Cover
Half Title
Series Page
Title Page
Copyright Page
Table of Contents
Contributors
Chapter 1 Introduction
1.1 Definition of Spacecraft System Engineering
1.1.1 System Engineering
1.1.2 Spacecraft System Engineering
1.2 Composition and Project Relationship of Spacecraft Engineering System
1.2.1 Spacecraft System
1.2.1.1 Spacecraft Classification
1.2.1.2 Composition of Spacecraft
1.2.2 Space Engineering System
1.3 Concept of Spacecraft System Design
1.3.1 Definition of Spacecraft System Design
1.3.1.1 Design Features of Spacecraft System
1.3.2 Principles of Spacecraft System Design
1.3.2.1 Principles of Spacecraft System Design
1.3.2.2 Special Requirements on Spacecraft System Design
References
Chapter 2 Design Method and Process of Spacecraft System
2.1 Design Method of Spacecraft System
2.1.1 System Design Procedure
2.1.1.1 System Scheme Design
2.1.1.2 System Verification
2.1.1.3 System Optimization Design
2.1.1.4 Position and Function of Spacecraft System Design
2.1.2 General Framework of System Design
2.2 Spacecraft System Development Phase
2.3 General Design Flow of Spacecraft System
2.3.1 Process of Conceptual Demonstration Phase
2.3.1.1 Primary Coverage
2.3.1.2 General Design Process
2.3.1.3 Key Links Description
2.3.2 Process of Scheme Design Phase
2.3.2.1 Primary Coverage
2.3.2.2 General Design Process
2.3.2.3 Key Link Description
2.3.3 Prototype Development Process
2.3.3.1 Primary Coverage
2.3.3.2 General Design Process
2.3.3.3 Description of Key Links
2.3.4 Flight Model Development Phase Process
2.3.4.1 Main Content
2.3.4.2 Universal Design Process
2.3.4.3 Key Links Description
References
Chapter 3 Spacecraft Environment Impact Analysis
3.1 Launch Environments and Their Impact on Spacecraft
3.1.1 Mechanical Environment in the Launching Process
3.1.1.1 Ground Noise Environment
3.1.1.2 Maximum Aerodynamic Load Environment
3.1.1.3 Steady-State Flight Environment
3.1.1.4 Stage Separation Environment
3.1.1.5 Fairing Separation Environment
3.1.1.6 Environment for Spacecraft-Rocket Separation
3.1.2 Other Environments During Launch
3.1.2.1 Thermal Environment
3.1.2.2 Pressure Environment
3.1.2.3 Electromagnetic Environment
3.2 In-orbit Operation Environments and Their Impact
3.2.1 In-orbit Space Environment
3.2.1.1 Sun and Its Activity
3.2.1.2 Near-Earth Space Environment Elements
3.2.1.3 Deep Space Environment
3.2.1.4 Micro Meteor and Debris
3.2.2 In-orbit Thermal Environment
3.2.2.1 Solar Radiation
3.2.2.2 Earth’s Albedo
3.2.2.3 Earth Infrared Radiation
3.2.3 In-orbit Mechanical Environment
3.2.3.1 External Mechanical Environment
3.3 Space Environmental Effects on Spacecraft and Its Protection Design
3.3.1 Space Environmental Effects
3.3.1.1 Atomic Oxygen erosion Effect
3.3.1.2 Solar Ultraviolet Radiation Effect
3.3.1.3 Charged Particle Radiation Effect
3.3.2 Requirements for Atmospheric and Vacuum Environment Protection Design
3.3.3 Requirements for Solar Ultraviolet Radiation Protection Design
3.3.4 Requirements for Charged Particle Radiation Protection Design
References
Chapter 4 Basis of Spacecraft Orbit Design
4.1 Geometric Analysis of Task Space
4.1.1 Basics of Spherical Trigonometry
4.1.2 Calculation of Ground-Station Tracking Arc
4.1.3 Calculation of Lighting Conditions
4.1.3.1 Angle between Sunlight and Orbital Plane
4.1.3.2 Sun Elevation Angle
4.1.3.3 Time of Earth Eclipse Times
4.1.4 Analysis of Launch Window
4.1.4.1 Constraints on Launch Time
4.1.4.2 Several Elements of Spacecraft Launch from a Launch Site
4.2 Basis of Orbital Dynamics
4.2.1 Two-Body Problem
4.2.2 Orbit Perturbation
4.2.2.1 Earth’s Non-spherical Gravitational Perturbation
4.2.2.2 Gravitational Perturbation of the Third Body
4.2.2.3 Air Drag Perturbation
4.2.2.4 Solar Radiation Pressure Perturbation
4.2.3 Orbital Maneuver
4.2.4 Multi-body Problem
4.3 Spacecraft Orbit Design
4.3.1 General Orbit Design for a Single Spacecraft
4.3.1.1 Sun-Synchronous Orbit (SSO)
4.3.1.2 Regressive Orbit
4.3.1.3 Frozen Orbit
4.3.1.4 GSO
4.3.1.5 Critical Inclination Orbit
4.3.2 Constellation Design
4.3.2.1 Constellation Characterization Parameters
4.3.2.2 Constellation Performance Evaluation Index
4.3.2.3 Summary of Constellation Design
4.4 Design of Deep-Space Exploration Orbit
4.4.1 Design Process of Deep-Space Exploration Orbit
4.4.2 Design of Lunar Exploration Orbit
4.4.2.1 Lunar Exploration Launch Window
4.4.2.2 Earth-Moon Transfer
4.4.3 Design of Planetary Exploration Orbit
4.4.3.1 Planetary Rendezvous Period and Launch Window
4.4.3.2 Optimization Design of Interplanetary Transfer Orbit
4.5 Propellant Budget
4.5.1 Analysis of Orbital Maneuvering Velocity
4.5.1.1 Determination of GEO Period
4.5.1.2 Determination of GEO Semi-major Axis
4.5.1.3 Orbital Maneuvering Method
4.5.1.4 Delta V Magnitude Calculation
4.5.2 Propellant Budget Analysis
References
Chapter 5 Spacecraft System Mission Analysis
5.1 Characteristics and Basic Analysis Methods of Space Missions
5.1.1 Classification and Objectives of Space Missions
5.1.1.1 Classification of Space Missions
5.1.1.2 Characteristics of Spacecraft Missions
5.1.1.3 Objectives of Space Missions
5.1.2 Basic Methods for Space Mission Analysis
5.1.2.1 Contents of Mission Analysis
5.1.2.2 Basic Technological Approach in Mission Analysis
5.1.3 Constraints on Space Mission Design
5.1.3.1 Analysis of Environmental Constraints
5.1.3.2 User’s Constraints on Mission Requirements
5.1.3.3 Limitations of the Existing Technological Base
5.1.3.4 Other Constraints
5.2 Analysis Process of Spacecraft System Mission
5.2.1 Analysis Process and Contents of Spacecraft System Mission
5.2.1.1 Analysis of Large System Constraints
5.2.1.2 Analysis of Engineering Implementation Constraints
5.2.1.3 Demand Investigation and Analysis
5.2.1.4 Investigation of the Spacecrafts in Similar Missions at Home and Abroad
5.2.1.5 Analysis of Exploration Mission Orbit
5.2.1.6 Networked Orbit Concept Design
5.2.1.7 Analysis of Payload Indexes and Configuration
5.2.1.8 Analysis of Spacecraft Service Requirements
5.2.1.9 Preliminary Design of Payload Concept
5.2.1.10 Platform Configuration Analysis
5.2.2 Analysis Example of a Mission with Typical Earth-Sensing Spacecraft System
5.3 Preliminary System Conception
5.3.1 Preliminary Selection of Spacecraft Mission Orbit
5.3.2 Preliminary Payload Conception
5.3.3 Preliminary Subsystem Conception
5.3.3.1 Requirements and Types of Control Subsystem
5.3.3.2 Requirements and Types of Propulsion Subsystem
5.3.3.3 Types and Requirements of Power Subsystem Concept
5.3.3.4 Requirements and Types of TT&C and Data Management Subsystem Concept
5.3.3.5 Types and Requirements of Thermal Control System Concept
5.4 Analysis and Summarization of General Performance Indexes
5.4.1 Main Contents of General Performance Indexes of a Spacecraft
5.4.2 Initial Distribution of General Performance Indexes
References
Chapter 6 Design of Spacecraft System Concept
6.1 Mission Profile Analysis
6.2 Overall System Design
6.2.1 Overall Power Supply and Distribution Design
6.2.1.1 Design Principles of Spacecraft Energy Flow
6.2.1.2 Design Ideas on Spacecraft Energy Flow
6.2.2 Overall Information Flow Design
6.2.2.1 Classification of Spacecraft Information Flows
6.2.2.2 Design Principles of Spacecraft Information Flow
6.2.2.3 Analysis of Spacecraft Information Requirements
6.2.2.4 TT&C Channel Design
6.2.2.5 Design of Data Transmission Channel
6.2.2.6 Spacecraft Information Flow Design
6.2.3 General Design of Attitude and Orbit Control
6.2.3.1 General
6.2.3.2 Classification of Attitude and Orbit Control Methods
6.2.3.3 Design Constraints
6.2.4 Overall Thermal Control Design
6.2.4.1 Analysis of Overall Thermal Control Task
6.2.4.2 Design Principles of Spacecraft-Level Thermal Control
6.2.4.3 General Idea on Thermal Control Design
6.2.4.4 Conceptual Design
6.2.5 Overall EMC Design
6.2.5.1 EMC Design Requirements
6.2.5.2 Contents and Process of Overall Spacecraft EMC Design
6.2.5.3 Introduction of the Analysis Method of EMC Safety Margin of Spacecraft System
6.2.6 Usability and Ease-of-Use Design
6.2.6.1 Definition of Concepts
6.2.6.2 Items of Usability and Ease-of-Use Design
6.3 Design of Internal Physical Interfaces
6.3.1 Design and Construction Specifications
6.3.1.1 Principles of Equipment Design
6.3.1.2 Main Contents of Design and Construction Specifications
6.3.2 Design of IDS
6.3.3 Design of Interface Control Document (ICD)
6.4 Flight Programming
6.4.1 Definitions Related to Flight Program
6.4.2 Constraints and Supporting Conditions
6.4.2.1 Constraints
6.4.2.2 Supporting Conditions
6.4.3 Principles and Contents of Flight Programming
6.4.4 Analysis of TT&C Conditions
6.4.5 Process of Flight Programming
6.5 Design and Verification of External System Interfaces
6.5.1 Design and Verification of the Interfaces to Launch Vehicle
6.5.1.1 Overview of Launch Vehicle
6.5.1.2 Design of the Interfaces to Launch Vehicle
6.5.1.3 Verification Test of the Interfaces to Launch Vehicle
6.5.2 Design and Verification of the Interfaces to TT&C System
6.5.2.1 Overview of TT&C System
6.5.2.2 Design of the Interfaces between Large TT&C Systems
6.5.2.3 Verification of TT&C System Interfaces
6.5.3 Design and Verification of the Interface to Ground-Receiving System
6.5.3.1 Overview of Ground-Receiving System
6.5.3.2 Design of Satellite-Ground Microwave Link Interface
6.5.3.3 Verification of Satellite-Ground Microwave Link Interface
6.5.3.4 Design of Satellite-Ground Laser Link Interface
6.5.3.5 Verification of Satellite-Ground Laser Link Interface
6.5.4 Design and Verification of the Interface to Launch Site
6.5.4.1 Overview of Launch Site System
6.5.4.2 Interface between Satellite and Launch Site
6.5.4.3 Experimental Verification
Chapter 7 Design of Spacecraft Configuration and Assembly
7.1 Design Criteria and Contents of Spacecraft Configuration
7.1.1 Design Criteria
7.1.1.1 Meet the Mission Requirements
7.1.1.2 Meet the Requirements of Large-System Interfaces
7.1.1.3 Meet the Subsystem and Equipment Requirements
7.1.1.4 Meet the Maintainability and Operational Accessibility Requirements
7.1.2 Contents of Configuration Design
7.1.2.1 Design of Flight Attitude and Orientation
7.1.2.2 Shape Design
7.1.2.3 Cabin Division Design
7.1.2.4 Design of Main Load-Bearing Structure
7.1.2.5 Configuration Design of Large Components
7.1.2.6 Design of Thermal Boundary and Heat Dissipation Channel
7.2 Layout Design Criteria and Design Contents
7.2.1 Design Criteria
7.2.1.1 Meet the Mission’s Requirements for Mass Characteristics
7.2.1.2 Meet the Rocket’s Requirements for Spacecraft Profile Envelope
7.2.1.3 Meet the Special Requirements for Subsystems and Equipment
7.2.1.4 Meet the Mechanical Resistance Requirements
7.2.1.5 Meet the Thermal Control Requirements
7.2.1.6 Meet the Electromagnetic Compatibility Requirements
7.2.1.7 Meet the Anti-irradiation Requirements
7.2.1.8 Meet the Lightweight Requirements of Cable Network
7.2.1.9 Meet the AIT Requirements
7.2.1.10 Meet the Basic Constraints of the Inherited Platform
7.2.2 Contents of Layout Design
7.2.2.1 Layout of Main Payloads
7.2.2.2 Layout of Attitude Control Components
7.2.2.3 Layout of Control and Execution Components
7.2.2.4 Layout of Navigation and TT&C Antennas
7.2.2.5 Piping Layout
7.2.2.6 Cable Network Layout
7.3 Final-Assembly Design Criteria and Design Contents
7.3.1 Final-Assembly Design Criteria
7.3.1.1 Meet the Subsystem Requirements
7.3.1.2 Meet the AIT Requirements
7.3.1.3 Meet the Piping and Cable Channel Layout Requirements
7.3.1.4 Meet the Requirements of Operability and Maintainability
7.3.1.5 Meet the Requirements of Productization, Generalization and Standardization
7.3.1.6 Meet the Final-Assembly Safety Requirements
7.3.2 Contents of Final-Assembly Design
7.3.2.1 Assembly Scheme Design
7.3.2.2 Equipment Installation Design
7.3.2.3 Pipeline Direction and Installation Design
7.3.2.4 Cable Routing and Installation Design
7.3.2.5 Design of Final Assembly Components
7.3.2.6 Accuracy Test Design
7.3.2.7 Design of Ground Mechanical Support Equipment
7.3.2.8 Design of Final Assembly Technique Process
7.4 Analysis of Configuration and Layout
7.4.1 Large-System Compatibility Analysis
7.4.1.1 Spacecraft-Rocket Compatibility Analysis
7.4.1.2 Spacecraft-Rocket Coupling Analysis
7.4.2 Mission Adaptability Analysis
7.4.2.1 Frequency Response Analysis
7.4.2.2 Analysis of Main Structure Accuracy and Thermal and Mechanical Stability
7.4.2.3 FOV Occlusion Analysis
7.4.2.4 Analysis of Quality Characteristics
7.4.2.5 Analysis of Solar Wing Occlusion
7.4.2.6 Stray Light Analysis
7.4.2.7 Analysis of Antenna Electrical-Performance Occlusion
7.4.2.8 Thruster Plume Analysis
7.4.2.9 Analysis of Moving-Parts Disturbance
7.4.2.10 Flexible Dynamics Analysis
7.5 Final Assembly Testing and Validation
7.5.1 Pipeline Leak Detection
7.5.1.1 Leak Detection Methods and Timing
7.5.2 Final-Assembly Accuracy Test
7.5.2.1 Contents of Final-Assembly Accuracy Test
7.5.2.2 Accuracy Test Method and Timing
7.5.3 Quality Characteristic Testing and Balancing
Chapter 8 Spacecraft Reliability Design
8.1 Reliability Design Analysis Method
8.1.1 Basic Theories of Reliability
8.1.2 Reliability Requirements and Allocation
8.1.2.1 Reliability Index Demonstration and Determination
8.1.2.2 Reliability Allocation
8.1.3 Reliability Modeling and Prediction
8.1.3.1 Reliability Modeling
8.1.3.2 Reliability Prediction
8.1.4 Margin Design
8.1.5 Derating Design
8.1.6 Fault Tolerant Design
8.1.7 FMEA
8.1.8 FTA
8.1.8.1 Selecting the Top Event
8.1.8.2 Identifying the Boundary Conditions
8.1.8.3 Building the Fault Tree
8.1.8.4 Qualitative Analysis and Analysis Result Application
8.1.8.5 Quantitative Analysis and Analysis Result Application
8.1.9 ETA
8.1.9.1 Event Tree Construction
8.1.9.2 Fault Modeling
8.1.9.3 Quantitative Analysis
8.1.9.4 Importance Calculation
8.1.10 PRA
8.1.10.1 PRA Classicfiation
8.1.10.2 PRA Process
8.1.11 Sneak Circuit Analysis
8.1.11.1 Basic Concept and Characteristics of Sneak Circuit
8.1.11.2 Sneak Circuit Analysis Methods
8.1.12 Worst Case Analysis
8.1.12.1 Extreme Value Analysis
8.1.12.2 Root Square Sum Analysis
8.1.12.3 Monte Carlo Analysis
8.1.13 Outage Analysis
8.1.13.1 General Requirements for Outage Analysis
8.1.13.2 Implementation Procedure of Outage Analysis
8.1.14 Reliability Mathematical Simulation Method
8.1.15 Reliability Assessment
8.1.15.1 Reliability Assessment Method Based on Life Data
8.1.15.2 Reliability Vericfiation Test and Reliability Assessment Method of Success-or-Failure Products
8.1.15.3 Reliability Verification Test and Reliability Assessment Method of Life-Type Mechanism
8.1.15.4 Reliability Verification Test and Reliability Assessment Method of Performance Parameter Measuring Mechanism
8.1.15.5 Comprehensive Reliability Assessment Method
8.2 Methods of Safety Design and Analysis
8.2.1 General Safety Design Method for Spacecraft Products
8.2.1.1 Safety Objective
8.2.1.2 Safety Design Criteria
8.2.1.3 Safety Design Priority
8.2.1.4 Safety Requirements for Propulsion System
8.2.1.5 Pressure Vessel Safety Requirements
8.2.1.6 Piping Safety Requirements
8.2.1.7 Safety Requirements for Valves, Pressure Regulators and Control Devices
8.2.1.8 Safety Requirements for Initiating Explosive Devices
8.2.1.9 Battery Safety Requirements
8.2.2 Methods of Hazard Source Identification and Hazard Analysis
8.2.3 Safety Verification and Evaluation
8.2.3.1 Safety Verification
8.2.3.2 Qualitative Safety Verification
8.2.3.3 Quantitative Safety Verification
8.2.3.4 Safety Evaluation
8.3 Maintainability Design and Analysis
8.3.1 General
8.3.2 Design Criteria for Hardware Maintainability
8.3.2.1 Simpliefid Maintenance Design
8.3.2.2 Accessibility Design
8.3.2.3 Standardization/Modularity/Interchangeability Design
8.3.2.4 Error-Proofing Design
8.3.2.5 Maintenance Safety Design
8.3.2.6 Human-Element Engineering Design
8.3.3 In-orbit Maintainability Design
8.4 Testability Design and Analysis
8.4.1 Design of Inherent Testability
8.4.2 Design of Fault Diagnosis Strategy
8.4.3 Design of Embedded Diagnosis
8.5 Supportability Design and Planning
8.5.1 Supportability Design and Supply
8.5.2 Support Planning
8.6 Risk Identification and Control
References
Chapter 9 Spacecraft System Testing and Verification
9.1 Connection between Spacecraft System Verification Method and Analysis
9.1.1 Test Verification Methods
9.1.2 Relationship between Analysis and Test Verification
9.2 Requirements for Spacecraft Environment Test Verification
9.2.1 Purpose of Environmental Test
9.2.2 Categories of Environmental Tests
9.2.2.1 Development Test
9.2.2.2 Qualification Test
9.2.2.3 Acceptance Test
9.2.3 Environmental Test Tailoring
9.2.4 Retest
9.3 Design of Test Matrix
9.3.1 Design of Qualification Test Matrix for Spacecraft System
9.3.1.1 Qualification Test Matrix
9.3.1.2 Qualification Function Test
9.3.1.3 Qualification EMC Test
9.3.1.4 Qualification Impact Test
9.3.1.5 Qualification Sound Test
9.3.1.6 Qualification Vibration Test
9.3.1.7 Qualification Pressure and Leak Test
9.3.1.8 Qualification Heat Balance Test
9.3.1.9 Qualification Thermal Vacuum Test
9.3.1.10 Qualification Modal Observation Test
9.3.1.11 Qualification Magnetic Test
9.3.1.12 Vacuum Discharge Test
9.3.2 Design of Subsystem Qualification Test Matrix
9.3.2.1 Subsystem Qualification Test Matrix
9.3.2.2 Subsystem-Level Qualification Structure Static-Load Test
9.3.2.3 Subsystem-Level Qualification Separation Test
9.3.3 Design of Component Qualification Test Matrix
9.3.3.1 Component Qualification Test Matrix
9.3.3.2 Component Qualification Function Test
9.3.3.3 Qualification Thermal Cycle Test of Electrical and Electronic Components
9.3.3.4 Component-Level Qualification Thermal Vacuum Test
9.3.3.5 Component-Level Qualification Vibration Test
9.3.3.6 Component-Level Qualification Acoustic Test
9.3.3.7 Component-Level Qualification Impact Test
9.3.3.8 Component-Level Qualification Leak Test
9.3.3.9 Component-Level Qualification Pressure Test
9.3.3.10 Component-Level Qualification Acceleration Test
9.3.3.11 Component-Level Qualification Life Test
9.3.3.12 Component-Level Qualification EMC Test
9.3.3.13 Component-Level Qualification Magnetic Test
9.3.3.14 Component-Level Qualification Climate Test
9.3.3.15 Component-Level Vacuum Discharge Test
9.3.3.16 Component-Level Microdischarge Test
9.3.4 Spacecraft System Acceptance Tests
9.3.5 Subsystem Acceptance Test
9.3.5.1 Subsystem Acceptance Test Matrix
9.3.5.2 Subsystem-Level Acceptance Structure Inspection-Load Test
9.3.5.3 Subsystem-Level Acceptance Pressure and Leak Test
9.3.6 Component Acceptance Test
9.4 Spacecraft Design Test Verification
9.4.1 Structural Design Test Verification
9.4.1.1 Method of Structural Design Verification
9.4.1.2 Verification of Structural Static Strength
9.4.1.3 Verification of Structural Dynamic Characteristics
9.4.2 Thermal Design Test Verification
9.4.3 Electrical Performance Test Verification
9.4.4 EMC Test Verification
9.4.4.1 Equipment EMC Test Verification
9.4.4.2 System-level EMC Test Verification
9.4.5 Magnetic Test Verification
Chapter 10 Digital Design and Development of Spacecraft System
10.1 Digital Design Techniques
10.1.1 Digital Mock-Up (DMU) Technique
10.1.2 Model-based Definition (MBD) Technique
10.1.3 Multidisciplinary Design Optimization (MDO) Technique
10.1.4 Product Lifecycle Management (PLM) Technique
10.2 Digital Spacecraft Development
10.2.1 Characteristics of Digital Spacecraft Development
10.2.1.1 Digital Development Based on Collaborative Environment
10.2.1.2 Personnel Organization in the Form of Integrated Product Team (IPT)
10.2.1.3 Digital Development Process with Model as the Core
10.2.1.4 Changes of Output
10.2.2 Collaborative Design of Spacecraft System Engineering/Structural/Thermal Control
10.2.2.1 Traditional Design Process
10.2.2.2 Digital Design Process
10.2.3 Spacecraft Design-Process Collaboration Mode
10.3 Model-based 3D Collaborative Design of a Spacecraft
10.3.1 General Requirements for 3D Model Classification and Construction
10.3.1.1 Classification by Development Stage
10.3.1.2 Classification by Purpose
10.3.2 3D Collaborative Design of Spacecraft System, Structure and Thermal Control
10.3.2.1 Construction of Spacecraft (Satellite) Framework
10.3.2.2 Construction of 3D System Design Model
10.3.2.3 3D Modeling of a Spacecraft Structure
10.3.2.4 3D Modeling of Spacecraft Thermal Control
10.3.2.5 Iterative Adjustment of 3D Design Model
10.3.3 3D Model Construction Oriented to Manufacturing Assembly
10.4 Collaborative Spacecraft Design Based on Equipment Interface Data
10.4.1 Role and Evolution of IDS
10.4.2 Application of IDS in Thermal Control Design
10.4.3 Application of IDS in Cable Network Design
10.4.4 Application of IDS in TT&C Information Flow Design
10.5 MDO Based on Model
10.5.1 Connotation of MB-MDO
10.5.2 Spacecraft Design Process Based on MB-MDO
10.6 Spacecraft Lifecycle Data Management and Configuration Management
10.6.1 Lifecycle Data Management for Aerospace Models
10.6.2 PLM-based Spacecraft Configuration Management Technology
10.6.2.1 Product Structure Management
10.6.2.2 Data Packet Baseline Management
10.6.2.3 Validity Management
10.6.2.4 Multi-view Management
10.6.2.5 Change Management
10.6.2.6 Integrated Management
10.6.3 AVIDM-based Aerospace Model Lifecycle Data Management
10.7 Spacecraft Co-design Environment
10.7.1 Process of Collaborative Design
10.7.2 Team of Collaborate Design
10.7.3 Areas of Collaborative Design
10.7.4 Basic Software and Hardware Environment for Collaborative Design
10.8 Prospect of Digital Spacecraft Development
10.8.1 Application of Cutting-Edge Digital Techniques
10.8.1.1 3D Printing
10.8.1.2 Virtual Reality/Augmented Reality
10.8.1.3 Digital Twin
10.8.2 MBSE
10.8.3 Model-based Enterprises (MBEs)
References