RESPOND & AI Capacity Building Programme Office ISRO HQ, Bengaluru RESPOND & AI Capacity Building Programme Office ISRO HQ, Bengaluru RESEARCH AREAS IN SPACE A Document for Preparing Research Project Proposals RESPOND & AI Capacity Building Programme Office ISRO HQ, Bengaluru January 2021 Technical Guidance Dr. M A Paul, Associate Director, RESPOND & AI, ISRO HQ Technical Support and Compilation Smt Nirupama Tiwari, Sci/Engr SE, CBPO, ISRO HQ Shri K Mahesh, Sr. Asst, CBPO, ISRO HQ Technical Guidance Dr. M A Paul, Associate Director, RESPOND & AI, ISRO HQ For any queries please contact Director, Capacity Building Programme Office (CBPO) Technical Support and Compilation Indian Space Research Organisation HQ Smt Nirupama Tiwari, Sci/Engr SE, CBPO, ISRO HQ Department of Space Shri K Mahesh, Sr. Asst, CBPO, ISRO HQ Government of India Antariksh Bhavan New BEL Road For any queries please contact Bangalore 560094 E-mail: [email protected] Director, Capacity Building Programme Office (CBPO) Indian Space Research Organisation HQ Department of Space Associate Director, RESPOND & Academic Interface Government of India Indian Space Research Organisation HQ Antariksh Bhavan Department of Space New BEL Road Government of India Bangalore 560094 Antariksh Bhavan E-mail: [email protected] New BEL Road Bangalore 560094 Associate Director, RESPOND & Academic Interface E-mail: [email protected] Indian Space Research Organisation HQ Department of Space Government of India Antariksh Bhavan New BEL Road Bangalore 560094 E-mail: [email protected] CONTENTS Sl. No. Programmes and Areas Page No Launch Vehicle A Aerospace Engineering 1-9 B Propulsion 9-21 C Propellants, Polymers & Chemicals 21-31 D Materials & Metallurgy 31-41 E Transducers and Sensors 41-45 F Mechanical Design & Analysis 45-46 G Control, Guidance & Simulation 46-47 H Composites, Launch Vehicle Structures 47-62 I Avionics 62-67 J Advanced Inertial Systems 68 K Launch Vehicle Tracking System, Range 69-70 Operation and Safety Engineering L Testing of Liquid Propulsion Systems 70-74 M Rocket systems including 74-78 Human Space Probes N Electronics and Measurement for Testing 78-81 Rocket Systems O Management 82 Satellite Communication A SATCOM & Navigation Payload 85-99 B SATCOM and SATNAV Applications and 99-112 Associated Technologies C Antenna Systems 112-114 D Electro-Optical Sensor Technology 114-124 E Microwave Sensor Technology 124-134 F Electronics and Microelectronics Design, 134-140 Fabrication and Testing Technologies G Mechanical Engineering Systems 140-155 H Systems Reliability 155-161 I Mission Development 161-163 J Communication & Power 164-165 K Integration & Checkout 166 L Controls and Digital 167-170 M Reliability and Components 170-171 N Production of Spacecraft Systems 171-172 O VLSI Design 172-183 P Process Technology 183-184 Q Compound Semiconductor Technology 184-185 R MEMS Design & Process Technology 185-187 S IC Package Design & Development 187-189 T Human Spaceflight Programme 189-192 Sl. No. Programmes and Areas Page No Earth Observations A Remote Sensing, Signal and Image 193-201 Processing and Software Development B Mission Development and Remote 201-205 Sensing-Sensor Technology C Remote Sensing Applications in Geosciences 205-206 D Microwave Remote Sensing Applications 207-210 in Agriculture, Soil Moisture, Forestry & Wetland Ecosystem E Information Extraction and Geospatial 210-212 Modelling F Satellite Data Reception and Ground Station 212-216 G Earth, Ocean, Atmosphere, Planetary 216-243 Sciences and Applications H Water Resources Studies 244-250 I Geoinformatics 250-258 J Aerial Remote Sensing 258-260 K Earth and Climate Sciences 260-271 L Disaster Management 271-273 Space Sciences A Space, Marine and Atmospheric Sciences 275-280 B Atmospheric Dynamics and Coupling 280-281 C Sun and Solar System 281-287 D Astronomy and Astrophysics 287-290 E Space Instrumentation 290-294 F Remote Sensing Data Analysis from 294-295 Planetary Exploration Missions G Laboratory Study of Astromaterials 295 H Study of Terrestrial Analogues of Moon 295 and Mars I Payloads for Upcoming Planetary Missions 295-296 J Earth System Science Studies 296-301 K Atomic, Molecular and Optical Physics 302-304 L Emerging Areas in Theoretical Physics 305-306 Meteorology A Weather and Climate 307-310 B Space Physics 310-312 C Signal & Data Processing 312 D Radar and Lidar Instrumentation for 312-314 Atmospheric Probing Annexure-1 315-319 Annexure-2 320-321 Annexure-3 322-324 Launch Vehicle Launch Vehicle A Area Aerospace Engineering (VSSC) A1 Sub Area Aerodynamics and Aero Thermal Engineering (VSSC) A1.1 Estimation of gaseous radiation during interplanetary missions (VSSC) Planetary entry missions involve penetration of its atmosphere at very high entry velocities. The external surface of entry body is exposed to extreme heating rates owing to dissipation of its large kinetic energy. Strong shocks are formed ahead of the entering body increasing the internal energy of entrapped gas. Gas within the shock layer attains very high temperature levels leading to thermochemical non-equilibrium. Gaseous radiation becomes significant in such conditions. Both equilibrium and non-equilibrium air radiation have to be modeled for estimation of radiative heating. Number densities of various chemical species, translational, rotational and vibrational temperatures of heavy particles and electrons are to be evaluated for modeling emission and absorption characteristics of air under these conditions. Available database on radiative properties incorporating spectral absorption and emission behavior of gases at high temperature are to be used. The proposed study should focus on establishing a methodology for evaluation of gas radiation for planetary entries. Comparison of estimated gas radiation levels with available measurements in literature is essential for validation. A1.2 Flow field over a double delta wing configuration (VSSC) Heat flux data for the double delta configuration is important, especially for regions of shock-shock interaction, leeward region flow, base flow, fuselage wing interaction for accurate distribution of TPS and for mass optimization. It is proposed that experimental heat flux measurements on the above region on ISRO’s RLV may be attempted at flow enthalpies of about 2 MJ.kg, M = 6.6, To = 1700 – 1800 K. Diagnostic shall be (a) heat flux (b) liquid crystal thermography/IR thermography (c) Flow visualization. The generated data shall be compared with the predictions, and suggestions for improving the prediction may also be attempted. A1.3 Influence of back pressure fluctuations on the unsteady transonic shock wave boundary layer interaction (VSSC) A study of shockwave boundary layer interaction in a constant area duct is proposed to understand the effect of back pressure rise on the unstart of typical ramjet/scramjet air intakes. One important factor which affect the large scale motion of the shock and shock wave/boundary later interaction (SWBLI) is the downstream pressure perturbations. Hence a proposal is invited to understand the response of shock wave and SWBLI to downstream perturbations to mitigate its ill effects. A1.4 Supersonic Retro Propulsion (VSSC) In order to reduce the peak dynamic pressure on the stage during its recovery or to reduce the speed of entry modules during planetary entry, supersonic retro propulsion is an attractive option. This is especially true for entry in planetary atmospheres like that of Mars, which 1 Research Areas in Space - 2021 has low-density and does not provide adequate drag to slow down the entry vehicle before touch-down. It has very practical applications in stage recovery where the high dynamic pressure of the recoverable stage is reduced using the impulse provided by propulsion in the supersonic / hypersonic regime of flight. The rocket motor exhaust exhausts into the opposing high speed free stream. The aim of optimal supersonic retro propulsion is to maximize the axial force exploiting the interaction between propulsion and aerodynamics and also to assess the aerodynamic and thermal impact on the parent stage / vehicle. Proposals are solicited for design, analysis and testing of deceleration system with Supersonic Retro Propulsion with single-jet and multi-jets (clustered configurations) to optimize the axial force for stage recovery and planetary entry conditions. A1.5 Simulation and studies of soil mechanics for understanding supersonic jet impingement and subsequent dust generation for planetary missions (VSSC) The search for extra-terrestrial life is being explored on a larger scale. This involves visiting other celestial bodies and exploring for signs of life. Generally, a propulsion system would be used to carry landing on the planed/meteoroids. Understanding the interaction of jet exhaust with the soil during the terminal descent phase is critical for nominal system performance. Proper physics modelling of soil and mechanics of soil-jet interaction, soil particulate formation and dust propagation form major parts of such a study. From this project it is expected that the capabilities would be developed for understanding and modeling of soil erosion and dust particle generation for future interplanetary missions to Moon, Mars, Titan and Venus. This could be in the form of a stand-alone code or be a feature addition to the current framework of PARAS-3D. A1.6 Development of an engineering procedure to account for the ground proximity effect on Aerodynamics for the small aspect ratio wing body configuration using CFD database (VSSC) The aerodynamic characteristic of the wing body configuration is influenced by the ground proximity effect. The ground proximity effect changes the aerodynamic lift, moment and drag coefficients of the wing body configuration. Therefore, it is essential to characteristic the vehicle in the presence of ground and also the associated aerodynamic loads has to be considered for the vehicle design. Ground proximity effect is measurable, when the height is below the one wing span of the vehicle. In general, the ground proximity effect increase the lift-curve slope, decrease the drag due to reduction in the induced drag, and increase or decrease the pitching moment of the wing-body configurations.