Beyond Space Applications: A Case Study of Indian Space Science Missions

Venkatesan Sundararajan1

The Indian Space Research Organization (ISRO) since its inception four decades ago, has primarily focused its program on the triad of space applications – remote sensing, telecommunications and meteorology for the immediate socio-economic benefit of the Indian citizens. Several of its Earth observation and telecommunication satellites though carried many astronomy and space science instruments as auxiliary payloads. Building on the success of these scientific payloads for advancing space science research, ISRO is currently developing dedicated space science missions exploiting the gains being made in the indigenous deep space capabilities. This paper presents a case study of current Indian space science missions. The aim of the paper is to discuss the space policy, scientific and economic aspects of Indian space based science missions. The international cooperation on these missions and Indian contributions to foreign space science probes is also outlined.

I. INTRODUCTION ndia has a long and cherished history in the inquisitive and mathematical development of astronomy as a discipline since ancient times.1,2 Ever since the establishment of the Indian Space Research Organization (ISRO) in 1969, and

subsequent development of satellites and launch vehicles, astronomy and space science payloads have formed an integral part of India’s primarily applications driven space program. The first Indian satellite, Aryabhata, launched on May 9, 1975 performed experiments in basic astronomy and atmospheric studies, signaling a modest endeavor in space based astronomical observation.

I

In 1996, the Indian X-ray astronomy experiment (IXAE) was incorporated as an auxiliary payload in the Indian

Remote Sensing (IRS-P3) satellite launched by a PSLV rocket. The primary scientific objectives of the astronomy payload were (i) pointed mode observations of periodic and non-periodic intensity variations of galactic X-ray sources (ii) detailed timing studies to measure pulse and orbital periods of x-ray binaries to understand accretion process (iii) search for long term variability in extragalactic sources. 3

The first space-borne solar astronomy experiment of India, namely, Solar X-ray Spectrometer (SOXS), was launched

by GSLV on May 8, 2003 on board a technology demonstration satellite GSAT-2. The SOXS consists of two independent payloads: SOXS Low-Energy Detector (SLD) and SOXS High-Energy Detector (SHD). The basic scientific objective of SLD payload is to study solar flares in the energy range from 4 to 60 keV with high spectral and temporal resolution. The SLD can observe iron (Fe) and iron-nickel (Fe-Ni) complex lines that are visible only during solar flares. SOXS has observed more than 200 solar flares and has enabled to establish the evolution characteristics of these lines with reference to the continuum plasma temperature and emission measure. It has been found that the minimum critical temperature required for Fe and Fe-Ni line evolution is 9 and 15 MK respectively.4

The steady growth in the launch capacity of indigenous launchers, PSLV and GSLV, coupled with satellite

development expertise based on IRS and INSAT/ GSAT configurations, and advancements being made in the domestic space science research and infrastructure presents a natural progression for ISRO to initiate dedicated space missions for planetary exploration and space science studies. ISRO is embarking on two major space science initiatives: CHANDRAYAAN-1, a lunar polar orbiter to be launched in March 2008 and ASTROSAT, a multi-wavelength space based observatory to be launched in 2009. There are plans to have follow-up missions for lunar and planetary exploration.

The following sections provide an overview of the Indian space science policy framework, key research institutions,

current missions and related economics, international cooperation and commercial launch for high value, medium sized (up to 1500 kg) satellites. An outline of future missions planning and findings is also presented.

1 Senior Member, AIAA

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1

AIAA SPACE 2007 Conference & Exposition18 - 20 September 2007, Long Beach, California

AIAA 2007-6007

Copyright © 2007 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

II. SPACE SCIENCE POLICY FRAMEWORK AND RESEARCH INSTITUTIONS

The Space Commission of India, constituted by the Government of India is the responsible body for the entire Indian Space Program. The Space Commission formulates guidelines and policies to promote the development and application of space science and technology for national development.

The Space Commission is supported by three major national level committees, namely, INSAT Coordination Committee (ICC), the Planning Commission on National Resources Management System (PCNRMS) and the Advisory Committee on Space Sciences (ADCOS).

ADCOS supports initiatives in (1) Astronomy, Astrophysics, (2) Space Weather, (3) Planetary Exploration, and (4) Weather & Climate Science of the Indian space program. A key priority of the current space activity is to undertake advanced space endeavors in the frontier areas of space research.

The Department of Space (DOS), created in 1972, acts as the implementation arm of the Space Commission’s policies and the Indian Space Research Organization (ISRO), under the guidance of DOS, is the main space dedicated body to implement the national space program through the various space centers located throughout the country. ISRO is also actively involved in international cooperation for space activities to achieve the national objectives. The Figure 1 provides the space science policy formulation framework and the main research and development centers.

Indian GovernmentPrime Minister

Space Commission

ISRO

ADCOS

Dept. of Space

PRL SPL SAID NARL

Antrix

Research & Development

Policy & Governance

Univ

PLANEXADCOS – Advisory Committee for Space ScienceAntrix – Marketing Corporation ISRO – Indian Space Research OrganizationPRL – Physical Research LaboratorySPL – Space Physics LaboratorySAID – Space Astronomy and Instrumentation DivisionNARL – National Atmospheric Research LaboratoryPLANEX – Planetary Science and Exploration ProgramRESPOND – Sponsored Research ProgramUNIV – Indian Universities

INDIAN SPACE SCIENCE POLICY AND RESEARCH FRAMEWORK

SpaceCenters

RESPOND

ResearchInstitutions

Figure 1

The Planetary Science and Exploration Program (PLANEX) was initiated in October 2001 with the Physical

Research Laboratory (PRL) located in Ahmedabad in western India as the nodal institution to catalyze and bring together Universities, autonomous research institutions and develop the human resources necessary for India’s current and future planetary exploration/ science missions. Selection and financial support of research projects in universities/ institutions and conducting training workshops for data processing and analysis also come under the purview of PLANEX.

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Based on India’s first dedicated planetary exploration/ science mission, Chandrayaan-1 slated for launch in March 2008 for scientific exploration from a lunar polar orbit of 100 km, the decision making process is a rigorous procedure consisting of many steps involving both scientific and political interest. The overall decision making process is outlined in Figure 2.

Decision Making Process for Planetary Exploration/ Science Mission

Idea Generation

Presentation to Indian Academy of Sciences

Discussion by Astronautical

Society of India

Interest of Scientific Community

Feasibility Assessment

Analysis

Parliamentary Standing CommitteeNational Task Force

Political Sensitization

Review by National Committee

Mission Definition & Review

Endorsement by Space Commission

Announcement by Prime Minister

Policy Makers Approval

Decision Making Process for Planetary Exploration/ Science Mission

Idea Generation

Presentation to Indian Academy of Sciences

Discussion by Astronautical

Society of India

Interest of Scientific Community

Feasibility Assessment

Analysis

Parliamentary Standing CommitteeNational Task Force

Political Sensitization

Review by National Committee

Mission Definition & Review

Endorsement by Space Commission

Announcement by Prime Minister

Policy Makers Approval

Figure 2

III. CURRENT PLANETARY EXPLORATION AND SPACE SCIENCE MISSIONS

The Indian Space Research Organization (ISRO) has started a new initiative to launch dedicated scientific satellites

assigned for planetary exploration, astronomical observation and space atmospheric sciences. ISRO is developing three dedicated planetary exploration/ science missions that form the initial endeavor, namely, (1) Chandrayaan-1: A Lunar exploration orbiter with eleven instruments, including science payloads from NASA, ESA and Bulgaria (2) Astrosat-1: A Multi-wavelength Astronomy Observatory for studies of celestial objects in the X-ray, UV and visible spectral bands with four co-aligned instruments and (3) Megha-Tropiques: An Indo-French collaborative venture for studies of water cycle and atmospheric energy budget over the tropics in the context of climate changes.

India is utilizing the push in planetary exploration/ science initiatives to develop, acquire, collaborate and upgrade

space dedicated infrastructure for its space program. The Physical Research Laboratory (PRL) is upgrading in a phased manner, with x-ray fluorescence spectrometer, plasma mass spectrometer, electron probe micro-analyzer, noble gas mass spectrometer getting ready for use by 2007.

An Indian Deep Space Network (IDSN) consisting of 11-meter, 18-meter and 32-meter antennas are being installed

in the village Byalalu near Bangalore for lunar and future planetary exploration missions. While the 18-meter antenna is being acquired from Germany, Indian industry is developing the 32-meter antenna and data communication center. The 11-meter antenna is dedicated for the science mission, Astrosat. A new National Space Science Data Center is being formed for storage and distribution of data from Chandrayaan-1 and future deep space missions to the scientific community for data analysis and research.5

On April 26, 2007, the Indian Cabinet approved an initial investment of about $66.5 million, with a provision of $10

million in recurring costs, to set up an Indian Institute of Space Science & Technology (IIST) to provide undergraduate and graduate education in space technology and science research with an intake of about 150-200 students each academic year. The campus for IIST is being built at the Vikram Sarabhai Space Center and Liquid Propulsion Center based in Thiruvananthapuram to enable close interaction with the space community.6

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1. CHANDRAYAAN-1: INDIA’S FIRST MISSION TO THE MOON

The first Indian lunar mission Chandrayaan-1 is a 1050 kg satellite with a lunar orbit weight of 590 kg, which includes an Impactor of 30 kg. The lunar orbiter is planned for orbiting at a low circular polar orbit of 100 km. Preparations are well underway for launch in early 2008 on board India’s Polar Satellite Launch Vehicle, PSLV-XL.

The scientific objectives of the Chandrayaan-1 are simultaneous geochemical, mineralogical and photogeological

studies of the whole lunar surface. A suite of baseline payloads, identified to meet this scientific objective, include a Terrain Mapping Camera (TMC), a Hyper-Spectral Imager (HySI), a low Energy X-ray Spectrometer (HEX) and a Lunar Laser Ranging Instrument (LLRI). These payloads will provide simultaneous mineralogical, chemical and photogeological mapping of the lunar surface at resolutions better than previous and currently planned lunar missions. They will allow (i) direct estimation of lunar surface concentration of the elements Mg, Al, Si, Ca, Ti and Fe with high spatial resolution (<= 20km), (ii) High resolution (~100m) UV-VIS-NIR mapping of the lunar surface to identify abundances of various lunar minerals, (iii) High resolution 3D mapping of the lunar surface, and (iv) nature of volatile transport on moon, particularly to colder lunar polar regions. 7

Chandrayaan-1 also carries several foreign payloads from NASA, ESA and Bulgaria. One of the significant scientific

instrument to be carried onboard Chandrayaan-1 is the Moon Minerology Mapper (M3, or “m-cube”). M3 is a state of the art mapping spectrometer developed by NASA. The primary science goal of M3 is to characterize and map lunar surface mineralogy in the context of its geologic evolution. In addition to exploring the global mineralogy of the Moon

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for the first time from orbit, M3 is designed to address the issue of whether the Hydrogen detected by earlier missions at the poles is in the form of water ice. 8

The Impactor probe in the Chandrayaan-1 orbiter carries three instruments, namely, a high sensitive mass

spectrometer, a video camera and a radar altimeter. The Impactor will be released once the lunar orbiter arrives at the designated orbit to land it at the predetermined location on the lunar surface. Apart from the video imaging of the impact site, the onboard mass spectrometer will try to detect possible presence of trace gases in the lunar exosphere.9

Figure 3: Schematic view of the Chandrayaan-1 orbiter under deployment and its scientific instruments

2. ASTROSAT: INDIAN NATIONAL MULTI-WAVELENGTH SPACE OBSERVATORY

ASTROSAT is India’s first full-fledged astronomy satellite. It is designed as a multi-wavelength observatory with

four co-aligned telescopes capable of covering a broad spectral band in the X-ray region (0.5 – 100 keV), Ultra violet band (130 -300 nm) and optical band (350 – 600 nm) with moderate imaging and spectral resolution.10

Most astronomical objects in the Universe emit radiation in the entire electromagnetic spectrum, ranging from the long wavelength radio emission to the extremely short wavelength gamma rays. To understand the physical nature of the cosmic sources that are frequency dependent and time variable, simultaneous observations by a multi-wavelength observatory is an efficient way to construct their energy spectra as well as measure their variability. ASTROSAT is proposed to meet the long felt need for such a mission and it is expected to provide observational data that would improve understanding of the radiation processes and environment in the vicinity of the central compact objects in the Active Galactic Nuclei (AGN), pulsars, micro-quasars, Super Nova Remnants (SNR), galaxy clusters and detection of new X-ray transients.11

Figure 4: ASTROSAT Multi-wavelength Astronomy Satellite with characteristics of its science instruments

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ASTROSAT multi-wavelength observatory is a collaborative effort of several Indian institutions with components from the Canadian Space Agency and the University of Leicester, UK. It consisting of five main science instruments:

• Large Area X-ray Proportional Counters (LAXPC) – For timing and spectral studies covering broad energy

band (3-80 keV). This is a cluster of three identical co-aligned proportional counters in a multi-layer geometry with 10 X 10 field of view (FOV). It is expected to provide high sensitivity in the hard X-ray band.

• Cadmium-Zinc-Telluride Imager (CZTI) – To provide medium resolution spectroscopy and low resolution imaging (0.1 degree) in the 10-100 keV. The CZT detector will be operated in -00 to -200 C range by passive cooling using a radiation plate.

• Soft X-ray Imaging Telescope (SXT) – To carry out moderate (3’) imaging, and medium resolution spectroscopy in the 0.3 to 8 keV. The gold coated X-ray reflecting mirrors are made by nesting 41 conical shells, formed by replicating process similar to the one used for the Japanese ASRO-E2 satellite. The CCD detectors are provided by the University of Leicester, UK gaining from its experience for the SWIFT and XMM-Newton missions. The CCD will be cooled to about -800C by a thermoelectric cooler coupled to a passive radiator plate.

• The Ultraviolet Imaging Telescope (UVIT) – It consists of two identical telescopes each with 38 cm aperture primary and 14 cm secondary and uses three channel plate multiplier and CCD/CMOS based photon counting detectors. They cover the far and near –UV and visible bands. The three Photon Counting Detectors (PCDs) are made in collaboration with the Canadian Space Agency (CSA). A Canadian science team will participate in the UVIT team and another Canadian team will get Astrosat observation time. 12

• Scanning X-ray Sky Monitor (SSM) – The SSM consists of three coded mask cameras with Position Sensitive Proportional Counters (PSPCs), mounted on a boom with rotation capability to scan the sky. The position of a source will be measured along the scan direction to an accuracy of 6’ to 8’ depending on the source intensity between 2-10 keV over a wide field of view. 13

ASTROSAT is a three axis stabilized satellite with three gyros and two star sensors. It will have a pointing accuracy

of about one arc second. A solid state recorder with 120 Gb storage capacity will be used for on board storage of data. The data will be transmitted at a rate of 105 Mb/ Sec. The total mass of ASTROSAT is about 1600 kg including 868 kg mass for scientific instruments. It will be launched in a circular orbit of about 600 km altitude with an orbital inclination of 8 degrees by an Indian PSLV in 2009. 14

3. SPACE CAPSULE RECOVEY EXPERIMENT (SRE)

ISRO achieved a major milestone in January 2007 when the Space Capsule Recover Experiment (SRE-1) was

successfully launched, orbited in space for twelve days and recovered after a splash down in the Indian Ocean. The SRE-1 is a 550 kg spherical cone shaped capsule that was launched on January 10, 2007 by PSLV-C7 along with

three other payloads, namely, CARTOSAT-2 (680 kg) of India, LAPAN-TUBSAT (56 kg) of Indonesia and a 6 kg experimental satellite PEHUENSAT of Argentina. The capsule orbited at an altitude of 635 km polar SSO and was de-orbited for an atmospheric reentry and splash down on January 22nd, 2007 at a specified location some 140 km from the Indian Spaceport, Satish Dhawan Space Center (SDSC) in the Sriharikotta island. The Indian Coast Guard recovered the capsule for scientific analysis of the two microgravity experiments conducted onboard the capsule.

The primary objective of the SRE-1 mission was to develop and validate a low-cost platform to perform micro-

gravity experiments. The successful launch, in-orbit operations, reorientation for deboost, atmospheric reentry and recovery of the capsule demonstrated capability in technologies such as aero-thermal structures, deceleration and flotation systems, navigation, guidance and control. A mastery of these basic satellite recovery elements is necessary for realizing future manned mission plans and reusable launch vehicle development. 15

The SRE-1 carried out two specific microgravity experiments in the separate payload platforms, (1) Isothermal

Heating Furnace and (2) Biomimetic Material Processing Reactor. The former was used to study the growth of Ga-Mg-Zn based quasi crystals in the space environment. The second experiment, a nano-materials research was performed to facilitate the synthesis of self-assembled Hydroxyapatite, a bone material that has a great potential in tissue engineering.16

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Figure 5: PSLV C-7 Payload Bay schematic, SRE-1 before Launch and Recovery

A Mission Management Unit (MMU) was developed specifically for the SRE-1 mission incorporating the traditional

functions of a spacecraft Bus Management Unit (BMU) such as Telecommand (TC) and Telemetry (TM) processing, Data acquisition from attitude and temperature sensors, Attitude and Orbital Control, Thermal Management and augmenting with Guidance and Navigation, On-board storage of multiple TM formats data, and special logics required by the Reentry Measurements into a single system. The MMU provided various modes of operation such as launcher phase, deboost phase and reentry phase. The software is modeled in UML and programmed in Ada. The precise returning point in the ocean of the capsule within a 15 km radius validated the excellent performance of the newly developed MMU. A follow on SRE-2 mission is planned within the next two years. 17

4. MEGHA-TROPIQUES: INDO-FRENCH JOINT MISSION FOR

TROPICAL ATMOSPHERIC STUDIES Megha-Tropiques satellite is a CNES – ISRO joint endeavor to study the tropical water cycle and energy exchanges.

The data from the mission is expected to improve the understanding of the role played by the water cycle in the tropical atmosphere and gather information about the tropical convection processes such as condensed water in the clouds, water vapor in the atmosphere, precipitation, and evaporation. Megha-Tropiques is a component of the international Global Energy and Water Cycle Experiment (GEWEX) to study energy and water exchanges in the Earth/ atmosphere system.18

The need for a study of tropical oceans is critical for a better understanding of the global climate change process and

for more accurate predictions of climatic events in the tropical zone such as cyclones, monsoons, floods or draughts with any certainty.

The Megha-Tropiques mission consists of the following three scientific instruments:

• MADRAS (Microwave Analysis and Detection of Rain and Atmospheric Structures), a microwave radiometer for imaging from 18.7 to 157 GHz in five frequencies and nine channels.

• SAPHIR (Sounder for Atmospheric Profiling of Humidity in the Inter-tropics by Radiometry) for water vapor profile in six atmospheric layers up to 12 km height with a horizontal resolution of 10 km.

• SCARAB (Scanner for Radiation Budget) to measure precipitation and cloud properties – Ice properties in cloud tops (80 & 157 GHz), Cloud liquid water and precipitation and sea surface wind speed (10, 18 & 37 GHz) and Integrated water vapor (23 GHz). 19

The satellite will be placed in an inclined orbit of 20 degrees for high repetivity (six times a day) at an altitude of 867

km by the Indian PSLV launcher in 2009. The MADRAS instrument is proposed to be associated with the multi-satellite cooperative Global Precipitation Mission (GPM).

ISRO is responsible for the system and satellite. It will provide the launcher, the platform, part of MDRAS

instrument and mission control center. CNES is providing the SAPHIR and SCARAB instruments and the microwave part of the MADRAS instrument. Data would be received by ISRO Tracking Center (ISTRAC) and scientific analysis of the data to be performed by both ISRO and French scientific community. 20

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IV. TECHNOLOGY DEVELOPMENT

The current technology capability of ISRO is sufficient for undertaking planetary exploration and science missions within the inner solar system by orbital probes. These include launch vehicle, satellite development, science payloads, communication and navigation. The development of Deep Space Network (DSN) antennas of 18 meter and 32 meter near Bangalore would be adequate for Lunar and future planetary exploration mission communications. The DSN is compatible with international networks and will be available for foreign missions when not in use by ISRO. Further technology development in robotics and rover, auto navigation and thermal management is necessary for further scientific exploration such as in-situ analysis.

In order to realize exploration of objects in the asteroid belt and outer solar system, significant technology

development is needed. The completion of GSLV Mk-III slated for test launch in 2009 would be necessary as a heavy-medium launcher for exploring beyond Mars. As shown in Figure 2, achieving a high impulse (∆V > 6 km/s) is a requirement for both flyby and rendezvous missions. The ∆V requirements for Mercury flyby and rendezvous missions are very high due to the enormous gravitational influence of Sun.21

Source: "Celestial Mechanics: The Waltz of the Planets" by Alessandra Celletti and Ettore Perozzi, Springer Publications, UK, 2007.

HOHMANN FLYBY AND RENDEZVOUS MISSIONS

Mercury(RZV)

Mars

Asteroid Belt

Jupiter Saturn Uranus Neptune

NeptuneUranusSaturnJupiter

Asteroid Belt

MarsVenus

Mercury(FBY)

0

2

4

6

8

10

12

14

16

18

20

0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32Minimum Distance from Earth (AU)

delta

V (k

m/s

)

Solar system escape velocity (12.3 km/s)

The current space propulsion performance (specific impulse, maximum ∆V) is shown in Figure 3. For ISRO to

undertake purposeful scientific exploration of planets and their moons in the outer solar system, development of advanced space propulsion that offer high impulse for post launch orbital maneuvers and power sources, such as Electric Ion Propulsion and Radioisotope Thermoelectric Generator (RTG) respectively is essential. The Radioisotope Heater Units (RHUs) and heat waste of an RTG could be used in spacecraft thermal management as demonstrated by NASA’s Galileo and Cassini missions to Jupiter and Saturn respectively.22

Source: "Advanced Space Propulsion Systems" by Martin Tajmar, Springer Engineering, New York, 2004

SPACE PROPULSION PERFORMANCE

Chemical (Solid)

Chemical (Liquid)

Nuclear (Fission) Electric (Electrothermal)

0

4

8

12

16

20

24

28

0 100 200 300 400 500 600 700 800 900 1000 1100 1200 1300

Specific Impulse (s)

Max

. del

ta V

(km

/s)*

*Assuming m/m0=0.1

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V. INTERNATIONAL MISSIONS ISRO is engaged in several international cooperative missions either as a carrier of foreign payloads or by providing

scientific instruments to international missions. The successful launch of the Italian Space Agency’s (ASI) astronomy satellite, AGILE, as the first foreign primary payload atop the PSLV-C8 on April 23, 2007 marked a new beginning in commercial launch of high-value, small/ medium size payloads by ISRO.

The AGILE Mission: The ASI’s AGILE satellite (352 kg) is a high-energy γ-ray astrophysics mission consisting of three detectors: Gamma Ray Imaging Detector (GRID), sensitive in the 30 MeV – 30 GeV energy range; the SuperAGILE detector (SA) which provides additional hard X-ray detection capability in the 15-45 keVenergy band, and the Minicalorimeter (MCAL) which is part of the GRID but will also provide spectral and accurate timing information on transient events independently of GRID. AGILE mission is expected to provide crucial data for the study of Active Galactic Nuclei (AGN), Gamma Ray Bursts (GRB), unidentified gamma ray sources, galactic compact objects, supernova remnants, TeV sources and fundamental physics by microsecond timing.23

TAUVEX-II in GSAT-4 Mission: The small TAUVEX Observatory (68.5 kg) is a collaborative effort between the Indian Institute of Astrophysics (IIA), Bangalore and the Tel Aviv University (TAU) to observe the ultraviolet sky. TAUVEX is a secondary payload on Indian GSAT-4 satellite and consists of a set of three co-aligned identical telescopes of standard Ritchey-Chretien design with a 20 cm primary mirror and a field of view (FOV) of 0.9 degree to achieve a spectral range between 130 and 300 nm through a set of five different filters. 24

The TAUVEX observatory has been fabricated by EIOp of Israel with the satellite interfaces and the pipeline

software system to convert the raw instrument data into images and other data products are being developed by IIA. Mounted as a secondary payload on GSAT-4, TAUVEX is not well suited to observe individual celestial targets. It is rather intended for use as a survey instrument observing large areas of the UV sky with moderate spatial resolution and high sensitivity. Observing regions of star formation is one of the main objectives of the mission. The telescopes’ high FOV is expected to facilitate observing nearby galaxies by measuring the intensity and wavelength of UV radiation in the interstellar regions in the sky to calculate the chemical composition, temperature and density. Besides the primary objective, it is also hoped to study variable stars, supernova and black holes from the geosynchronous orbit.25

The GSAT-4 is expected to be launched by the Indian GSLV launcher into a 36,000 km GEO altitude in 2008. The

expected lifetime of the mission is 3-7 years.

Italian Space Agency (ASI)’s AGILE Astronomy Satellite Israel Space Agency’s UV Telescope Payload in GSAT-4

Figure 6

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The SARAL Mission: Apart from the Megha-Tropiques mission, ISRO is currently engaged in another collaborative effort with the French space agency, CNES, in the atmospheric sciences. The Satellite with ARgos and ALtika (SARAL) is proposed as an ISRO satellite that would carry three payloads from CNES. The small satellite bus (SSB) is being designed such that the interdependency between the payload module and the platform module is minimized to allow integrating different types of payloads and enable parallel activities from them in orbit.

The payloads to be provided by CNES are (1) high-resolution Altika altimeter, working in the Ka-band at 35 GHz (2) the Doris precise orbitography system with LRA and (3) an Argos location and data collection system. The satellite is to be launched into 800 km dawn to dusk SSO by a PSLV launcher by the end of 2009 with an expected mission lifetime of three years. 26

The primary objectives of the mission is to obtain precise, repetitive global measurements of sea surface height,

significant wave heights and wind speed for developing operational oceanography models. Argos is a global satellite system dedicated to science applications such as meteorological observations operated by CNES and NOAA. The SARAL mission is expected to be a complement to the Ocean Surface Topography Mission (OSTM)/ JASON-2 mission (NASA/ NOAA/ CNES) planned for launch in 2009. 27

The CORONAS-PHOTON Mission: The Coronas-Photon mission is the third satellite in the Russian Solar observation and solar-terrestrial studies program. The primary objective of the mission is to study hard electromagnetic radiation in the UV, X-ray and γ-ray spectrum up to 2000 MeV targeted at solar energy accumulation, acceleration of particles during energy formation, and correlation of solar activities with the physical and chemical processes at the Earth’s upper atmosphere. The scientific instruments are being provided by Russia, Ukraine, Poland and India. 28

TATA Institute of Fundamental Research (TIFR), a premier research institution in India is providing a Low-energy γ-

ray telescope (RT2) consisting of three detectors to register the temporal profiles of the solar and galaxy X-ray radiation in the 10-15 keV range and X-ray spectrometry in the energy range of 0.10 – 2 MeV.

The 1,900 kg satellite with a 540 kg payload of scientific instruments is planned to be placed in a 500 km circular SSO at an inclination of 82.5o in 2007-08 with an expected nominal lifetime of three years. 29

ROSA in the OCEANSAT-2 Mission: The Oceansat-2 mission is the second ISRO satellite dedicated for oceanographic studies. It is slated to be launched in 2007-08 by the Indian PSLV into a polar SSO at an altitude of 720 km. As part of the onboard payload, the Italian Space Agency is providing a GPS Radio Occultation Experiment to contribute to a better understanding of the climate change. The Radio Occultation Sounder for the Atmosphere (ROSA) would take accurate measurements of the atmospheric refractive indexes from which it is possible to derive vertical profiles of atmospheric temperature, pressure and humidity, as well as profiles of electron content in the ionosphere. It is expected to be able to perform over 500 atmospheric profiles per day on a global scale. 30

The data from ROSA would be received by both the Indian and Italian ground stations based in Hyderabad and Space

Geodesy Center of Matera respectively for analysis. A web based GRID computing infrastructure has been developed to optimize the power and time for data analysis utilizing open source mode for synchronizing all the contributions of the scientific partners involved in the project. 31

In 2004, the governments of United Sates and India initiated the Next Steps in Strategic Partnership (NSSP) as part of

the strategic partnership between the world’s largest democracies. A Joint Working Group (JWG) on Civil Space Cooperation forms a component of this initiative to serve as a permanent platform for joint review and formulation of policies. On February 27-28, 2007, the second meeting of the JWG was held in Washington, D.C. A key feature of the endorsement from the meeting is to explore “additional opportunities for cooperation in the field of space science, including astrophysics, robotic exploration of the solar system, and the investigation of the relationship between the Earth and the Sun.” 32

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VI. ECONOMICS AND FUTURE PLANS

The Indian Space Program ranks sixth in the world, with an annual budget of about $918 Million for the FY2007-08. The annual space expenditure represents about 0.09% of the Indian GDP. 33 Since inception, the two primary goals of the space program have been the indigenous development of launch vehicles (39%) and satellite communication and meteorology (36%). As shown in the graph below, the allocation for space sciences is about $74 Million representing 8.06% of the total ISRO budget for FY2007-08.

Indian Space Research Organization (ISRO) Annual Budget($, Millions)

$0 $50 $100 $150 $200 $250 $30

Administration

Launch Tracking

Space Sciences

INSAT Operational

Space Applications

Satellite Tech

Launch Vehicle Tech

2005-06 2006-07 2007-08

The planned five year outlay (2007-12) for the Indian Space Program is about $9.5 Bill

1 Crore = 10 Million) with a space sciences allocation of about $736.25 Million. The includes provision for Chandrayaan-1 launch in March 2008 and development of Chandraylaunch in 2010-11. The budget for Planetary Exploration includes the development of MarsThe allocation for Astronomy & Astrophysics includes spacecraft development costs for AWeather and Atmospheric Science program consists of missions for better understanding Ocean/ Climate observations. 34

Indian Space Program - Space Science Budget Outlay (2007-Total: $736.25 Million

$96.75

$221.50

$141.00

$31.25

$75.00 $89.50

$81.25

Lunar Exploration

Planetary Exploration

Astronomy & Astr

Atmospheric ScienceSpace Weather

Climate & Meteorology

Auxiliary SS Activities

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$1 = Rs. 42

0 $350 $400

ion (Rs. 39,750 Crores, where outlay for Lunar Exploration aan-2 orbiter with a Rover for Orbiter for a launch in 2014. strosat-2 and Aditya-1. Space of the Sun-Earth System and

12)

ophysics

The Space Commission’s working group report on space expenditure for the 11th five year plan submitted to the Indian Government’s Planning Commission has proposed an ambitious set of planetary exploration/science missions as part of the overall Indian Space Program outlay for the FY2007-12. The following table outlines the salient features of the space science/ planetary exploration missions and key development challenges associated with achieving these missions.

Primary Mission Objectives:

To further investigate the origin and evolution of the Moon with improved versions of Chandrayaan-1 instruments for imaging, mineralogy and chemistry, addition of alpha and neutron spectrometers for studies of lunar radiation environment.In-situ analysis of lunar samples (regolith properties) using Rover is also planned

A space based solar coronagraph in the visible and near infrared bands with polarimeter and spectrograph to study coronal magnetic field structures. Gather new information on the velocity fields and their variability in the inner corona that will clearly highlight the role of waves during coronal heating during solar maximum

A X-ray and Gamma ray multi-wavelength astronomy satellite with high-resolution soft x-ray spectroscopy, blackhole monitor and high sensitivity hard x-ray experiment

To understand the Martian atmospheric processes and weather/ dust storms, ionosphere, surface magnetic field, effect of solar wind and search for paleo-water and surface resources.To monitor radiation, electric and magnetic fields and energetic particles in Martian space

To study evolution of asteroids and comets, early solar system processes, meteorite-asteroid connection, physical and chemical properties of asteroid and cometary materials.Studies of energetic particles, radiation and fields in interplanetary space. Prime target is 4 Vesta.

A technology demonstration mission capable of exploring outer solar system objectsValidate advanced technology propulsion, imaging and in-situ analysis instruments and techniques

Launch Date 2011 2012 2014 2014-15 2017-18 2019-20

Launch Vehicle PSLV - XL PSLV PSLV GSLV GSLV Mk-III GSLV Mk-III w/stages

DestinationSpacecraft in lunar orbit & Rover on surface for in-situ analysis of regolith Sun synchronous Orbit

A circular Earth orbit at altitude of about 600 KM

Low altitude orbit around Mars (< 100km)

Rendezvous selected prime target asteroid belt object

Flyby orbit to target Outer Solar System object(s)

Development Challenges

1) Development of specific technologies such as Lander, Robotics & Rover, Auto navigation and Thermal management.2) Techniques to sustain spacecraft in low orbit (~ 50 km) under low gravity environment3) Improved versions of Chandrayaan-1 science instruments and additional domestic/ international payloads

1) Develop the primary science instruments such as polarimeter and spectrograph in the context of the small science mission2) Coordination with ground based optical and radio telescopes and related data analysis s/w development

1) Development and calibration of high sensitivity x-ray and gamma ray astronomy instruments2) Advanced algorithms to synthesize simultaneous multi-wavelength observational data for imaging and analysis

1) Develop instruments to detect and measure Martian weak magnetic fields and plasma2) Completion of Deep Space Network (DSN) antennas and ground support requirements

1) Achieve high impulse propulsion (> 6 km/s) required to explore beyond Mars orbit.2) Develop miniaturized (mass, size) remote sensing instruments for conserving total payload mass and power required3) Gain expertise in command, communication, navigation, control and orbit capture of deep space probes

1) Develop and demonstrate advanced technology such as Ion Propulsion/ Radioisotope Thermoelectric Generator (RTG)2) Develop expertise in auto navigation, high gain antenna systems for the spacecraft and possible impactor/ penetrator technologies

Estimated SC Development Cost $125,000,000 $31,250,000 $70,000,000 $131,250,000 $131,250,000 $135,000,000

Mis

sio

n O

ve

rvie

w

Space Science & Exploration Mission

Chandrayaan-2 & Lander/ Rover

Aditya-1 Astrosat-2 Mars OrbiterFlyby to Outer Solar

SystemAsteroid Orbiter &

Comet Flyby

The estimated total individual budget allocation for the spacecraft development for the proposed missions is shown in the graph below:

Exploration/ Science Mission Development Cost

SRE-

1

Cha

ndra

yaan

-1

Astro

sat-1

Meg

ha-T

ropi

ques

Cha

ndra

yaan

-2 &

Rov

er

Adity

a-1

Astro

sat-2

Mar

s O

rbite

r

Aste

roid

Orb

iter &

Com

et F

lyby

Flyb

y to

Out

er S

olar

sys

tem

$0

$20

$40

$60

$80

$100

$120

$140

$1602007 2008 2009 2010 2011 2012 2014 2016 2018

Year of Launch

FY20

07 ($

, Mill

ions

)

The Manned Mission Initiatives (MMI) is a new program being launched during the FY2007-08 with an objective to

develop a fully autonomous manned space vehicle to carry two crew to 400 km LEO and safe return to earth after mission duration of few orbits to 2 days extendable up to 7 days, rendezvous and docking capability with space station/ orbital platform, safety provisions and provision for extra vehicular activity. The planned manned mission development is estimated to take 10 to 12 years. The primary focus during the period FY2007-12 is on developing critical technologies required to achieve realization of the first Indian manned mission by 2015-17. The Manned Mission Initiatives is allotted about $1.25 Billion for the period FY2007-12. It is estimated that another $1.5 Billion would be required to realize the Manned Mission. 35

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VII. FINDINGS/ RECOMMENDATIONS

The Indian Space Program has enjoyed steady patronage from the government and scientific community since its modest beginning with sounding rockets four decades ago and has achieved tremendous progress in its primary objective of improving the social-economic development of its citizens.

The INSAT system is one of the largest telecommunications network in the Asia-Pacific region and responsible for increasing the coverage of public television from 26% of the Indian population in 1983 to over 90% by 2005. It also provides advanced warnings on the frequent monsoon floods and cyclones that affect India. EDUSAT, a dedicated satellite launched in 2004 for transmission of educational materials in the audio-visual medium from urban centers to rural areas is based on the INSAT configuration.

The IRS constellation forms the largest civilian remote sensing satellites in the world and provides immense support for planning in agriculture and fisheries for the Indian sub-continent. The satellite configurations derived from the IRS bus form the basis for many Indian scientific missions, including India’s first mission to the Moon, Chandrayaan-1.

Space Science/ R&D have been an integral component of the Indian Space Program accounting for about 6% of the annual budget over the past decade. The space-borne science payloads have been designed to complement the large ground based space science infrastructure and research activities.

The dedicated planetary exploration/ science missions such as the Chandrayaan-1 and Astrosat-1 signal the entry of India in the resurgent global interest in the exploration and exploitation of Moon and beyond. International cooperation and participation is encouraged both at the agency and institutional levels. Follow up missions to these and future deep space missions are bound to propel technical innovation and research activities for Indian science.

Climate and Weather Science is emerging as an area of interest and concern due to the impact of global warming on climate changes. India’s vast experience in Earth Observation satellites and dedicated missions such as Megha-Tropiques provide an opportunity for the Indian Space Program to take a lead in global climate science missions and scientific data analysis and modeling in the tropical and Indian Ocean regions.

ISRO’s offer to carry small scientific satellites as a piggy-back payload on regular satellite launches with excess capacity offers the Indian scientific community immense opportunity for proposing missions to study the Earth-Sun interface from space and also can serve as a test-bed for advanced technologies.

Given the comprehensive development of the Indian Space Program, there is a need for developing a National Civil Space Policy Framework with a defined space science/ exploration strategic planning process involving not only the government and space community but also from research institutions, universities, the Indian general public and international scientific community to form a basis for sustainable and relevant programs in the future.

Development of critical technologies, such as mastery of atmospheric reentry, aero-thermal management, advanced space propulsion systems, robotics and rovers, human life support & crew safety features and ground based space infrastructures are essential for achieving the planned manned mission by 2014 and for future deep space exploration missions of new scientific value and importance.

The successful demonstration of both the manned mission and deep space exploration capability would be critical if India were to avoid technology denial regimes and fully exploit outer space for national development and for international standing with the leading space-faring nations of the world.

The workhorse of the Indian space transportation, PSLV and the operational GSLV vehicles have more than 70% of components coming from the Indian industry and it is logical that the entire development of future PSLV and GSLV vehicles could be transferred to industry. The completion of indigenous development of GSLV MK-III with cryogenic engines by ISRO is paramount for achieving the planned Indian manned mission and planetary exploration of outer solar system bodies.

The development of Indian Deep Space Network (IDSN), establishment of National Space Science Data Center and the government approval and funding for an Indian Institute of Space Science and Technology (ISST) augurs well for the prospect of Indian Space Program playing a significant role in space science and planetary exploration endeavors.

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