NIUSAT Mission Objective

NIUSAT is a Nano satellite designed and developed by Noorul Islam Centre for Higher Education under Noorul Islam University with a Miniature Wide Field Sensor (MWiFS) for agriculture and disaster management support applications.

The imagery from the NIUSAT is used for identifying potential agricultural diseases of the crops around Kanya Kumari District and providing timely assistance to the Disaster Management Support (DMS) programme to address disasters due to flood, cyclone, drought, forest fire, landslide and Earthquake.

Nano satellite project is a Noorul Islam University program, involving students and staff of the university, making use of the state-of-the art proven technologies and modules.

NOORUL ISLAM CENTRE FOR HIGHER EDUCATION NIUSAT

Power

NIUSAT Nano satellite Features

WIDEFIELD SENSOR (WiFS)

Resolution : 50 to 80 m

Swath : 100 to 160 km

Quantisation : 8 bit

Input Data Rate: 14 Mbps

Data Compression : JPEG 2000

Output Data Rate : 1 Mbps

NOORUL ISLAM CENTRE FOR HIGHER EDUCATION NIUSAT

Overall size:270 x 270 x 270 cm3

Mass: 12kg

Structure mass: 2.8 kg

Solar Panel Deployment Mechanism

Antenna Deployment Mechanism

Passive and Active Thermal Control System

Polar Sun Synchronous Orbit

Orbit altitude : 560 – 880 km

Orbital inclination : 97o-99o

Orbital Period : 96-100 min

Repetivity/ Revisit : Everyday

Visibility : 4 orbits per day

High performance dual core 32 bit Power Architecture

2 MB Code flash memory with ECC

32 GB storage flash for payload data storage

Supports I2C, CAN and UART ports

Supports software tunes and WDT

Housekeeping TM data transmitter in VHF (145 MHz) band

Tele-metry data transmission in UHF (435 MHz) band

Payload data transmission in S- band (2240MHz).

4 element monopole Antenna for VHF/HF data

transmission & reception

High gain patch antenna for S-band transmitter

Total Power Generation : ~40 W

Battery Storage Capacity (2 nos.) : 5AH

Multi Junction Solar Cells based Solar Array

Stowed during launch and deployed in Orbit

MPPT based Battery Charge Regulator

Satellite checkout system,

Mission control centre,

The UHF/VHF antenna for TM/TC

Ground station is capable of

operating with other amateur radio

satellites

S-band data reception using 3.7 m

parabolic antenna

3 axis stabilization using Sun sensor, Magnetometer, MEMS Gyroscopes as sensors and Reaction Wheels, Magnetic Torquers as actuators

Provision kept for star tracker for improved pointing accuracy

Provision is kept for PPT for Orbit Correction

Structure/Thermal/Mechanism

Payload

Mission

Communication System

On Board Computer

Ground Station

AOCS

NIUSAT MISSION

Payload Coverage Details No. of Special Bands : B2, B3, B4

Miniature WiFS

Resolution : 50m-80m

Swath : 100-180 km

Area Covered : 225000 sq. km

Orbital Details

Orbit Type : Polar Sun Synchronous

Orbit Altitude : 560 km to 880 km

Orbital Inclination : 97o-99o

Orbital Period : 96-100 min

Repeatavity/Revisit : Everyday

No. of orbits per day : 14/15

Visibility : 4 orbits/day (2 day pass and 2 night pass) : from NIU Ground Station (5-10 min/pass)

NOORUL ISLAM CENTRE FOR HIGHER EDUCATION NIUSAT

NIUSAT Ground Trace

NIUSAT Configuration

=

Front View Internal View

Back View Stowed View Exploded View 1 Bottom Deck

2 OBC and TMT Stacks

3 Reaction Wheel Support

4 Reaction Wheel

5 Gyroscope

6 Sun sensor

7 +ve axis yaw side panel (EP01)

8 S band transmitter, UHF receiver, VHF transmitter

9 Solar panel

10 -ve roll axis side panel (EP02)

11 PPT, BMDE, Battery –II

12 -ive yaw axis sidepanel (EP03)

13 Satellite positioning system

14 +ve roll axis side panel (EP04)

15 PMDE, Battery –I

16 Angle Plate

17 Star sensor

18 Star sensor support

19 Top panel

20 Magnetometer

21 Payload

NOORUL ISLAM CENTRE FOR HIGHER EDUCATION NIUSAT

Electrical Power System (EPS)

The EPS consists of Solar panel, Battery and Power Management and Distribution Electronics (PMDE). The solar panels are designed to generate power for the satellite. The PMDE regulate and control the distribution of power to the other systems of the satellite. Advanced multi junction solar cells are connected in series, to boost voltage, and connected in parallel, to provide the required current. Li-ion battery is used to power the satellite during eclipse.

Solar Panel

4 Numbers of 240x240 mm solar panels made of glass fibre substrate / printed circuit board.

Power generated per panel is 10 watts Total power generation is 40 W for 100% illumination. 5 cells in series in a sub-string and 10 cells per string Solar cell efficiently : 27-28 % Solar panel voltage : 11.5-13V Maximum current per panel : 0.8A Mass of the solar panels (4 numbers ) : 0.8 Kg

Battery

No. of Batteries : 2 Nos. of Li-ion Battery

Battery capacity (each) : 5AH

Depth of discharge : 10-20%

No of charge discharge cycle : 5110 Per year

Battery Voltage : 6-8.2 V

Mass of the Battery (each) : 0.25 Kg

Power Management and Distribution

MPPT based Battery Charge Discharge Regulator

24 nos. of MOSFET switches for switching Row bus (11-13V) and regulated voltages (5V and 3.3 V)

Current monitoring and over current protection

NOORUL ISLAM CENTRE FOR HIGHER EDUCATION NIUSAT

EPS Block Diagram

Payload Features

Miniature WiFS (MWiFS)

Spectral bands Resolution Swath

B2 (Green) 520- 600 nm 50m 100km

B3 (Red) 620 -680 nm 50m 100km

B4 (NIR) 770 -860 nm 50m 100km

Payload Parameters

Aperture 75mm

Focal length 600mm

Field of View 1175 deg

Data rate before compression

14 Mbps

Date rate after compression & storage

1 Mbps

Data Storage 32 GB

Size 100 x 100 x 250 mm

Mass 1.5 Kg

Power Consumption 8 Watts

Data interface with OBC I2C/CAN Bus

Power Supply 5 V/3.3 V

NOORUL ISLAM CENTRE FOR HIGHER EDUCATION NIUSAT

MwiFS: Miniature Wide Field Sensor

Video processing and data handling system

RF Communication System RF Communication system of NIUSAT comprises of the following modules

Housekeeping data transmitter in VHF (145 MHz) band Tele-command data reception in UHF (435 MHz) band Payload data transmission in S- band (2240MHz).

4 element monopole Antenna for VHF/UHF data transmission & reception High gain patch antenna for S-band transmitter

UHF/VHF Transceiver

Carrier Frequency 435/145 MHz

TM transmitter O/P power 25 dbm (0.5W)

Modulation for HK TM BPSK/AX-25

Data rate for HK Transmitter

1 Kbps

Half power beam width (deg)

60

Power consumption <5W

Antenna monopole

S-band Transmitter

Carrier Frequency 2240 MHz

Transmitter O/P power 25 dbm (0.5W)

Modulation BPSK/PM

Data rate 1 Mbps

Half power beam width (deg)

60

Power consumption <5W

Antenna patch

NOORUL ISLAM CENTRE FOR HIGHER EDUCATION NIUSAT

Telemetry Functional Block Diagram

Telemetry & Tele-command System Telemetry System Tele-command System

Telemetry system of NIUSAT acquires health parameters of various sub-systems of the spacecraft and puts them in a proper format and transmits to the ground after PCM-FM/PM modulation.

Tele-command system receives the tele-command data and clock from the TC receiver. TC decodes the data and provides various command pulses or data for execution of the commands to operate various sub-systems as per the mission operation requirements

Specification TC Data rate 100 bps

Number of ON/OFF commands

32

Number of Data commands

8

Number of high level pulse commands

8

Number of time-tag commands

8

Specification Telemetry data

rate 1 Kbps

Sub-carrier frequency

32 Khz

Frame Length 128 channels

Frame Rate 64 seconds

NOORUL ISLAM CENTRE FOR HIGHER EDUCATION NIUSAT

Tele-command Functional Block Diagram

To Subsystem

Attitude and Orbit Control System

The AOCS stabilizes the NIUSAT and orients it in desired directions during the mission despite the external disturbance torques acting on it

De-tumbling mode : de-tumble satellite after launcher separation

Sun pointing mode : point solar array towards the Sun

3 axis stabilisation mode : point payload (camera, antenna, and scientific instrument etc.) to desired direction

Perform spacecraft attitude maneuver for payloads operation

Attitude determination using sun sensors, magnetometers and MEMS Gyroscopes

Miniature Reaction wheels & magnetic torquers used as actuators The Control algorithms resides in OBC and is executed in every minor cycle

NOORUL ISLAM CENTRE FOR HIGHER EDUCATION NIUSAT

Sun Sensor

Magnetometer

Gyros

Control

Algorithm

Star Sensor

(Optional)

Magneto-

torquer

Reaction

Wheel

PPT

(Optional)

OBC On-Board Computer

AOCS Block Diagram Overall AOCS Configuration

Attitude & Orbit Control Components

Magnetometer Magnetometer is a measuring instrument used for measuring the

Earth's magnetic fields

Gyroscope A gyroscope is a device for measuring the body rates, based on

the principles of conservation of angular momentum

Magnetometer Value Unit

Dynamic Range

±3.5 gauss

Scale factor 0.5 mgauss

Initial Bias Error

±4 %FS

Output Noise 1.25 Mgauss rms

Dimensions 23 x 23 x 23 mm

Mass 16 g

Gyroscope Value Unit

Dynamic Range ±300, ±150, ±75 O/s

Scale factor 0.05, 0.0025, 0.0125

O/s

Initial Bias Error

±3 o/hr

Bias Stability 0.007 O/s

Dimensions 23x23x23 mm

Mass 16 g

Power 0.35 W

Reaction Wheel Reaction wheels are devices which aim a spacecraft in different

directions.

Sun Sensor The sun sensor determines the spacecraft body angles with

respect to the sun.

Reaction Wheel

Value Unit

Momentum Storage

10 mNms

Max Torque 3 mNm

Dimensions 5x5x3 cm

Mass 200 g Power (normal) 0.7 W

Sun Sensor Value Unit

Resolution <0.5 O

Accuracy <1.5 O

Dimensions 3x3x1 cm

Mass <6 g

Power <0.175 W

NOORUL ISLAM CENTRE FOR HIGHER EDUCATION NIUSAT

Ground Station

TMC

AOCS

Payload

Thermal

Power

Mission

MISSION CONTROL CENTRE

Flat Panel Displays Relay

UHF/VHF S-Band

NOORUL ISLAM CENTRE FOR HIGHER EDUCATION NIUSAT

NIUSAT Ground Station located in NIU campus is an integrated ground station topology which combines the requirement of o Satellite checkout system, o Mission control centre, o Ground Station System.

The UHF/VHF antenna and the ground station are capable of operating with other amateur radio satellites.

Assembly Integration & Testing

The assembly of the NIUSAT from structural component units to full flight assembly is done through multiple phases.

The first assembly activity involves a simple fit-check where all components are assembled to their appropriate location according to the established assembly order.

The second full test assembly is done on the flight structure to establish wire lengths for the panel harnesses.

Final assembled satellite will undergo Full functional testing, Thermo Vacuum testing and Vibration testing.

First and second test assemblies

NOORUL ISLAM CENTRE FOR HIGHER EDUCATION NIUSAT

Final Assembly

Flat Bed Testing

Disaster Management Support

Ground Station (Payload Data Reception) NIUSAT

(WiFS payload, 60M resolution 100-160km swath, 3 spectral bands

(Green, Red, NIR))

Disaster

Data Processing (Feature Extraction, Change Selection,

Data Analysis)

Metication & Rescue

Disaster Management Centre

NIUSAT MISSION

CENTRE

NOORUL ISLAM CENTRE FOR HIGHER EDUCATION NIUSAT

Agriculture Application

NOORUL ISLAM CENTRE FOR HIGHER EDUCATION NIUSAT

Farm (Water stress/Drought Better Yield

NIUSAT (WiFS payload, 60M resolution

100-160km swath, 3 spectral bands (Green, Red, NIR))

Ground Station (Payload Data Reception)

Data Processing (Feature Extraction, Change Selection,

Data Analysis)

NIUSAT MISSION

CENTRE

Processed information (Agricultural disease, plant growth, yield prediction, crop assessment)