記述言語：英語   掲載種別：研究論文（学術雑誌）  

記述言語：英語   掲載種別：研究論文（学術雑誌）  

記述言語：英語   掲載種別：研究論文（学術雑誌）  

リポジトリ公開URL： https://hdl.handle.net/2324/7238296

出版者・発行元：Journal of Space Safety Engineering  

This study proposes a relative orbit control law for laser debris removal missions considering the uncertainties of laser ablation and atmospheric drag. A removal spacecraft irradiates laser pulses to a target debris to generate the ablation force for deorbiting. The deorbiting force lowers the target altitude, and the removal spacecraft must follow it to maintain its relative position for continuous laser irradiation. The difficulty stems from uncertainties of the magnitude of laser ablation and external disturbances such as atmospheric drag. To tackle this problem, this study derives an adaptive control method using the Gaussian process regression to cancel the uncertainties with a nonparametric regression model. Numerical simulations verify the proposed control law under the uncertainties of laser ablation and atmospheric drag. The proposed control law can contribute to the realization of a safer and more secure mission not only for laser debris removal missions, but also for other on-orbit services.

DOI： 10.1016/j.jsse.2024.04.007

Scopus

出版者・発行元：Journal of Space Safety Engineering  

This paper proposes less fuel strategies for space debris removal. To mitigate the risk of space debris cost-efficiently, multi-rendezvous missions are under development. On the other hand, multi-rendezvous missions often require changing orbital planes of removal satellites, which requires a huge amount of ΔV. Therefore, this study focuses on exploiting the J2 perturbation force as an auxiliary force and aims to establish maneuver rules that minimize ΔV consumption while maximizing the benefit of the J2 perturbation. The J2 perturbation equation is explored analytically, which clarifies whether the change in the semi-major axis or the inclination dominates the efficiency of the exploitation. A straightforward criterion is extracted which determines the efficient maneuver based on the initial inclination of the satellite.

DOI： 10.1016/j.jsse.2024.08.002

Scopus

記述言語：英語   出版者・発行元：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES  

<p>This paper proposes an attitude estimation technique that focuses on rapid change in light intensity, called glint. The states of space objects, such as shape, attitude, and surface properties, are essential information for performing active debris removal and monitoring the operational states of the satellite. Light curve inversion is a cost-effective measure to inversely estimate dynamic states. However, the light curve inversion suffers from divergence when the initial estimate is far from the true state. The glint occurs when a specific geometrical constraint is satisfied, and this glint constraint can be exploited to correct the attitude estimate in a Kalman filter. Thus, assuming a target object as a flat plate, this paper examines whether glint can be used in attitude estimation to improve estimation accuracy. Numerical simulations verify that the attitude estimation filter successfully converges, even when the initial estimate contains a significant error.</p>

DOI： 10.2322/tastj.22.59

CiNii Research

出版者・発行元：AIAA SciTech Forum and Exposition, 2024  

This paper proposes a close approach analysis method considering object attitude change. Implementing a detailed close approach analysis is important for space situational awareness. Conventional conjunction assessment methods assume the shape of the object as a encompassing sphere, which excludes considering the attitude change. However, most of the spacecraft are not spherical, and conventional methods result in overestimation. The proposed method in this paper consists of two steps: 1) calculation of the time of close approach with two objects as point masses and 2) interpolation of the first and last states in the time duration when the close distance is less than a given threshold. Dual quaternions are employed to express the translational and rotational motions, which ensures the uniqueness of the interpolation. Numerical simulations are performed to verify the proposed method and compare it with a conventional method.

DOI： 10.2514/6.2024-1632

Scopus

記述言語：英語   掲載種別：研究論文（学術雑誌）   出版者・発行元：Journal of Guidance, Control, and Dynamics  

This paper considers high-fidelity solar radiation pressure that is modeled with a detailed reflection model. The Cook-Torrance model is used to represent the isotropic reflection. Using the spherical Gaussian distribution, the analytical approximation method of the solar radiation pressure is derived.

DOI： 10.2514/1.G005961

Web of Science

Scopus

リポジトリ公開URL： https://hdl.handle.net/2324/6791121

記述言語：英語  

An active debris removal method using a laser is a promising technology for its advantage in contactless operations. This paper deals with the attitude control of an uncooperative target by a laser, which is an important phase before deorbiting. The difficulty of attitude control by the laser stems from the torque directional constraint because the laser generates thrust along the normal vector of the irradiated face irrespective of the irradiating direction. Thus, the control torque along the normal vector cannot be generated, which makes the attitude control with the laser torque challenging. To tackle this problem, this paper first designs a reference controller that assumes arbitrary control torques are available. Then, a method for determining the irradiating point is proposed so that the difference between the reference torque and the actual one is minimized. Although the proposed controller does not guarantee theoretical convergence to the desired attitude, the effectiveness of the proposed controller is numerically verified for a box-type object. Furthermore, the robustness to the uncertainties of thrust magnitude and direction is also examined by Monte Carlo simulations.

CiNii Research

記述言語：英語  

DOI： 10.3389/frspt.2022.867236

Web of Science

researchmap

記述言語：その他   掲載種別：研究論文（学術雑誌）   出版者・発行元：Journal of Space Safety Engineering  

This paper presents an overview of space solar power satellites for the Moon and Mars mission and simultaneously demonstrates the compression of traditional power generation methods for the orbiter, lander, and habitat on Mars and the Moon. Interplanetary missions are where the space engineers work on the satellites, conceptual design of space habitat, and exploration system. The state of the art in those missions relies on radioisotope thermoelectric generators or solar panels attached with batteries to store power, both of which are plagued by limitations. For instance, when a spacecraft moves away from the Sun, the energy collection efficiency on the solar panel is reduced, and at temperatures below -100°Celsius, individual solar cells degrade unpredictably, deteriorating the performance of solar arrays. Furthermore, these power generation unit satellites carry a pack of batteries to store energy whose total system accounts for more than 10-25 % of the mass of the satellites. In an interplanetary mission, power generation and management are essential for research and investigation on the surface. For Mars, sandstorms affect the collection of energy at the attached solar panel to the rover. Moreover, the rovers must investigate at the far side of the Moon, where sunlight is unavailable for few consecutive days. This challenge can be suitably overcome by employing space solar power satellites, which can be used for wireless power transmission, independent of its location. Such techniques have possible applications towards power transmission for unmanned aerial vehicles for faster mapping purposes. As such, the dependence of those aerial vehicles towards fixed energy storage becomes alleviated. In hindsight, space solar power satellite serves as a potential for an improved energy transmission source than the traditional method for interplanetary rovers and habitat.

DOI： 10.1016/j.jsse.2021.10.008

Web of Science

Scopus

researchmap

記述言語：その他   掲載種別：研究論文（学術雑誌）   出版者・発行元：Journal of Space Safety Engineering  

End-of-life support of satellites is necessary to improve post-mission-disposal compliance rates for maintaining space environment. Deorbit mission with low thrust, e.g. a laser, induces a low-level deceleration on the target object that gradually lowers the target altitude. Since such a low-thrust trajectory is time-consuming, the risk of collision greatly influences the mission success rate. In this context, this paper assesses the collision risk during deorbit trajectories with low thrust. Furthermore, parametric studies for the relationship between the re-entry time and the risk of collision are performed.

DOI： 10.1016/j.jsse.2021.11.002

Web of Science

Scopus

researchmap

出版者・発行元：Proceedings of the International Astronautical Congress, IAC  

Space-advertisement is getting closer with advances in satellite formation flying, which displays an artificial constellation in the night sky. The formation shape composed of pixels of satellites equipping light sources is observed from the ground and different from formation in relative orbits. For realizing the advertisement shape of high quality, there are two requirements, placing the pixels of the advertisement shape properly and keeping the shape during a visible span. It is not enough to satisfy the requirements by the usual coordinate systems and equations. Considering a topocentric coordinate system, the new transforming equations are derived so that an arbitrary advertisement shape is designed at the target time. Also, stable orbits that keep the formation shape without control are found and an example of stable orbits is presented.

Scopus

記述言語：英語   出版者・発行元：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES  

<p>This paper aims to assess the risk of mission termination for a large constellation of satellites in a low-Earth orbit. Many large constellations will be deployed to provide broadband network services using thousands of satellites. There is concern that such large constellations will have a serious impact on the long-term sustainability of outer space activities due to the rapid increase in population. First, therefore, the authors conducted an assessment under nominal activities (referred to as “business-as-usual”) on the basis of a prediction by ESA’s MASTER-2009 and NASA standard breakup model 2001 revision. The assessment found that nearly one catastrophic collision may happen in a large constellation, generating more than two million fragments as small as 1 mm in size. Second, the authors conducted a further assessment assuming a hypothetical collision of a satellite in a large constellation using the NASA standard breakup model and a spherical finite element model adopted in ESA’s MASTER-2009. In consequence, another catastrophic collision may happen to a large constellation, generating approximately a half-million fragments as small as 1 mm in size. Therefore, such catastrophic collisions and resulting secondary collisions should be prevented for large constellations.</p>

DOI： 10.2322/tastj.20.10

CiNii Research

researchmap

出版者・発行元：Proceedings of the International Astronautical Congress, IAC  

The 21st century is marked by the unprecedented progress of human knowledge in space, quantum mechanics, and machine learning. This progress has in turn lead to a significant increase in satellite launches, with various organizations developing mega-constellations in space to provide new business opportunities. While current predictions estimate that space in Low Earth Orbit will be overcrowded in the future, and sustainability of space will become a critical question as the estimated traffic of 89,000 satellites will be launched by the year 2035. To allow sustainable development of space, especially in Low Earth Orbit, there is a need to develop accurate traffic management and active debris removal mission planning. Lately, several organizations proposed and completed space demonstration experiments for debris removal. Current their designs are part of an ongoing project to develop contact-based debris removal technology. However, this technology poses several problems for satellite removal. We propose a complementary method based on a laser system. The laser is capable to operate from a safe distance by stopping the continuous rotation (detumbling) of space objects. In this paper, we present a case study using the ENVISAT satellite. ENVISAT is an 8,211 kg satellite, launched by European Space Agency. Since 2012, communication has stopped, and it is no longer operational. It is predicted to self-deorbit in the next 150 years. However, the orbital simulation of existing objects found two cataloged space debris which will pass within 200 m., resulting in a close approach every year. The elevated mass of the satellite and the number of close approaches, therefore, pose a considerable threat, leading to the production of debris. SKY Perfect JSAT Corporation is working jointly with Japanese institutions to collaboratively develop laser satellites to stop detumbling and the careful removal of debris. The demonstration mission will be launched by the year 2026-2027. With this case study, a laser-based contactless method can be practiced for removing mega debris like ENVISAT from the Low Earth Orbit.

Scopus

出版者・発行元：Proceedings of the International Astronautical Congress, IAC  

Laser ablation is a vital technology for contactless active debris removal, where a service satellite with a laser system irradiates laser pulses to a target satellite to generate the ablation force for deorbiting. The deorbiting force decelerates the target, and the service satellite needs to maintain its relative position and keep irradiating. In other words, both the service satellite and the target are supposed to be deorbited simultaneously, where both satellites have accelerations. The difficulty of simultaneous deorbiting stems from the relative motion between the service satellite and the target in powered flight because conventional formation flying missions assume that only a service satellite maneuvers. This paper derives the relative equations of motion between the service satellite and the target in powered flight. A control law for the simultaneous deorbit is proposed, which determines the timing and direction of the laser ablation and the electrical thrust so that the formation periodically returns to the desired formation. Numerical simulations are performed for two test cases to verify the control law under the uncertainties of thrust magnitude and orbital perturbation.

Scopus

出版者・発行元：Proceedings of the International Astronautical Congress, IAC  

Collisions and explosions of satellites generate a large amount of sub-millimeter-size debris, which can cause fatal damage to a spacecraft. However, such tiny debris cannot be tracked from the ground. Therefore, an in-situ debris measurement satellite, which can detect impacts with sub-millimeter-size debris, has been proposed. Based on this concept, previous studies proposed the method to estimate some orbital parameters of the broken-up object. In those studies, it is assumed that the measurement satellite detects impacts at the intersection of the orbital planes of the measurement satellite and the broken-up object. However, simulated measurement data includes fragments contrary to this assumption. Thus, this study introduces a new approach to estimating the orbital parameters of the broken-up object from simulated measurement data. In this study, the inclination, the right ascension of the ascending node, and the nodal precession rate are estimated from the history of geocentric declination using the iteratively reweighted nonlinear least square method.

Scopus

記述言語：英語   出版者・発行元：Space Solar Power Systems Society  

<p>Wireless Power Transmission (WPT) technology using a satellite-to-satellite system represents a valuable and convenient technology for transferring power wirelessly among Space Solar Power Satellites (SSPS) to Satellite and potential upcoming interplanetary missions. This direct transmission offers a possible solution to deliver continuous, convenient, and unlimited energy supply to satellites to help replace traditional power storage and reduce the weight and ultimately the costs of launching satellites. Satellite industries traditionally use photovoltaic cells and nuclear generators to satisfy the needed electricity by spacecraft. Current power generation and effective management systems occupy up to 10-25% of the satellite's mass. The concept of laser-based WPT from Energy Satellite (E-Sat) can overcome substantial problems. This consistent idea can be adopted for spacecraft by developing a constellation of E-Sat called Energy Orbit (E-Orbit) to supply sufficient power to spacecraft within range. It will increase the impressive performance and operational lifetime. In addition, creating 1600 E-Sat’s constellations to fulfill the power demand in Low Earth Orbit. The overall efficiency variation depends on the selection of Laser, transmitter, transmission distance, and photovoltaic cells, the same as increasing the maximum transmission efficiency of information in a wireless communication network. Consequently, in general, and adequate guidelines of the satellite-to-satellite power transmission system design in practice. The development and demonstration of this technology can help fulfill Space Solar Power Satellite’s idea to transfer gigawatts of renewable energy to Earth.</p>

DOI： 10.24662/sspss.7.0_12

CiNii Research

出版者・発行元：Proceedings of the International Astronautical Congress, IAC  

Solar radiation pressure (SRP) is a major disturbance for a spacecraft operated in deep space missions, affecting its orbit and attitude, and high accuracy of the SRP calculation is required. The accuracy of SRP calculation is affected by the shape and surface characteristics of the satellite. However, existing computational models do not sufficiently take into account the exact reflective properties of the satellite surface. A detailed reflection model and considering the optical characteristics yield a different SRP and its torque from the conventional ones, resulting in a different attitude motion. In this study, an SRP calculation method that considers the exact reflective properties is applied to investigate the attitude dynamics.

Scopus

記述言語：その他   掲載種別：研究論文（学術雑誌）  

DOI： 10.1016/j.jsse.2021.08.004

記述言語：英語   掲載種別：研究論文（学術雑誌）  

記述言語：英語   掲載種別：研究論文（学術雑誌）  

記述言語：英語  

DOI： 10.2514/1.G005877

記述言語：英語   掲載種別：研究論文（学術雑誌）  

記述言語：英語   掲載種別：研究論文（学術雑誌）  

DOI： 10.2514/1.G004966

リポジトリ公開URL： http://hdl.handle.net/2324/4481550

記述言語：その他   掲載種別：研究論文（学術雑誌）  

DOI： 10.1016/j.asr.2018.07.034

記述言語：英語   掲載種別：研究論文（学術雑誌）  

DOI： 10.1016/j.ast.2018.03.021

リポジトリ公開URL： http://hdl.handle.net/2324/4481549

記述言語：英語   掲載種別：研究論文（学術雑誌）  

DOI： 10.1016/j.asr.2018.01.014

記述言語：英語   掲載種別：研究論文（学術雑誌）  

DOI： 10.1016/j.actaastro.2017.11.020

記述言語：英語   掲載種別：研究論文（学術雑誌）  

DOI： 10.1155/2018/2825681

記述言語：英語   掲載種別：研究論文（学術雑誌）  

Spacecraft Line of Sight Maneuver Control Using Skew-arrayed Two Single-Gimbal Control Moment Gyros

DOI： 10.2322/tastj.14.Pd_31

記述言語：英語   掲載種別：研究論文（学術雑誌）  

DOI： 10.2322/tjsass.59.107

記述言語：英語   掲載種別：研究論文（学術雑誌）  

DOI： 10.2514/1.G001249

記述言語：英語   掲載種別：研究論文（学術雑誌）  

DOI： 10.1016/j.asr.2015.07.037

記述言語：英語   掲載種別：研究論文（学術雑誌）  

DOI： 10.1299/kikaic.79.225

記述言語：英語   掲載種別：研究論文（学術雑誌）  

DOI： 10.20965/ijat.2011.p0892

開催年月日： 2024年10月

記述言語：英語   会議種別：口頭発表（一般）  

国名：イタリア共和国  

開催年月日： 2024年9月

記述言語：英語   会議種別：ポスター発表  

開催年月日： 2024年7月

記述言語：英語   会議種別：口頭発表（一般）  

国名：大韓民国  

開催年月日： 2024年7月

記述言語：英語   会議種別：口頭発表（一般）  

国名：大韓民国  

開催年月日： 2023年9月

記述言語：英語   会議種別：口頭発表（一般）  

国名：日本国  

開催年月日： 2023年9月

記述言語：英語   会議種別：口頭発表（一般）  

国名：日本国  

開催年月日： 2023年9月

記述言語：日本語   会議種別：口頭発表（一般）  

開催地：富山   国名：日本国  

開催年月日： 2023年9月

記述言語：日本語   会議種別：口頭発表（一般）  

開催地：富山   国名：日本国  

開催年月日： 2023年9月

記述言語：日本語   会議種別：口頭発表（一般）  

開催地：富山   国名：日本国  

開催年月日： 2023年9月

記述言語：日本語   会議種別：口頭発表（一般）  

開催地：富山   国名：日本国  

開催年月日： 2023年9月

記述言語：日本語   会議種別：口頭発表（一般）  

開催地：富山   国名：日本国  

開催年月日： 2023年9月

記述言語：日本語   会議種別：口頭発表（一般）  

開催地：富山   国名：日本国  

開催年月日： 2023年9月

記述言語：英語   会議種別：口頭発表（一般）  

国名：日本国  

開催年月日： 2023年9月

記述言語：英語   会議種別：口頭発表（一般）  

国名：日本国  

開催年月日： 2023年9月

記述言語：英語   会議種別：口頭発表（一般）  

国名：アメリカ合衆国  

開催年月日： 2023年6月

記述言語：英語   会議種別：口頭発表（一般）  

国名：フランス共和国  

開催年月日： 2023年6月

記述言語：英語   会議種別：口頭発表（一般）  

国名：フランス共和国  

開催年月日： 2023年6月

記述言語：英語   会議種別：口頭発表（一般）  

国名：フランス共和国  

開催年月日： 2023年6月

記述言語：英語   会議種別：口頭発表（一般）  

国名：フランス共和国  

開催年月日： 2023年6月

記述言語：英語   会議種別：口頭発表（一般）  

国名：フランス共和国  

開催年月日： 2023年6月

記述言語：日本語   会議種別：口頭発表（一般）  

開催地：熊本   国名：日本国  

開催年月日： 2023年6月

記述言語：日本語   会議種別：口頭発表（一般）  

開催地：熊本   国名：日本国  

開催年月日： 2023年6月

記述言語：日本語   会議種別：口頭発表（一般）  

開催地：熊本   国名：日本国  

開催年月日： 2023年6月

記述言語：日本語   会議種別：口頭発表（一般）  

開催地：熊本   国名：日本国  

開催年月日： 2023年6月

記述言語：日本語   会議種別：口頭発表（一般）  

開催地：熊本   国名：日本国  

開催年月日： 2023年6月

記述言語：日本語   会議種別：口頭発表（一般）  

開催地：熊本   国名：日本国  

開催年月日： 2023年6月

記述言語：英語   会議種別：口頭発表（一般）  

国名：日本国  

開催年月日： 2023年6月

記述言語：英語   会議種別：口頭発表（一般）  

国名：日本国  

開催年月日： 2023年3月 - 2024年3月

記述言語：日本語   会議種別：口頭発表（一般）  

国名：日本国  

開催年月日： 2022年6月

記述言語：英語   会議種別：口頭発表（一般）  

国名：日本国  

開催年月日： 2022年6月

記述言語：英語  

国名：日本国  

開催年月日： 2022年6月

記述言語：英語   会議種別：口頭発表（一般）  

国名：日本国  

開催年月日： 2022年6月

記述言語：英語   会議種別：口頭発表（一般）  

国名：日本国  

開催年月日： 2022年6月

記述言語：英語   会議種別：口頭発表（一般）  

国名：日本国  

開催年月日： 2019年12月

記述言語：英語  

国名：アメリカ合衆国  

開催年月日： 2019年10月

記述言語：英語  

国名：アメリカ合衆国  

開催年月日： 2017年9月

記述言語：英語  

国名：オーストラリア連邦  

開催年月日： 2016年9月

記述言語：日本語  

researchmap

開催年月日： 2011年8月

記述言語：英語  

国名：アメリカ合衆国  

開催年月日： 2011年7月 - 2011年8月

記述言語：英語  

国名：アメリカ合衆国  

記述言語：英語  

記述言語：日本語  

記述言語：英語  

記述言語：英語  

記述言語：日本語  

記述言語：日本語  

記述言語：英語  

記述言語：英語  

記述言語：英語  

記述言語：英語  

記述言語：日本語  

記述言語：日本語  

記述言語：日本語  

記述言語：日本語  

記述言語：英語  

記述言語：英語  

記述言語：日本語  

記述言語：日本語  

記述言語：日本語  

記述言語：日本語  

記述言語：日本語  

記述言語：日本語  

記述言語：日本語  

記述言語：日本語  

記述言語：日本語  

記述言語：日本語  

記述言語：日本語  

記述言語：日本語  

記述言語：英語  

記述言語：英語  

記述言語：日本語  

記述言語：日本語  

記述言語：日本語  

記述言語：英語  

記述言語：英語  

記述言語：英語  

記述言語：英語  

記述言語：英語  

国名：日本国  

記述言語：英語  

記述言語：英語   会議種別：口頭発表（一般）  

国名：日本国  

記述言語：日本語   会議種別：口頭発表（一般）  

開催地：online   国名：日本国  

記述言語：日本語   会議種別：口頭発表（一般）  

開催地：online   国名：日本国  

記述言語：日本語  

開催地：オンライン   国名：日本国  

記述言語：日本語  

開催地：オンライン   国名：日本国  

記述言語：日本語  

開催地：調布，東京   国名：日本国  

記述言語：日本語  

開催地：調布，東京   国名：日本国  

記述言語：日本語  

開催地：調布，東京   国名：日本国  

記述言語：日本語  

開催地：調布，東京   国名：日本国  

記述言語：日本語  

開催地：調布，東京   国名：日本国  

記述言語：日本語   会議種別：口頭発表（一般）  

researchmap

種別：査読等 

外国語雑誌　査読論文数：2

種別：査読等 

外国語雑誌　査読論文数：5

国際会議録　査読論文数：1

種別：査読等 

外国語雑誌　査読論文数：4

種別：査読等 

外国語雑誌　査読論文数：1