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)
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