A Student Satellite Initiative

Indian Institute of Technology

Project Presentation 2011

Central Lecture Theatre

IIT Madras

31st Aug 2011

sat

1

Student initiative

Design & build a Nano-satellite

6 faculty coordinators from 5 different departments

25 students

Active for the past 1.5 years

₹ 65 lakh commitment from the institute

Starting work on the development model

Introduction

2

Part 1: Mission The goals and objectives

Part 2: Phenomenon The phenomenon we propose to study

Part 4: Project Status & Plan The status of the project and timeline & how you can contribute.

3

Part 3: Satellite System The subsystems and work involved

Mission The goals and objectives

4

Mission Objectives

1. Make and test the payload instrument (particle detector) on ground 1. Make and test the payload instrument (particle detector) on ground

2. Build and test a satellite 2. Build and test a satellite

3. Launch the satellite and confirm operations 3. Launch the satellite and confirm operations

4. Characterize the link between energetic particle precipitation and seismic activity 4. Characterize the link between energetic particle precipitation and seismic activity

Build a small satellite and use it for a socially relevant scientific experiment.

Build a small satellite and use it for a socially relevant scientific experiment. 5

A Scientific Quest

Observations made by

• SAMPEX (NASA, USA)

• DEMETER (CNES, France)

Observations made by

• SAMPEX (NASA, USA)

• DEMETER (CNES, France)

suggests suggests

Correlation between Earthquakes and Energetic

Particle Precipitation in upper ionosphere

Correlation between Earthquakes and Energetic

Particle Precipitation in upper ionosphere

What researchers have found: What researchers have found:

• There is a correlation

• Earthquakes M>5.0

• High energy particle bursts

• 2-3 hours before the earthquakes

What we want to do: What we want to do:

• A scientific mission

• Verify correlation between earthquakes & particle bursts w.r.t.

• Magnitude

• Time

• Location (V. Sgrigna, 2005)

6

Mission concept • One satellite

• One ground-station

• Store data on satellite • Downlink to the ground station

7

Application

As a component in global earthquake warning systems in the future

Advantages of this particular phenomenon:

• Global scale • does not have to be above the epicenter

• Short term precursor

• happens a few hours before the earthquake

Only satellites can be used to study this phenomenon.

8

Phenomenon The phenomenon we propose

to study

9

1. Pressure build up

2. ULF/ELF waves generated

3. Propagation of waves

4. Interaction with Inner-

Van Allen belt

5. Precipitation of charged particles

1000 km Inner- Van Allen

belt lower boundary

500 km Ionosphere

References: Sgrigna, V. (2005). Alexandrin, S. (2009).

1. Pressure build up 1. Pressure build up 2. ULF/ELF

waves generation

2. ULF/ELF waves

generation

3. Propagation of waves

3. Propagation of waves

4. Interaction with Inner Van

Allen belt

4. Interaction with Inner Van

Allen belt

5. Precipitation of charged particles

5. Precipitation of charged particles

Overview

10

http://www.tethers.com/WebImages/RadiationTrapping.jpg, 08 Aug 2011, 19:00 Hrs http://www.spacerad.com/modules/m226.html , 08 Aug 2011, 19:00 Hrs

3 kinds of particle motion Gyration Bounce Longitudinal Drift

Concept of Mirror Points

Concept of Pitch angle

Particle velocity vector

Trapped Particle Motion

𝑣⊥

𝑣∥

11

Ionospheric capture region (300 km - 500 km)

Inner Van- Allen Belt Boundary (1000 km)

12

Pressure build-up

Capture region

300km - 500km

1000 km

13

Lowering of mirror points

300km - 500km

1000 km

30 14

Satellite System The requirements and configuration of

the satellite

15

Payload Schematic

HEPD is designed to measure protons and electrons of high (often relativistic) energies and directional particle flux.

HEPD is designed to measure protons and electrons of high (often relativistic) energies and directional particle flux.

Payload Specifications

Dimensions 34 x 34 x 90 mm3

Mass < 1.5 kg

Average power

consumption < 1.5 W

Energy range Protons : 10 to 100 MeV

Electrons : 1 to 15 MeV

High Energy Particle Detector (HEPD) 43

16

Attitude Determination and Control System

17

Tasks Sensor: Testing Actuator: Fabrication and Testing Control System Design Software Development:

Sensor Processing Algorithms (Extended Kalman Filter…) Control Laws (PID…) Fault Detection algorithms (Compensation for sensor failure )

OILS and HILS

Sensors: Actuators:

Communication Subsystem

Tasks

RF circuit design

Receiver

High Speed (HS) Transmitter

Beacon Transmitter

Implementation of Data Link Layer Protocol

Error Correction Coding (Convolutional)

Antenna Design, fabrication and Testing

18

Ground Station Receiver and FSK Demodulator of iitmsat pre-engineering model

19

Ground station overview Tasks

Ground Station Architecture Design

Satellite Tracking Mechanism

Ground station hardware procurement

Real Time Software for Data handling

Ground Station

Ref. Swiss cube - EPFL

Electrical Power System

EPS architecture Overview

20

Tasks 1. Solar Cell: Modeling and Hardware

simulation 2. Battery: Selection, modeling and testing 3. Power Transfer: Peak power Tracker/ Direct

Energy Transfer 4. Circuit Design: Power Electronics 5. Electronics Reliability Analysis and

Redundancy design

Ref. Swiss cube - EPFL

Structure: Modified GNB Architecture

Tasks:

Vibration Analysis: FEA

Design for X

Wire Cabling

Materials and Fasteners selection

Fabrication

Environmental Testing

(PSLV Launch Environment)

References: http://events.eoportal.org

GNB internal architecture

iitmsat proposed structure

21

Thermal Control System

Tasks:

Surface thermal properties Tests Contact Resistance Measurements Finite Element Analysis Thermal Sensors calibration and mounting Bake out Testing Thermal

22

Preliminary Thermal simulation in ANYSYS

Command and Data Management System

23

Command and Data Management System

Tasks: 1. Data Compression and

Management 2. Clock Synchronization 3. Networking of microcontrollers 4. Satellite Boot Sequence 5. Command Handling 6. RTOS (Real Time Operating

System) implementation on ARM7 and MSP 430 microcontrollers

IITMSAT CDMS board made as a part of pre-engineering model

System Engineering

Tasks:

Mission Operations Level of Autonomy System Design Budgets Model Philosophy Verification Plan

System Engineering

ADCS

CDMS

Power

COM

Ground Station

Structure

Thermal

Payload

Satellite Configuration

Specifications Value

Mass 10 kg (10% margin)

Size 20 x 20 x 24 cm

Orbit average power generation

5.77 W (worst case)

Power consumption 5.70 W (17% margin)

Data rate (Downlink) 115 kilobits/sec

Telecommunication frequency

HS Downlink: 2.4 GHz

Beacon: 435 MHz

Uplink: 145 MHz

Launch adapter IBL 230

Attitude stabilization type

3- axes stabilized

26

Proposed configuration of iitmsat

Project Status & Timeline

The status of the project and timeline

27

Timeline Overview and Model Philosophy

Conceptual Design

Development Model

Integrated Model;

Structural model

Qualification Model; Flight

model

Launch

2011 2012 2013

Reviews: 1. System Requirements Review 2. Preliminary Design Review 3. Critical Design Review 4. Qualification Review

28

Cost Budget: 3 Crore INR

Team

System Engineering

ADCS

CDMS

EPS

COM

Ground Station

Structure

Thermal

Payload Team Strength: 25

Batch No.

B. Tech II Yr 12

B. Tech III Yr 5

B. Tech IV Yr 5

Dual V Yr 2

MS 1

Total 25

29

Visit to TIFR, PRL, IIG

• 4 Projects

• Payload Instrumentation

Pre-Engineering Model

• Attitude Control Test Set-up

• Communication Receiver

• Power Distribution Board

• On-board computing system

Work in ISAC • Particle Detector

Design

• Hands-on experience with detectors

• Working on data from RADOM in Chandrayaan -1

Proposal to SSG, ISRO

• Zeroth Level Design

• Zeroth Level requirement definition

Conceptual Design

• Refining conceptual design

• Refining of requirements

• Refining project plan and timeline

Progress

Dec ‘09 Jan ‘10 May ‘10 Oct‘10 Feb‘11

Modification in the casing of CZT in TIFR

Pre-amplifier output (Cyan)

and Final Post-amplifier output

(Magenta) of the HEX front-

end electronics.

30

31

Proposal to IITM

• Meeting with the Director

• 6 Faculty Coordinators

Funding for Phase A

• ₹ 65 lakh

Work in IIST, Trivandrum

• Calibration of NaI Scintillator Detector

• Validation of our simulations

Thermal Systems Work in ISAC

• Preliminary design of the thermal subsystem

• Simulations

Presentation to ISAC Director

• Project was deemed technically feasible

• Green Signal

Apr ‘11 May ‘11 June ‘11 July ‘11 Aug ‘11

Recent Progress

Project packages Technical projects

With detailed objectives, requirements, timeline and deliverables

≈29 Project Packages from different subsystems (about 60 new team members)

Put up in our website http://iitmsat.iitm.ac.in/

All students can apply

(last date 10th September 2011)

32

Project Packages How can you contribute?

Example project package 2 to 3 working members

Short term commitment (3-6 months)

Periodic internal and faculty reviews

Credit

Can continue in the satellite project after completion

33

Our experiences in this project.

34