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Inertial Navigation System for India’s Reusable Launch Vehicle-Technology Demonstrator (RLV-TD HEX) Mission
Abstract This work presents the configuration of Inertial Navigation System (INS) used in India’s Reusable Launch Vehicle-Technology Demonstrator (RLV-TD) Program. In view of the specific features and requirements of the RLV-TD, specific improvements and modifications were required in the INS. A new system was designed, realised and qualified meeting the mission requirements of RLV-TD, at the same time taking advantage of the flight heritage attained in INS through various Launch vehicle Missions of the country. The new system has additional redundancy in acceleration channel, in-built inclinometer based bias update scheme for acceleration channels and sign conventions as employed in an aircraft. Data acquisition in micro cycle periodicity (10 ms) was incorporated which was required to provide rate and attitude information at higher sampling rate for ascent phase control. Provision was incorporated for acquisition of rate and acceleration data with high resolution for aerodynamic characterisation and parameter estimation. GPS aided navigation scheme was incorporated to meet the stringent accuracy requirements of the mission. Navigation system configuration for RLV-TD, specific features incorporated to meet the mission requirements, various tests carried out and performance during RLV-TD flight are highlighted.
Inertial Navigation System for India’s Reusable Launch Vehicle-Technology Demonstrator (RLV-TD HEX) Mission
Abstract This work presents the configuration of Inertial Navigation System (INS) used in India’s Reusable Launch Vehicle-Technology Demonstrator (RLV-TD) Program. In view of the specific features and requirements of the RLV-TD, specific improvements and modifications were required in the INS. A new system was designed, realised and qualified meeting the mission requirements of RLV-TD, at the same time taking advantage of the flight heritage attained in INS through various Launch vehicle Missions of the country. The new system has additional redundancy in acceleration channel, in-built inclinometer based bias update scheme for acceleration channels and sign conventions as employed in an aircraft. Data acquisition in micro cycle periodicity (10 ms) was incorporated which was required to provide rate and attitude information at higher sampling rate for ascent phase control. Provision was incorporated for acquisition of rate and acceleration data with high resolution for aerodynamic characterisation and parameter estimation. GPS aided navigation scheme was incorporated to meet the stringent accuracy requirements of the mission. Navigation system configuration for RLV-TD, specific features incorporated to meet the mission requirements, various tests carried out and performance during RLV-TD flight are highlighted.
Inertial Navigation System for India’s Reusable Launch Vehicle-Technology Demonstrator (RLV-TD HEX) Mission
Umadevi, P. (Autor:in) / Navas, A. (Autor:in) / Karuturi, Kesavabrahmaji (Autor:in) / Shukkoor, A. Abdul (Autor:in) / Kumar, J. Krishna (Autor:in) / Sreekumar, Sreejith (Autor:in) / Basim, A. Mohammed (Autor:in)
Journal of The Institution of Engineers (India): Series C ; 98 ; 689-696
24.10.2017
8 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
| Springer Verlag | 2017
Configuration and Design of Checkout System for Reusable Launch Vehicle
| Springer Verlag | 2017
Configuration and Design of Checkout System for Reusable Launch Vehicle
| Online Contents | 2017