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PUJLLAYBUENOS AIRES

12 - 11 - 2019

2nd IAA Latin American Symposium on Small Satellites

1

THE FIRST NANOSATELLITE ENGINEERING MODEL DEVELOPED IN UNSAM

Introduction

The Team

Burroni, Tomás IgnacioConde, Nicolás ValentínEscobar, Matías IgnacioLópez, Luis SantiagoMucanna, CamilaPenida, Matías

Tutor:

Rosito, Claus

Burroni

López Mucanna

Conde

Penida

Escobar

Astronautical Engineering Students

(ECyT,UNSAM)

209/05/2019Cube Design 2019 - 1st Review Cube Design 2019 - 1st Review 09/05/2019Cube Design 2019 - INPE 24/07/2019

Challenge

2nd Cube Design

Instituto Nacional de Pesquisas Espaciais

INPE

July 24th to 27th, 2019

-Engineering students

-3 Categories: cubesat, cansat, mockup.

São José Dos Campos, São Paulo, Brasil

INGENIERIAESPACIAL

Cube Design 2019 - UNSAM

Competition

Competition TestsEnvironmental Tests

Dimension

100mm x 100mmRev 13

Thermal Cycle-10°C to 50°C

2 cycles1,5°C p/min

Vibration14.1 Grms

2 min e/axisFalcon 9

Basic Level TestsCommunicationTelecommands

10 m

Intermediate Level Tests

MechanismAntenna DeployTelecommand100mm (Min)

Attitude Det.

Azimuth onlyLight Source

Battery ChargeLight source (Sun)

Send dataEvery 1 min

Advance Level Tests

Att. Stable

Initial Speed60 rpm

Att. Ctrl 2Set 2 different

azimuthsTelecommand

Att. Ctrl 1Set Azimuth towards light

source

Mission

Satellite Image

Take picture of an imageRecognize deforested areaIdentify fire focuses


Proposal

Tests we aim for

1. Environmental Tests1.1. Dimension1.2. Thermal Cycle1.3. Vibration

2. Basic Level Tests2.1. Communication

3. Intermediate Level Tests3.1. Mechanisms3.2. Battery Charge3.3. Attitude Determination

4. Advance Level Tests4.1. Attitude Stabilization4.2. Attitude Control 14.3. Attitude Control 2

5. Mission Tests5.1. Satellite Image

Prioridad Prueba

Primaria

1.1

1.2

1.3

Secundaria

2.1

3.1

3.2

3.3

Terciaria

4.1

4.2.

4.3

5.1


Project Management

WBS

1. Project Management1.1. Documentation Management1.2. Schedule Management1.3. Resource Management1.4. Challenge Management1.5. Communication and Coordination

Management1.6. WBS

1.6.1. WBS Block Diagram1.6.2. WBS Description Document


Documentation plan

Project Proposal

Block Diagram

WBS / Diagram / Schedule

Requirements Specification

Mass and Power Budget

Structure Analysis and Design

Command and Data Handling Analysis and Design

Power Analysis and Design

Thermal Control Analysis and Design

Communication Analysis and Design

Attitude Determination and Control Analysis and Design

V&V Plan

Interface Document

Inventory

Purchases Register

Operation in competition Checklist

PDR Presentation

Final Presentation

Documents Register


Resources

Facilitated by the Colomb Institute (CONAE-UNSAM), ECyT UNSAM, CNEA, Testa Brava and Ernesto Mayer S.A.

Working Facilities

Materials

809/05/2019

Collaborators

Technical Advice:

Hernan Socolovsky Silvio Scechet Pablo MeilánLeonel Garategaray Nahuel Castello Roberto AlonsoRoberto Yasielsky Carlos Canal Edgardo RoggeroAníbal Feder Pablo Servidia

Tutor: Claus Rosito

Cube Design 2019 - 1st Review Cube Design 2019 - 1st Review 09/05/2019Cube Design 2019 - INPE 24/07/2019

System WBS

WBS: Satellite and Ground Station


System Engineering

Block Diagram


Satellite

11

Satellite

❏ Subsystems❏ Structure❏ Command and Data Handling❏ Power❏ Attitude Determination and Control❏ Communication❏ Thermal Control


Satellite | Configuration

External Configuration

Payload on face +X; Antenna on face +Z; Panels on XY- It can be achieved if the payload fits within an area of 10mm high and less than 60mm

wide.

- Antenna internal. The deployment of the antenna becomes more complex.

- The +Z and -Z sides are free.

- More efficient in the occupied surface.13


Structure

14

Satellite | Structure

Primary Structure Initial Weight: 242 g ; Material: Al 6061



Secondary Structure

DIN 975 (M3) - Stainless SteelIt consists of 4 threaded steel rods that cross in the Z direction to the primary structure. These will be anchored with two nuts, one side and the other side of the Z face.

And the PCBs separated by Stand Off of 8, 10 and 15mm.



Analysis: Body Load on X

1709/05/2019Cube Design 2019 - 1st Review

Max Stress Allowed MoS

12.275 MPa 175 MPa 850%


27.06 MPa 270 MPa 565%


20.18 MPa 270 MPa 791%


-94.68 MPa 215 MPa 51.39%

Cube Design 2019 - 1st Review 09/05/2019Cube Design 2019 - INPE 24/07/2019

Boundary Conditions


Analysis: EigenValues & Frequency Response

1809/05/2019Cube Design 2019 - 1st Review

F [Hz] Modal Mass

391 0.032

886 0.293

1010 0.314

1134 0.777

2000 0.785


INGENIERIAESPACIAL



Command and Data Handling

20

Commands - Data

INGENIERIAESPACIAL


INGENIERIAESPACIAL


PCB

Satellite | Command and Data Handling


ESP32Specifications

Pin Diagram



Software

Three software packages: onBoardESP32, groundESP32 and groundPC.

-> User graphic interface.

-> Decrypt data and RF communication.

-> Different operation modes.

■ Stand-by Mode.■ Full Mode.

groundPC

groundESP32

onBoardESP32


Power

25

System Engineering

Power Budget

Description Consumption by hour [Ah] Quantity Total [Ah] Hours [h]

Power Supply 0,0093 1,0000 0,0093

SOC sensors 0,0010 2,0000 0,0093 4,6667Control Térmico 0,3159 1,0000 0,3159Temperature sensors 0,0001 7,0000 0,0033 4,6667Heater 0,5000 1,0000 0,3127 0,6253Control and data handling 0,2333 1,0000 0,2333ESP32 0,0500 1,0000 0,2333 4,6667Communication 0,0355 1,0000 0,0355ESP32 Receiver (ON) 0,2500 1,0000 0,0194 0,0777ESP32 Receiver (OFF) 0,0035 1,0000 0,0161 4,5889Deployment System 0,0000 1,0000 0,0000 0,9333Attitude Determination 0,0000 1,0000 0,0000Light Sensor 0,0000 4,0000 0,0000 4,6667TOTAL 0,5941


Satellite | Power

Design


Satellite | Power


Satellite | Power

V&V 1. Battery characterization2. Solar Cells acceptance3. Solder verification4. Voltage measurement

characterization5. Circuit verification


Thermal Control

30

Satellite | Thermal Control

31Cube Design 2019 - 1st Review 09/05/2019

AFT Requirements HARDWARE

Allowable Flight Temperature

Temperature Requirements [°C ]

Operational Non Operational

min [°C] máx [°C] min [°C] máx [°C]

Control and Data Handling Subsystem

ESP32 -40 125 -40 150

Power Subsystem

Solar Panels -90 90 -90 90

Battery 0 60 -10 150

BMS (Battery Management System) -55 125 -55 150

Communication Subsystem

RF Tx-Rx -40 125 -40 150

Antena -100 200 -100 200

Sistema de Despliegue -40 100 -40 100


Active Thermal ControlHeater

INGENIERIAESPACIAL

Prototype made in Microlab CAD Design

Schematic

Final Product



INGENIERIAESPACIAL

Passive Thermal Control Thermal mass



Tests

INGENIERIAESPACIAL

NOTA: Se aplicó en la gráfica un algoritmo de suavizamiento natural por spline



Attitude Determination and Control

35

Satellite | Attitude Determination and Control

Schematic

36Cube Design 2019 - 1st Review 09/05/2019Cube Design 2019 - INPE 24/07/2019


Algorithm

3709/05/201924/07/2019

az

Unknown values: el and az


Design



1. Solar sensors acceptance

2. Solder verification

3. Current measurement characterisation

4. Attitude determination

V&V


Communication

40

Satellite | Communication

Antenna

Frequency

Two 172,29 mm long strips for UHF frequency range

Dimensions

Length: 172,29 mmWidth: 12 mmThickness: 0,3 mm

Material

[Flexibility and shape memory]

Position

+Z facePointing in opposite +Y and -Y directionsLineal emission patterns



Antenna Deployment Mechanism

Position 1: Antenna foldedAntenna strips go around the cubesat form +Z to -Z on opposite sides and are tied up with a nylon string that goes through the nichrome spring.

Transition: DeploymentA command is sent from the ground station and received by the cubesat. This allows the burning of the -Z face resistor and therefore the burning of the nylon string for release of the antenna.

Position 2: Antenna deployedThe antenna strips are standing straight on top of +Z face and pointing towards opposite Y directions.

-Z face

Burning resistor

20 mm nichrome springed wire

Stages

Mechanism

Activates by commandAllows to be folded again



Antenna Deployment and Configuration Analysis



Circuits

44

Main Deployment



V&V1. Antenna deployment

2. Antenna folding

3. ESP32 reception through ESP32 antenna

4. ESP32 transmission through ESP32 antenna

5. ESP32 reception through external antenna

6. ESP32 transmission through external antenna

7. Antenna radiation pattern characterization (Anechoic chamber)


PDR

INGENIERIAESPACIAL


PDR at CONAE


Development and fabrication

INGENIERIAESPACIAL


The team

Fabrication

INGENIERIAESPACIAL


Final result

INGENIERIAESPACIAL


Performance at the competition

INGENIERIAESPACIAL


Test - Fit Check

INGENIERIAESPACIAL


Dimension

100mm x 100mmRev 13

Test - Thermal Cycle

INGENIERIAESPACIAL


Thermal Cycle-10°C to 50°C

2 cycles1,5°C p/min

Tests - Attitude determinationAttitude Det.

Azimuth onlyLight Source

Test - Shaker

INGENIERIAESPACIAL


Vibration14.1 Grms

2 min e/axisFalcon 9

Tests - Battery charge

Battery ChargeLight source (Sun)

Send dataEvery 1 min

Results

INGENIERIAESPACIAL


Results

3rd place at CubeDesign


Future plans

INGENIERIAESPACIAL


Future plans

1. Circuit design improvements2. Structure optimization3. Payload development and integration4. Team expansion

a. More studentsb. Different majorsc. Different Universities?

5. Radiation testing (goes beyond CubeDesign)


Thank you! Questions?

59Cube Design 2019 - INPE 24/07/2019