is providing the alternating AC current to the coil. The coil is located the the right of the coils circuit in the regolith coils, section view.

In this image you can see the cruicible secures by the screws and suspended in the middle of the coil, there is also enough room on the outside for the electric field to flow freely without effecting other subsystems and without losing effectiveness.

In the full system image you can also see the two 22.2V batteries that will be powering the regolith coil, it will also be connnected to the programming section which will house the switch.

On the bottom of the full system images you can see the star tracker sitting on its rotory motor. The star tracker will have a unrestricted view out of the payload.

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Systems Overview: Design Overview (Continued)

**(Unit = Inches)

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Electrical Box

**(Callouts on future slide)

Star Tracker

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Kye

Here you can see the payload layout with the Regolith, Star tracker and programming subsystems.

Looking at the top left most image you can see the programming subsystem, housing all the brains of the payload, this subsystem is sitting on top of the induction coils circuit, the circuit is providing the alternating AC current to the coil. The coil is located the the right of the coils circuit in the regolith coils, section view.

In this image you can see the cruicible secures by the screws and suspended in the middle of the coil, there is also enough room on the outside for the electric field to flow freely without effecting other subsystems and without losing effectiveness.

In the full system image you can also see the two 22.2V batteries that will be powering the regolith coil, it will also be connnected to the programming section which will house the switch.

On the bottom of the full system images you can see the star tracker sitting on its rotory motor. The star tracker will have a unrestricted view out of the payload.

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Systems Overview: Design Overview (Cont.)

**(Unit = Inches)

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Regolith Housing

Induction Heater

**(Callouts on future slide)

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Kye

Here you can see the payload layout with the Regolith, Star tracker and programming subsystems.

Looking at the top left most image you can see the programming subsystem, housing all the brains of the payload, this subsystem is sitting on top of the induction coils circuit, the circuit is providing the alternating AC current to the coil. The coil is located the the right of the coils circuit in the regolith coils, section view.

In this image you can see the cruicible secures by the screws and suspended in the middle of the coil, there is also enough room on the outside for the electric field to flow freely without effecting other subsystems and without losing effectiveness.

In the full system image you can also see the two 22.2V batteries that will be powering the regolith coil, it will also be connnected to the programming section which will house the switch.

On the bottom of the full system images you can see the star tracker sitting on its rotory motor. The star tracker will have a unrestricted view out of the payload.

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Weight Budget

Under the weight limit
Structural shell will weigh more once subsystem housing is fabricated
The team will ballast the payload

w/ additional housing materials
w/ fabricated box for personal items

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Weight Budget
Subsystem	Total Weight (lb)
Star Tracker	1
Computer hardware	0.5
Crucible	0.13
Induction Coil	2.46
Regolith	0.79
Structural shell (0.125 in thickness)	2.67
Experiment deck	3.3


Total Over / Under	10.85
Limit	15 lbs

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Power Budget

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STATIC Project Power Budget
Subsystem	Voltage (V)	Current (A)	Time On (min)	Amp-Hours
Sensors	5	5.36E-05	8.5	7.5933E-06
Star Tracker	5	0.6	2.5	0.025
Regolith	5	0.16	2	0.006
Control Components	5	3	8.5	0.425

Regolith Battery Power Power: Two 6S Lipo Batteries in series 22.2 V, 1800Mah			Total (A-hr):	0.456
			Over/Under	0.044

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Payload Positioning

Two potential positions of star tracker

Orientation is dependent on another payload - requesting Nadir/West pointed away from Earth and Sun.

Red arrows are the largest FOV

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Representation of our experiment on this diagram is shown with arrows for field of view.

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Power Pins

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Power Pin	Function	Intended Use
1	GSE 1	Not used
2	Timer Event Redundant (TE-RA)	Not used
3	Timer Event Redundant (TE-RB)	Not used
4	Timer Event 1 (TE-1)	Not used
5	GND	GND
6	GND	GND
7	GND	GND
8	GND	GND
9	GSE 2	Power for main computer, camera and sensors
10	Timer Event 2 (TE-2)	Timing trigger to begin sintering process and timing sequence for star tracker camera
11	Timer Event 3 (TE-3)	Not used
12	GND	GND
13	GND	GND
14	GND	GND
15	GND	GND

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Telemetry Pins

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Telemetry	Function	Intended Use
1	Analog 1	Not used
2	Analog 2	Not used
3	Analog 3	Not used
4	Analog 4	Not used
5	Analog 5	Not used
6	Analog 6	Not used
7	Analog 7	Not used
8	Analog 8	Not used
9	Analog 9	Not used
10	Analog 10	Not used
11	Parallel Bit 1 (MSB)	Not used
12	Parallel Bit 2	Not used
13	Parallel Bit 3	Not used
14	Parallel Bit 4	Not used
15	Parallel Bit 5	Not used
16	Parallel Bit 6	Not used
17	N/C	N/C
18	Ground	Ground

19	Ground	Ground
20	Parallel Bit 7	Not used
21	Parallel Bit 8	Not used
22	Parallel Bit 9	Not used
23	Parallel Bit 10	Not used
24	Parallel Bit 11	Not used
25	Parallel Bit 12	Not used
26	Parallel Bit 13	Not used
27	Parallel Bit 14	Not used
28	Parallel Bit 15	Not used
29	Parallel Bit 16 (LSB)	Not used
30	Parallel Read Strobe	Not used
31	N/C	N/C
32	RS-232 Data (TP1)	System status information
33	RS-232 GND (TP2)	Ground
34	N/C	N/C
35	N/C	N/C
36	Ground	Ground
37	Ground	Ground

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Systems Overview: User Guide Compliance

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Requirement	Status/Reason (if needed)
Center of gravity in 1" plane of plate?	Yes
Weight 15.0+/- 1.0	Yes
Max Height < 5.13”	Half deck < 5.13"
Bottom of deck has flush mount hardware?	Yes
Within Keep-Out Zone	Yes
Using < 10 A/D Lines	Not Using
Using/Understand Parallel Line	Not Using
Using/Understand Asynchronous Line	Yes
Using X GSE Line(s)	Yes, GSE 2
Using X Non-Redundant PWR Lines (TE-1, TE-2, TE-3)	Yes, TE-2
Using X Redundant Power Lines (TE-R)	No
Using < 1 Ah	Yes
Using <= 28 V	Yes
Using RF (If yes, list frequency and TX Power)	No
Using deployable?	No
Whole team consists of US Persons	Yes
Using ITAR and/or Export Controlled hardware	No

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Section 3: Subsystem Testing Results �Nicholas Betz, Mallory Shaloy, Christian Mack, Sebastian Gomez, and Ruth Ehler, Sebastian Gomez

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Regolith

Power

Power: Two 6S Lipo Batteries in series

22.2 V, 1800Mah,

Weight: 250g
Discharge Rate: 25 C. At 1800 Mah the battery can supply 45 amps.
Initial test obtained 156 C in 22 seconds.
Approximated time 170 seconds to reach 1200 C.

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Regolith

Induction

Induction coil sintering method.
1800 watts of AC current
LRS has higher iron content with more ferromagnetic properties.
Graphite crucible will be heated via induction and transfer thermal energy
Sintering in flight at t = 0.5 min to obtain sintering temp near apogee

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70%

Induction Heating Housing

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Regolith

Insulation/Containment

Materials used for insulation include:

Ceramic fiber board
Ceramic fiber blanket
Alumina screws

Containment for g force stress:

Alumina screws
Ceramic fiber

blanket

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Ceramic Fiber Board

Alumina Screws

Ceramic Fiber Blanket

Graphite Crucible

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Regolith

On Ground Testing Power Inhibitor

A solid-state relay will be used to inhibit the sintering experiment during ground integration testing. It will be activated via a key and lock mechanism.

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Regolith

Remaining Testing:

Insulation test
Dry run test
Vibration test

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Date:

3/1/2024

3/8/2024

3/15/2024

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Programming/Electrical

Power - 0.428 Ah
Data - RS-232
Volume – 10.35in x 7.18in x 2.25in; A: 55.76in^2
Weight – 0.5lbs
Will interface with GSE and TE electrical systems at Wallops
Will interface with other on-board systems via thermally resistant wiring where possible
Will interface with star tracker camera via data cable

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Housing

Batteries

Voltage Regulators

Pi Boards

Solid State Relay

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Programming/Electrical

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Hardware

Raspberry Pi 4B
Uxcell Electric ON Off Metal Keylock Switch (pictured earlier)
Valefod LM2596 Voltage Regulators
Zero2Go Omini: Wide Input Range, Multi-Channel Power Supply for Raspberry Pi
Motor hat for Raspberry Pi
TMP36 Temperature Sensor
SparkFun Altitude/Pressure Sensor
Voltage Sensor
SparkFun Atmospheric Sensor
CG Solid State Relay

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Programming/Electrical

Completed Testing Date:

Star Tracker software timing test 2/16/2024
Sensor test 2/19/2024

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20%

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Programming/Electrical

Test Results

Star Tracker software testing – Ran several simulations of full in-flight calculations with accurate test images

Success

Sensor testing – wired and tested sensor readings

Success

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Programming/Electrical

Remaining testing Date:

Full sensor wiring and integration week of 2/25
Star tracker motor control sequence 3/1/2024
Star tracker imaging sequence 3/1/2024
Regolith activation/deactivation sequence week of 3/11
Full mission sequence TBD

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Star Tracker

Power Consumption: 5v
Currently have all materials for structure – Assembly in progress
Working on connecting bottom most mount to a rigid stationary structure.

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Pi Camera

Housing

Camera Mount

Servo Motor

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Star Tracker

So far testing has comprised of:

Test programs to move the servo and take pictures.
Pictures using the specified camera and lens.
Mechanical 3d printed prototypes for dimensional testing.
Test images being run through the LOST software.
Testing of power consumption.

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Star Tracker

Top level tests -

servo strength
camera's ability to take clear night sky images
initial trials of the LOST software database

Software has been configured for generic star images and outputting correct navigational data
Camera needs long exposure images for best results but can clearly identify dim stars in the dark sky.
Overall, tests have been successful

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RasPi

Camera

Images:

Software

Test:

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Star Tracker

Remaining Testing:

Integration of Raspberry Pi Camera and LOST software database.
Integration of Servo control systems and Software.
Lens filter testing for glare and/or light collection.
Test window durability and clarity for protected viewing.
Integration of both the Programming and Star Tracker subsystems.

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Date:

3/1/2024

3/15/2024

3/29/2024

4/5/2024

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Mechanical

2.6 Lbs, no electrical components
Wires run through housing and connect to plate & Wallops equipment
Houses all subsystems
1/8" 2024-T3 aluminum from McMaster-Carr
Physical proof of concept will be built, design not finalized until completed.

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Aluminum sheet

Induction coil

Programming

Star Tracker

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Mechanical

Delay in part ordering

Assembly has not been started

Future testing includes:

Stress tests

Durability (drop test)
Vacuum chamber
Heat resistance

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10%

Star Tracker

Induction Coil

Programming

Induction Heater

Enclosed Walls

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Mechanical

Remaining Tests:

Riveting
Assembly
Housing stress tests
Subsystem housing fabrication
Subsystem structural integration testing

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Date:

2/23/2024

3/1/2024

3/8/2024

3/15/2024

3/22/2024

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Section 4: Plan for Integrated Subsystems Testing Review (ISTR) �Christian Mack

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Integrated Subsystem Timeline

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Section 5: Summary Test Plan �Leighanne Bennett

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Testing Plan Master List

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Section 6: Initial Wallop Test Plan �Mallory Shaloy

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Step-by-step Plan (Pre-integration)

System Power/Timing - Ensure all subsystems are receiving power, transmitting data, and have the correct timing sequence
Charge regolith experiment batteries
Final installation of regolith

Step-by-step Plan (Post-integration)

Inhibit regolith system with metal key lock switch
System Power/Timing - Ensure all subsystems are receiving power, transmitting data, and have the correct timing sequence

Special requests for Wallops

Access to payload exterior following integration testing to turn metal key lock switch (inhibition switch)

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Initial Wallops Test Plan

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Section 7: Project Management �Ruth Ehler, Kye Jackson, Mallory Shaloy, Antonino Piscitella, Sebastian Gomez, and Leighanne Bennett

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Team Schedule *Team Meets twice a week (T,F)

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Regolith Subsystem Timeline

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Date	Event	Completed? N/Y or�In Progress (IP)
12/8/2023	Finish timeline/ Sintering testing	Y
12/15/2023	CDR/attempt to sinter regolith	Y
12/22/2023	Get down power specs and order batteries. Order all other materials. Confirm energy transfer of 1000 watts from coil to regolith.	Y
1/5/2024	Get down weight requirements. Research structural integrity testing methods.	Y
1/12/2024	Research into how microgravity affects the sintering process for lunar regolith simulant (LRS)	Y
1/19/2024	Thermal insulation/crucible securement testing.	N
1/26/2024	Vibration testing and G force shock testing	N

Date	Event	Completed? N/Y or�In Progress (IP)
2/2/2024	Vacuum/cool down time sintering testing	N
2/9/2024	Confirm energy transfer of 1000 watts from coil to regolith.	Y
2/16/2024	Confirm energy transfer of 1000 watts from coil to regolith.	Y
2/23/2024	STR presentation	Y
3/1/2024	Insulation test and sintering test	IP
3/8/2024	Dry Run test in vacuum chamber	IP
3/15/2024	Subsystem structrual integration Vibration testing and G force shock testing
3/22/2024	ISTR Review
3/29/2024	Sintering experiment
4/5/2024	Heat capacity/timing test
4/12/2024	vacuum test

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Kye

Here is the regolith timeline,

In the coming weeks we will be doing a insulation test, this is to ensure our subsystem doesn't leak heat onto other subsystems effecting the test.

After that we will do a dry run to test the system without being water cooled.

Next, we will do a vibration test and G-force shock test to ensure our cruicible is sufficiently secured with the ceramic insulator and screws.

On the 22nd we will integrate our tested inuction system onto the payload before we test the full expierement on its own, with computer timings. Over theweeks after that we will test the timing and validify our calculated heat capacity.

We will later try to test in a vauum and see how that effects the expierement.

And lastly as a control we will sinter regolith and proform structural, and microscope analysis to compare to the sample that will be on our payload.

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Programming Subsystem Timeline

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Date	Event	Completed? N/Y or�In Progress (IP)
2/16/2024	Run Star Tracker software tests - completion time	Y
2/23/2024	STR	Y
3/1/2024	Integrate Star Tracker motor and camera with Raspberry Pi board	IP
3/8/2024	Begin wiring�1.) Connect solid state relay to ras pi�2.) Connect solid state relay to keys switch�3.) Connect the regolith experiment to ras pi
3/15/2024	Subsystem structrual integration� Regolith activation sequence testing and structural assembly�All System and Power Testing
3/22/2024	ISTRReview
3/29/2024	Integration testing
4/5/2024	Finish wiring and integration as needed

Date	Event	Completed? N/Y or�In Progress (IP)
12/8/2023	Raspberry Pi OS installed and board set up	Y
12/15/2023	CDR	Y
12/15/2023	Finish integrating star tracker software/hardware	Y
12/22/2023	Run Star Tracker software tests�critical metrics: processing speed, board temperature, memory usage, data storage accuracy	Y
1/5/2024	Motor and sensor wiring mockup and testing�Collaberate with mechanical team to finalize computer components housing	IP
1/12/2024	Continue wiring setup and testing	N
1/19/2024	Begin sensor and motor control software programming	Y
1/26/2024	Continue programming work	Y
2/16/2024	Run Star Tracker software tests - completion time	Y

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Star Tracker Subsystem Timeline

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Date	Event	Completed? N/Y or�In Progress (IP)
12/8/2023	Have materials ordered	Y
12/15/2023	Integrate servo motor	Y
12/15/2023	Test mounting plates	Y
12/22/2023	Test housing, motor, and camera	Y
1/22/2024	Prototype housing, and mounting	Y
1/5/2024	Run working software	Y
1/12/2024	Camera working with software	Y
1/19/2024	Full initial test run	Y
1/26/2024	RasPi Image Testing	Y
2/2/2024	Software Image Testing	Y
2/9/2024	Run Star Tracker software tests - completion time	Y
2/16/2024	Run Star Tracker software tests - completion time	Y
2/23/2024	STR Presentation	Y

Date	Event	Completed? N/Y or�In Progress (IP)
3/1/2024	Determine materials for view window and housing�Order materials for view window�Determine build steps for housing�Integration: Pi Camera and LOST Software	IP
3/1/2024	Connect startracker to pi board�Connect pi board to power�Integration: Servo Motor Control and LOST Software
3/8/2024	Test the motor hat and the zero to go rasberry pie�Test all Star Tracker components�Lens Filter Testing
3/15/2024	Subsystem structrual integration Complete Lens Filter Testing
3/20/2024	Order Window for Pi Camera
3/22/2024	ISTR Review
3/29/2024	Test Window for Pi Camera

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Mechanical Subsystem Timeline

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Date	Event	Completed? N/Y or�In Progress (IP)
3/1/2024	Machining plan�Cut aluminum to housing dimensions with an extra inch on all sides for riveting�Bend the extra inch of aluminum to overlay so we can rivet�Drill holes for rivets�Rivet overlaid aluminum together�Build star tracker housing	IP
3/8/2024	Subsystem structural integration
3/15/2024	Subsystem structural integration Stress tests (heat, drop test, etc.)
3/22/2024	ISTR Review Subsystem structural integration testing
3/29/2024	Integration testing

Date	Event	Completed? N/Y or�In Progress (IP)
12/8/2023	Have materials ordered	Y
12/15/2023	Make structural box	N
12/22/2023	Test thermal components	N
1/12/2024	Have prototype finished	N
1/19/2024	Structure box durability stress testing	N
1/26/2024	Implemented changes needed from stress test	N
2/2/2024	Assess and adjust subystems needs	N
2/9/2024	All subsystems integrated to structure for testing	N
2/16/2024	Parts ordered	Y
2/23/2024	STR / Riveting	IP

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Budget

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Classification	Schools
Actual	ACC	RRCC	Combined
Travel	$5,000.00	$5,000.00	$10,000.00
Materials	$1,508.54	$480.00	$1,988.54
Flight Fee/ Shipping	$7,500.00	$7,500.00	$15,000.00
Total Spent	$14,008.54	$12,980.00	$26,988.54
Total Reamining	$491.46	$1520.00	$3531.46

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Student/Mentor Plan

External mentors

Advisors from other COSGC teams help with problem-solving
Continued variety of guidance from past RRCC and ACC Space Grant Teams
Additional Acquaintances

William Mason of Cedar Rapids, IA

Retired engineer who built lenses for particles accelerators
Expertise with ceramic and glass artistry
Assisted our search for payload insulation

Clint Mitchel

Aerospace electrical engineer
Participated in Orion mission, asteroid mining, NASA missions
Assisted in power source and circuitry

Weekly meetings with advisors (Jennifer Jones, Lynne Albert, and Annie Strange)

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Partnerships

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Estimated Team Size

Total of 8 team members
Funding for 2 team members

One from each school, for June testing and August launch
Different team members from each school will be at each event

Other members that may attend August launch will conduct fundraising or pay out of pocket

Estimated 4 – 6 additional team members

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Section 8: Next Steps & Conclusions�Leighanne Bennett and Nicholas Betz

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Next Steps

Structural assembly and subsystem housing assembly
Subsystem testing include payload stress tests
Integrating all subsystems together

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Conclusion

Regolith

The ability to sinter lunar regolith simulant in a microgravity environment will pose valuable data for humanity. Understanding how this in-situ resource will be affected in these environments during the sintering process gives us vital information for future missions such as the Artemis mission.

Star Tracker

Future missions will also require efficient and intelligent navigation. Creating a cost efficient star tracker for cheaper use on future spacecraft will be vital for navigating our solar system and eventually our galaxy.

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Requests For Wallops/Questions

Recharge battery before flight
Ability to test power systems prior to integration on rocket

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Questions?

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