Multiple near-earth asteroid rendezvous mission: Solar-sailing options

Peloni, Alessandro; Dachwald, Bernd; Ceriotti, Matteo

doi:10.1016/j.asr.2017.10.017

Cited by 29 publications

(24 citation statements)

References 41 publications

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“…That is, ATOSS found a multi-phase trajectory that is about 300 days (~10 months) shorter than the reference solution. The mission time of the second optimized test case is 3,183 days, whereas the solution found in [24] for the same sequence showed a mission completed in 3,521 days, which is about 340 days (~11 months) longer than what was found by ATOSS. In both cases, the sailcraft spends more than 90 days in the proximity of each asteroid.…”

Section: Campaign 2: Multiple Nea Rendezvousmentioning

confidence: 65%

“…The first one is the five-NEA rendezvous mission shown in [14]. The second test case is the first five-NEA rendezvous mission shown in [24].…”

Section: Campaign 2: Multiple Nea Rendezvousmentioning

confidence: 99%

“…To the best of the authors' knowledge, the work of Peloni et al [24] is the only one that shows a large number of solar-sail multiple-rendezvous OCPs solved in an automated way.…”

Section: Introductionmentioning

confidence: 99%

“…For the aforementioned reasons, the primary aim of this paper is to present a toolbox able to find solar-sail multiple-rendezvous trajectories in an automated way, thus improving the results shown in [24]. Such tool is the first step towards a more efficient way to generate several solutions for preliminary solar-sail mission design.…”

Section: Introductionmentioning

confidence: 99%

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Automated Trajectory Optimizer for Solar Sailing (ATOSS)

Peloni

Rao

Ceriotti

2018

Aerospace Science and Technology

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The problem of finding an optimal solar-sail trajectory must be solved by means of numerical methods, since no analytical, closed-form solutions exist. A new tool named ATOSS (Automated Trajectory Optimizer for Solar Sailing) has been developed for optimizing multi-phase solar-sail trajectories. A shape-based method for solar sailing and a two-stage approach for the optimization are the keys to the success of ATOSS, which operates with minimum inputs required to the user. Once the initial guess is generated by means of the shape-based method, the above mentioned two-stage approach works as follows. First, a solution to the optimal control problem at hand is sought; subsequently, the boundaries on the times are modified so that a better solution, in terms of total mission duration, is searched. Several numerical test cases are presented to demonstrate ATOSS' ability to automatically find optimal solar-sail trajectories for single-and multi-phase optimization problems. Moreover, the shape-based method for solar sailing has been validated as a viable method to produce initial guess solutions for a direct optimization algorithm.

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Section: Campaign 2: Multiple Nea Rendezvousmentioning

confidence: 65%

“…The first one is the five-NEA rendezvous mission shown in [14]. The second test case is the first five-NEA rendezvous mission shown in [24].…”

Section: Campaign 2: Multiple Nea Rendezvousmentioning

confidence: 99%

“…To the best of the authors' knowledge, the work of Peloni et al [24] is the only one that shows a large number of solar-sail multiple-rendezvous OCPs solved in an automated way.…”

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Automated Trajectory Optimizer for Solar Sailing (ATOSS)

Peloni

Rao

Ceriotti

2018

Aerospace Science and Technology

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“…1 -3D view of [184] contains two almost km-sized PHAs after a very small first target possibly of interest to ARRM-like missions [102]. Its total ΔV for only 3 targets is 52.1 km/s, considered not feasible with near-term high-performing electric-propulsion technology [184]. Low-thrust missions requiring a consumable propellant are restricted to the thin end of the low-ΔV tail of the total ΔV distribution of sequences.…”

Section: Table 1 -Reference Mnr Mission Sequence [10]mentioning

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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