ISSUE : 1 Page : 2/35 CHANGE RECORDS ISSUE DATE DESCRIPTION OF CHANGES AUTHOR 1 03/10/07 Initial issue (MTG-TAF-SA-RS-39) J. VIEILLOT 1 20/09/10 Updated version for kick off : L.OUCHET New reference (MTG-TAF-SA-SS-0039) AD/ND numbering Substitution of UVS by UVN Substitution of FTS by IRS Introduction of DCS & GEOSAR, and RMU as modules : Thermal models organization tables 3.1 & 3.2 External radiative surfaces allocations tables 5.1 & 5.2 Thermal node allocation tables 6.1 & 6.2 Thermal node numbering tables 6.3 & 6.4 Interface nodes definition and numbering tables 6.5 & 6.6 Reference test case definition table 7.1
ISSUE : 1 Page : 3/35 TABLE OF CONTENT 1. INTRODUCTION AND SUMMARY... 7 2. DOCUMENTARY REFERENCE SYSTEM... 8 2.1 Applicable documents...8 2.2 Applicable norms and standards...8 2.3 Reference documents...8 2.4 Acronyms...8 3. MTG THERMAL MODEL ARCHITECTURE... 9 3.1 Hierarchy of the thermal models...9 3.2 Applicability of the specification...9 4. GENERAL REQUIREMENTS... 12 4.1 General statements...12 4.2 Unit system...12 4.3 Softwares...13 5. SPECIFIC REQUIREMENTS FOR GEOMETRICAL MODELS... 14 5.1 Geometrical model identification...14 5.2 Reference axis and origin...14 5.3 Radiative surface allocation...14 5.4 Geometrical model construction and verification...15 6. SPECIFIC REQUIREMENTS FOR THERMAL MODELS... 17 6.1 Thermal model identification and commenting...17 6.2 Thermal node allocation and numbering...18 6.3 Interface node identification...19 6.4 Thermal model construction and verification...23 6.5 Specific requirements for equipment (appendices/units) thermal model...24
ISSUE : 1 Page : 4/35 7. VALIDATION OF REDUCED THERMAL MODEL... 26 8. THERMAL MODEL AND DOCUMENTATION DELIVERY... 28 9. ANNEX... 30 LIST OF APPENDICES APPENDICES : 1. REQUIREMENTS APPLICABILLITY MATRIX...31 APPENDICES : 2. SATELLITES OVERVIEW...33 LIST OF TABLES TABLE 3-1 ORGANIZATION OF MTG-I THERMAL MODELS...10 TABLE 3-2 ORGANIZATION OF MTG-S THERMAL MODELS...11 TABLE 5-1: EXTERNAL RADIATIVE SURFACE ALLOCATION FOR MTG-I MODELS...15 TABLE 5-2: EXTERNAL RADIATIVE SURFACE ALLOCATION FOR MTG-S MODELS...15 TABLE 6-1: THERMAL NODE ALLOCATION FOR MTG-I...18 TABLE 6-2: THERMAL NODE ALLOCATION FOR MTG-S...18 TABLE 6-3: THERMAL NODE NUMBERING SPECIFICATION FOR MTG-I...19 TABLE 6-4: THERMAL NODE NUMBERING SPECIFICATION FOR MTG-S...19 TABLE 6-5: INTERFACE NODE DEFINITION AND NUMBERING FOR MTG-I...21 TABLE 6-6: INTERFACE NODE DEFINITION AND NUMBERING FOR MTG-S...23 TABLE 7-1: REFERENCE TEST CASE DEFINITION FOR REDUCED MODEL VALIDATION...26 LIST OF FIGURES FIGURE 1 : MTG-I SATELLITE DEPLOYED...33 FIGURE 2 : MTG-I SATELLITE STOWED...33 FIGURE 3 : MTG-S SATELLITE DEPLOYED...34 FIGURE 4 : MTG-S SATELLITE STOWED...34
ISSUE : 1 Page : 5/35 LIST OF REQUIREMENTS REFERENCE MTG-SC-TCS-TMM-005...9 REFERENCE MTG-SC-TCS-TMM-010...12 REFERENCE MTG-SC-TCS-TMM-015...12 REFERENCE MTG-SC-TCS-TMM-020...12 REFERENCE MTG-SC-TCS-TMM-025...13 REFERENCE MTG-SC-TCS-TMM-030...13 REFERENCE MTG-SC-TCS-TMM-035...14 REFERENCE MTG-SC-TCS-TMM-040...14 REFERENCE MTG-SC-TCS-TMM-045...14 REFERENCE MTG-SC-TCS-TMM-050...14 REFERENCE MTG-SC-TCS-TMM-055...15 REFERENCE MTG-SC-TCS-TMM-060...15 REFERENCE MTG-SC-TCS-TMM-065...16 REFERENCE MTG-SC-TCS-TMM-070...16 REFERENCE MTG-SC-TCS-TMM-075...16 REFERENCE MTG-SC-TCS-TMM-080...17 REFERENCE MTG-SC-TCS-TMM-085...17 REFERENCE MTG-SC-TCS-TMM-090...17 REFERENCE MTG-SC-TCS-TMM-095...17 REFERENCE MTG-SC-TCS-TMM-100...18 REFERENCE MTG-SC-TCS-TMM-105...18 REFERENCE MTG-SC-TCS-TMM-110...18 REFERENCE MTG-SC-TCS-TMM-115...19 REFERENCE MTG-SC-TCS-TMM-120...19 REFERENCE MTG-SC-TCS-TMM-125...23 REFERENCE MTG-SC-TCS-TMM-130...23 REFERENCE MTG-SC-TCS-TMM-135...23 REFERENCE MTG-SC-TCS-TMM-140...23 REFERENCE MTG-SC-TCS-TMM-142...23 REFERENCE MTG-SC-TCS-TMM-145...24 REFERENCE MTG-SC-TCS-TMM-150...24 REFERENCE MTG-SC-TCS-TMM-155...24
ISSUE : 1 Page : 6/35 REFERENCE MTG-SC-TCS-TMM-160...24 REFERENCE MTG-SC-TCS-TMM-165...24 REFERENCE MTG-SC-TCS-TMM-170...25 REFERENCE MTG-SC-TCS-TMM-175...26 REFERENCE MTG-SC-TCS-TMM-180...26 REFERENCE MTG-SC-TCS-TMM-185...26 REFERENCE MTG-SC-TCS-TMM-190...28 REFERENCE MTG-SC-TCS-TMM-195...28 REFERENCE MTG-SC-TCS-TMM-200...28 REFERENCE MTG-SC-TCS-TMM-205...28 REFERENCE MTG-SC-TCS-TMM-210...28 REFERENCE MTG-SC-TCS-TMM-215...28 REFERENCE MTG-SC-TCS-TMM-220...29
ISSUE : 1 Page : 7/35 1. INTRODUCTION AND SUMMARY This specification identifies all the requirements concerning the detailed and reduced thermal mathematical models to be delivered by the module and equipment supplier to the MTG prime contractor. It includes: the Geometrical Mathematical Models (GMM) used for the generation of the radiative couplings and the absorbed environment heat fluxes and the Thermal Mathematical Models (TMM) used for the generation of temperatures and energy balance
ISSUE : 1 Page : 8/35 2. DOCUMENTARY REFERENCE SYSTEM 2.1 Applicable documents Title Reference Issue Date AD-33C MTG General Design & Interface Requirements To be issued in Phase B AD-26C List of acronyms and abbreviations To be issued in Phase B 2.2 Applicable norms and standards Title Reference Issue Date ND-13 Thermal Control ECSS-E-ST-31C ND-55 Soyuz from the Guiana Space Issue 1 Rev. 0 1.0 June 2006 Centre User s Manual ND-54 Ariane 5 User s Manual Issue 5 Rev. 0 4.0 Jul 2008 Arianespace - Technical A4-SG-1 3 01/10/92 Specification for the Payload Thermal Model ND-56 Proton Launch System Mission Planner's Guide Revision 6 6 Dec 2004 2.3 Reference documents 2.4 Acronyms See AD-26C
ISSUE : 1 Page : 9/35 3. MTG THERMAL MODEL ARCHITECTURE 3.1 Hierarchy of the thermal models Three different levels are defined for the thermal mathematical models to be used on MTG programme. Level 1 : Satellite level Level 2 : Module level It includes the models for platform, instruments and payloads Level 3 : Equipment level It includes the models for external appendices such as Star trackers, Thrusters, Antennas, Sensors, Solar array and internal dissipative units. Different types of models are defined according to their objective. Detailed model : This model is used by the subcontractor to establish the thermal design of the assembly under his responsibility. If this model has to be delivered to the prime contractor, it shall be compliant with the requirements of this document. Reduced model : This model is used at an upper level, introduced into a bulk thermal model. It allows representing the thermal interfaces of the concerned element. It has to be compliant with the requirements of this document and has to be delivered to the prime contractor according to chapter 8. This model shall be correlated with the detailed element model from which it has been reduced following requirements of chapter 7. Coupled Launch Analysis model : This model is delivered to the launcher authority to perform the satellite/launcher thermal coupled analyses. It has to be compliant with the requirements defined by the launcher authority. This model shall be correlated with the detailed satellite model from which it has been reduced following requirements of chapter 7. 3.2 Applicability of the specification Reference MTG-SC-TCS-TMM-005 This specification shall be applied to non-homogenous (in temperature) modules and equipements, and is applicable for the delivery of the following models: Modules (PF, instruments, payload) : Platform
ISSUE : 1 Page : 10/35 FCI main unit IRS LI UVN DCS and GEOSAR RMU Equipments : External appendices Antennae Sensors Solar array Star trackers Thrusters Internal units Dissipative units RW isolators The organisation of the thermal models and their denomination is given in Table 3-1 and Table 3-2. Level 1 Level 2 Level 3 Model definition MTG-I MTG-I Satellite thermal model PF-I MTG-I Platform thermal model Units Units thermal model Appendices Appendices thermal model FCI main unit FCI main unit thermal model Units Units thermal model LI LI thermal model Units Units thermal model DCS & DCS and GEOSAR thermal model GEOSAR Units Units thermal model Appendices Appendices thermal model RMU RMU RMU thermal model Table 3-1 Organization of MTG-I thermal models
ISSUE : 1 Page : 11/35 Level 1 Level 2 Level 3 Model definition MTG-S MTG-S Satellite thermal model PF-S MTG-S Platform thermal model Units Units thermal model Appendices Appendices thermal model IRS IRS thermal model Units Units thermal model UVN UVN thermal model Units Units thermal model RMU RMU RMU thermal model Table 3-2 Organization of MTG-S thermal models
ISSUE : 1 Page : 12/35 4. GENERAL REQUIREMENTS 4.1 General statements Reference MTG-SC-TCS-TMM-010 The satellite, the module and the equipment Geometrical and Thermal Mathematical Models (GMM and TMM) shall allow performing separate as well as combined thermal analysis by mating the individual GMMs and TMMs. Annex 5 of ND-14 provides the recommended approach on thermal analysis. Major deviations between ND-14 and contractor preferred approach shall be highlighted for discussion and agreement with the agency. Reference MTG-SC-TCS-TMM-015 Reduced GMM and TMM of the satellite, the module shall be established to enable the Launcher Authority to perform coupled launcher/satellite thermal analysis. They shall be established following the requirements of the Launcher Authority : ARIANE5 launcher : see ND-54 SOYUZ launcher : see ND-55 PROTON launcher : see ND-56 4.2 Unit system Reference MTG-SC-TCS-TMM-020 TMM and GMM shall only use the International System of Units (SI units) with the following basic units: Length meter (m) Mass kilogram (kg) Time second (s) Temperature Celsius ( C) Heat dissipation Watt (W) Heat capacity joule per Celsius (J/ C) Conductive coupling Watt per Celsius (W/ C) Radiative coupling square meter (m²)
ISSUE : 1 Page : 13/35 4.3 Softwares Reference MTG-SC-TCS-TMM-025 The satellite, the module and the equipment Geometrical and Thermal Mathematical Models (GMM and TMM) shall be established in ESARAD version 6.2 and ESATAN version 10.2 under LINUX platform. Use of other S/W codes is only acceptable if previously agreed with the Agency and the prime contractor. Reference MTG-SC-TCS-TMM-030 All updated versions of ESARAD and ESATAN shall be approved at ESA and prime contractor level before any use for GMM and TMM to be delivered to the prime contractor.
ISSUE : 1 Page : 14/35 5. SPECIFIC REQUIREMENTS FOR GEOMETRICAL MODELS 5.1 Geometrical model identification Reference MTG-SC-TCS-TMM-035 In order to facilitate the management of the different models, ESARAD input and associated files shall be named as follow : NAMETUXX.TYP_ZZ with: NAME is the generic name of the model (see Tables 3.1 & 3.2) T represents the type of model o D for detailed model o R for reduced model o L for Coupled Launch Analysis model U represents the model configuration (for example O for operational configuration, L for launch configuration, T for transfer orbit configuration) XX is the version number of the model (for example 01 for the 1st version) TYP is the type file as defined by ESARAD (for example ERG for geometry model creation, ERK for calculation case definition) ZZ represents the enclosure number 5.2 Reference axis and origin Reference MTG-SC-TCS-TMM-040 The overall geometry of each module or equipment shall be defined relative to its own reference frame as defined in AD-33C. Reference MTG-SC-TCS-TMM-045 If not defined in AD-33C, the origin of the module or unit axis system shall be its mechanical reference point and the axis will be parallel and oriented in the same direction as satellite axis defined in AD-33C. 5.3 Radiative surface allocation Reference MTG-SC-TCS-TMM-050 The size of the external geometrical models to be delivered to the prime contractor, for incorporation into the satellite reduced and launch coupled analysis models, shall be limited. The maximal number of radiative surfaces allowed for each external geometrical model is defined in following Table 5-1 and Table 5-2.
ISSUE : 1 Page : 15/35 Model definition Max number of external radiative surfaces for satellite reduced thermal model Max number of external radiative surfaces for coupled launch analysis model PF-I thermal model 1000 TBC 500 TBC FCI main unit thermal model 1100 TBC 200 TBC LI thermal model 400 TBC 100 TBC DCS and GEOSAR model 200 TBC 50 TBC RMU model 50 TBC 10 TBC Total satellite 2750 860 Model definition Table 5-1: External radiative surface allocation for MTG-I models Max number of external radiative surfaces for satellite reduced thermal model Max number of external radiative surfaces for coupled launch analysis model PF-S thermal model 1000 TBC 500 TBC IRS thermal model 1000 TBC 200 TBC UVN thermal model 400 TBC 100 TBC RMU model 50 TBC 10 TBC Total satellite 2450 810 Table 5-2: External radiative surface allocation for MTG-S models 5.4 Geometrical model construction and verification Reference MTG-SC-TCS-TMM-055 Each ESARAD file shall correspond to a single radiative enclosure and shall be identified as defined in 5.1. Reference MTG-SC-TCS-TMM-060 The convergence of the model shall be checked. In particular, the geometrical calculation parameters (for example number of rays) shall be selected to have an acceptable independence of the temperature results with regard to these parameters.
ISSUE : 1 Page : 16/35 Reference MTG-SC-TCS-TMM-065 Any automatic or manual treatment of the results from radiative calculation software, such as specific GR deletion or trimming area coefficients, before using as ESATAN file inputs shall be fully and clearly documented. Reference MTG-SC-TCS-TMM-070 Computation of external fluxes for equipment with moving parts and submitted to flux inputs will take into account unit motion and associated motion control law. Any deviation shall be approved at ESA and prime contractor level. Reference MTG-SC-TCS-TMM-075 Computation of radiative exchanges for equipment with moving parts will take into account unit motion and associated motion control law. Any deviation shall be approved at ESA and prime contractor level.
ISSUE : 1 Page : 17/35 6. SPECIFIC REQUIREMENTS FOR THERMAL MODELS 6.1 Thermal model identification and commenting Reference MTG-SC-TCS-TMM-080 In order to facilitate the management of the different models, ESATAN input and associated files shall be named as follow : NAMETUXX.TYP_REF with: NAME is the generic name of the model (see Table 3-1 and Table 3-2) T represents the type of model o D for detailed model o R for reduced model o L for Coupled Launch Analysis model U represents the model configuration (for example O for operational configuration, L for launch configuration) XX is the version number of the model (for example 01 for the 1st version) TYP is the type file as defined by ESATAN (for example D for model input file, OUT for computation output file) REF is a unique identifier for each thermal analysis case Reference MTG-SC-TCS-TMM-085 In order to ensure the compatibility between the analyses performed at the different levels, each model shall be clearly identified with a comment header using following rules: The first comment shall give the name of the model, the original date of creation and the author s name Then, the purpose of the model shall be clearly stated Then, each version of the model shall be clearly described with version number, date, author s name and a brief description of the modification Reference MTG-SC-TCS-TMM-090 The here above rules for comment header block shall also be applied for any sub-model, subroutine or function. Reference MTG-SC-TCS-TMM-095 All modifications of the thermal model shall be identified as specified in the here above rules.
ISSUE : 1 Page : 18/35 Reference MTG-SC-TCS-TMM-100 The model version identification shall use two digits (for example version 1.2). The fist digit stands for major changes (mainly concerning thermal assumptions) The second digit is used for other changes of the model even if theses modification lead to significantly different results Reference MTG-SC-TCS-TMM-105 Any comment shall use the English language. 6.2 Thermal node allocation and numbering Reference MTG-SC-TCS-TMM-110 The size of the reduced thermal models to be delivered to the prime contractor shall be limited. The maximal number of thermal nodes allowed for each reduced model is defined in Table 6-1 and Table 6-2. Model definition Max number of thermal nodes for satellite reduced thermal model Max number thermal nodes for coupled launch analysis model MTG-I Platform thermal model 1500 TBC 150 TBC FCI main unit thermal model 1500 TBC 100 TBC LI thermal model 500 TBC 50 TBC DCS and GEOSAR 200 TBC 50 TBC RMU 50 TBC 5 TBC Total satellite 3750 455 Model definition Table 6-1: Thermal node allocation for MTG-I Max number of thermal nodes for satellite reduced thermal model Max number thermal nodes for coupled launch analysis model MTG-S Platform thermal model 1500 TBC 150 TBC IRS thermal model 1500 TBC 100 TBC UVN thermal model 500 TBC 50 TBC RMU 50 TBC 5 TBC Total satellite 3550 405 Table 6-2: Thermal node allocation for MTG-S
ISSUE : 1 Page : 19/35 Reference MTG-SC-TCS-TMM-115 The numbering of the thermal nodes (applicable to detailed, reduced and coupled models) shall follow the numbering range specified in Table 6-3 and Table 6-4. Model definition Numbering range MTG-I platform thermal 1 to 19999 model FCI main unit thermal model 20000 to 29999 LI thermal model 30000 to 39999 DCS & GEOSAR 40000 to 49999 RMU 50000 to 59999 Interface nodes 60000 to 69999 Space 99999 Table 6-3: Thermal node numbering specification for MTG-I Model definition Numbering range MTG-S platform thermal 1 to 19999 model IRS thermal model 20000 to 29999 UVN thermal model 30000 to 39999 RMU 50000 to 59999 Interface nodes 60000 to 69999 Space 99999 Table 6-4: Thermal node numbering specification for MTG-S 6.3 Interface node identification Reference MTG-SC-TCS-TMM-120 The definition and numbering of the interface nodes used for the different models shall be as specified in Table 6-5 and Table 6-6.
ISSUE : 1 Page : 20/35 Concerned model Platform I thermal model FCI main unit thermal model LI thermal model I/F definition I/F node number FCI mounting panel / PF earth panel In range 60000 to 60099 conductive coupling FCI sunshade / PF earth panel In range 60100 to 60199 conductive coupling FCI mounting panel / PF earth panel In range 60200 to 60299 MLI radiative coupling (one node per FCI cavity) FCI / satellite external area In range 60300 to 60399 Radiative couplings (one node per FCI external area) (MLIs, solar baffle, radiators ) LI mounting panel / PF earth panel In range 60400 to 60499 conductive coupling LI sunshield / PF earth panel In range 60500 to 60599 conductive coupling LI mounting panel / PF earth panel In range 60600 to 60699 MLI radiative coupling (one node per LI cavity) LI / satellite external area In range 60700 to 60799 Radiative couplings (one node per LI external area) (MLIs, solar baffle, radiators ) DCS and GEOSAR / PF earth panel In range 60800 to 60849 Conductive coupling DCS and GEOSAR / satelllite external In range 60850 to 60899 area (one node per external area) Radiative coupling RMU / PF earth panel In range 60900 to 60949 Conductive coupling RMU / satellite external area In range 60950 to 60999 radiative coupling (one node per external area) FCI mounting panel / PF earth panel In range 61000 to 61099 conductive coupling FCI sunshade / PF earth panel In range 61100 to 61199 conductive coupling FCI mounting panel / PF earth panel In range 61200 to 61299 MLI radiative coupling (one node per FCI cavity) FCI / satellite external area In range 61300 to 61399 Radiative couplings (one node per FCI external area) (MLIs, solar baffle, radiators ) LI mounting panel / PF earth panel In range 62400 to 62499 conductive coupling LI sunshield / PF earth panel In range 62500 to 62599 conductive coupling LI mounting panel / PF earth panel In range 62600 to 62699 MLI radiative coupling (one node per LI cavity) LI / satellite external area In range 62700 to 62799
ISSUE : 1 Page : 21/35 DCS & GEOSAR thermal model RMU thermal model Radiative couplings (MLIs, solar baffle, radiators ) DCS and GEOSAR / PF earth panel Conductive coupling DCS and GEOSAR / satelllite external area Radiative coupling RMU / PF earth panel Conductive coupling RMU / satellite external area radiative coupling (one node per LI external area) In range 63800 to 63849 In range 63850 to 63899 (one node per external area) In range 64900 to 64949 In range 64950 to 64999 (one node per external area) Table 6-5: Interface node definition and numbering for MTG-I
ISSUE : 1 Page : 22/35 Concerned model Platform S thermal model IRS thermal model UVN thermal model RMU thermal model I/F definition I/F node number IRS mounting panel / PF earth panel In range 60000 to 60099 conductive coupling IRS sunshade / PF earth panel In range 60100 to 60199 conductive coupling IRS mounting panel / PF earth panel In range 60200 to 60299 MLI radiative coupling (one node per FCI cavity) IRS / satellite external area In range 60300 to 60399 Radiative couplings (one node per FCI external area) (MLIs, solar baffle, radiators ) UVN mounting panel / PF earth panel In range 60400 to 60499 conductive coupling UVN sunshield / PF earth panel In range 60500 to 60599 conductive coupling UVN mounting panel / PF earth panel In range 60600 to 60699 MLI radiative coupling (one node per LI cavity) UVN / satellite external area In range 60700 to 60799 Radiative couplings (one node per LI external area) (MLIs, solar baffle, radiators ) RMU / PF earth panel In range 60900 to 60949 Conductive coupling RMU / satellite external area In range 60950 to 60999 radiative coupling (one node per external area) IRS mounting panel / PF earth panel In range 61000 to 61099 conductive coupling IRS sunshade / PF earth panel In range 61100 to 61199 conductive coupling IRS mounting panel / PF earth panel In range 61200 to 61299 MLI radiative coupling (one node per FCI cavity) IRS / satellite external area In range 61300 to 61399 Radiative couplings (one node per FCI external area) (MLIs, solar baffle, radiators ) UVN mounting panel / PF earth panel In range 62400 to 62499 conductive coupling UVN sunshield / PF earth panel In range 62500 to 62599 conductive coupling UVN mounting panel / PF earth panel In range 62600 to 62699 MLI radiative coupling (one node per LI cavity) UVN / satellite external area In range 62700 to 62799 Radiative couplings (one node per LI external area) (MLIs, solar baffle, radiators ) RMU / PF earth panel In range 64900 to 64949 Conductive coupling RMU / satellite external area In range 64950 to 64999
ISSUE : 1 Page : 23/35 radiative coupling (one node per external area) Table 6-6: Interface node definition and numbering for MTG-S 6.4 Thermal model construction and verification Reference MTG-SC-TCS-TMM-125 To facilitate the understanding of the thermal models, the thermal data belonging to a common set shall be grouped and clearly identified with comment lines. For example: Conductive couplings Conductive couplings through MLI s GL(..,..).. Conductive couplings inside structure GL(..,..).. Reference MTG-SC-TCS-TMM-130 To facilitate the understanding of the thermal models, the thermal data belonging to a common set shall be as far as possible defined in dedicated files and incorporated in the ESATAN thermal model by INCLUDE instruction. Reference MTG-SC-TCS-TMM-135 The definition of nodes with a low ratio of thermal capacity to conductance shall be avoided in order to limit the computation time for transient cases. Reference MTG-SC-TCS-TMM-140 The coupled launch analysis thermal model shall include the internal/external convective couplings and the specific MLI blanket efficiency relative to the on ground and under launcher fairing conditions. Reference MTG-SC-TCS-TMM-142 The coupled launch analysis thermal model shall be built considering the solar array panels and antennae in a stowed configuration (launch configuration).
ISSUE : 1 Page : 24/35 Reference MTG-SC-TCS-TMM-145 When using an interpolation table giving a physical property values as a function of temperature, all computed temperatures shall be within the temperature range of this table. Reference MTG-SC-TCS-TMM-150 For the condensed version of sub-models, the solution routines and associated control parameters used for steady states and transient cases shall be submitted to prime contractor approval in order to ensure consistent temperature results with the overall satellite model and sub-models. Reference MTG-SC-TCS-TMM-155 It shall be possible to activate at an upper level any specific tool used at lower level for model creation or evaluation when not included in the ESATAN library. Reference MTG-SC-TCS-TMM-160 The temperature results obtained with transient calculation shall be quasi stabilized (orbital cycling or asymptotic stabilization) with accuracy better than 0.1 C/hour. This verification shall be clearly demonstrated and documented. 6.5 Specific requirements for equipment (appendices/units) thermal model Accuracy of temperature calculation is mainly linked to the accuracy and the good modelling of the equipment heat transfer through the mounting structure (conductive exchanges) and with the equipment radiative environment (radiative exchanges). Reference MTG-SC-TCS-TMM-165 Each equipment reduced model (incorporated into its reduced module model) shall include: One or several interface nodes representative of the conductive heat transfer through the unit fixation One or several interface nodes representative of the radiative heat transfer through the unit housing If any, space node representative of the heat transfer to space. no more than 5 nodes for internal units dissipating strictly less than 20 W no more than 15 nodes for internal units dissipating above 20 W. no more than 20 nodes for external appendices
ISSUE : 1 Page : 25/35 NOTA: The number of nodes for the equipment reduced model depends on the interfaces: fixation, radiative environment, and equipment design. It is then impossible to specify a generic number of nodes for all equipment. Reference MTG-SC-TCS-TMM-170 Equipment dissipations shall be provided in Watt for all nodes in following cases: nominal use worst case of dissipation
ISSUE : 1 Page : 26/35 7. VALIDATION OF REDUCED THERMAL MODEL The validation of the reduced models has a dual purpose: Check that the transfer of data has been carried out correctly Check the homogeneity of the calculation methods used at the different levels Reference MTG-SC-TCS-TMM-175 The reduced thermal model shall be correlated with the detailed element model from which it has been reduced. This correlation shall at least be done with the typical mission configurations defined in Table 7-1. Mission Phase Launch mode - steady state and transient Operating mode Hot case - steady state and transient Operating mode Cold case - steady state and transient Safe mode Cold case - steady state and transient Satellite Modules Appendices Model Models Models X X X Units Models X X X X X X X X X X X Table 7-1: Reference test case definition for reduced model validation Reference MTG-SC-TCS-TMM-180 Each reference test case shall take into account the corresponding external environmental conditions, including orbit and satellite attitude. Reference MTG-SC-TCS-TMM-185 The validation of the reduced thermal model shall satisfy to the following constraints: For units : less than 2 C between temperatures calculated in reduced and detailed thermal models on the thermal reference point(s) For appendices : less than 5 C between temperatures calculated in reduced and detailed thermal models For structural parts : less than 5 C between temperatures calculated in reduced and detailed thermal models For other elements ((MLI blankets,...): less than 10 C between temperatures calculated in reduced and detailed thermal models Less than 5% of difference on power exchanges with the environment between reduced and detailed thermal models
ISSUE : 1 Page : 27/35 Less than 5% of difference on heating power consumption between reduced and detailed thermal models Remark: for a given part of an element meshed in N and 1 thermal nodes in respectively the detailed model and the reduced model, the temperature of the reduced model single node will be compared to the average of the temperatures of the corresponding N thermal nodes of the detailed model.
ISSUE : 1 Page : 28/35 8. THERMAL MODEL AND DOCUMENTATION DELIVERY Reference MTG-SC-TCS-TMM-190 For all modules, equipments, the detailed geometrical and thermal models, including any local models, shall be delivered to the prime contractor Reference MTG-SC-TCS-TMM-195 For all modules, equipments, the reduced geometrical and thermal models shall be delivered to the prime contractor. Reference MTG-SC-TCS-TMM-200 The delivery of each model shall be composed of: A single zipped electronic file containing all geometrical and thermal model data, allowing the computation of radiative couplings, absorbed fluxes and temperatures for all the mission modes and test calculation results. A document with the description of the geometrical and thermal models allowing a better understanding of the models and with the results of their validation. Reference MTG-SC-TCS-TMM-205 The model electronic file shall include all command and output files used and generated by the software s and a text file with a descriptive list of all the model files. Reference MTG-SC-TCS-TMM-210 The thermal data relative to the reduced models shall include the modelling of internal and external convective couplings to be used for the coupled launch analyses. Reference MTG-SC-TCS-TMM-215 The mathematical model report document shall at least include the following information and data. Number and list of thermal nodes, including node designation, internal or external location and thermal capacity Temperature specifications Internal heat dissipation (steady state and transient) of all studied cases
ISSUE : 1 Page : 29/35 Heater power dissipations of nodes for all studied cases, including in case of active control switching: o The control law o The temperature threshold o The definition of node used for heater monitoring Summary of assumptions taken into account for thermal interface modelisation Summary of coating thermo-optical properties (BOL/EOL values) Summary of orbit and thermal environment data used for external fluxes calculation Detailed drawings showing the nodal distribution and the mesh of the geometrical model with thermo-optical properties. Reference MTG-SC-TCS-TMM-220 In addition the documentation for reduced models shall include: The version number of the detailed models used to establish the reduced model Engineering assumptions made to reduce the complexity of the detailed models Demonstration of the correlation between the detailed and the reduced models Thermal assumptions made to calculate the internal convective coupling for model relative to coupled launch analysis.
ISSUE : 1 Page : 30/35 9. ANNEX
ISSUE : 1 Page : 31/35 APPENDICES : 1. REQUIREMENTS APPLICABILLITY MATRIX Satellite Reduced Models Satellite CLA Models Module Reduced Models Module CLA Models Equipment reduced models Requirements MTG-SC-TCS-TMM-005 X X X X X MTG-SC-TCS-TMM-010 X X X X X MTG-SC-TCS-TMM-015 X X MTG-SC-TCS-TMM-020 X X X X X MTG-SC-TCS-TMM-025 X X X X X MTG-SC-TCS-TMM-030 X X X X X MTG-SC-TCS-TMM-035 X X X X X MTG-SC-TCS-TMM-040 X X X X X MTG-SC-TCS-TMM-045 X X X X X MTG-SC-TCS-TMM-050 X X X X MTG-SC-TCS-TMM-055 X X X X X MTG-SC-TCS-TMM-060 X X X X X MTG-SC-TCS-TMM-065 X X X X X MTG-SC-TCS-TMM-070 X X X X X MTG-SC-TCS-TMM-075 X X X X X MTG-SC-TCS-TMM-080 X X X X X MTG-SC-TCS-TMM-085 X X X X X MTG-SC-TCS-TMM-090 X X X X X MTG-SC-TCS-TMM-095 X X X X X MTG-SC-TCS-TMM-100 X X X X X MTG-SC-TCS-TMM-105 X X X X X MTG-SC-TCS-TMM-110 X X X X X MTG-SC-TCS-TMM-115 X X X X X MTG-SC-TCS-TMM-120 X X MTG-SC-TCS-TMM-125 X X X X X MTG-SC-TCS-TMM-130 X X X X X MTG-SC-TCS-TMM-135 X X X X X MTG-SC-TCS-TMM-140 X X MTG-SC-TCS-TMM-145 X X X X X MTG-SC-TCS-TMM-142 X X X X X MTG-SC-TCS-TMM-150 X X X MTG-SC-TCS-TMM-155 X X X MTG-SC-TCS-TMM-160 X X X X X MTG-SC-TCS-TMM-165 X MTG-SC-TCS-TMM-170 X MTG-SC-TCS-TMM-175 X X MTG-SC-TCS-TMM-180 X X MTG-SC-TCS-TMM-185 X X X MTG-SC-TCS-TMM-190 X X X MTG-SC-TCS-TMM-195 X X X
ISSUE : 1 Page : 32/35 MTG-SC-TCS-TMM-200 X X X X X MTG-SC-TCS-TMM-205 X X X X X MTG-SC-TCS-TMM-210 X X MTG-SC-TCS-TMM-215 X X X X X MTG-SC-TCS-TMM-220 X X X
ISSUE : 1 Page : 33/35 APPENDICES : 2. SATELLITES OVERVIEW Figure 1 : MTG-I satellite deployed Figure 2 : MTG-I satellite stowed
ISSUE : 1 Page : 34/35 Figure 3 : MTG-S satellite deployed Figure 4 : MTG-S satellite stowed
ISSUE : 1 Page : 35/35 END OF DOCUMENT