Session
Session 2: Next on the Pad
Abstract
This work presents the adaptation of MYRIADE satellite to the mission TARANIS. The particularity of this mission is the 8 instruments embedded, in various area of science: : electro-magnetic detection instrument, optical detection and radiation detector. This heterogeneity has strong impact on satellite design, and moreover on an existing platform. First adaptation was made on mechanical structure to accept a 200kg satellite, instead of 130 kg previously, in perimeter of launcher constraint, which was a small allocated volume and stronger random vibration level. Second adaptation was the power budget design. Maximum capacity of MYRIADE satellite was around 100W for all satellite, and payload was expected 70W of consumption. This high consumption required to reduce severely all margin historically taken (on system, on thermal control) and to have a strong payload consumption follow up with the scientific instrument’s designers. Thirdly, the compactness and sensibility of payload require a specific design of harness payload and also a stronger test campaign on EM model for testing the payload auto-compatibility. Finally, 8 instruments require a synchronization of 1ms with the ground. This level of performance forced to adapt MYRIADE dating performance from 15ms to 1ms in adding new counter and new oscillator compensation algorithm.
TARANIS: Myriade Small Satellite for TLE Observation, 8 Instruments Challenge.
This work presents the adaptation of MYRIADE satellite to the mission TARANIS. The particularity of this mission is the 8 instruments embedded, in various area of science: : electro-magnetic detection instrument, optical detection and radiation detector. This heterogeneity has strong impact on satellite design, and moreover on an existing platform. First adaptation was made on mechanical structure to accept a 200kg satellite, instead of 130 kg previously, in perimeter of launcher constraint, which was a small allocated volume and stronger random vibration level. Second adaptation was the power budget design. Maximum capacity of MYRIADE satellite was around 100W for all satellite, and payload was expected 70W of consumption. This high consumption required to reduce severely all margin historically taken (on system, on thermal control) and to have a strong payload consumption follow up with the scientific instrument’s designers. Thirdly, the compactness and sensibility of payload require a specific design of harness payload and also a stronger test campaign on EM model for testing the payload auto-compatibility. Finally, 8 instruments require a synchronization of 1ms with the ground. This level of performance forced to adapt MYRIADE dating performance from 15ms to 1ms in adding new counter and new oscillator compensation algorithm.
