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Indian Space Research Organisation (ISRO) has successfully demonstrated on certain critical technologies of Reusable Launch Vehicle in May 2018. During this mission, the demonstrator was heavily instrumented and excellent flight data were obtained on-board through suitable sensors and flight telemetry system which gave valuable and crucial details of hypersonic aero-thermodynamics, autonomous navigation, guidance, control, integrated flight management, etc. The flight measured data were analysed and found to be excellent match with ground simulation and predictions, which gives confidence to take up further developmental activities in this area. It is appropriate to consolidate the valuable data and publish the technical contents as a Special Issue in Journal of The Institute of Engineers (India): Series C. Towards this, 14 technical articles covering wide ranges viz. aeroacoustics, thermal protection system, aero thermal structure, guidance, control, material, sensor etc. are presented. The paper, ‘‘Quality Assurance and T&E of Inertial Systems for RLV Mission’’ describes the Quality assurance and Test and Evaluation (T&E) activities carried out for the inertial systems flown successfully. As part of reliability analysis, Failure Mode effect and Criticality Analysis (FMECA) and derating analysis are carried out in the initial design phase. Test data analysis, health parameter plotting and test report generation are automated. The automations significantly reduced the time required for these activities and helped to avoid manual errors. Further, T&E cycle is optimized without compromising on quality aspects. Meticulous planning and execution of T&E helped to achieve zero defect delivery of inertial systems. The paper, ‘‘Inertial Navigation System for India’s Reusable Launch Vehicle Technology Demonstrator (RLV TD—HEX) Mission’’ describes the configuration of Inertial Navigation System (INS) used in RLV TD Program. A new INS is designed, realised and qualified to meet the mission requirements of RLV TD. Additional redundancy in acceleration channel, in-built inclinometer based bias update scheme for acceleration channels and sign conventions as employed in aircrafts are introduced in new INS. For ascent phase control, data acquisition in micro cycle periodicity (10 ms) is incorporated which is required to provide rate and attitude information at higher sampling rate. Provision is incorporated for acquisition of rate and acceleration data with high resolution for aerodynamic characterisation and parameter estimation. GPS aided navigation scheme is incorporated to meet the stringent accuracy requirements of the Mission. The paper, ‘‘Mission Management Computer Software for RLV-TD’’ describes the functions and features of the components of the Mission Management Computer software. A hard real-time system is introduced for handling the mission requirements in an integrated manner and for meeting the stringent timing constraints. Redundancy management and faulttolerance techniques are also built into the system. It is introduced to achieve a successful mission even in presence of component failure. The paper, ‘‘Mission Management Computer and Sequencing Hardware for RLV-TDHEX-01 Mission’’ describes the details of mission critical avionics hardware mainly Mission Management Computer (MMC) and Sequencing hardware. The Navigation, & K. Sivan director@vssc.gov.in; k_sivan@vssc.gov.in

Special Theme: India’s Reusable Launch Vehicle Technology Demonstrator: The Future of Space Transportation System