Refine
Year of publication
Document Type
- Conference Proceeding (16)
- Article (8)
- Part of a Book (3)
Keywords
- GOSSAMER-1 (2)
- solar sail (2)
- DLR-ESTEC GOSSAMER roadmap for solar sailing (1)
- Hybrid Propellants (1)
- MASCOT (1)
- Reusable Rocket Engines (1)
- Small spacecraft (1)
- Solar sail (1)
- Spacecraft (1)
- heliosphere (1)
- ion propulsion (1)
- low-thrust (1)
- low-thrust trajectory optimization (1)
- multiple NEA rendezvous (1)
- near-Earth asteroid (1)
- responsive space (1)
- sample return (1)
- small solar system body characterisation (1)
- small spacecraft (1)
- small spacecraft asteroid lander (1)
- small spacecraft solar sail (1)
- solar system (1)
- system engineering (1)
Institute
Solar sailcraft provide a wide range of opportunities for high-energy low-cost missions. To date, most mission studies require a rather demanding performance that will not be realized by solar sailcraft of the first generation.
However, even with solar sailcraft of moderate performance, scientifically relevant missions are feasible. This is demonstrated with a Near Earth Asteroid sample return mission and various planetary rendezvous missions.
Solar sailcraft of the first generation technology development / Seboldt, Wolfgang ; Dachwald, Bernd
(2003)
A technology reference study for a multiple near-Earth object (NEO) rendezvous mission with solar sailcraft is currently carried out by the authors of this paper. The investigated mission builds on previous concepts, but adopts a strong micro-spacecraft philosophy based on the DLR/ESA Gossamer technology. The main scientific objective of the mission is to explore the diversity of NEOs. After direct interplanetary insertion, the solar sailcraft should—within less than 10 years—rendezvous three NEOs that are not only scientifically interesting, but also from the point of human spaceight and planetary defense. In this paper, the objectives of the study are outlined and a preliminary potential mission profile is presented.
A technology reference study for a displaced Lagrange point space weather mission is presented. The mission builds on previous concepts, but adopts a strong micro-spacecraft philosophy to deliver a low mass platform and payload which can be accommodated on the DLR/ESA Gossamer-3 technology demonstration mission. A direct escape from Geostationary Transfer Orbit is assumed with the sail deployed after the escape burn. The use of a miniaturized, low mass platform and payload then allows the Gossamer-3 solar sail to potentially double the warning time of space weather events. The mission profile and mass budgets will be presented to achieve these ambitious goals.