Monitoring the greenhouse gases on theterrains of Continental Collision Plates andw a r n i n g s y s t e m o f g l a c i a l l a ke o u t b u r s tfloods over the Hindu Kush Himalayan range

Team Members

Bhawana Pokharel
IOE

Bibek Yonzan
IOE

Simonkrith Lamichhane
IOE

OutlineINTRODUCTIONINTRODUCTION• Climate change• Increase in global mean
temperature by 0.18°𝐶 perdecade• Climate change is sensitive toaltitude.

• Mountains are particularly sensitive toclimate change.
• Disasters like outburst floods andlandslides can be attributed to climatechange.

INTRODUCTION

Fig 1: Flash-flood at the site of the Namche Small Hydel Fig 2: Massive mudflows in the mountains of Nelson
Plant, on August 4, 1985.
County due to Hurricane Camille, 1969.

Fig 3: Imja Glacial Lake in 2007 (a) andin 2014 (b).

Fig 4: Avalanche in Galtur, Austria,1999.

INTRODUCTION
Greenhouse gases

Glaciers• Predominant indicators ofatmospheric climate change.
• Tipping elements like loss of major
ice sheets, disruption of tropicalmonsoons and ecosystem shifts canbe directly or indirectly correlated.

• Another key indicator of climatechange in continental collision
terrain.
• Disastrous events like outburst
floods, landslides and avalanches
can be attributed to climate change
in the region.

At present, there is a data gap relating the two phenomena, due to a lack ofcomprehensive and excessive data.

MISSIONMISSION
Remote sensing over theterrains formed bycontinental
plates collision

Reduce potential damage
from glacial lake outburst
floods

HKH region as an early
indicator of climate change

Possible relationbetween greenhouse gases
and geographical terrain

MISSION
Primary Objective
To monitor greenhouse gas levels
in terrains formed by continental
plates collision.

Secondary Objective
To monitor and analyze glaciallakes in the areas of interest.

CONCEPT OF
OPERATIONSCONCEPT OF OPERATIONSSPACE SEGMENT
Constellation of 3 satellites in a hybrid
SSO/LEO• Satellite in LEO in 35° inclination will
monitor data over the HKH region.
• Satellite in LEO 65° in inclination will
monitor other continental collisionplates terrain, as well.
• Satellite in dawn dusk SSO will capturedata for auto correlation.
Fig 5: Constellation Orbit

LAUNCH SEGMENT• The satellites will be launched from Polar
Satellite Launch Vehicle (PSLV) and deployedfrom the Dhruva Space Orbit Deployer.
• After deployment, the satellite will start the
detumbling mode, while sending beacons forcommunication.
• The satellites can be tracked using Two-LineElement (TLE) set.

Fig 6: PSLV rocket

GROUND SEGMENT• Ground station• The primary ground station selected for the mission isNational Remote Sensing Centre (NRSC), India.
• The ground station at Kyutech University whichsupports communication in S band, will be used todownlink the data.
• The ground stations that are part of the BIRDS groundstation network will be used to downlink data, ifupgraded to X/S band.

Fig 7: NRSC, India

GROUND SEGMENT• Post-processing• Using Argus GSE, the captured greenhouse gas
data will be analyzed.
• The images, once downlinked, will beprocessed using ArcGIS to calculate the NDWI.
• The data, raw and processed, will be madeavailable via a web-portal for further
processing or research.

Fig: 8 Satellite image before andafter calculating NDWI
Fig: 9 Food and Agriculture
Organization

Fig 10: International Centre forIntegrated Mountain Development

KEY PERFORMANCEPARAMETERS

KEY PERFORMANCE PARAMETERS

Constellation

Data Acquisition

Constellation• The mission will have 2 6U satellites in
Bender constellation with an additional
satellite in 35° inclination.
• Due to greater spatial coverage, the Benderconstellation was selected for this mission.
Fig 11: Bender constellation, ground track(4 days).

Data acquisition• To map the spatial variations in greenhousegases, Argus 2000 IR spectrometer will beused.
• To capture the glacial lake data, Multiscape
100 CIS imager will be used.
• A hybrid NADIR/Spinning configuration will
be used for optimal data acquisition.

Fig 12: Argus 2000 IR
SpectrometerFig 13: Multiscape 100CIS imager

SATELLITEDESIGNPayloads:
Spectrometer and Imager
ADCS
3 reaction wheels, 3 magnetorquer and a star
tracker
Communication system
X-band transmitter and an S-band transceiverCommand and Data-handling system
On-board computer with a combined mass
memoryPower system
3U solar panels on the sides
6U-XL solar panels on the front and the backMaximum generated power = ~55W
50 W-h Li-Po BatteryStructure
6U-XL Aluminum structure
Projected cost = <$500,000 per satellite

Fig 14: Bus design

SATELLITEDESIGN

Risk
CAUSE

MITIGATION

Insufficient
Solar Power

Satellite configuration

Power optimization mode forsatellites in LEO

Data
Downlink

Frequency band
incompatibility

Using leased compatible groundstation network

RISKIMPLEMENTATION
PLANIMPLEMENTATION PLAN

Fig 15: Gantt chart

Conclusion
Lack of data in GHG induced
climate change

Possible relation between
greenhouse gas and outburst
flood occurrenceConstellation of three 6Usatellites

Mitigate the effects of outburst
floods in the downstream
communities

Fill the data gap that has been
missing

Use the relevant findings for acredible scientific assessment

Thank you for yourattention

Questions?

Appendix
Subsystem
Spectrometer – Argus
2000 IR
Imager – Multiscape
100 CISADCS – iADCS400
Communications
mini-X-band
transmitter
microTTC S-band
transceiverCommand and Data
handling – Sirius
Command and Data
Handling System
Electrical Power
Subsystem
Solar Panels

Battery
Structure
6U-XL Aluminum
structure

MassPowerSize280 gm< 1W

46*80*80mm³1300 gm

2.5 W – readout
5.8 W – imaging
2-5 W

95.4 x 95.9 x 67.3 mm

300gm

<10W

96*90*24 mm³

N/A

<10W

96*90*24 mm³

130 gm1.3W

230*155*37 mm³

390*2 + 146*2 gm= 1072 gm
210 gm

19.2*2 + 8.4*2
Orbital Power - N/A
50 Whr226.3*366*1.6mm³
100*366*1.6 mm³89*95*7 mm³1600 gm

908 g

Table 1: Mass and Power budget

98 x 98 x 176 mm

100 x 226.3 x 366 mm³

Appendix
Orbital Parameters

LEO SAT 1

LEO SAT 2

SSO SAT 3

Semi major axis (km)6978.146978.146978.14

Eccentricity (deg)

0.00070.00070

Inclination (deg)

3565

97.8

Angle of perigee (deg)

280

280

0

RAAN (deg)

250

250

82.5

True Anomaly (deg)

0180

0

Pointing

NADIR

Spinning

NADIR

Table 2: Orbital parameters and pointing configuration

Appendix
GroundStation

Transmitter 1

Transmitter 2

Transmitter 3

Average

Duration

No ofAccessDuration

No ofAccessDuration

No ofAccessDuration

No ofAccess

KyuTech698.4927628.858

6697.162

4673.602

6

UPD

637.927

9586.477

5661.72

4586.4776

DITT

662.6238563.822

6579.324

5609.502

6UiTM

639.3457532.601

5695.394604.999

5NRSC

640.995

9705.908

4528.697

5624.226

6

Table 3: Ground station access times

Image Credit
Background Credit: James Webb Space telescope, NASAEarth: https://www.istockphoto.com/photo/earth-map-gm172263073-2870355
Fig 1: Dig Tsho (4,400 m a.s.1.), the pear-shaped glacial lake lies embedded in the uppermost Langmoche
valley, one of the tributary valleys of the Bhote Kosi valley, above Thame, Khumbu Himal. Photograph byTj. Peters, 14 October 1982.
Fig 2: https://www.washingtonpost.com/weather/2019/08/19/virginias-deadliest-natural-disasterunfolded-years-ago-hurricane-camille/
Fig 3: Watanabe, Teiji & Byers, Alton & Somos-Valenzuela, Marcelo & Mckinney, Daene. (2016). The Needfor Community Involvement in Glacial Lake Field Research: The Case of Imja Glacial Lake, Khumbu, Nepal
Himalaya. 10.1007/978-3-319-28977-9_13. , photographs by Alton Byers
Fig 4: https://www.forbes.com/sites/davidbressan/2016/12/20/evaluating-avalanches-danger-in-awarming-world-lessons-from-past-climate-change/?sh=4ad4aa33594a
Fig 6: https://www.indiatoday.in/science/story/isro-pslv-c54-mission-oceansat-eos-06-nano-satellitessriharikota-2301072-2022-11-24
Fig 7: NRSC, ISRO.
Fig 8: Gu, C. et al. Monitoring Glacier Lake Outburst Flood (GLOF) of Lake Merzbacher Using Dense Chinese
High-Resolution Satellite Images

Image Credit
Fig 9: Food and Agricultural Organization, https://www.fao.org/home/en
Fig 10: International Centre for Integrated Mountain Development (ICIMOD), https://www.icimod.org/
Fig 11: NASA General Mission Analysis Tool (GMAT)
Fig 12: http://thothx.com/getmedia/4c0d3242-b4fb-4e9d-abf7-85dbb5c6653f/20180815-Argus-2K-Owners-Manual,-Thoth-Technology,-rel-1-03.aspx
Fig 13: https://catalog.orbitaltransports.com/multiscape100-cis/