1 Introduction
1.1 Mission of Spacecraft Thermal Control
1.2 Demand for Thermal Control
1.2.1 Temperature Level
1.2.2 Temperature Uniformity and Stability
1.2.3 Wind Speed and Humidity
1.3 Thermal Characteristics
1.3.1 Heat Source
1.3.2 Magnitude and Fluctuation of Heat Dissipation
1.3.3 Heat Flux
1.3.4 Thermal Capacity
1.4 Main Constraints
1.5 Main Technology of Thermal Control
1.6 Main Tasks
References
2 Space Environment
2.1 Overview
2.2 Environment at Launching Phase
2.3 Earth Orbital Space Environment
2.3.1 Earth Orbital Thermal Environment
2.3.2 Other Earth Orbit Space Environment
2.4 Moon and Planetary Space Environment
2.4.1 Lunar Environment
2.4.2 Mercury Environment
2.4.3 Venus Environment
2.4.4 Mars Environment
2.5 Thermal Environment at Re-entry or Entry Phase
2.6 Inductive Environment
2.6.1 Inductive Environment Caused by Engine Operation
2.6.2 Inductive Environment for Spinning Spacecraft
or Equipment
References
3 Design of Spacecraft Thermal Control Subsystem
3.1 Overview
3.2 Mission Characteristics
3.2.1 Ground Phase
3.2.2 Launch and Ascent Phase
3.2.3 Orbiting Phase
3.2.4 Reentry or Entry Phase
3.2.5 Landing Phase
3.3 Basic Principles of Thermal Control Design
3.4 Design Method of Thermal Control System
3.4.1 Thermal Control Design Requirements
and Conditions
3.4.2 Selection of Thermal Design Cases
3.4.3 Selection of System Design Methods
3.4.4 Selection of Thermal Control Technologies
3.5 Thermal Control Design Stages and Key Points
3.5.1 Concept Phase
3.5.2 Initial Prototype Phase
