Small spacecraft in small solar system body applications

Grundmann, Jan Thimo; Meb, Jan-Gerd; Biele, Jens; Seefeldt, Patric; Dachwald, Bernd; Spietz, Peter; Grimm, Christian; Spröwitz, Tom; Lange, Caroline; Ulamec, Stephan

doi:10.1109/aero.2017.7943626

Cited by 4 publications

(2 citation statements)

References 49 publications

(37 reference statements)

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“…The development of new electronic and optical technologies allows us to fundamentally change the appearance and capabilities of SSC. Thus, at present SSC with a mass of up to 100 kg can often have a payload with characteristics comparable to those of a large spacecraft [1].…”

Section: Introductionmentioning

confidence: 99%

Application of Low-Power Pulse Plasma Thrusters in Thrust Units of Small Spacecrafts

Bogatiy

Dyakonov

Elnikov

et al. 2021

Applied Mathematics and Computational Mechanics for Smart Applications

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The chapter considers the current state of work on flight models of pulsed plasma propulsion systems. It is shown that the primary application area for propulsion systems based on an ablative pulsed plasma thruster is the station-keeping of small spacecraft with the power of supply system of up to 100 W and with an active lifetime in a range from 1 to 10 years in low Earth orbits with altitudes in a range from 400 to 700 km. It is also shown that ablative pulsed plasma thrusters can be efficiently used to solve the problems of accurate attitude control and angular stabilization of spacecraft.

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Section: Introductionmentioning

confidence: 99%

Application of Low-Power Pulse Plasma Thrusters in Thrust Units of Small Spacecrafts

Bogatiy

Dyakonov

Elnikov

et al. 2021

Applied Mathematics and Computational Mechanics for Smart Applications

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“…They integrate at the instrument level to their mothership on 'small' as well as larger interplanetary missions. [5][6] The DLR (German Aerospace Center) -ESTEC (European Space Research and Technology Centre) GOSSAMER Roadmap NEA Science Working Groups studied small spacecraft concepts. Target-flexible Multiple NEA Rendezvous (MNR) [7], Solar Polar Orbiter (SPO) [8], and Displaced L 1 (DL1) spaceweather early warning [9] were identified as science missions uniquely feasible with solar sail propulsion.…”

Section: Introductionmentioning

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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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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Small spacecraft in small solar system body applications

Cited by 4 publications

References 49 publications

Application of Low-Power Pulse Plasma Thrusters in Thrust Units of Small Spacecrafts

Application of Low-Power Pulse Plasma Thrusters in Thrust Units of Small Spacecrafts

Solar Sails for Planetary Defense & High-Energy Missions

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

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