UAE National Space Programme

Adnan Alrais Mohammed Bin Rashid Space Centre (MBRSC)

FISO Telecon 01-30-19

1 Overview:

2006 2015

Establishment of Establishment of “Emirates Institution for Advanced Science “Mohammed Bin Rashid Space and Technology” Centre (MBRSC)”

2 Vision:

“To be recognized globally as a center of excellence in the field of space science 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.” 3 UAE National Space Programme

Satellite Development Mars Exploration Mars UAE Astronauts Program Program 2117 Program

4 1 Satellite Development Programme

5 Phase 1: Tech/Know-How Transfer Program DubaiSat-1

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 th Launch date 29 July 2009 6 Phase 2: Joint-Development Project DubaiSat-2 Altitude (km) 600 Mass < 300 Kg Spatial Resolution PAN 1M, MS 4m

Data Quantization 10-bits Mass Storage 256 Gbits Imaging Modes Single Strip Fast Multi-Strip Single Pass Stereo D/L Date Rate 160Mbps

Swath Width (km) 12 Launch date 21st Nov 2013

7 Phase 3: 100% Development in the UAE

KhalifaSat

8 KhalifaSat

Item 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 PAN < 1.21 micro-radian PAN GSD = 0.7 m @ 600 km Instantaneous FOV MS < 4.86 micro-radian 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 9 Ground Segment Architecture:

S-Band S-Band -Telecommand X-Band -Telecommand - Telemetry -Image Data - Telemetry - ANC Data X-Band -Image Data - ANC Data

MBRSC Subsidiary Customer IRPS Ground Site Ground Site Ground Site S-Band Ground X-Band Ground S-Band Ground X-Band Ground System System System System

-Telecommand -Telecommand - Telemetry -Telemetry - Initial Orbit Data

-Telecommand Launch Site - TLE Main MCS -Telemetry - Image Data - Image Data - ANC Data Subsidiary MCS - ANC Data - Schedule Request - Imaging Request

NORAD -Mission Timeline -Imaging Request Confirm/Reject -Reference TLE -Mission Timeline -Satellite Operation Constraints -Reference TLE Customer IRPS Main IRPS -Satellite Status Data -Satellite Operation Constraints -Satellite Status Data - Catalog -Catalog Search - Catalog -Catalog Search - Order Status -Imaging Order - Order Status -Imaging Order - Product -Product Order - Product -Product Order

User User 10 MBRSC Ground Station:

• Supports MBRSC’s Satellite Missions: DS-1, DS-2 , KhalifaSat and upcoming missions • Provides Ground Station Support services to international commercial and scientific missions • MBRSC provides Antenna Hosting Services for local and international entities.

11 DMSAT-1

• DMSAT-1 (Dubai Municipality Satellite) is a high-performance small microsatellite designed to perform multi‐spectral observations in visual and near-infrared bands for aerosol and greenhouse gas monitoring. • Developed by “University of Toronto Institute for Aerospace Studies – Space Flight Laboratory – UTIAS-SFL”.

12 DMSAT-1

• DMSAT-1 contains three instruments to monitor the aerosols and greenhouse gases in the atmosphere. Specification Value Mechanical Spacecraft Volume 40x20x20 cm Spacecraft Mass 15.7 kg Attitude Attitude Solution <0.5o Attitude Control <1.0o (2σ) Primary Instrument Attitude Pointing Modes Target Tracking; Nadir-Aligned; Inertial Polarimeter Power Power Generation 6.5-42 W WCH-EOL Battery Capacity 108 Wh – Li-ion Communication Downlink S-Band Secondary instruments Data Downlink Up to 2 Mbps Spectrometers Uplink S-Band Data Storage Up to 1 GB

13 DMSAT-1 Operational Scenario

- 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

14 DMSAT-1 Instruments

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

15 DMSAT-1 Instruments

Primary Instrument – Polarimeter • Expected Products Model Radiance Aerosol Optical Depth

Source: PARASOL data (Spatial Resolution 6 km x 7 km at nadir) 16 DMSAT-1 Instruments

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

Instrument Name Spectrometer #1 Instrument Name Spectrometer #2 Spectral Range 1215 – 2000nm Spectral Range 1730 – 2400nm Spectral Resolution ~6nm Spectral Resolution ~6nm Constituents Greenhouse gases Constituents Greenhouse gases

H2O (1200nm, 1400nm) CO2 (2050nm) CO2 (1420nm, 1570nm, 1600nm) CH4 (2250nm) Spatial Resolution 1.5km @ 600km altitude Spatial Resolution 1.5km @ 600km altitude Field of view 0.15° Field of view 0.15°

17 DMSAT-1 Instruments

Secondary Instruments – Spectrometers 1 & 2 • Expected Products Model Radiance Carbon Dioxide Concentration

H2O

CO2

CO2

CO2 CH4 H2O

Source: NASA OCO-2

18 DMSAT-1 Data Products Flow

DMSAT- Look up tables Tools Ground Station 1 Data

Expected Products: Reflection - Aerosol Optical Depth (PM2.5, PM10) - Aerosol Effective Radius - Greenhouse gases

concentration (CH4, CO2, H2O)

19 2 Emirates Mars Mission (EMM) Hope Mission

20 Program Objectives • 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.

21 EMM Partnerships

Project Management Fund Science Spacecraft, Mission Operations, Observatory and Spacecraft I&T

Instruments Navigation Lead Launch Vehicle

22 EMM Science Motivation • 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

23 EMM Science Questions EMM 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?

24 EMM Science Flow

Science Questions Science Objectives Science Investigations

Determine the three- dimensional Characterize the state of the How does the Martian lower thermal state of the lower Martian lower atmosphere on atmosphere respond globally, atmosphere and its diurnal variability, global scales and its diurnally and seasonally to on sub-seasonal timescales geographic, diurnal and solar forcing? seasonal variability Determine the geographic and diurnal distribution of key constituents in the lower atmosphere on sub-seasonal Correlate rates of thermal and How do conditions timescales photochemical atmospheric throughout the Martian escape with conditions in the atmosphere affect rates of collisional Martian atmospheric escape? Determine the abundance and spatial atmosphere variability of key neutral species in the thermosphere on sub-seasonal timescales

How do key constituents in Characterize the spatial the Martian exosphere structure and variability of key Determine the three-dimensional behave temporally and constituents in the Martian structure and variability of key species spatially? exosphere in the exosphere and their variability on sub-seasonal timescales

25 EMM Science Flow

Science Investigations Physical Parameters Observable Quantity Instruments

Absolute radiance of CO2 Determine the three- Temperature Profiles <50 km absorption band dimensional thermal state (7-8 μm and 14-16 μm) of the lower atmosphere and its diurnal variability, Absolute radiance over a subset of on sub-seasonal Surface Temperatures the spectral range timescales (7 - 12 μm)

H20 vapor column abundance 2D image of radiance in 260 ±5nm EMIRS (IR)

Relative radiance of H2O ice absorption bands (10-15 μm) Ice column integrated optical depth at 12 μm and 320 nm Determine the Relative radiance of dust absorption geographic and diurnal bands (8 -25 μm) distribution of key constituents in the lower atmosphere on sub- 2D image of radiance in 320 ±5nm seasonal timescales Dust column integrated optical depth 9 μm and 220 nm 2D image of radiance in 220 ±5nm EXI and 635 ±5nm (VIS/UV)

Ozone column integrated 2D image of radiance in 260 ±5nm 26 abundance EMM Science Flow

Science Investigations Physical Parameters Observable Quantity Instruments

Carbon Monoxide Column CO Emmistion Determine the abundance Density (CO 4PG: 140–170 nm) and spatial variability of key neutral species in the thermosphere on sub- Light intensity image at O seasonal timescales Oxygen Column Density (130.4 nm & 135.6nm)

Light intensity at H (121.6 nm and 102.6 nm) Density of Hydrogen Corona EMUS (FUV) Determine the three- Altitude profiles at H emission dimensional structure (121.6 nm and 102.6 nm) and variability of key species in the exosphere and their variability on Light intensity at O sub-seasonal timescales (130.4 nm) Density of Oxygen Corona Altitude profiles at O emission (130.4nm)

27 EMM Instruments

2 6 5 K

1 4 5 K EMIRS EMUS EXI (ASU/MBRSC) (LASP/MBRSC) (LASP/MBRSC)

Imager with 12 MP Fourier Transform IR Ultra Violet Imaging camera with 6 bandpass Spectrometer Spectrometer filters (VIS/UV)

28 EMUS Instrument Description • 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). Instrument Specifications Science Targets

Specification Not to scale Field of view (0.18°, 0.25°, 0.7°) × 11.0° Region 1: 0 – 1.06 RM thermosphere: H, O, CO

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

Wavelength range 100 – 170 nm Region 3: 1.6 – 6 RM exosphere: bound O corona; H corona

Region 4: 6 – 10 RM exosphere: escaping O; H corona Spectral resolution 1.3, 1.8, 5 nm Targets Wavelength Spatial resolution with 0.14° × 0.20° narrow slit H 102.6, 121.6 nm O 130.4, 135.6 nm Detector photocathode CsI CO 4PG 140-170 nm

FUV spectrum of Mars [Feldman. Icarus 214.2 (2011): 394-399] 29 EMIRS Instrument Description • 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 Instrument Specifications Science Targets

Measurement Required Science Need Specification Relative radiance of dust To characterize dust. Instantaneous Field of 6 mrad view absorption bands Spectral Resolution 5 cm-1 Relative radiance of ice To characterize water ice Spectral Range 6-40+ µm absorption bands clouds. Spatial Resolution <300 km resolution Relative radiance of H2O To track the Martian water Observation Capability Observe ½ of Mars within ½ vapor absorption bands cycle.

hour of observing Absolute radiance of CO2 Track the thermal state of the ~60 observations per week absorption band Martian atmosphere. (~20/orbit) Radiance at 1300 cm-1 Boundary condition for the lower atmosphere.

30 EXI Instrument Description VIS • 12 Mpix CMOS Imager with re-closeable door and filter wheel Channel • 6 filter band-passes UV • UV1: 220±5 nm CW, ≤30 nm FWHM Channel • 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

Instrument Specifications Science Targets

Specification UV VIS Science Product Spatial Image Focal Plane Format 12.6 MP 4:3 format Resolution Wavelengths 4096x3072 @5.5 um Technology CMOS Dust Dynamic Range 12-bit, 13,500 e full well Column-integrated ≤ 10 km 220 and 635 nm Lens System 48 mm, f/3.6 51 mm, f/4.25 optical Depth Field of View 19.0o 25.8o by 19.2o Water Ice cloud Pixel Angular View 23 arcsec per pixel 22 arcsec per pixel Column- integrated ≤ 10 km 320 nm Plate Scale 0.85 mm/o 0.9 mm/o optical depth Distortion @9.35o +6% -2% Ground coverage at Full Disk Ozone apoapsis and priapsis Column-integrated ≤ 10 km 260 nm Ground resolution at 4.9 /2.3 km per pixel 4.6 / 2.2 km per pixel abundance apoapsis / priapsis Filter Spectral Bands UV1: 205-235 nm Blue: 427-447 nm Color images of ≤ 10 km 437, 546, and 635 nm UV2: 245-275 nm Green: 536-556 nm Mars UV3: 305-335nm Red: 625-645 nm 31 Spacecraft – Hope Probe • Spacecraft Design is Low Mass and High Heritage

Technical Specifications S/C Dimension 3m x 7.9m Wet Mass 1500kg RF Band X Band Power Requirement 477 W Propulsion Type Monopropellant Hydrazine System

32 Instrument Payload on the Observatory

EXI Electronics EMIRS

Star Star Tracker Tracker EMUS EXI Reaction Wheel EMUS Electronics

Launch Vehicle Adapter (LVA) 33 Science Orbit • 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.

Key Features: Hope’s Orbit • Periapse altitude: 20,000 km • Apoapse altitude: 43,000 km Deimos’ Orbit Phobos’ • Orbital period: 55 hours Orbit MAVEN MEX 3 orbits per week MGS MRO ~2.24 sols • Inclination: 25 deg • Periapse placed near equator: AOP: 177 deg • Primary science collection

starts ~May 2021 34 EMM Ground Segment

35 EMM Launch Segment

Tanegashima Space Center

• Mitsubishi Heavy Industries, LTD (MHI) H-IIA launch vehicle • Tanegashima Space Center, Yoshinobu Launch Complex Launch scheduled for summer 2020

36 Mission Architecture Diagram

37 3 Mars 2117

38 Vision:

To enable the UAE to contribute to humanity’s interplanetary endeavors.

39 Mission

To establish a lasting colony on Mars by 2117.

40 Pillars of Mars 2117

Contributing to global efforts Imbedding a culture of of colonizing the red planet discovery & exploration Research & Education Development

Building effective and lasting Collaboration Enable Enabling youth to play an active international partnerships role in advancing global efforts

41 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

43 4 UAE Astronauts Program

44 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

45 The selection process: 9

Advanced Medical & 39 4,022 Psychometric test Applications ROSCOSMOS 95 587 The Flight to the ISS 2 Initial Interview Close Basic medical & receiving 18 applications Start First two Astronaut psychometric testOnline psychometric Candidates receiving test applications Final Panel Interview

December June 2018 May 2018 September 2018 2017 June 2018 June 2018 March 2018 July 2018

46 Astronauts candidates

Hazzaa AlMansoori & Sultan AlNeyadi

47 The Team: 200 members 48 Avg. Age:

27 Years 49 Women Participation: 40%

50 st Image of the moon taken by DubaiSat-2 on July 1 , 2015 51 52