UAE National Space Programmefiso.spiritastro.net/telecon/AlRais_1-30-19/AlRais_1-30...Adnan Alrais Mohammed Bin Rashid Space Centre (MBRSC) FISO Telecon 01-30-19 1 Establishment of

UAE National Space ProgrammeAdnan Alrais

Mohammed Bin Rashid Space Centre (MBRSC)

FISO Telecon 01-30-19

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Establishment of “Mohammed Bin Rashid Space

Centre (MBRSC)”

2015

Establishment of “Emirates Institution for Advanced Science

and Technology”

Overview:

2006

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Vision: “To be recognized globally as a centerof excellence in the field of spacescience and technological innovation.”

Mission: “To build a sustainable Science and Technology sector that contributes to the national knowledge based economy, through the launch and implementation of advanced space projects, and prepare a generation of Emirati scientists, to take our country towards a brighter future.”

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Satellite Development Program

Mars ExplorationProgram

UAE Astronauts Program

Mars 2117

UAE National Space Programme

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Satellite Development Programme1

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Phase 1: Tech/Know-How Transfer Program

Altitude (km) 680

Mass ~ 200 kg

Spatial Resolution PAN 2.5m, MS 5m

Data Quantization 8-bits

Mass Storage 64 Gbits

Imaging Modes Single Strip

D/L Date Rate 30Mbps

Swath Width (km) 20

Launch date 29th July 2009

DubaiSat-1

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Phase 2: Joint-Development Project

Altitude (km) 600

Mass < 300 Kg

Spatial Resolution PAN 1M, MS 4m

Data Quantization 10-bits

Mass Storage 256 Gbits

Imaging Modes Single StripFast Multi-StripSingle Pass Stereo

D/L Date Rate 160Mbps

Swath Width (km) 12

Launch date 21st Nov 2013

DubaiSat-2

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KhalifaSat

Phase 3: 100% Development in the UAE

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KhalifaSatItem Features Notes

Imaging type Push-broom imaging With TDI function

Imaging bands 1 PAN, 4 MS (RGB + NIR) Visible & NIR region

Design orbit 600 km Sun-synchronous circular

Instantaneous FOVPAN < 1.21 micro-radian

MS < 4.86 micro-radian

PAN GSD = 0.7 m @ 600 km

MS GSD = 2.98 m @ 600 km

FOV > 1.15 degrees for each band Swath 12 km @ 600 km

Pixel quantization 10 bits

Storage capacity 512 Gbits @ BOL

Image data Tx. speed 320 Mbps @ BOL

Mass < 300 kg

Launch Date 29th Oct 2018

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X-Band

-Image Data

- ANC Data

Launch Site

MBRSC

Ground Site

Subsidiary

Ground Site

Customer IRPS

Ground Site

S-Band Ground System

X-Band Ground System

Main IRPS

Main MCS

Customer IRPS

Subsidiary MCS

User

S-Band

-Telecommand

- Telemetry

S-Band

-Telecommand

- Telemetry

X-Band

-Image Data

- ANC Data

- Telemetry-Telecommand-Telecommand

-Telemetry

-Telecommand

-Telemetry

- Image Data

- ANC Data

- Image Data

- ANC Data

- Schedule Request

-Mission Timeline

-Reference TLE

-Satellite Operation Constraints

-Satellite Status Data

S-Band Ground System

X-Band Ground System

- Imaging Request

-Imaging Request Confirm/Reject

-Mission Timeline

-Reference TLE

-Satellite Operation Constraints

-Satellite Status Data

-Catalog Search

-Imaging Order

-Product Order

- Catalog

- Order Status

- Product

User

-Catalog Search

-Imaging Order

-Product Order

- Catalog

- Order Status

- Product

- Initial Orbit Data

NORAD

- TLE

Ground Segment Architecture:

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MBRSC Ground Station:• Supports MBRSC’s Satellite

Missions: DS-1, DS-2 , KhalifaSatand upcoming missions

• Provides Ground Station Supportservices to internationalcommercial and scientificmissions

• MBRSC provides AntennaHosting Services for local andinternational entities.

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DMSAT-1

• DMSAT-1 (Dubai Municipality Satellite) is ahigh-performance small microsatellitedesigned to perform multi‐spectralobservations in visual and near-infraredbands for aerosol and greenhouse gasmonitoring.

• Developed by “University of TorontoInstitute for Aerospace Studies – SpaceFlight Laboratory – UTIAS-SFL”.

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• DMSAT-1 contains three instruments to monitor the aerosols and greenhouse gases in the atmosphere.

DMSAT-1

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Primary InstrumentPolarimeter

Secondary instrumentsSpectrometers

Specification ValueMechanical Spacecraft Volume 40x20x20 cm

Spacecraft Mass 15.7 kg

Attitude Attitude Solution <0.5o

Attitude Control <1.0o (2σ)

Attitude Pointing Modes Target Tracking; Nadir-Aligned; Inertial

Power Power Generation 6.5-42 W WCH-EOL

Battery Capacity 108 Wh – Li-ion

Communication Downlink S-Band

Data Downlink Up to 2 Mbps

Uplink S-Band

Data Storage Up to 1 GB

DMSAT-1 Operational Scenario

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- Spacecraft performs a target tracking maneuver to keep ground target in field of view

- At each of 5-7 pointing angles take a sequence of images

- Red, Blue, NIR

- Each image is spaced by at least 1.5 seconds to allow readout and transfer of the filter wheel to next filter

- Each pointing angle is separated by 30 seconds to allow transfer of image data from RAM to Flash memory

- Simultaneously, spectrometer data is taken

- Alternatively, spectrometer can be run in Nadir pointing mode to collect swath

DMSAT-1 Instruments

Primary Instrument – Polarimeter• Detect aerosol optical depth and effective radius (PM2.5, PM10) content in the

atmosphere.

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Instrument Name Multi-spectral, dual polarization imager

Spectral Bands Blue (480-500nm)

Red (660-680nm)

Near-Infrared (860-880nm)

Two polarization states: 0° linear and 90° linear

Constituents Aerosols (PM2.5 and PM10)

Spatial Resolution 40m @ 650km altitude

DMSAT-1 Instruments

Primary Instrument – Polarimeter• Expected Products

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Aerosol Optical Depth

Source: PARASOL data (Spatial Resolution 6 km x 7 km at nadir)

Model Radiance

DMSAT-1 Instruments

Secondary Instruments – Spectrometers 1 & 2• Detect Greenhouse gases (CO2, CH4, H2O) in the atmosphere.

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Instrument Name Spectrometer #1

Spectral Range 1215 – 2000nm

Spectral Resolution ~6nm

Constituents Greenhouse gasesH2O (1200nm, 1400nm)CO2 (1420nm, 1570nm, 1600nm)

Spatial Resolution 1.5km @ 600km altitude

Field of view 0.15°

Instrument Name Spectrometer #2

Spectral Range 1730 – 2400nm

Spectral Resolution ~6nm

Constituents Greenhouse gasesCO2 (2050nm)CH4 (2250nm)

Spatial Resolution 1.5km @ 600km altitude

Field of view 0.15°

DMSAT-1 Instruments

Secondary Instruments – Spectrometers 1 & 2• Expected Products

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Carbon Dioxide Concentration

Source: NASA OCO-2

Model Radiance

H2O

H2O

CO2

CO2

CO2 CH4

DMSAT-1 Data Products Flow

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Look up tables

Data

DMSAT-1

Tools Ground Station

Expected Products:- Aerosol Optical Depth

(PM2.5, PM10)- Aerosol Effective Radius- Greenhouse gases

concentration (CH4, CO2, H2O)

Reflection

Emirates Mars Mission (EMM)2

Hope Mission20

• Program goals announced by UAE’s Government on 16 July 2014:

• Complete Mars orbiter insertion by the UAE’s 50th anniversary in 2021

• Contribute to the development of the Science and Technology Sector in the UAE

• Develop UAE Scientific Capabilities

• Increase UAE’s Contribution to the Scientific Community

• Program Requirements

• The mission should be unique, and should aim for unique and significant discoveries.

• The mission should have significant contribution to the ongoing work of the global space science community, and should be of a great value to humanity.

• The mission should help build a sustainable outer space exploration program in UAE.

• The mission should include valuable contribution from UAE engineers and scientists.

Program Objectives

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EMM Partnerships

Project Management

Spacecraft, Mission Operations, Observatory and Spacecraft I&T

Instruments Launch VehicleNavigation Lead

Fund

Science

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• Most of the Mars diurnal (i.e. day-to-night) cycle is unexplored over much of the planet• Crucial for understanding global circulation and the transfer of matter and

energy from the lower-middle atmosphere to the upper layers and out to space

• It is still unclear how and when Mars transitioned from a thicker atmosphere billions of years ago to the cold, thin, arid atmosphere we see today

Before? After

EMM Science Motivation

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EMM Science QuestionsEMM will, for the first time, explore the dynamics in

the atmosphere of Mars on a global scale. It will provide holistic, global and diurnal understanding of

the atmospheric dynamics of Mars

1. How does the Martian lower atmosphere respond globally, diurnally, and seasonally to solar forcing?

2. How do conditions throughout the Martian atmosphere affect rates of atmospheric escape?

3. How does the Martian exosphere behave temporally and spatially?

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EMM Science Flow

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Science Questions

How does the Martian lower atmosphere respond globally,

diurnally and seasonally to solar forcing?

How do conditions throughout the Martian

atmosphere affect rates of atmospheric escape?

How do key constituents in the Martian exosphere behave temporally and

spatially?

Science Objectives

Characterize the state of the Martian lower atmosphere on

global scales and its geographic, diurnal and

seasonal variability

Correlate rates of thermal and photochemical atmospheric

escape with conditions in the collisional Martian

atmosphere

Characterize the spatial structure and variability of key

constituents in the Martian exosphere

Science Investigations

Determine the three- dimensional thermal state of the lower

atmosphere and its diurnal variability, on sub-seasonal timescales

Determine the geographic and diurnal distribution of key constituents in the

lower atmosphere on sub-seasonal timescales

Determine the abundance and spatial variability of key neutral species in the

thermosphere on sub-seasonal timescales

Determine the three-dimensional structure and variability of key species in the exosphere and their variability

on sub-seasonal timescales

EMM Science FlowScience Investigations

Determine the three-dimensional thermal state of the lower atmosphere and its diurnal variability,

on sub-seasonal timescales

Determine the geographic and diurnal

distribution of key constituents in the lower

atmosphere on sub-seasonal timescales

Physical Parameters

Temperature Profiles <50 km

Surface Temperatures

Ice column integrated optical depth at 12 μm and 320 nm

Dust column integrated optical depth 9 μm and 220

nm

Ozone column integrated abundance

H20 vapor column abundance

Instruments

EMIRS(IR)

EXI(VIS/UV)

Observable Quantity

Absolute radiance of CO2 absorption band

(7-8 μm and 14-16 μm)

Absolute radiance over a subset of the spectral range

(7 - 12 μm)

Relative radiance of H2O ice absorption bands (10-15 μm)

Relative radiance of dust absorption bands (8 -25 μm)

2D image of radiance in 260 ±5nm

2D image of radiance in 260 ±5nm

2D image of radiance in 220 ±5nm and 635 ±5nm

2D image of radiance in 320 ±5nm

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EMM Science Flow

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Determine the abundance and spatial variability of

key neutral species in the thermosphere on sub-

seasonal timescales

Determine the three-dimensional structure and variability of key

species in the exosphere and their variability on

sub-seasonal timescales

Oxygen Column Density

Carbon Monoxide Column Density

Density of Oxygen Corona

EMUS(FUV)

Density of Hydrogen Corona

Light intensity image at O

(130.4 nm & 135.6nm)

CO Emmistion

(CO 4PG: 140–170 nm)

Light intensity at O(130.4 nm)

Light intensity at H (121.6 nm and 102.6 nm)

Altitude profiles at H emission (121.6 nm and 102.6 nm)

Altitude profiles at O emission (130.4nm)

Science Investigations Physical Parameters InstrumentsObservable Quantity

EMM Instruments

EMIRS(ASU/MBRSC)

Fourier Transform IR Spectrometer

EMUS(LASP/MBRSC)

Ultra Violet ImagingSpectrometer

EXI(LASP/MBRSC)

Imager with 12 MP camera with 6 bandpass filters (VIS/UV)

265K

145K

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EMUSInstrument Description

Instrument Specifications Science Targets

SpecificationField of view (0.18°, 0.25°, 0.7°) × 11.0°

Wavelength range 100 – 170 nm

Spectral resolution 1.3, 1.8, 5 nm

Spatial resolution with narrow slit

0.14° × 0.20°

Detector photocathode CsI

Targets Wavelength

H 102.6, 121.6 nm

O 130.4, 135.6 nm

CO 4PG 140-170 nm

FUV spectrum of Mars [Feldman. Icarus 214.2 (2011): 394-399]

Region 2: 1.06 – 1.6 RM exosphere: thermal O corona; H corona

Region 3: 1.6 – 6 RM exosphere: bound O corona; H corona

Region 4: 6 – 10 RM exosphere: escaping O; H corona

Region 1: 0 – 1.06 RM thermosphere: H, O, CO Not to scale

• Far ultraviolet imaging spectrograph that will characterize the escape of hydrogen and oxygen from Mars and the state of the Mars Thermosphere.

• It consists of a single telescope mirror feeding a Rowland circle imaging spectrograph with a photon-counting and locating detector.

• The EMUS spatial resolution of less than 300km on the disk is sufficient to characterize spatial variability in the Martian thermosphere (100-200 km altitude) and exosphere (>200 km altitude).

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EMIRSInstrument Description

Instrument Specifications Science Targets

SpecificationInstantaneous Field of view

6 mrad

Spectral Resolution 5 cm-1Spectral Range 6-40+ µmSpatial Resolution <300 km resolutionObservation Capability Observe ½ of Mars within ½

hour of observing~60 observations per week (~20/orbit)

• EMIRS is the 5th generation ASU built FTIR spectrometer with OTES, Mini-TES (2x), MGS-TES and MO-TES heritage

• Simple, FTIR spectrometer w/ pointing mirror

• Acquires 9 interferograms every 4 seconds

• Space and internal blackbody provide 1.5% absolute calibration

• Electronics compress and packetize science and housekeeping data

Measurement Required Science Need

Relative radiance of dust

absorption bands

To characterize dust.

Relative radiance of ice

absorption bands

To characterize water ice

clouds.

Relative radiance of H2O

vapor absorption bands

To track the Martian water

cycle.

Absolute radiance of CO2

absorption band

Track the thermal state of the

Martian atmosphere.

Radiance at 1300 cm-1 Boundary condition for the

lower atmosphere.

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EXIInstrument Description

Instrument Specifications Science Targets

Specification UV VISFocal Plane Format 12.6 MP 4:3 format

4096x3072 @5.5 umTechnology CMOSDynamic Range 12-bit, 13,500 e full wellLens System 48 mm, f/3.6 51 mm, f/4.25Field of View 19.0o 25.8o by 19.2o

Pixel Angular View 23 arcsec per pixel 22 arcsec per pixelPlate Scale 0.85 mm/o 0.9 mm/o

Distortion @9.35o +6% -2%Ground coverage at apoapsis and priapsis

Full Disk

Ground resolution at apoapsis / priapsis

4.9 /2.3 km per pixel 4.6 / 2.2 km per pixel

Filter Spectral Bands UV1: 205-235 nmUV2: 245-275 nmUV3: 305-335nm

Blue: 427-447 nmGreen: 536-556 nmRed: 625-645 nm

• 12 Mpix CMOS Imager with re-closeable door and filter wheel

• 6 filter band-passes

• UV1: 220±5 nm CW, ≤30 nm FWHM • UV2: 260±5 nm CW, ≤30 nm FWHM • UV3: 320±5 nm CW, ≤30 nm FWHM• Blue: 437±5 nm CW, ≤20 nm FWHM • Green: 546±5 nm CW, ≤20 nm FWHM • Red: 635±5 nm CW, ≤20 nm FWHM

EXI E-Box

UV Channel

VIS Channel

Science Product Spatial Resolution

ImageWavelengths

DustColumn-integrated

optical Depth≤ 10 km 220 and 635 nm

Water Ice cloud Column- integrated

optical depth≤ 10 km 320 nm

OzoneColumn-integrated

abundance≤ 10 km 260 nm

Color images of Mars

≤ 10 km 437, 546, and 635 nm

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• Spacecraft Design is Low Mass and High Heritage

Spacecraft – Hope Probe

Technical SpecificationsS/C Dimension 3m x 7.9mWet Mass 1500kgRF Band X BandPower Requirement 477 WPropulsion Type Monopropellant

Hydrazine System

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EMUS

EMIRS

Star Tracker

Star Tracker

EXI

EXI Electronics

EMUS Electronics

Launch Vehicle Adapter (LVA)

Instrument Payload on the Observatory

Reaction Wheel

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• EMM’s target orbit is exciting! No spacecraft has flown an orbit like it. Further, it is low-risk, simple to fly, and produces excellent opportunities to collect EMM’s science.

Science Orbit

Key Features:• Periapse altitude: 20,000 km• Apoapse altitude: 43,000 km• Orbital period: 55 hours

3 orbits per week~2.24 sols

• Inclination: 25 deg• Periapse placed near equator:

AOP: 177 deg• Primary science collection

starts ~May 2021

Deimos’ Orbit

Hope’s Orbit

Phobos’ Orbit

MGS

MEXMAVEN

MRO

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EMM Ground Segment

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EMM Launch Segment

• Mitsubishi Heavy Industries, LTD (MHI) H-IIA launch vehicle

• Tanegashima Space Center, Yoshinobu Launch Complex

Tanegashima Space Center

Launch scheduled for summer 202036

Mission Architecture Diagram

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Mars 21173

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Vision:

To enable the UAE to

contribute to humanity’s

interplanetary endeavors.

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Mission

To establish a lasting

colony on Mars by 2117.

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Pillars of Mars 2117

Research &

DevelopmentEducation

Collaboration Enable

Imbedding a culture of discovery & exploration

Enabling youth to play an active role in advancing global efforts

Contributing to global efforts of colonizing the red planet

Building effective and lasting international partnerships

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Focus of the Mars Science City

Education

Science of Food, Water, and Energy

Laboratories for research

Museum 42

Provides a viable and realistic model to simulate living on the surface of Mars

Laboratories for food, energy and water, agricultural testing and studies about food security in the future

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UAE Astronauts Program4

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Programme Objectives:

• Developing the first Emirati astronaut corps• Sending astronauts to space on scientific

mission• Inspiring new generations• Positioning the UAE as an internationally

recognized participant in human space flight• Support UAE’s vision of a future depend on

knowledge based economy

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December 2017

Start receiving

applications

March 2018

Close receiving

applications

4,022Applications

May 2018

Online psychometric test

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June 2018

Basic medical & psychometric test

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June 2018

Initial Interview

Final Panel Interview

June 2018

Advanced Medical & Psychometric test

ROSCOSMOS

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July 2018

First two Astronaut Candidates

2The Flight to the ISS

September 2018

587

The selection process:

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Astronauts candidates

Hazzaa AlMansoori & Sultan AlNeyadi

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The Team:

200 members48

Avg. Age:

27 Years 49

Women Participation: 40%

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Image of the moon taken by DubaiSat-2 on July 1st, 2015 51

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