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Thermal Design, Analysis and Validation Plan of the Thermal Architecture for the SMILE Satellite Payload Module

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Thermal Design, Analysis and Validation Plan of the Thermal Architecture for the SMILE Satellite Payload Module ICES-2020-392 Thermal Design, Analysis and Validation Plan of the Thermal Architecture for the SMILE Satellite Payload Module Lorena del Amo Martín Airbus Defence and Space, Avenida de Aragón 404, Madrid, Spain, 28022 This document aims to provide a general description of the Payload Module concept for the SMILE satellite and a comprehensive description of the thermal design, analysis and future validation plan of the Thermal Architecture of the SMILE Satellite Payload Module (PLM), including the relevant thermal interfaces with the Platform and the Instruments. Nomenclature ASW = Application Software BOL = Begining of Life CAS = Chinise Academy of Sciences CCD = Charge Coupled Device CoG = Centre of Gravity EOL = End of Life ESA = European Space Agency FoV = Field Of View GMM = Geometrical Mathematical Model HEO = High Elliptical Orbit HW = Hardware IF = Interface LIA = Light Ion Analyzer MAG = Magnetometer MLI = Multi Layer Insulation PF = Platform PL = Payload PFM = Proto-Flight Model PLM = Payload Module ECU = Extended Control Unit PM = Propulsion Module RF = Radio Frequencies SC = Spacecraft SMILE = Solarwind Magnetosphere Ionosphere Link Explorer SSO = Sun Synchronous Orbit STM = Strucutural Thermal Model SVM = Service Module SXI = Soft X-ray Imager TCS = Thermal Control Subsystem TMM = Thermal Mathematical Model UVI = Ultraviolet Imager I. Introduction MILE (Solar wind Magnetosphere Ionosphere Link Explorer) is a collaborative science mission for the S investigation of the solar wind interaction with Earth magnetosphere in order to further understand the Sun- Earth connection. SMILE satellite would be launched into a High Elliptical Orbit (HEO) that would allow observing the specific regions in the near-Earth space where these interactions occur. The aim is to acquire several images and movies of the magnetopause, known as the boundary where the Earth's magnetosphere and the solar wind encounter and Copyright © 2020 Lorena del Amo Martín interact. SMILE mission will also study the polar cusps and the auroral oval, each of them occurring in each hemisphere. This project is a joint science mission between European Space Agency (ESA) and the Chinese Academy of Sciences (CAS) for which Phase CD activities are currently on-going. II. SMILE Satellite and Mission SMILE satellite consists of a Platform (PF) composed by the Propulsion Module (PM) and the Service Module (SVM), both provided by CAS, and a Payload Module (PLM), which is provided by ESA. The PLM accommodates SMILE scientific instruments, the PLM Control Unit and Power Unit, the memory and the X-band communication system. The PLM is located on the top of the PF and shares the baseplate with PF for mass saving purposes. The SMILE mission aims increasing our understanding of the connection between the interaction of the solar wind with the Earth’s magnetosphere. SMILE satellite will study the nose and polar cusps of the magnetosphere and the aurorae at the North Pole while simultaneously monitoring the in situ plasma environment. In particular, SMILE will: Investigate the dynamic response of the Earth’s magnetosphere to the solar wind impact in a unique and global manner Combine Solar Wind Charge eXchange X-ray imaging of the dayside magnetosheath and the cusps with simultaneous UV imaging of the Earth’s northern aurora, while monitoring the solar wind conditions in situ The chain of events that drive Sun-Earth relationships Two orbit options have been proposed to maximize the possible launcher candidates, and both the PF and the PLM design shall be compatible with them: Option 1: (shared launch on Soyuz or A62): injection into a 700 km circular SSO and argument of perigee 287.5 degrees. Then transfer to a HEO of 5000 km x 121000 km with inclination and argument of perigee identical to injection orbit. Figure 1. SMILE PLM Concept. - Option1.1: RAAN of final science operations orbit = 0 degrees (baseline) - Option 1.2: RAAN of final science operations orbit = 165 degrees (back-up) Option 2 (VEGA-C): injection into a 700 km circular orbit with inclination of 70 degrees and argument of perigee 287.5 degrees. Then, transfer to a HEO of 5000 km x 121000 km with inclination and argument of perigee identical to injection orbit. RAAN of final science operations orbit = 206 degrees. III. SMILE Payload Module Design SMILE PLM concept is based on a supporting baseplate, shared with the SVM, with a configuration that optimizes the FoV of the three Instruments SXI, UVI and MAG and that houses all the units for the PLM operations.The SMILE payload consists of four instruments: Soft X-ray Imager (SXI): Capable of imaging the interaction between the solar wind and Earth’s magnetic field. The development is under ESA lead. The Ultra Violet Imager (UVI): Capable of simultaneously imaging the entire northern auroral oval. The development is under ESA lead. Magnetometer (MAG): Capable of measuring the in-situ magnetic field. The development is under CAS lead. Light Ion Analyzer (LIA): Capable of measuring in-situ ions in all relevant parts of the orbit. The development is under CAS lead. LIA is currently located on the SVM. Therefore, no thermal analysis is being performed concerning LIA instrument at PLM level. 2 International Conference on Environmental Systems The three instruments are integrated within the SMILE Payload Module on an Al-honeycomb support panelmtogether with the following set of equipment which support the full operation of the instruments: PLM Extended Control Unit (PLM-ECU): Contains the processing resources for the flight mission software and the interfaces with the SVM central computer. It supports the communications (command and control) of the rest of PLM units (including instruments). It also includes the Power Distribution Unit in charge of managing the PLM power distribution network. It also accounts for the Mass Memory Unit providing permanent storage for all data susceptible of being downloaded to Ground, i.e. SVM, PLM and instruments house keeping data and instruments scientific data. X-Band Subsystem: Routes to Ground all PLM data coming from the PLM-ECU. Composed of the X-Band Antenna and a set of transceivers. Thermal Control Subsystem (TCS): Assures the temperature ranges (operational/non-operational) at every PLM unit interface. Harness Subsystem (power, signal and RF coax). IV. SMILE PLM Thermal Architecture The Thermal Architecture is in charge of providing the PLM (including the instruments and the interfaces with the SVM) with the necessary means, functions and support to achieve the requested science performances by maintaining appropriate thermal conditions (temperature ranges, thermal stability and gradients, among others) for all the mission phases and operating conditions. The PLM thermal design concept, for what concerns the interface with the Platform due to the sharing concept, will be based on thermal decoupling from the PF thermal environment. The interface couplings (conductive and radiative) will need to be minimised by design to a suitable level and verified by analysis. The PLM is responsible of the thermal control of all PLM equipment except during mission-level safe mode (or PLM OFF), with the exception of the sensor part of the instruments. For the Instruments, the PLM controls the interface temperatures and provides the routing of harness needed for their internal thermal control. The PLM provides also thermistors for monitoring purposes, to be acquired directly by the PF when PLM is OFF. The instruments pointing constraints define an attitude of the satellite leading to privileged direction for radiators location on +X side, since it is always pointed towards the anti-sun direction. +Y/-Y sides are also very good candidates to act as radiators since they are always kept in shadows in nominal operation, and the only external heat input is due to the radiative coupling with the solar array and other protruding elements from the Platform. As a baseline, radiators will be aluminium plates (to protect also the PLM equipment versus radiation) with a high emissivity coating. A heat pipe network collects the heat dissipated by the different PLM thermally coupled electronic units and transfers it to the radiator areas in +X and –Y sides. This solution offers the following advantages compared to a design based on doublers or straps: It is very flexible in terms of accommodation of equipment, allowing future modifications in the units location, and very efficient in terms of heat transport capability and radiator heat rejection capability. Due to the efficiency in the heat pipes heat transport, generating almost no gradients between the equipment and the radiators, the impact in mass of this solution is lower compared to a design based on straps or doublers, in which larger radiators are needed due to the gradient generated between the equipment and the radiators. It homogenizes the temperature of the different equipment for the different operational modes; minimizing the heaters power consumption for instrument electronic units (heat dissipated by ON units is transmitted to OFF units). The heat pipe network solution imposes a limitation to the testing configuration of the PLM. For the heat pipes to perform properly, the condenser shall always be located in the same plane of the evaporator (no gravity assistance), or above the evaporator (gravity assisting to the return of the condensed fluid). For the PLM configuration, the possible test orientations are with the gravity oriented towards the –Z PLM axis, or with the gravity oriented towards the –X PLM axis. This limitation is perfectly compatible with the foreseen test orientations both at PLM and SC level. PLM thermally coupled units have been grouped according to their design temperature ranges, in order to minimize the heater power consumption for non-operational modes. Instrument back-end electronics have been grouped together and connected to the –Y radiator, and PLM avionics have been grouped together and connected to the +X radiator. 3 International Conference on Environmental Systems As a baseline, PLM radiators will be 2 mm thickness (minimum) aluminium plates (to protect the PLM equipment versus radiation) with a high emissivity coating externally.
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