Presentations -
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Stochastic State Variable Model to Evaluate Survivability of Net-type Tether
Hiroshi Hirayama,Subaru Suzuki
(Himeji) 2024.11 - 2024.11 Japan Society for Aeronautical and Space Sciences
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Development of Control Model for Redundant Actuator in More Electric Aircraft
Riho Sawada, Megumi Watanabe, Taiga Kudo, Hiroshi Hirayama
61st Aircraft Symposium (Kitakyushu) 2023.11 - 2023.11 Japan Society for Aeronautical and Space Sciences
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Analytic Response of Redundant Flight Control Actuator in Jamming Failure
Hiroshi Hirayama, Megumi Watanabe, Riho Sawada, Taiga Kudo
61st Aircraft Symposium (Kitakyushu) 2023.11 - 2023.11 Japan Society for Aeronautical and Space Sciences
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Investigation and Evaluation of Flywheel Battery Model Sizing for Aircraft Electrification
Megumi Watanabe, Riho Sawada, Taiga Kudo, Hiroshi Hirayama
61st Aircraft Symposium (Kitakyushu) 2023.11 - 2023.11 Japan Society for Aeronautical and Space Sciences
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Applied Velocity Changes Using the Patched-Conic Approximation for Permanent Removal of Orbital Debris from Geostationary Orbit
Kento Komatsu, Hiroshi Hirayama
32nd Space Engineering Conference (Semboku) 2023.11 - 2023.11 The Japan Society of Mechanical Engineers, Space Engineering Division
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Application of Deep Learning to On-orbit Observation of Micro-debris Impact Features
Hiroshi Hirayama, Motoharu Nakayama, Kengo Saito
32nd Space Engineering Conference (Semboku) 2023.11 - 2023.11 The Japan Society of Mechanical Engineers, Space Engineering Division
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Survivability of Net-type Tether Considering Simultaneous Severing of Strings
Hiroshi Hirayama
(Toyama) 2023.10 - 2023.10 Japan Society for Aeronautical and Space Sciences
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Analysis of Motion and Evaluation of Elements of The System Configuration in Lunar Vertical Hole Descent Spacecraft
Takashi Shinzawa, Hiroshi Hirayama
(Toyama) 2023.10 - 2023.10 Japan Society for Aeronautical and Space Sciences
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Motion Control of Asteroid Probe and Core Sampler for Tether Recovery
Ryohei Koide, Hiroshi Hirayama
(Toyama) 2023.10 - 2023.10 Japan Society for Aeronautical and Space Sciences
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Measurement evaluation and discussion of wheels for driving on the Martian polar cap
Makoto Ishizuka, Mahiro Kita, Hiroshi Hirayama
(Toyama) 2023.10 - 2023.10 Japan Society for Aeronautical and Space Sciences
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Evaluation of Penetration Performance by Tip Shape of Tubular Sampler for Asteroids
Rokuto Akiyama, Naoki Taira, Hiroshi Hirayama
(Toyama) 2023.10 - 2023.10 Japan Society for Aeronautical and Space Sciences
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Development of a Control System and Improvement of Equipment for MBD, a Method of Observing Microdebris Impact Traces Using a Camera-Mounted Morphable Beam
Motoharu Nakayama, Kengo Saito, Hiroshi Hirayama
(Toyama) 2023.10 - 2023.10 Japan Society for Aeronautical and Space Sciences
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Increased Velocity Using the Patched Conic Approximation for Permanent Removal of Space Debris from Geostationary Orbit
Kento Komatsu, Hiroshi Hirayama
(Toyama) 2023.10 - 2023.10 Japan Society for Aeronautical and Space Sciences
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Collision Avoiding Control of Space Debris Removal Satellites with Operational Satellites
Hiroshi Hirayama, Shintaro Tan
第34回宇宙技術および科学の国際シンポジウム (久留米) 2023.06 - 2023.06 日本航空宇宙学会
A calculation method to estimate survivability of net like tether system is explained in this paper. Electro-dynamic tether is a candidate device to decelerate an orbital debris without propellant. Major problem on using a tether in space is its vulnerability against collisions by space debris. Some conceptual designs are proposed to enhance the survivability of tether, such as tape tether, multiline tether or net-type tether. Authors formulated survivability of multi-segmented double-line tether in preceding study. In this study, the calculation method is extended to treat a net type triple tether which has been developed for the EDT by JAXA. Procedure of the calculation is as follows. First, fatality rates of each element in net type tether are calculated by integrating differential flux multiplied by cross-sectional area, then survivabilities of each tether element are obtained as a function of time. Next, considering topology of net, probabilities along possible severing paths are summed up, and survivability of whole tether is obtained. At last, a simplified method with desirable precision and faster computation time is introduced. Numerical example shows that the net tether has much higher survivability than that of the double tether.
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Failure Response Analysis of Redundant Actuator Model in Aircraft Electrification
Ryosuke Suzuki, Riho Sawada, Hiroshi Hirayama
JSASS Northern Branch 2023 Annual Meeting and the 4th Symposium on Reusable Space Transportation Vehicles (Kakuda, Miyagi) 2023.03 - 2023.03 Northern Branch of the Japan Society for Aeronautical and Space Sciences
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Evaluation of Control Models for Redundant Actuator Test Equipment in Aircraft Electrification
Riho Sawada, Megumi Watanabe, Hiroshi Hirayama
JSASS Northern Branch 2023 Annual Meeting and the 4th Symposium on Reusable Space Transportation Vehicles (Kakuda, Miyagi) 2023.03 - 2023.03 Northern Branch of the Japan Society for Aeronautical and Space Sciences
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Study of Permanent Removal Trajectory of Space Debris from Geostationary Orbit
Kento Komatsu, Hiroshi Hirayama
JSASS Northern Branch 2023 Annual Meeting and the 4th Symposium on Reusable Space Transportation Vehicles (Kakuda, Miyagi) 2023.03 - 2023.03 Northern Branch of the Japan Society for Aeronautical and Space Sciences
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A Study on Penetration and Stratigraphic Retention of Asteroid Soil Core Sampler
Kakeru Yoshimoto, Rokuto Akiyama, Hiroshi Hirayama
(Kumamoto) 2022.11 - 2022.11 Japan Society for Aeronautical and Space Sciences
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Soichiro Yagi, Motoharu Nakayama, Hiroshi Hirayama
10th Space Debris Workshop (Chofu) 2022.11 - 2022.11 Japan Aerospace Exploration Agency, Research and Development Directorate
There is a data gap in the information on the spatial density of micro debris in orbit. This is particularly noticeable in SSO and GEO, where analysis and inspection by recovered spacecraft are relatively difficult. We are developing a debris impact masks observation system, ODIM, as one of the observation instruments for spacecraft in these orbits, which can autonomously observe debris impact marks on the exterior of the onboard spacecraft and obtain information on the existence spatial density of micro debris. The ODIM consists of a depth camera and a morphable beam (MB), a structural material that can maintain its shape even when subjected to external forces. One of the challenges is that the MB control relies on manual operation via uplink. This is because the bending accuracy is not sufficient due to the MB's flexibility, and because it is a nonholonomic system, it is not easy to control the tip position. In this research, in order to solve this problem, we developed and evaluated an integrated system MBD-4 equipped with a new MB and an autonomous control system for the MB. The system creates a three-dimensional map based on the geometry data of the entire spacecraft and determines the current position of the MB tip using image processing on deep learning and localization. This system is expected to fully automate debris impact marks observation with ODIM alone.
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Development of In-situ Observation System for Micro Space Debris Impact Marks using Deep Learning and Autonomous Control
Soichiro Yagi, Motoharu Nakayama, Hiroshi Hirayama
(Kumamoto) 2022.11 - 2022.11 Japan Society for Aeronautical and Space Sciences