EN 14607-1:2004

Foreword
1 Scope
2 Normative references
3 Terms, definitions and abbreviated terms
  3.1 Terms and definitions
  3.2 Definitions for unit internal thermal design
  3.3 Abbreviated terms
4 Requirements
  4.1 Mission
      4.1.1 General
      4.1.2 Ground and pre-launch
      4.1.3 Launch and ascent
      4.1.4 Planetary orbital phases
      4.1.5 Interplanetary phases
      4.1.6 Docking, docked and separation phases
      4.1.7 Descent, (re-)entry and landing
      4.1.8 Post-landing phases
  4.2 Performance
      4.2.1 General
      4.2.2 Temperatures
      4.2.3 Functionality
      4.2.4 Additional and other performance requirements
  4.3 Interfaces
      4.3.1 General
      4.3.2 Mechanical interface
      4.3.3 Electrical interface
      4.3.4 AOCS interface
      4.3.5 TM/TC interface
      4.3.6 OBDH and S/W interface
      4.3.7 Launcher interface
      4.3.8 GSE interface
  4.4 Design
      4.4.1 General
      4.4.2 Budgets
      4.4.3 Parts, materials and processes (PMP)
      4.4.4 EEE components
      4.4.5 Lifetime
      4.4.6 Predictability and testability
      4.4.7 Flexibility
      4.4.8 Accessibility
      4.4.9 Reliability
      4.4.10 Redundancy
      4.4.11 Interchangeability
      4.4.12 Maintenance
      4.4.13 Cleanliness
      4.4.14 Safety
      4.4.15 Availability
  4.5 Verification
      4.5.1 General
      4.5.2 Review of design
      4.5.3 Verification by similarity
      4.5.4 Verification by inspection
      4.5.5 Verification by analysis
      4.5.6 Verification by test
      4.5.7 Thermal Balance (TB) test
  4.6 Production and manufacturing
      4.6.1 General
      4.6.2 Manufacturing process
      4.6.3 Manufacturing drawings
      4.6.4 Quality management
      4.6.5 Cleanliness
      4.6.6 Procurement
      4.6.7 Tooling
      4.6.8 Integration
      4.6.9 Marking
      4.6.10 Packaging, handling, transportation
      4.6.11 Storage
      4.6.12 Repair
      4.6.13 In-service requirements
  4.7 Product assurance
  4.8 Deliverables
      4.8.1 General
      4.8.2 Hardware
      4.8.3 Documentation
  4.9 Use standard to define project requirements
Annex A (normative) Development approach
  A.1 Uncertainties
      A.1.1 Uncertainty philosophy
      A.1.2 Sources for temperature uncertainties
      A.1.3 Sensitivity analysis and temperature uncertainty
  A.2 Margins
  A.3 Test approach and test success criteria
      A.3.1 Test approach
      A.3.2 Test success criteria
  A.4 Correlation approach and correlation success criteria
      A.4.1 General
      A.4.2 Temperature level criteria
      A.4.3 Standard deviation criteria
      A.4.4 Individual unit success criteria
  A.5 Analysis approach
      A.5.1 Objectives of thermal analysis
      A.5.2 Thermal analysis methods
      A.5.3 Interfaces and deliverables
      A.5.4 Quality
Annex B (normative) Cryogenic temperature range
  B.1 Applicability
      B.1.1 General
      B.1.2 Cryogenic definitions (exceptions)
  B.2 Complementary terminology for the cryogenic
      temperature range
  B.3 Applicability matrix
Annex C (normative) High temperature range
  C.1 Applicability
  C.2 Complementary terminology for the high temperature
      range
  C.3 Applicability matrix
Annex D (informative) TCS development methodology
  D.1 Conventional temperature range
      D.1.1 General
      D.1.2 First stage (preliminary) configuration
      D.1.3 Final thermal design
      D.1.4 Reason for thermal analyses
      D.1.5 Typical parameter inaccuracies
  D.2 Cryogenic temperature range
      D.2.1 General
      D.2.2 Reason for thermal analyses
      D.2.3 Typical parameter inaccuracies
Bibliography

EN 14607 Part 1 of Space engineering - Mechanical specifies requirements for the discipline of thermal engineering.This document specifies the requirements for the definition, analysis, design, manufacture, verification and in­service operation of thermal control subsystems of spacecraft and other space products.This document applies to the thermal engineering activities of all spacecraft and space related products for all thermal aspects and temperature levels for space products.For this document, the complete temperature scale is divided into three ranges defined as follows:- Cryogenic temperature range, below 120 K;- Conventional temperature range, between 120 K and 420 K;- High temperature range, above 420 K.The core part of this document concerns the conventional temperature range; complementary information, requirements and definitions for the cryogenic and high temperature range respectively are provided in annexes B and C. When viewed from the perspective of a specific project context, the requirements defined in this document should be tailored to match the genuine requirements of a particular profile and circumstances of a project.NOTETailoring is a process by which individual requirements of specifications, standards and related documents are evaluated, and made applicable to a specific project by selection, and in some exceptional cases, modification of existing or addition of new requirements.This document is applicable to:- thermal engineering activities of all space and space related products, covering all thermal engineering aspects involved in the achievement of the required thermal performance, particularly: design, verification, manufacturing and in service operations;- thermal control subsystem and to relevant parts of all space products.