Hayabusa2 asteroid sample return mission : technological innovation and advances /

Hayabusa2 Asteroid Sample Return Mission: Technological Innovation and Advances covers the second Japanese asteroid sample return mission. The purpose of the mission is to survey the asteroid Ryugu's surface features, touch down on the asteroid, form an artificial crater by shooting an impactor...

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Detalles Bibliográficos
Clasificación:Libro Electrónico
Otros Autores: Hirabayashi, Masatoshi (Editor ), Tsuda, Yuichi (Editor )
Formato: Electrónico eBook
Idioma:Inglés
Publicado: Amsterdam, Netherlands : Elsevier, 2022.
Temas:
Hayabusa2 (Spacecraft)
Space flight to asteroids.
Near-earth asteroids > Exploration.
Near-earth asteroids > Exploration
Space flight to asteroids
Acceso en línea:Texto completo
Tabla de Contenidos:
  • Intro
  • Hayabusa2 Asteroid Sample Return Mission: Technological Innovations and Advances
  • Copyright
  • Contents
  • Contributors
  • Chapter 1: Hayabusa2 as the beginning of deep space sample return
  • Chapter 2: Mission objectives, planning, and achievements of Hayabusa2
  • 2.1. Introduction
  • 2.2. Mission design
  • 2.2.1. Mission definition and success criteria
  • 2.2.2. Sample return technology development
  • 2.2.3. Scientific instruments aboard the Hayabusa2 spacecraft
  • 2.2.4. Mission planning and spacecraft development
  • 2.3. Mission operation results
  • 2.3.1. Launch and forward trip cruise
  • 2.3.2. Asteroid proximity operations
  • 2.3.3. Return trip cruise and earth return
  • 2.3.4. Extended mission
  • 2.4. Mission achievements
  • 2.4.1. Engineering achievements
  • 2.4.2. Scientific achievements
  • 2.4.3. Other achievements
  • 2.5. Conclusion
  • Acknowledgments
  • References
  • Chapter 3: Spacecraft system design of Hayabusa2
  • 3.1. Introduction
  • 3.2. Spacecraft system
  • 3.2.1. System configuration
  • 3.2.2. Subsystems
  • 3.3. Spacecraft resources and operation concept
  • 3.3.1. Fuel budget
  • 3.3.2. Attitude/thermal constraints
  • 3.3.3. Flight dynamics functions and capabilities
  • 3.3.4. Spacecraft autonomy
  • 3.4. Spacecraft development and external interfaces
  • 3.4.1. Spacecraft integration
  • 3.4.2. Interface to launch vehicle and early orbit phase operation
  • 3.4.3. Interface to ground facilities
  • 3.5. Conclusion
  • References
  • Chapter 4: Earth-Ryugu round-trip trajectory design and operation result
  • 4.1. Introduction
  • 4.2. Round-trip trajectory design
  • 4.2.1. Selecting target asteroid
  • 4.2.2. Primary and backup trajectory sequences
  • 4.2.3. Low- and continuous thrust optimization
  • 4.2.4. Global parameters outside local optimization
  • 4.2.5. Characteristics of derived trajectory
  • 4.2.6. Launch window and launch sequence
  • 4.3. Ion engine propulsive cruise operation
  • 4.3.1. Cyclic orbital guidance and navigation process
  • 4.3.2. Earth gravity assist
  • 4.3.3. Ion engine orbital maneuver operation result
  • 4.4. Terminal guidance operations
  • 4.4.1. Asteroid-approach phase operation [3]
  • 4.4.2. Earth reentry terminal guidance phase operation
  • 4.5. Conclusion
  • Acknowledgments
  • References
  • Chapter 5: Orbit determination for Hayabusa2
  • 5.1. Introduction
  • 5.2. OD methods during continuous ion-engine thrusting phase
  • 5.2.1. Conventional navigation scheme based on the ion-engine thrust model
  • 5.2.2. Quasi-kinematic OD method
  • 5.2.3. Comparison of each method by covariance error analysis
  • 5.2.4. Navigation results during the second and third continuous ion-thrust phases
  • 5.3. Simultaneous OD of Hayabusa2 and Ryugu
  • 5.3.1. A priori Ryugu ephemeris on the JPL HORIZONS system
  • 5.3.2. Simultaneous OD of Hayabusa2 and Ryugu
  • 5.3.3. Update history of Ryugu's ephemeris by JAXA
  • 5.3.3.1. JAXA-OPNAV1 solution
  • 5.3.3.2. JAXA-OPNAV2 solution

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