Session
Technical Session VI: The Future
Abstract
The EARTH-Sun-Heliosphere INteractions Experiment is a novel space mission designed to answer key questions about how Earth’s climate and space environment are influenced by the Sun. Using a small satellite orbiting about the L1 Lagrange point located approximately 1.5 million kilometres from the Earth, the scientific payload will have a unique and continuous view of the dayside of Earth, and an uninterrupted view of the Sun. From here measurements of the reflective properties of clouds over large viewing angles will be made, whilst simultaneously monitoring the variations and effects of the electromagnetic, particle and field outputs of the Sun. The mission is designed to be a low-cost, fast and responsive project and therefore requires that the payload and spacecraft should be simple and robust, and have a high degree of autonomy. Spacecraft subsystems must be low mass and power, and require little or no development to minimise risk and be consistent with the project timescales and proposed budget. The paper presents the main drivers for the mission and describes the four scientific instruments that make up the payload. It also explores some of the system level trade-offs performed to keep the spacecraft mass under 130kg and power below 140W.
Presentation Slides
Earthshine – A Deep Space Science Mission using Small Satellite Technology
The EARTH-Sun-Heliosphere INteractions Experiment is a novel space mission designed to answer key questions about how Earth’s climate and space environment are influenced by the Sun. Using a small satellite orbiting about the L1 Lagrange point located approximately 1.5 million kilometres from the Earth, the scientific payload will have a unique and continuous view of the dayside of Earth, and an uninterrupted view of the Sun. From here measurements of the reflective properties of clouds over large viewing angles will be made, whilst simultaneously monitoring the variations and effects of the electromagnetic, particle and field outputs of the Sun. The mission is designed to be a low-cost, fast and responsive project and therefore requires that the payload and spacecraft should be simple and robust, and have a high degree of autonomy. Spacecraft subsystems must be low mass and power, and require little or no development to minimise risk and be consistent with the project timescales and proposed budget. The paper presents the main drivers for the mission and describes the four scientific instruments that make up the payload. It also explores some of the system level trade-offs performed to keep the spacecraft mass under 130kg and power below 140W.
