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著者人数: 13名, 資料番号: SA1190067000

Accepted: 2018-10-08, 資料番号: SA1180410000

Accepted: 2018-03-12, 資料番号: SA1170290000

Accepted: 2016-12-08, 資料番号: SA1170048000

第29回アストロダイナミクスシンポジウム (2019年7月22-23日. 宇宙航空研究開発機構宇宙科学研究所), 相模原市, 神奈川県, The 29th Workshop on JAXA Astrodynamics and Flight Mechanics 2019 (July 22-23, 2019. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000153060, レポート番号: C-8

This is a COSPAR roadmap to advance the frontiers of science through innovation and international collaboration using small satellites. The world of small satellites is evolving quickly and an opportunity exists to leverage these developments to make scientific progress. In particular, the increasing availability of low-cost launch and commercially available hardware provides an opportunity to reduce the overall cost of science missions. This in turn should increase flight rates and encourage scientists to propose more innovative concepts, leading to scientific breakthroughs. Moreover, new computer technologies and methods are changing the way data are acquired, managed, and processed. The large data sets enabled by small satellites will require a new paradigm for scientific data analysis. In this roadmap we provide several examples of long-term scientific visions that could be enabled by the small satellite revolution. For the purpose of this report, the term "small satellite" is somewhat arbitrarily defined as a spacecraft with an upper mass limit in the range of a few hundred kilograms. The mass limit is less important than the processes used to build and launch these satellites. The goal of this roadmap is to encourage the space science community to leverage developments in the small satellite industry in order to increase flight rates, and change the way small science satellites are built and managed. Five recommendations are made; one each to the science community, to space industry, to space agencies, to policy makers, and finally, to COSPAR. (C) 2019 COSPAR. Published by Elsevier Ltd.

第28回アストロダイナミクスシンポジウム (2018年7月30-31日. 宇宙航空研究開発機構宇宙科学研究所), 相模原市, 神奈川県, The 28th Workshop on JAXA Astrodynamics and Flight Mechanics 2018 (July 30-31, 2018. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000135073, レポート番号: C-20

第28回アストロダイナミクスシンポジウム (2018年7月30-31日. 宇宙航空研究開発機構宇宙科学研究所), 相模原市, 神奈川県, The 28th Workshop on JAXA Astrodynamics and Flight Mechanics 2018 (July 30-31, 2018. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 著者人数: 13名, 資料番号: SA6000135058, レポート番号: C-5

第28回アストロダイナミクスシンポジウム (2018年7月30-31日. 宇宙航空研究開発機構宇宙科学研究所), 相模原市, 神奈川県, The 28th Workshop on JAXA Astrodynamics and Flight Mechanics 2018 (July 30-31, 2018. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000135007, レポート番号: A-7

第25回アストロダイナミクスシンポジウム (2015年7月27-28日. 宇宙航空研究開発機構宇宙科学研究所), 相模原市, 神奈川県, The 25th Workshop on JAXA Astrodynamics and Flight Mechanics 2015 (July 27-28, 2015. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000054014, レポート番号: A-13

第25回アストロダイナミクスシンポジウム (2015年7月27-28日. 宇宙航空研究開発機構宇宙科学研究所), 相模原市, 神奈川県, The 25th Workshop on JAXA Astrodynamics and Flight Mechanics 2015 (July 27-28, 2015. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 著者人数: 12名, 資料番号: SA6000054028, レポート番号: B-6

OMOTENASHI (Outstanding MOon exploration TEchnologies demonstrated by Nano Semi-Hard Impactor) is a JAXA 6U cubesat that aims to perform a semi-hard landing at the Moon surface after being deployed into a lunar fly-by orbit by the American Space Launch System, Exploration Mission-1. In this paper, we present the analysis and design of OMOTENASHI trajectory, divided in a Earth-Moon transfer using a cold gas thruster and a landing phase using a solid rocket motor. Strong constrains exists between the two phases, making the mission design a very challenging task. The flight path angle at Moon arrival must be shallow in order to minimize the effect of delays at the deceleration maneuver. This, together with the execution error of the cold gas maneuver, demands a correction maneuver after the first one to compensate for these errors. Requirements on the ground station tracking are also deduced from this analysis. Under the current subsystems design, we found that the most critical factors in the landing success rate are the maneuver orientation, thrust duration and total delta-v errors. Results suggest accuracy requirements to the landing devices, solid rocket motor and attitude accuracy, as well as to the transfer phase trajectory design.

第17回宇宙科学シンポジウム (2017年1月5日-6日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)相模原キャンパス), 相模原市, 神奈川県, 17th Space Science Symposium (January 5-6, 2017. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)Sagamihara Campus), Sagamihara, Kanagawa Japan, 資料番号: SA6000060108, レポート番号: P-066

第17回宇宙科学シンポジウム (2017年1月5日-6日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)相模原キャンパス), 相模原市, 神奈川県, 17th Space Science Symposium (January 5-6, 2017. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)Sagamihara Campus), Sagamihara, Kanagawa Japan, 著者人数: 18名, 資料番号: SA6000060026, レポート番号: S4-011

This work studies periodic solutions applicable, as an extended phase, to the JAXA asteroid rendezvous mission Hayabusa 2 when it is close to target asteroid 1999 JU3. The motion of a spacecraft close to a small asteroid can be approximated with the equations of Hill’s problem modified to account for the strong solar radiation pressure. The identification of families of periodic solutions in such systems is just starting and the field is largely unexplored. We find several periodic orbits using a grid search, then apply numerical continuation and bifurcation theory to a subset of these to explore the changes in the orbit families when the orbital energy is varied. This analysis gives information on their stability and bifurcations. We then compare the various families on the basis of the restrictions and requirements of the specific mission considered, such as the pointing of the solar panels and instruments. We also use information about their resilience against parameter errors and their ground tracks to identify one particularly promising type of solution., 資料番号: PA1510014000

Accepted: 2014-02-07, 資料番号: SA1140127000

第24回アストロダイナミクスシンポジウム (2014年7月28-29日. 宇宙航空研究開発機構宇宙科学研究所), 相模原市, 神奈川県, The 24th Workshop on JAXA Astrodynamics and Flight Mechanics 2014 (July 28-29, 2014. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000039021, レポート番号: B-1

第22回アストロダイナミクスシンポジウム (2012年7月30-31日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県, The 22th Workshop on JAXA Astrodynamics and Flight Mechanics 2012 (July 30-31, 2012. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000041001, レポート番号: A-1

第23回アストロダイナミクスシンポジウム (2013年7月29-93日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県, The 23rd Workshop on JAXA Astrodynamics and Flight Mechanics 2013 (July 29-30, 2013. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000040063, レポート番号: C-21

第26回アストロダイナミクスシンポジウム (2016年7月25-26日. 宇宙航空研究開発機構宇宙科学研究所), 相模原市, 神奈川県, The 26th Workshop on JAXA Astrodynamics and Flight Mechanics 2016 (July 25-26, 2016. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000088034, レポート番号: B-13

We consider the interplanetary trajectory design problem posed by the 8th edition of the Global Trajectory Optimization Competition and present the end-to-end strategy developed by the team ACT-ISAS (a collaboration between the European Space Agency's Advanced Concepts Team and JAXA's Institute of Space and Astronautical Science). The resulting interplanetary trajectory won 1st place in the competition, achieving a final mission value of $J=146.33$ [Mkm]. Several new algorithms were developed in this context but have an interest that go beyond the particular problem considered, thus, they are discussed in some detail. These include the Moon-targeting technique, allowing one to target a Moon encounter from a low Earth orbit; the 1-$k$ and 2-$k$ fly-by targeting techniques, enabling one to design resonant fly-bys while ensuring a targeted future formation plane% is acquired at some point after the manoeuvre ; the distributed low-thrust targeting technique, admitting one to control the spacecraft formation plane at 1,000,000 [km]; and the low-thrust optimization technique, permitting one to enforce the formation plane's orientations as path constraints., Presented at the 26th AAS/AIAA Space Flight Mechanics Meeting, Napa, CA. Paper AAS 16-275

第16回宇宙科学シンポジウム (2016年1月6日-7日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)相模原キャンパス), 相模原市, 神奈川県, 16th Space Science Symposium (January 6-7, 2016. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)Sagamihara Campus), Sagamihara, Kanagawa Japan, 著者人数: 14名, 資料番号: SA6000046057, レポート番号: P-058

第16回宇宙科学シンポジウム (2016年1月6日-7日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)相模原キャンパス), 相模原市, 神奈川県, 16th Space Science Symposium (January 6-7, 2016. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)Sagamihara Campus), Sagamihara, Kanagawa Japan, 著者人数: 13名, 資料番号: SA6000046053, レポート番号: P-054

第22回アストロダイナミクスシンポジウム (2012年7月30-31日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県, The 22th Workshop on JAXA Astrodynamics and Flight Mechanics 2012 (July 30-31, 2012. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000041024, レポート番号: A-24

Accepted: 2011-07-06, 資料番号: SA1004275000

Accepted: 2011-06-13, 資料番号: SA1003102000

第21回アストロダイナミクスシンポジウム (2011年7月25-26日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県, The 21th Workshop on JAXA Astrodynamics and Flight Mechanics 2011 (July 25-26, 2011. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000042006, レポート番号: A-7

第20回アストロダイナミクスシンポジウム (2010年7月26-27日. 宇宙航空研究開発機構宇宙科学研究所), 相模原市, 神奈川県, The 20th Workshop on JAXA Astrodynamics and Flight Mechanics 2010 (July 26-27, 2010. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, The announced missions to the Saturn and Jupiter systems renewed the space community interest in simple design methods for gravity assist tours at plnetary moons. A key element in such trajectories are the V-Infinity Leveraging Transfers (VILT) which link simple impulsive maneuvers with two consecutive gravity assists at the same moon. VILTs typically include a tangent impulsive maneuver close to an apse location, yielding to a desired change in the excess velocity relative to the moon. In this paper we study the VILT solution space and derive a linear approximation which greatly simplifies the computation of the transfers, and is amenable to broad global searches. Usilng this approximation, Tisserand graphs, and heuristic optimization procedure we introduce a fast design method for multiple-VILT tours. We use this method to design a trajectory from a highly eccentric orbit around Saturn to a 200 km science orbit at Enceladus. The trajectory is then recomputed removing the linear approximation, showing a Delta v change of less than 4%. The trajectory is 2.7 years long and comprises 52 gravity assists at Titan, Rhea, Dione, Tethys, and Enceladus, and several deterministic maneuvers. Total Delta v is only 445 m/s, including the Enceladus orbit insertion, almost 10 times better then the 3.9 km/s of the Enceladus orbit insertion from the Titan-Enceladus Hohmann transfer. The new method and demonstrated results enable a new class of missions that tour and ultimately orbit small mass moons. Such missions were previously considered infeasible due to flight time and Delta v constraints., 資料番号: AA0065115022

第25回アストロダイナミクスシンポジウム (2015年7月27-28日. 宇宙航空研究開発機構宇宙科学研究所), 相模原市, 神奈川県, The 25th Workshop on JAXA Astrodynamics and Flight Mechanics 2015 (July 27-28, 2015. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000054021, レポート番号: A-20

第25回アストロダイナミクスシンポジウム (2015年7月27-28日. 宇宙航空研究開発機構宇宙科学研究所), 相模原市, 神奈川県, The 25th Workshop on JAXA Astrodynamics and Flight Mechanics 2015 (July 27-28, 2015. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000054030, レポート番号: B-8

第15回宇宙科学シンポジウム (2015年1月6日-7日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)相模原キャンパス), 相模原市, 神奈川県, 15th Space Science Symposium (January 6-7, 2015. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)Sagamihara Campus), Sagamihara, Kanagawa Japan, 資料番号: SA6000034245, レポート番号: P-246

第24回アストロダイナミクスシンポジウム (2014年7月28-29日. 宇宙航空研究開発機構宇宙科学研究所), 相模原市, 神奈川県, The 24th Workshop on JAXA Astrodynamics and Flight Mechanics 2014 (July 28-29, 2014. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000039039, レポート番号: B-19

第14回宇宙科学シンポジウム (2014年1月9日-10日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)相模原キャンパス), 相模原市, 神奈川県, 14ｔh Space Science Symposium (January 9-10, 2014. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)Sagamihara Campus), Sagamihara, Kanagawa Japan, 資料番号: SA6000058154, レポート番号: P2-122

第14回宇宙科学シンポジウム (2014年1月9日-10日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)相模原キャンパス), 相模原市, 神奈川県, 14ｔh Space Science Symposium (January 9-10, 2014. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)Sagamihara Campus), Sagamihara, Kanagawa Japan, 著者人数: 11名, 資料番号: SA6000058155, レポート番号: P2-123

第23回アストロダイナミクスシンポジウム (2013年7月29-90日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県, The 23rd Workshop on JAXA Astrodynamics and Flight Mechanics 2013 (July 29-30, 2013. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000040060, レポート番号: C-18

第11回宇宙科学シンポジウム (2011年1月5日-7日. 宇宙航空研究開発機構宇宙科学研究所相模原キャンパス), 相模原市, 神奈川県, 11th Space Science Symposium (January 5-7, 2011. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency), Sagamihara, Kanagawa Japan, 形態: カラー図版あり, 形態: CD-ROM1枚, Physical characteristics: Original contains color illustrations, Note: One CD-ROM, 資料番号: AA0065426047

第11回宇宙科学シンポジウム (2011年1月5日-7日. 宇宙航空研究開発機構宇宙科学研究所相模原キャンパス), 相模原市, 神奈川県, 11th Space Science Symposium (January 5-7, 2011. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency), Sagamihara, Kanagawa Japan, 形態: カラー図版あり, 形態: CD-ROM1枚, Physical characteristics: Original contains color illustrations, Note: One CD-ROM, 資料番号: AA0065426175

Following the spectacular results of the Cassini mission, NASA and ESA plan to return to Titan. For missions such as this to the giant planets and their moons, the primary challenge for trajectory designers is to minimize ΔV requirements while simultaneously ensuring a reasonable time of flight. Employing a combination of invariant manifolds in the planar circular restricted three-body problem and multiple resonant gravity assists allows for the design of trajectories with a very low ΔV. However, these trajectories typically exhibit long flight times. In this study, desired resonances are targeted that, at any single node, minimize the time of flight. The resulting time of flight for a trajectory created using this methodology is compared to that of a trajectory utilizing the maximum single point decrease in semi-major axis. Then, using this framework, the effect of the Jacobi constant on the trajectory’s total ΔV and time of flight is explored. The total trajectory ΔV is shown to vary over the range of Jacobi constants tested due to the interaction between the ΔV required for capture at Titan and the resonances encompassed by the targeted invariant manifold exit region. Over the range of Jacobi constants tested, the total ΔV varies by 28 m/s while the time of flight varies by 3.2 months between the minimum and maximum cases. The lowest Jacobi constant tested results in a 23-month trajectory and a total ΔV of 626 m/s, including a controlled insertion into a 1000 km circular orbit about Titan.

This paper presents the design of a mission to Europa using solar electric propulsion as main source of thrust. A direct transcription method based on Finite Elements in Time was used for the design and optimisation of the entire low-thrust gravity assist transfer from the Earth to Europa. Prior to that, a global search algorithm was used to generate a set of suitable first guess solutions for the transfer to Jupitor, and for the capture in the Jovian system. In particular, a fast deterministic search algorithm was developed to find the most promising set of swing-bys to reach Jupitor. A second fast search algorithm was developed to find the best sequence of swing-bys of the Jovian moons. After introducing the global search algorithms and the direct transcription through Finite Elements in Time, the paper presents a number of first guess solutions and a fully optimised transfer from the Earth to Europa.

With an environment comparable to that of primordial Earth, a surface strewn with liquid hydrocarbon lakes, and an atmosphere denser than that of any other moon in the solar system, Saturn's largest moon Titan is a treasure trove of potential scientific discovery and is the target of a proposed NASA mission scheduled for launch in roughly one decade. A chief consideration associated with the design of any such mission is the constraint imposed by fuel limitations that accompany the spacecraft's journey between celestial bodies. In this study, we explore the use of patched three-body models in conjunction with a discrete mechanical optimization algorithm for the design of a fuel-efficient Saturnian moon tour focusing on Titan. In contrast to the use of traditional models for trajectory design such as the patched conic approximation, we exploit subtleties of the three-body problem, a classic problem from celestial mechanics that asks for the motion of three masses in space under mutual gravitational interaction, in order to slash fuel costs. In the process, we demonstrate the aptitude of the DMOC (Discrete Mechanics and Optimal Control) optimization algorithm in handling celestial mechanical trajectory optimization problems.

著者人数: 12名, 資料番号: SA1004910000

This dissertation expands across three topics the geometric theory of phase space transit in the circular restricted three-body problem (CR3BP) and its generalizations. The first topic generalizes the low energy transport theory that relies on linearizing the Lagrange points in the CR3BP to time-periodic perturbations of the CR3BP, such as the bicircular problem (BCP) and the elliptic restricted three-body problem (ER3BP). The Lagrange points are no longer invariant under perturbation and are replaced by periodic orbits, which we call Lagrange periodic orbits. Calculating the monodromy matrix of the Lagrange periodic orbit and transforming into eigenbasis coordinates reveals that the transport geometry is a discrete analogue of the continuous transport geometry in the unperturbed problem. The second topic extends the theory of low energy phase space transit in periodically perturbed models using a nonlinear analysis of the geometry. This nonlinear analysis relies on calculating the monodromy tensors, which generalize monodromy matrices in order to encode higher order behavior, about the Lagrange periodic orbit. A nonlinear approximate map can be obtained which can be used to iterate initial conditions within the linear eigenbasis, providing a computationally efficient means of distinguishing transit and nontransit orbits that improves upon the predictions of the linear framework. The third topic demonstrates that the recently-discovered "arches of chaos" that stretch through the solar system, causing substantial phase space divergence for high energy particles, may be identified with the stable and unstable manifolds to the singularities of the CR3BP. We also study the arches in terms of particle orbital elements and demonstrate that the arches correspond to gravity assists in the two-body limit. Doctor of Philosophy Suppose that we have a spacecraft and we want to model its motion under gravity. Depending upon what trade-offs we are willing to make between accuracy and complexity, we have several options at our disposal. For example, the restricted three-body problem (R3BP) and its generalizations prove useful in many real-world situations and are rich in theoretical power despite seeming mathematically simple. The simplest restricted three-body problem is the circular restricted three-body problem (CR3BP). In the CR3BP, two masses (like a star and a planet or a planet and a moon) orbit their common center of gravity in circular orbits, while a much smaller body (like a spacecraft) moves freely, influenced by the gravitational fields that the two masses create. If we add in an extra force that acts on the spacecraft in a periodic, cycling way, the regular CR3BP becomes a periodically-perturbed CR3BP. Examples of periodically-perturbed CR3BP's include the bicircular problem (BCP), which adds in a third mass that appears to orbit the center of the system from a distance, and the elliptic restricted three-body problem (ER3BP), which allows the two masses to orbit more realistically as ellipses rather than circles. The purpose of this dissertation is to determine how to select trajectories that move spacecraft between places of interest in restricted three-body models. We generalize existing theories of CR3BP spacecraft motion to periodically-perturbed CR3BP's in the first two topics, and then we investigate some new areas of research in the unperturbed CR3BP in the third topic. We utilize numerical computations and mathematical methods to perform these analyses.