By Editor
BENGALURU: Isro on Wednesday stated that the primary developmental flight of the small satellite tv for pc launch automobile (SSLV-D1) mission couldn’t be achieved on August 7, 2022, “attributable to an anomaly throughout the second stage (SS2) separation, which triggered a mission salvage mode — a process adopted to aim minimal stabilised orbital situations for the spacecraft in case of an anomaly within the automobile system.
“An in depth evaluation of the flight occasions and observations starting from countdown, lift-off, propulsion efficiency, stage separations and satellite tv for pc injection of SSLV-D1 revealed that there was a vibration disturbance for a brief period on the tools bay (EB) deck throughout SS2 separation, that affected the inertial navigation system (INS), leading to declaring the sensors defective by the logic in fault detection & isolation (FDI) software program,” the abstract of the failure evaluation committee (FAC) learn.
The SSLV makes use of a newly developed INS — the MEMS (Micro-electromechanical techniques) INS or MINS-6S — which consists of six MEMS gyros for measuring rotation charges and 6 ceramic servo accelerometers for measuring accelerations. The system can be designed with an in-built NavIC receiver and in addition acts because the MINS navigation pc processor for operating inertial navigation and aided navigation software program.
“A novel algorithm estimates the error within the orientation launched as a result of MEMS gyros, place and velocity of MEMS INS, utilizing NavIC knowledge and corrects them, in order that mission accuracy is achieved. Realizing the well being of accelerometers is paramount for the functioning of MINS, as it’s used for orientation aiding. The failure detection logic identifies degraded accelerometers (one or all 6) and isolates the identical for improved mission efficiency,” the abstract learn.
Throughout the SS2 separation occasion, all six accelerometers skilled measurement saturation attributable to excessive vibration ranges for a brief period, it added.
“The accelerometers acquired saturated at completely different time instants, inside 20 millisecond (ms) interval of knowledge sampling, which resulted in several acceleration values being measured by every sensor. This resulted in excessive residue values (distinction amongst them) past a specified restrict for a period of 2-seconds. The software program implementing FDI assessed that sensor outputs crossed pre-set threshold restrict and raised alert for salvage mode initiation, which is a security method for mission,” it learn.
Nonetheless, accelerometers had been discovered functioning nicely after this transient occasion. The salvage mission mode was totally executed with out the assist of accelerometer knowledge and the satellite tv for pc was injected to an unstable orbit attributable to decrease injection velocity (round 56m/s lower than the required 7,693 m/s).
“Although that is as programmed and anticipated, if stored observing for longer period, the residue among the many sensors could be inside restrict and failure logic wouldn’t have been executed,” the abstract added.
Shock & Vibrations
The FAC added that vibrations had been nicely inside pre-flight take a look at specs besides throughout SS2 separation when the EB and satellite tv for pc interface had dominant vibration response.
“The shock response measured at EB throughout SS2 separation exceeded expectations and groundtest ranges each in high and low frequency in addition to in time period. Resulting from this, excitation at MINS sensors was persistent for greater than 10 millisecond (ms) which was not anticipated. It’s typically noticed that shock from such occasions lasts for about 2ms,” the abstract learn.
Additional, primarily based on the flight telemetry knowledge, all accelerometers had been discovered functioning usually after the transient occasion until the tip of the mission, indicating no injury to them.
“Nonetheless, attributable to mission salvage setting by the FDI programme, knowledge from accelerometers weren’t used for additional mission execution,” it added.
Suggestions & Subsequent Flight
The FAC has beneficial corrections that embody: Change of separation system; modification of MINS FDI logic; technique of utilizing NavIC knowledge; holding Velocity Trimming Module (VTM) in loop for salvage mode and design modification of EB and satellite tv for pc meeting system together with VTM.
Isro stated: “SSLV-D1 mission demonstrated passable built-in efficiency of SSLV in all its techniques together with its flight by the aerodynamic regime, which is an accomplishment by itself. Contemplating clear identification of the reason for the flight anomaly and instructed corrective actions, the following growth flight (SSLV-D2) is deliberate to be executed complying to suggestions, its passable implementation, assessment and approval by the authorised committees.”
It added that the second developmental flight SSLV-D2 is scheduled within the first quarter of 2023 and can launch a complete payload mass of about 334kg, together with EOS-07 (an Earth remark satellite tv for pc) and two co-passenger satellites.
“An in depth evaluation of the flight occasions and observations starting from countdown, lift-off, propulsion efficiency, stage separations and satellite tv for pc injection of SSLV-D1 revealed that there was a vibration disturbance for a brief period on the tools bay (EB) deck throughout SS2 separation, that affected the inertial navigation system (INS), leading to declaring the sensors defective by the logic in fault detection & isolation (FDI) software program,” the abstract of the failure evaluation committee (FAC) learn.
The SSLV makes use of a newly developed INS — the MEMS (Micro-electromechanical techniques) INS or MINS-6S — which consists of six MEMS gyros for measuring rotation charges and 6 ceramic servo accelerometers for measuring accelerations. The system can be designed with an in-built NavIC receiver and in addition acts because the MINS navigation pc processor for operating inertial navigation and aided navigation software program.
“A novel algorithm estimates the error within the orientation launched as a result of MEMS gyros, place and velocity of MEMS INS, utilizing NavIC knowledge and corrects them, in order that mission accuracy is achieved. Realizing the well being of accelerometers is paramount for the functioning of MINS, as it’s used for orientation aiding. The failure detection logic identifies degraded accelerometers (one or all 6) and isolates the identical for improved mission efficiency,” the abstract learn.
Throughout the SS2 separation occasion, all six accelerometers skilled measurement saturation attributable to excessive vibration ranges for a brief period, it added.
“The accelerometers acquired saturated at completely different time instants, inside 20 millisecond (ms) interval of knowledge sampling, which resulted in several acceleration values being measured by every sensor. This resulted in excessive residue values (distinction amongst them) past a specified restrict for a period of 2-seconds. The software program implementing FDI assessed that sensor outputs crossed pre-set threshold restrict and raised alert for salvage mode initiation, which is a security method for mission,” it learn.
Nonetheless, accelerometers had been discovered functioning nicely after this transient occasion. The salvage mission mode was totally executed with out the assist of accelerometer knowledge and the satellite tv for pc was injected to an unstable orbit attributable to decrease injection velocity (round 56m/s lower than the required 7,693 m/s).
“Although that is as programmed and anticipated, if stored observing for longer period, the residue among the many sensors could be inside restrict and failure logic wouldn’t have been executed,” the abstract added.
Shock & Vibrations
The FAC added that vibrations had been nicely inside pre-flight take a look at specs besides throughout SS2 separation when the EB and satellite tv for pc interface had dominant vibration response.
“The shock response measured at EB throughout SS2 separation exceeded expectations and groundtest ranges each in high and low frequency in addition to in time period. Resulting from this, excitation at MINS sensors was persistent for greater than 10 millisecond (ms) which was not anticipated. It’s typically noticed that shock from such occasions lasts for about 2ms,” the abstract learn.
Additional, primarily based on the flight telemetry knowledge, all accelerometers had been discovered functioning usually after the transient occasion until the tip of the mission, indicating no injury to them.
“Nonetheless, attributable to mission salvage setting by the FDI programme, knowledge from accelerometers weren’t used for additional mission execution,” it added.
Suggestions & Subsequent Flight
The FAC has beneficial corrections that embody: Change of separation system; modification of MINS FDI logic; technique of utilizing NavIC knowledge; holding Velocity Trimming Module (VTM) in loop for salvage mode and design modification of EB and satellite tv for pc meeting system together with VTM.
Isro stated: “SSLV-D1 mission demonstrated passable built-in efficiency of SSLV in all its techniques together with its flight by the aerodynamic regime, which is an accomplishment by itself. Contemplating clear identification of the reason for the flight anomaly and instructed corrective actions, the following growth flight (SSLV-D2) is deliberate to be executed complying to suggestions, its passable implementation, assessment and approval by the authorised committees.”
It added that the second developmental flight SSLV-D2 is scheduled within the first quarter of 2023 and can launch a complete payload mass of about 334kg, together with EOS-07 (an Earth remark satellite tv for pc) and two co-passenger satellites.
