Automated Trajectory Optimizer for Solar Sailing (ATOSS)

Peloni, Alessandro; Rao, Anil V.; Ceriotti, Matteo

doi:10.1016/j.ast.2017.11.025

Cited by 22 publications

(12 citation statements)

References 29 publications

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“…That is, we consider a mass penalty of 100 kg added solely for the not-sail-optimized overhead to the 50 kg bus + payload of our one-MASCOT MNR sailcraft (Grundmann et al, 2019a). To achieve ac = 0.2 mm/s², and thus the same performance as baselined by Grundmann et al (2017) and the trajectory optimization by Peloni et al (2018b) it was based on, it would have to grow to (85 m)², merely the limit of the GOSSAMER technology 'comfort zone'.…”

Section: Going Slowly Still Goesmentioning

confidence: 99%

Sailing at the brink – The no-limits of near-/now-term-technology solar sails and SEP spacecraft in (multiple) NEO rendezvous

Ceriotti

Viavattene

Moore

et al. 2021

Advances in Space Research

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Near-Earth object (NEO) in-situ exploration can provide invaluable information for science, possible future deflection actions and resource utilisation. This is only possible with space missions which approach the asteroid from its vicinity, i.e. rendezvous. This paper explores the use of solar sailing as means of propulsion for NEO rendezvous missions. Given the current state of sail technology, we search for multiple rendezvous missions of up to ten years and characteristic acceleration of up to 0.10 mm/s². Using a tree-search technique and subsequent trajectory optimisation, we find numerous options of up to three NEO encounters in the launch window 2019-2027. In addition, we explore steerable and throttleable low-thrust (e.g. solar-electric) rendezvous to a particular group of NEOs, the Taurid swarm.We show that an acceleration of 0.23 mm/s 2 would suffice for a rendezvous in approximately 2000 days, while shorter transfers are available as the acceleration increases. Finally, we show low-thrust options (0.3 mm/s 2 ) to the fictitious asteroid 2019 PDC, as part of an asteroid deflection exercise.

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Section: Going Slowly Still Goesmentioning

confidence: 99%

Sailing at the brink – The no-limits of near-/now-term-technology solar sails and SEP spacecraft in (multiple) NEO rendezvous

Ceriotti

Viavattene

Moore

et al. 2021

Advances in Space Research

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“…[10] Again, the last leg (Table 1) is replaced by a leg to PHA 2011 AG 5 , for which a fictitious impact was expected for February 3 rd , 2040. A methodology similar to [153][154][155][156] [226] has been used. Total mission duration is ~12 years; arrival at 2011 AG 5 on May 25 th , 2037, about 3 years before impact.…”

Section: Planetary Defense Exercisesmentioning

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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“…Optimal sail trajectories to the outer solar system have been investigated by Dachwald 20 . More recently, the automated trajectory optimizer for solar sailing has been developed for trajectory design for sail propelled planetary transfers or NEA rendezvous by Peloni et al 21,22 Locally optimal solutions have been obtained for planet‐centered orbits but do not account for eclipsing or high‐fidelity dynamics models 23‐30 . Ultimately, none of these works address the specific challenges of Earth‐centered orbit transfer and phasing maneuvering using realizable sail‐system masses or dimensions.…”

Section: Introductionmentioning

confidence: 99%

Geostationary debris mitigation using minimum time solar sail trajectories with eclipse constraints

Kelly

Bevilacqua

2020

Optim Control Appl Methods

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SummaryMinimum time solar sailing trajectories are introduced using a combination of indirect and direct optimal control techniques. Here, large‐scale, multiphase optimal control problems are solved using a pseudospectral collocation technique applied to an orbital debris mitigation concept. These solutions are obtained for realistic sail dimensions, producing multirevolution, Earth‐centered trajectories while accounting for uncontrolled spacecraft dynamics in the eclipse regions. Specifically, minimum time solutions for orbit transfer and phasing maneuvers are obtained using only solar radiation pressure for propulsion and control. First, an optimal primer vector steering history is obtained through numerical approximation. Locally optimal, closed‐form solutions are then implemented based on the primer vector direction, resulting in minimum time satisfaction of desired terminal orbital conditions. In addition, a novel solution strategy is presented for multiphase optimal control problems characterized by uncontrollable dynamics with flexible phase boundaries. The maneuvers presented will be shown to enable efficient orbital debris mitigation for large‐scale debris in geostationary orbits.

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Automated Trajectory Optimizer for Solar Sailing (ATOSS)

Cited by 22 publications

References 29 publications

Sailing at the brink – The no-limits of near-/now-term-technology solar sails and SEP spacecraft in (multiple) NEO rendezvous

Sailing at the brink – The no-limits of near-/now-term-technology solar sails and SEP spacecraft in (multiple) NEO rendezvous

Solar Sails for Planetary Defense & High-Energy Missions

Geostationary debris mitigation using minimum time solar sail trajectories with eclipse constraints

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