BIRD Microsatellite Thermal Control System – 5 Years of Operation in Space

Lura, F.; Biering, B.; Lötzke, Horst Georg; Studemund, H.; Baturkin, Volodymyr

doi:10.1007/978-1-4020-6943-7_25

Cited by 3 publications

(2 citation statements)

References 3 publications

(4 reference statements)

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“…Consequently, we classify MASCOT (9.8 kg) and its derivatives as 'nanolanders' also for the features they share with Earth-orbiting nanosatellites such as a common integrated electronics compartment (E-Box) even though their mass is close to or sometimes exceeds the most commonly applied 10 kg boundary. We classify PHILAE (96 kg) or the JAXA Solar Power Sail Jupiter Trojan Asteroid Lander as a 'microlanders' not just for their mass being slightly below 100 kg but also for their similarity in design with highly compact microsatellites such as BIRD (92 kg) [99], TET-1 (110 kg) [100], or AsteroidFinder (~127 kg) [101].…”

Section: Small Spacecraftmentioning

confidence: 99%

Capabilities of Gossamer-1 derived small spacecraft solar sails carrying Mascot-derived nanolanders for in-situ surveying of NEAs

et al. 2019

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Any effort which intends to physically interact with specific asteroids requires understanding at least of the composition and multi-scale structure of the surface layers, sometimes also of the interior. Therefore, it is necessary first to characterize each target object sufficiently by a precursor mission to design the mission which then interacts with the object. In small solar system body (SSSB) science missions, this trend towards landing and sample-return missions is most apparent. It also has led to much interest in MASCOT-like landing modules and instrument carriers. They integrate at the instrument level to their mothership and by their size are compatible even with small interplanetary missions.The DLR-ESTEC GOSSAMER Roadmap NEA Science Working Groups' studies identified Multiple NEA Rendezvous (MNR) as one of the space science missions only feasible with solar sail propulsion. Parallel studies of Solar Polar Orbiter (SPO) and Displaced L1 (DL1) space weather early warning missions studies outlined very lightweight sailcraft and the use of separable payload modules for operations close to Earth as well as the ability to access any inclination and a wide range of heliocentric distances. These and many other studies outline the unique capability of solar sails to provide access to all SSSB, at least within the orbit of Jupiter. Since the original MNR study, significant progress has been made to explore the performance envelope of nearterm solar sails for multiple NEA rendezvous.However, although it is comparatively easy for solar sails to reach and rendezvous with objects in any inclination and in the complete range of semi-major axis and eccentricity relevant to NEOs and PHOs, it remains notoriously difficult for sailcraft to interact physically with a SSSB target object as e.g. the HAYABUSA missions do.The German Aerospace Center, DLR, recently brought the GOSSAMER solar sail deployment technology to qualification status in the GOSSAMER-1 project. Development of closely related technologies is continued for very large deployable membrane-based photovoltaic arrays in the GOSOLAR project.We expand the philosophy of the GOSSAMER solar sail concept of efficient multiple sub-spacecraft integration to also include landers for one-way in-situ investigations and sample-return missions. These are equally useful for planetary defence scenarios, SSSB science and NEO utilization. We outline the technological concept used to complete such missions and the synergetic integration and operation of sail and lander. We similarly extend the philosophy of MASCOT and use its characteristic features as well as the concept of Constraints-Driven Engineering for a wider range of operations.

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Section: Small Spacecraftmentioning

confidence: 99%

Capabilities of Gossamer-1 derived small spacecraft solar sails carrying Mascot-derived nanolanders for in-situ surveying of NEAs

et al. 2019

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“…[3] MASCOT (9.64 kg) and its derivatives are 'nanolanders'. PHILAE (96 kg) is a 'microlander' [3] by similarity in design with highly compact microsatellites such as BIRD (92 kg) [89], TET-1 (110 kg) [90], or AsteroidFinder (~127 kg) [91]. Design-driving constraints apply mainly to the launch configuration.…”

Section: Motivationmentioning

confidence: 99%

Solar Sails for Planetary Defense & High-Energy Missions

Grundmann

Bauer

Borchers

et al. 2019

2019 IEEE Aerospace Conference

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20 years after the successful ground deployment test of a (20 m)² solar sail at DLR Cologne, and in the light of the upcoming U.S. NEAscout mission, we provide an overview of the progress made since in our mission and hardware design studies as well as the hardware built in the course of our solar sail technology development. We outline the most likely and most efficient routes to develop solar sails for useful missions in science and applications, based on our developed 'now-term' and near-term hardware as well as the many practical and managerial lessons learned from the DLR-ESTEC GOSSAMER Roadmap. Mission types directly applicable to planetary defense include single and Multiple NEA Rendezvous ((M)NR) for precursor, monitoring and follow-up scenarios as well as sail-propelled head-on retrograde kinetic impactors (RKI) for mitigation. Other mission types such as the Displaced L1 (DL1) space weather advance warning and monitoring or Solar Polar Orbiter (SPO) types demonstrate the capability of near-term solar sails to achieve asteroid rendezvous in any kind of orbit, from Earth-coorbital to extremely inclined and even retrograde orbits. Some of these mission types such as SPO, (M)NR and RKI include separable payloads. For one-way access to the asteroid surface, nanolanders like MASCOT are an ideal match for solar sails in micro-spacecraft format, i.e. in launch configurations compatible with ESPA and ASAP secondary payload platforms. Larger landers similar to the JAXA-DLR study of a Jupiter Trojan asteroid lander for the OKEANOS mission can shuttle from the sail to the asteroids visited and enable multiple NEA sample-return missions. The high impact velocities and re-try capability achieved by the RKI mission type on a final orbit identical to the target asteroid's but retrograde to its motion enables small spacecraft size impactors to carry sufficient kinetic energy for deflection. TABLE OF CONTENTS 1. INTRODUCTION……………………………….2 2. MOTIVATION.

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