The Geostrategic Implications of India's Space Program
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Semi Cryogenic Propellants: an Overview of a Non Toxic Propellant for Delivering Heavier Payloads to Space
INTERNATIONAL JOURNAL FOR INNOVATIVE RESEARCH IN MULTIDISCIPLINARY FIELD ISSN: 2455-0620 Volume - 6, Issue - 10, Oct – 2020 Monthly, Peer-Reviewed, Refereed, Indexed Journal with IC Value: 86.87 Impact Factor: 6.719 Received Date: 12/10/2020 Acceptance Date: 26/10/2020 Publication Date: 31/10/2020 SEMI CRYOGENIC PROPELLANTS: AN OVERVIEW OF A NON TOXIC PROPELLANT FOR DELIVERING HEAVIER PAYLOADS TO SPACE 1Aiswarya A. Satheesan, 2Akash R S, 3Gokul Krishna Menon, 4Ishwaragowda V Patil 1, 2, 3Student, 4Assistant Professor 1, 2, 3ACE College of Engineering, Trivandrum, 4 Shree Devi Institute of Techchnology Email - [email protected], [email protected] Abstract: Semi cryogenic fueled rockets use refined kerosene instead of liquid hydrogen, which is used in combination with liquid oxygen as the propellant in the cryogenic engine which is stored in a normal temperature. The refined kerosene needs lesser space to make it possible to carry more propellant in the semi cryogenic fuel part. Semi cryogenics is more powerful, ecofriendly and the cost effective compared to cryogenic engines. Key Words: Semi cryogenics, Cryogenics, Propellant, ULV. 1. INTRODUCTION: Kerosene as a fuel has its advantage of burn off gas eco-friendly and cost effective and relative safety. Unlike liquid hydrogen and oxygen which has to store at -253 and 183 degree Celsius respectively, it is stable at room temperature. Kerosene is a fuel which produces line fumes in its paraffin form, it is considered environmentally friendly. It is a non-corrosive fuel, safe to store for a long time. Depending in what kind of container in which it is stored, kerosene can be kept in storage for a 1 year to 10 year. -
Ariane-DP GB VA209 ASTRA 2F & GSAT-10.Indd
A DUAL LAUNCH FOR DIRECT BROADCAST AND COMMUNICATIONS SERVICES Arianespace will orbit two satellites on its fifth Ariane 5 launch of the year: ASTRA 2F, which mainly provides direct-to-home (DTH) broadcast services for the Luxembourg-based operator SES, and the GSAT-10 communications satellite for the Indian Space Research Organization, ISRO. The choice of Arianespace by the world’s leading space communications operators and manufacturers is clear international recognition of the company’s excellence in launch services. Based on its proven reliability and availability, Arianespace continues to confirm its position as the world’s benchmark launch system. Ariane 5 is the only commercial satellite launcher now on the market capable of simultaneously launching two payloads and handling a complete range of missions, from launches of commercial satellites into geostationary orbit, to dedicated launches into special orbits. Arianespace and SES have developed an exceptional relationship of mutual trust over more than 20 years. ASTRA 2F will be the 36th satellite from the SES group (Euronext Paris and Luxembourg Bourse: SESG) to use an Ariane launcher. SES operates the leading direct-to-home (DTH) TV broadcast system in Europe, based on its Astra satellites, serving more than 135 million households via DTH and cable networks. Built by Astrium using a Eurostar E3000 platform, ASTRA 2F will weigh 6,000 kg at launch. Fitted with active Ku- and Ka-band transponders, ASTRA 2F will be positioned at 28.2 degrees East. It will deliver new-generation DTH TV broadcast services to Europe, the Middle East and Africa, and offers a design life of about 15 years. -
Overview of Sensors for Applications
OVERVIEW OF SENSORS FOR APPLICATIONS Deepak Putrevu Head, MTDD/AMHTDG EM SPECTRUM Visible 0.4-0.7μm Near infrared (NIR) 0.7-1.5μm Optical Infrared Shortwave infrared (SWIR) 1.5-3.0μm Mid-wave infrared (MWIR) 3.0-8.0μm (OIR) Region Longwave IR(LWIR)/Thermal IR(TIR) 8.0-15μm Far infrared (FIR) Beyond15μm Gamma Rays X Rays UV Visible NIR SWIR Thermal IR Microwave P-band: ~0.25 – 1 GHz Microwave Region L-band: 1 -2 GHz S-band: 2-4 GHz •Sensors are 24x365 C-band: 4-8 GHz •Signal data characteristics X-band: 8-12 GHz unique to the microwave region of the EM spectrum Ku-band: 12-18 GHz K-band: 18-26 GHz •Response is primarily governed by geometric Ka-band: 26-40 GHz structures and hence V-band: 40 - 75 GHz complementary to optical W-band: 75-110 GHz imaging mm-wave: 110 – 300GHz Basic Interactions between Electromagnetic Energy and the Earth’s Surface Incident Power reflected, ρP Reflectivity: The fractional part of the radiation, P incident radiation that is reflected by the surface. Power absorbed, αP Absorptivity: the fractional part of the = Power emitted, εP incident radiation that is absorbed by the surface. Power transmitted, τP Emissivity: The ratio of the observed flux emitted by a body or surface to that of a P= Pr + Pt + Pa blackbody under the same condition. 푃 푃 푃 푟 + 푡 + 푎 = 1 푃 푃 푃 Transmissivity: The fractional part of the ρ + τ + α =1 radiation transmitted through the medium. At thermal equilibrium, absorption and emission are the same. -
Indian Payload Capabilities for Space Missions
INDIAN PAYLOAD CAPABILITIES FOR 13, Bangalore - SPACE MISSIONS July 11 A.S. Kiran Kumar Director Space Applications Centre International ASTROD Symposium, Ahmedabad th 5 Application-specific EO payloads IMS-1(2008) RISAT-1 (2012) MX/ HySI-T C-band SAR CARTOSAT-2/2A/2B RESOURCESAT-2 (2011) (2007/2009/2010) LISS 3/ LISS 4/AWiFS PAN RESOURCESAT-1 (2003) LISS 3/ LISS 4 AWiFS CARTOSAT-1 (2005) (Operational) STEREOPAN Megha-Tropiques (2011) TES(2001) MADRAS/SAPHIR/ScARaB/ Step& Stare ROSA PAN OCEANSAT-2 (2009) OCM/ SCAT/ROSA YOUTHSAT(2011) LiV HySI/RaBIT INSAT-3A (2003) KALPANA-1 (2002) VHRR, CCD VHRR Application-specific EO payloads GISAT MXVNIR/SWIR/TIR/HySI RISAT-3 RESOURCESAT-3A/3B/3C L-band SAR CARTOSAT-3 RESOURCESAT-2A LISS 3/LISS 4/AWiFS PAN LISS3/LISS4/AWiFS RESOURCESAT-3 LISS 3/LISS 4/ CARTOSAT-2C/2D AWiFS (Planned) PAN RISAT-1R C-band SAR SARAL Altimeter/ARGOS OCEANSAT-3 OCM , TIR GISAT MXVNIR/SWIR/ INSAT- 3D TIR/HySI Imager/Sounder EARTH OBSERVATION (LAND AND WATER) RESOURCESAT-1 IMS-1 RESOURCESAT-2 RISAT-1 RESOURCESAT-2A RESOURCESAT-3 RESOURCESAT-3A/3B/3C RISAT-3 GISAT RISAT-1R EARTH OBSERVATION (CARTOGRAPHY) TES CARTOSAT-1 CARTOSAT-2/2A/2B RISAT-1 CARTOSAT-2C/2D CARTOSAT-3 RISAT-3 RISAT-1R EARTH OBSERVATION (ATMOSPHERE & OCEAN) KALPANA-1 INSAT- 3A OCEANSAT-1 INSAT-3D OCEANSAT-2 YOUTHSAT GISAT MEGHA–TROPIQUES OCEANSAT-3 SARAL Current observation capabilities : Optical Payload Sensors in Spatial Res. Swath/ Radiometry Spectral bands Repetivity/ operation Coverage (km) revisit CCD 1 1 Km India & 10 bits 3 (B3, B4, B5) 4 times/ day surround. -
History of the Indian Remote Sensing Programme
History of the Indian Remote Sensing Programme Ranganath Navalgund Vikram Sarabhai Distinguished Professor Indian Space Research Organisation Bangalore, India Workshop on Small Satellites & Sensor Technology for Disaster Management, Indo-US S&T Forum CANEUSMarch SSTDM 31, 2014 2014 BEGINNING Stared with the pioneering experiment of detecting Coconut Root Wilt Disease using Color Infrared Film in 1970s by Prof. P. R. Pisharoty. Jun 07,1979 Bhaskara-I (1979) and Bhaskara-II (1981) – Experimental Remote Sensing Satellites provided the Aerial view of Grove Area foundation for the operational Indian Remote Sensing Programme. Nov 20, 1981 (Coconut Root Wilt Disease Study) The Result is operational Indian Remote Sensing Programme with the launch of IRS-1A on March 17, 1988 CANEUS SSTDM 2014 DURING 1980s NRSA established Earth Station Complex at Annaram Village, Shadnagar, 59 km from Balanagar in 1979 to receive Landsat Data TERMINAL-1 (10M DIA) L & S Band 15 Mbps 1980-83: Landsat 2,3 & NOAA- 2, 3 1983-88: Landsat 5, ERS, SPOT & NOAA Today: Multimission ScenarioCANEUS - 4 SSTDMTerminals 2014 (7.5m) - upto 960Mbps EVOLUTION OF (Microwave RISAT-1 (2012) Capability) INDIAN EO SYSTEMS C Band SAR (5.35 GHz) IMS-1 (2008) (Hyperspectral HySI Sensor (64 bands, 506 m) Capability) TWSAT-MX (4 bands, 37 m) TES, Cartosat-1, 2/2A/2B (1999, (High Spatial Resolution 2005, 2007, 2008, 2010) & Stereo Capability) PAN : 2.5 m, 1m Fore +26o Aft: -5o Resourcesat-1/2 (2003, 2011) (Multi resolution, Frequent LISS-3: 23 m, 4 XS, observations, Better LISS-4: 5.8 -
INTERNATIONAL Call for Papers & Registration of Interest
ORGANIZED BY: HOSTED BY: st 71 INTERNATIONAL ASTRONAUTICAL CONGRESS 12–16 October 2020 | Dubai, United Arab Emirates Call for Papers & Registration of Interest Second Announcement SUPPORTED BY: Inspire, Innovate & Discover for the Benefit of Humankind IAC2020.ORG Contents 1. Message from the International Astronautical Federation (IAF) 2 2. Message from the Local Organizing Committee 2 3. Message from the IPC Co-Chairs 3 4. Messages from the Partner Organizations 4 5. International Astronautical Federation (IAF) 5 6. International Academy of Astronautics (IAA) 10 7. International Institute of Space Law (IISL) 11 8. Message from the IAF Vice President for Technical Activities 12 9. IAC 2020 Technical Sessions Deadlines Calendar 49 10. Preliminary IAC 2020 at a Glance 50 11. Instructions to Authors 51 Connecting @ll Space People 12. Space in the United Arab Emirates 52 www.iafastro.org IAF Alliance Programme Partners 2019 1 71st IAC International Astronautical Congress 12–16 October 2020, Dubai 1. Message from the International Astronautical Federation (IAF) 3. Message from the International Programme Committee (IPC) Greetings! Co-Chairs It is our great pleasure to invite you to the 71st International Astronautical Congress (IAC) to take place in Dubai, United Arab Emirates On behalf of the International Programme Committee, it is a great pleasure to invite you to submit an abstract for the 71st International from 12 – 16 October 2020. Astronautical Congress IAC 2020 that will be held in Dubai, United Arab Emirates. The IAC is an initiative to bring scientists, practitioners, engineers and leaders of space industry and agencies together in a single platform to discuss recent research breakthroughs, technical For the very first time, the IAC will open its doors to the global space community in the United Arab Emirates, the first Arab country to advances, existing opportunities and emerging space technologies. -
Access to Space Through Isro Launch Vehicles
Volume -2, Issue-4, October 2012 ACCESS TO SPACE THROUGH ISRO subsystems of a complex launch vehicle but also the maturity attained in conceiving, designing and realizing LAUNCH VEHICLES other vital elements viz., control, guidance, navigation Introduction : and staging systems. The nation’s capability to plan, integrate and carry out a satellite launch mission which is Climbing out of the Earth’s gravity well and transcending truly a multi-disciplinary technological challenge was the dense atmospheric shield is the most energy intensive proved on July 18, 1980 when India successfully orbited crucial first step in the journey into space and the Launch Rohini-1 satellite on SLV-3 E02 flight. Vehicles are the primary viable means of accomplishing this task. India acquired the capability to orbit a satellite While the sub-orbital sounding rockets which just carry in 1980, when SLV-3 the indigenously developed all the payload instruments upto a height of 100 to 200 solid launcher deployed the 40 kg Rohini satellite around kilometers have very few sub-systems apart from the earth. Tremendous progress has been made in this area propulsive device, a Satellite Launcher which has to in the last three decades and today, India is one among import a velocity of around 8 km/sec and precisely the leading space-faring nations with assured access to deliver the payload into a pre targeted injection vector in space through the work-horse operational launcher space has far more complex systems all of which have to PSLV, the Polar Satellite Launch Vehicle. function flawlessly for a successful orbital mission. -
India's Early Satellites – Spin-Stabilized and Bias Momentum
India’s Early Satellites – Spin-Stabilized and Bias Momentum ISRO Aryabhata – for Space Science (Launch date 19 April 1975) Aryabhata was India's first satellite It was launched by the Soviet Union from Kapustin Yar Mission type Astrophysics Satellite of Earth Aryabhata was built by the ISRO Launch date 19 April 1975 engineers to conduct Carrier rocket Cosmos-3M experiments related to X-ray astronomy, solar physics, and Mass 360.0 kg Power 46 W from solar panels aeronomy. Orbital elements Regime LEO The satellite reentered the Inclination 50.7º Orbital period 96 minutes Earth's atmosphere on 11 Apoapsis 619 km February 1992. Periapsis 563 km *National Space Science Data Center, NASA Goddard Space Flight Center Bhaskara (Earth Observation) Satellites (launched in 1979-1981)* Bhaskara-I and II Satellites were built by the ISRO, and they were India's first low orbit Earth Observation Satellite.They collected data on telemetry, oceanography, hydrology. Bhaskara-I, weighing 444 kg at launch, was launched on June 7, 1979 from Kapustin Yar aboard the Intercosmos launch vehicle. It was placed in an orbital Perigee of 394 km and Apogee of 399 km at an inclination of 50.7°. The satellite consisted of- Two television cameras operating in visible (0.6 micrometre) and near-infrared (0.8 micrometre) and collected data related to hydrology, forestry and geology. Satellite microwave radiometer (SAMIR) operating at 19 GHz and 22 GHz for study of ocean-state, water vapor, liquid water content in the atmosphere, etc. The satellite provided ocean and land surface data. Housekeeping telemetry was received until re-entry on 17 February 1989. -
PT-365-Science-And-Tech-2020.Pdf
SCIENCE AND TECHNOLOGY Table of Contents 1. BIOTECHNOLOGY ___________________ 3 3.11. RFID ___________________________ 29 1.1. DNA Technology (Use & Application) 3.12. Miscellaneous ___________________ 29 Regulation Bill ________________________ 3 4. DEFENCE TECHNOLOGY _____________ 32 1.2. National Guidelines for Gene Therapy __ 3 4.1. Missiles _________________________ 32 1.3. MANAV: Human Atlas Initiative _______ 5 4.2. Submarine and Ships _______________ 33 1.4. Genome India Project _______________ 6 4.3. Aircrafts and Helicopters ____________ 34 1.5. GM Crops _________________________ 6 4.4. Other weapons system _____________ 35 1.5.1. Golden Rice ________________________ 7 4.5. Space Weaponisation ______________ 36 2. SPACE TECHNOLOGY ________________ 8 4.6. Drone Regulation __________________ 37 2.1. ISRO _____________________________ 8 2.1.1. Gaganyaan _________________________ 8 4.7. Other important news ______________ 38 2.1.2. Chandrayaan 2 _____________________ 9 2.1.3. Geotail ___________________________ 10 5. HEALTH _________________________ 39 2.1.4. NaVIC ____________________________ 11 5.1. Viral diseases _____________________ 39 2.1.5. GSAT-30 __________________________ 12 5.1.1. Polio _____________________________ 39 2.1.6. GEMINI __________________________ 12 5.1.2. New HIV Subtype Found by Genetic 2.1.7. Indian Data Relay Satellite System (IDRSS) Sequencing _____________________________ 40 ______________________________________ 13 5.1.3. Other viral Diseases _________________ 40 2.1.8. Cartosat-3 ________________________ 13 2.1.9. RISAT-2BR1 _______________________ 14 5.2. Bacterial Diseases _________________ 40 2.1.10. Newspace India ___________________ 14 5.2.1. Tuberculosis _______________________ 40 2.1.11. Other ISRO Missions _______________ 14 5.2.1.1. Global Fund for AIDS, TB and Malaria42 5.2.2. -
NISAR Science Workshop – 2014
Science Workshop – 2014 NISAR Space Applications Centre NISAR Mission Overview Tapan Misra (ISRO) & Paul Rosen (JPL) Space Applications Centre (SAC) NASA ISRO Synthetic Aperture Radar (NISAR) NISAR Mission Overview Payload / Mission Characteristics Would Enable 1 L-band (24 cm wavelength) Low temporal decorrelation and foliage penetration 2 S-band (12 cm wavelength) Sensitivity to light vegetation 3 SweepSAR technique with Imaging Swath > Global data collection 240 km 4 Polarimetry (Single/Dual/Quad) Surface characterization and biomass estimation 5 12-day exact repeat Rapid Sampling 6 3 – 10 meters mode-dependent SAR resolution Small-scale observations 7 3 years science operations (5 years Time-series analysis consumables) 8 Pointing control < 273 arcseconds Deformation interferometry 9 Orbit control < 500 meters Deformation interferometry 10 > 30% observation duty cycle Complete land/ice coverage 11 Left/Right pointing capability Polar coverage, north and south th th *Mission Concept – Pre-decisional – for Planning and NISAR Science Workshop, SAC Ahmedabad – 17 & 18 Nov. 2014 2 Discussion Purposes Only Key Capabilities for NISAR Repeatable orbits and instrument pointing Swath width sufficient to cover ground-track spacing at equator Polarimetric synthetic aperture radar with “industry-standard” performance parameters valid over the full swath All imaging with the instrument boresight pointed 37 degrees off-nadir and +/- 90 degrees off the body-fixed velocity vector Orbit reconstruction to cm-scale accuracy for efficient interferometric processing and calibration Sufficient duty cycle and mission resources to strobe Earth’s land and ice on ascending and descending orbits each repeat cycle 24-hour turnaround on urgent retargeting and 5-hour latency for data designated as urgent th th *Mission Concept – Pre-decisional – for Planning and NISAR Science Workshop, SAC Ahmedabad – 17 & 18 Nov. -
MIT Japan Program Working Paper 01.10 the GLOBAL COMMERCIAL
MIT Japan Program Working Paper 01.10 THE GLOBAL COMMERCIAL SPACE LAUNCH INDUSTRY: JAPAN IN COMPARATIVE PERSPECTIVE Saadia M. Pekkanen Assistant Professor Department of Political Science Middlebury College Middlebury, VT 05753 [email protected] I am grateful to Marco Caceres, Senior Analyst and Director of Space Studies, Teal Group Corporation; Mark Coleman, Chemical Propulsion Information Agency (CPIA), Johns Hopkins University; and Takashi Ishii, General Manager, Space Division, The Society of Japanese Aerospace Companies (SJAC), Tokyo, for providing basic information concerning launch vehicles. I also thank Richard Samuels and Robert Pekkanen for their encouragement and comments. Finally, I thank Kartik Raj for his excellent research assistance. Financial suppport for the Japan portion of this project was provided graciously through a Postdoctoral Fellowship at the Harvard Academy of International and Area Studies. MIT Japan Program Working Paper Series 01.10 Center for International Studies Massachusetts Institute of Technology Room E38-7th Floor Cambridge, MA 02139 Phone: 617-252-1483 Fax: 617-258-7432 Date of Publication: July 16, 2001 © MIT Japan Program Introduction Japan has been seriously attempting to break into the commercial space launch vehicles industry since at least the mid 1970s. Yet very little is known about this story, and about the politics and perceptions that are continuing to drive Japanese efforts despite many outright failures in the indigenization of the industry. This story, therefore, is important not just because of the widespread economic and technological merits of the space launch vehicles sector which are considerable. It is also important because it speaks directly to the ongoing debates about the Japanese developmental state and, contrary to the new wisdom in light of Japan's recession, the continuation of its high technology policy as a whole. -
India's Evolving Cooperation with Space Agencies in Europe
India’s Evolving Cooperation with Space Agencies in Europe Imtiaz Ali Khan Counsellor (Space) & ISRO Technical Liaison ESPI Evening event Officer, 1 February, 2017 Embassy of India, Paris Vienna, Austria Outline of presentation Facets of Indian Space Programme Objectives of International Cooperation Cooperation through multi-lateral fora UN treaties and Space policy Space Cooperation with Europe Scope of Activities Some specific examples Potential areas for future cooperation The Facets of Indian Space programme (1962 INCOSPAR; • Initiated in 1960’s – Space 1969 ISRO; 1972 - Space Commission & – Exploration DOS) Space • 3 National committees coordinate Satellite Navigation Commerce space system establishment and applications: • INSAT Coordination Committee (ICC) Advanced Satellite • Planning Committee on National Communicat Space Natural Resources Management System ions Systems (PC-NNRMS) • Advisory Committee for Space Sciences (ADCOS) Earth Launch Vehicles • Completed 137 missions (54LV + 80SC) Observation • US$ 1.1 Billion budget Space • 35 satellites in orbit Applications • Launched 74 satellites from 21 countries VISION Harness space technology for national development, while pursuing space science research and planetary exploration Objectives of International Cooperation • Share the expertise for meeting the National needs • Prepare for Scientific and technological challenges • Enable an environment for sustainable and peaceful uses of outer space • Assistance to other developing countries • Addressing global concerns • Strengthening