Presentations -

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

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

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

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

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

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

Survivability of Net-type Tether Considering Simultaneous Severing of Strings

Hiroshi Hirayama

(Toyama)  2023.10  -  2023.10  Japan Society for Aeronautical and Space Sciences

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

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

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

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

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

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

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.

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

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

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

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

Development of In-situ Observation Robot for Micro Space Debris Impact Marks using Localization and Autonomous Control

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.

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

Proposal and Evaluation of a Wheel Shape for Driving on the Martian Polar cap

Makoto Ishizuka, Hiroshi Hirayama

(Kumamoto)  2022.11  -  2022.11  Japan Society for Aeronautical and Space Sciences

Motion Control of a Spacecraft During Recovery of a Tethered Asteroid Soil Sampler

Ryohei Koide, Hiroshi Hirayama

(Kumamoto)  2022.11  -  2022.11  Japan Society for Aeronautical and Space Sciences

A Study on Dynamics Analysis and System Configuration into Lunar Vertical Holes Descent Probe

Takashi Shinzawa, Hiroshi Hirayama

(Kumamoto)  2022.11  -  2022.11  Japan Society for Aeronautical and Space Sciences

Risk Assessment of Simultaneous Disconnection in Net-type Tethers

Shintaro Tan, Hiroshi Hirayam

(Kumamoto)  2022.11  -  2022.11  Japan Society for Aeronautical and Space Sciences

Attitude Control of Passive Debris Remover to Reduce Collision Risk with Operational Satellites

Hiroshi Hirayama

(Kumamoto)  2022.11  -  2022.11  Japan Society for Aeronautical and Space Sciences

Development and Evaluation of Flywheel Battery Model in Aircraft Electrification

Megumi Watanabe, Hiroshi Hirayama

60th Aircraft Symposium  (Niigata)  2022.10  -  2022.10  Japan Society for Aeronautical and Space Sciences

Electromagnetic Design of Dual Winding Permanent Magnet Synchronous Motor for Electromechanical Actuators of Flight Control Systems

Yutaka Terao, Hiroshi Hirayama, Hirotaka Sugawara, Hitoshi Oyori

International Power Electronics Conference  (姫路市)  2022.05  -  2022.05 

This paper deals with PM motors using multipole anisotropic ring magnet for electro mechanic actuators (EMAs) of future aircraft flight control systems. The electromagnetic design via FEM software and evaluations of motor torque, losses in healthy and failure state are carried out. The results showed that even if one-phase open circuit of an inverter occurred or one-side of the 3-phase current supply system failed, the PM motor could operate at 100% of the average torque of 5.5 Nm or over 14.6 Nm, which is over 97 % of the maximum torque of 15.0 Nm.

DOI

Research and Development of Flywheel Battery Model in Aircraft Electrification

Kyohei Igari, Kakeru Ino, Hiroshi Hirayama

JSASS Northern Branch 2022 Annual Meeting and the 3rd Symposium on Reusable Space Transportation Vehicles  (online)  2022.03  -  2022.03  Japan Society for Aeronautical and Space Sciences

A Study of the Spacecraft Descent System into the Lunar Holes Considering the Friction and Tipping of the Anchors.

Takashi Shinzawa, Hiroshi Hirayama

JSASS Northern Branch 2022 Annual Meeting and the 3rd Symposium on Reusable Space Transportation Vehicles  (online)  2022.03  -  2022.03  Japan Society for Aeronautical and Space Sciences

Research and Development of Redundant Actuator Model in Aircraft Electrification

Kakeru Ino, Kyohei Igari, Hiroshi Hirayama

JSASS Northern Branch 2022 Annual Meeting and the 3rd Symposium on Reusable Space Transportation Vehicles  (online)  2022.03  -  2022.03  Japan Society for Aeronautical and Space Sciences

Development and Evaluation of Redundant Actuator Test Equipment for Aircraft Electrification

Riho Sawada, Hiroshi Hirayama

JSASS Northern Branch 2022 Annual Meeting and the 3rd Symposium on Reusable Space Transportation Vehicles  (online)  2022.03  -  2022.03  Japan Society for Aeronautical and Space Sciences

Development and Evaluation of Flywheel Battery Test Equipment in Aircraft Electrification

Megumi Watanabe, Hiroshi Hirayama

JSASS Northern Branch 2022 Annual Meeting and the 3rd Symposium on Reusable Space Transportation Vehicles  (online)  2022.03  -  2022.03  Japan Society for Aeronautical and Space Sciences

Proposal and Evaluation of a Wheel Shape for Driving on the Martian Polar Cap

Makoto Ishizuka, Hiroshi Hirayama

JSASS Northern Branch 2022 Annual Meeting and the 3rd Symposium on Reusable Space Transportation Vehicles  (online)  2022.03  -  2022.03  Japan Society for Aeronautical and Space Sciences

A Study on Attitude Control of Spacecraft with Asteroid Soil Core Sampler

Ryohei Koide, Hiroshi Hirayama

JSASS Northern Branch 2022 Annual Meeting and the 3rd Symposium on Reusable Space Transportation Vehicles  (online)  2022.03  -  2022.03  Japan Society for Aeronautical and Space Sciences

Collision Avoiding Control of Space Debris Removal Satellites with Operational Satellites

Noriyuki Nishijou, Hiroshi Hirayama

第33回宇宙技術および科学の国際シンポジウム  (オンライン)  2022.02  -  2022.03  日本航空宇宙学会

Passive removal satellites for small space debris have been studied. When they are deployed over a large area, there is a possibility that they will collide with an operating satellite instead of debris. In this study, we aim to reduce the risk of collision by temporarily folding or changing the attitude of deployed removal satellites. The debris environment model MASTER or ORDEM is used to estimate the collision risk. In addition, effect of a low-thrust collision avoidance maneuver using solar light pressure and aerodynamic force, which is suitable for large-area removal satellites, are investigated.

Influence of Cutting Path and Calculation Parameters for Survival Probability of Net-type Tethers

Shintaro Tan, Hiroshi Hirayama

(online)  2021.11  -  2021.11  Japan Society for Aeronautical and Space Sciences

Remote Class of Basic Engineering to Build Model of Planetary Exploration Rover

Hiroshi Hirayama

(online)  2021.11  -  2021.11  Japan Society for Aeronautical and Space Sciences

Development of an on-orbit observation system for micro space debris impact marks using deep learning

Soichiro Yagi, Hiroshi Hirayama

(online)  2021.11  -  2021.11  Japan Society for Aeronautical and Space Sciences

Collision Avoiding Control of Space Debris Removal Satellites with Operational Satellites

Noriyuki Nishijou, Hiroshi Hirayama

(online)  2021.11  -  2021.11  Japan Society for Aeronautical and Space Sciences

A Study on the Penetration Performance of Asteroid Soil Core Sampler with Stratigraphic Retention Performance

Kakeru Yoshimoto, Hiroshi Hirayama

(online)  2021.11  -  2021.11  Japan Society for Aeronautical and Space Sciences

Traction Performance of Wheels for Mars Polar Rover on Ice and Sand

Yuya Iwasa, Hiroshi Hirayama

(online)  2021.11  -  2021.11  Japan Society for Aeronautical and Space Sciences

Study on Collision Avoidance Method between Space Debris Removal Satellite and Active Satellite

Noriyuki Nishijou, Hiroshi Hirayama

JSASS Northern Branch 2021 Annual Meeting and the 2nd Symposium on Reusable Space Transportation Vehicles  (online)  2021.03  -  2021.03  Japan Society for Aeronautical and Space Sciences

Evaluation of Survival Probability Considering the Cutting Path of Net-type Tethers

Shintaro Tan, Hiroshi Hirayama

JSASS Northern Branch 2021 Annual Meeting and the 2nd Symposium on Reusable Space Transportation Vehicles  (online)  2021.03  -  2021.03  Japan Society for Aeronautical and Space Sciences

Development of a System for Real-time Inspection of Satellite Appearance using Image Processing

Soichiro Yagi, Hiroshi Hirayama

JSASS Northern Branch 2021 Annual Meeting and the 2nd Symposium on Reusable Space Transportation Vehicles  (online)  2021.03  -  2021.03  Japan Society for Aeronautical and Space Sciences

A Study on the Structure of Asteroid Soil Core Sampler Considering Penetration Impact

Kakeru Yoshimoto, Hiroshi Hirayama

JSASS Northern Branch 2021 Annual Meeting and the 2nd Symposium on Reusable Space Transportation Vehicles  (online)  2021.03  -  2021.03  Japan Society for Aeronautical and Space Sciences

Research on Removal Low-orbital Small Space Debris with Laser

Hansol Kim, Hiroshi Hirayama

JSASS Northern Branch 2021 Annual Meeting and the 2nd Symposium on Reusable Space Transportation Vehicles  (online)  2021.03  -  2021.03  Japan Society for Aeronautical and Space Sciences

Research and Development of Flywheel Battery Model in Aircraft Electrification

Kyohei Igari, Kakeru Ino, Yasuhiko Yamamoto, Hirotaka Sugawara, Hitoshi Oyori, Hiroshi Hirayama

(online)  2020.11  -  2020.11  Japan Society for Aeronautical and Space Sciences

Research and Development of Redundant Actuator Model in Aircraft Electrification

Kakeru Ino, Kyohei Igari, Yasuhiko Yamamoto, Hirotaka Sugawara, Hitoshi Oyori, Hiroshi Hirayama

(online)  2020.11  -  2020.11  Japan Society for Aeronautical and Space Sciences

A Study of the Traction by Wheels Capable of Traveling on the Martian Polar Ice Caps

Yuya Iwasa, Hiroshi Hirayama

(online)  2020.10  -  2020.10  Japan Society for Aeronautical and Space Sciences

Improving Performance of Soil Core Sampler for Asteroid

Hiroshi Hirayama, Masanari Horii

(online)  2020.10  -  2020.10  Japan Society for Aeronautical and Space Sciences

Dynamics and Simulation of Tether Capture Process for Space Debris

Zhihong Wang, Hiroshi Hirayama

(online)  2020.10  -  2020.10  Japan Society for Aeronautical and Space Sciences

A Study on Deformation of Tape Tether with Slight Rarefied Atmospheric Drag

Morie Koseki, Hiroshi Hirayama

(online)  2020.10  -  2020.10  Japan Society for Aeronautical and Space Sciences

Development of an Asteroid Soil Core Sampler using Rectangular Tube

Hiroshi Hirayama, Ichiri Nakamura

(Tokushima)  2019.11  -  2019.11  Japan Society for Aeronautical and Space Sciences

Development of Extension and Deformation Device 2 to Control Morphable Beam

Shogo Saito, Hiroshi Hirayama

(Tokushima)  2019.11  -  2019.11  Japan Society for Aeronautical and Space Sciences

Experiment model developmentof a Multipoint Suspended Explorer in a Lunar Hole

Takehiro Suzuki, Hiroshi Hirayama

(Tokushima)  2019.11  -  2019.11  Japan Society for Aeronautical and Space Sciences

Corporate collaboration and human resource development in student joint experiment as space education activities including Noshiro space event

Keisuke Maeda, Yutaka Wada, Akimasa Tsutsumi, Hiroshi Hirayama, Harunori Nagata, Hiroaki Akiyama

(Tokushima)  2019.11  -  2019.11  Japan Society for Aeronautical and Space Sciences

Lecture on Rockets:(History and Technology)

Hiroshi Hirayama  [Invited]

(Akita)  2019.09  -  2019.09  Japan Society of Mechanical Engineers

DOI

Development of Extension and Deformation Device 2 to Control Morphable Beam

Shogo Saito, Hiroshi Hirayama

(Akita)  2019.09  -  2019.09  Japan Society of Mechanical Engineers

A Study on Movement of a Multipoint Suspended Explorer in a Lunar Hole

Takehiro Suzuki, Hiroshi Hirayama

(Akita)  2019.09  -  2019.09  Japan Society of Mechanical Engineers

Proposal for Shapes of Wheels Driven on Icy Mars Polar Cap

Hiroshi Hirayama, Tsubasa Oyama

(Akita)  2019.09  -  2019.09  Japan Society of Mechanical Engineers

Motion Analysis of Capturing Space Debris using Tether

Hiroshi Hirayama, Keigo Sato

第32回宇宙技術および科学の国際シンポジウム  (福井市)  2019.06  -  2019.06  日本航空宇宙学会

This paper describes motion analysis of a tethered satellite which contacts to a space debris in order to capture and remove it. One of difficulties about removal of the debris is how to capture an uncooperative object. We propose a capturing method using a tether. First, a mother satellite extends a tether with a daughter satellite, after a while they will be vertically stabilized by gravity gradient torque. Next, the satellites approaches to a target object in slow relative velocity. If the tether intercept the object in appropriate condition, the tether will wind around the target while the daughter will turn around it. The daughter is assumed to have some mechanisms to catch their own tether. Two dimensional motions of the mother, daughter and target are numerically simulated in this study. Some successful motions of the daughter turning around the target are shown when the parameters are appropriate. This method of capturing is very adaptable to electro-dynamic tether (EDT), which is a promising candidate to decelerate the space debris without propellant. So, this study will contribute to the removal of the space debris.

A Study on Movement of a Multipoint Suspended Explorer in a Lunar Hole

Takehiro Suzuki, Hiroshi Hirayama

第32回宇宙技術および科学の国際シンポジウム  (福井市)  2019.06  -  2019.06  日本航空宇宙学会

This paper proposes a new method to descend into lunar hole for an unmanned explorer. The vertical holes of about 50 m diameter were found on the lunar surface in 2009. A candidate method to explore is tether suspended descent, but single tethered probe is limited only along vertical movement. So, we propose a lunar hole explorer that has a descending probe suspended by tethers from two or three points on a rim of the hole. The probe can move in two or three dimensionally by controlling length of each tether so that has advantage for geological survey on wall in the hole at close range. However it has limitation on movable region. First, the movable region was formulated from equilibrium of forces. Next the region is calculated and visualized assuming values of design parameters. Finally descending trajectories are proposed within the region.

A Study on Deformation of Tape Tether with Rarefied Atmospheric Drag

Morie Koseki, Hiroshi Hirayama

第32回宇宙技術および科学の国際シンポジウム  (福井市)  2019.06  -  2019.06  日本航空宇宙学会

This paper describes a study on deformation analysis of the tape tether. A tape shaped tether has advantages that it is easy to extend and it has better survivability, compared to conventional string shaped tether. We focus on the tape tether in this study, because there are a lot of studies on behaviour or control of the string tether but not many analysis have been done on deformation of the tape tether.Hence, we study a deformation analysis of the tape tether considering rarefied atmospheric drag. Result of the numerical simulation shows the deformation of the tape tether and overall atmospheric drag.

Extension and Deformation Control Device of Morphable Beam

Shogo Saito, Hiroshi Hirayama

第32回宇宙技術および科学の国際シンポジウム  (福井市)  2019.06  -  2019.06  日本航空宇宙学会

This paper describes mechanism of a Morphable Beam (MB) with a camera to observe surface of satellite. Increasing number of space debris is serious problem on sustainable space development. Especially, micro debris is believed to exist in huge number but its distribution is not clearly known, because it can be estimated only from inspection of damages on surface of objects retrieved from orbit. Thus, we propose the mechanism to solve these problems. First, we developed an extension and bending mechanism for the MB attached with an observation camera on the tip, which is controlled to reach target point. And then, we conducted three types of experiments to verify its performance of extension and deformation of the MB. Results of the experiments shows that the extension lengths and the deformations are almost proportional to control inputs. Therefore, it is considered that the proposed mechanism is capable to control the MB. According to the proposed mechanism, in-situ surface inspection of satellite becomes possible and the density data of micro debris can be acquired.

Feasibility Study on Capturing Space Debris using Metal Welding

Takeru Yoshimura, Hiroshi Hirayama

JSASS Northern Branch 2019 Annual Meeting and the 20th Symposium on Propulsion System for Reusable Launch Vehicles  (Kakuda)  2019.03  -  2019.03  Japan Society for Aeronautical and Space Sciences

Proposal of a Soil Core Sampler for Asteroid

Ichiri Nakamura, Hiroshi Hirayama

JSASS Northern Branch 2019 Annual Meeting and the 20th Symposium on Propulsion System for Reusable Launch Vehicles  (Kakuda)  2019.03  -  2019.03  Japan Society for Aeronautical and Space Sciences

A Study on Deformation of Tape Tether with Rarefied Atmospheric Drag

Morie Koseki, Hiroshi Hirayama

JSASS Northern Branch 2019 Annual Meeting and the 20th Symposium on Propulsion System for Reusable Launch Vehicles  (Kakuda)  2019.03  -  2019.03  Japan Society for Aeronautical and Space Sciences

Proposal for Shapes of Wheels Driven on Icy Mars Polar Cap

Tsubasa Oyama, Hiroshi Hirayama

JSASS Northern Branch 2019 Annual Meeting and the 20th Symposium on Propulsion System for Reusable Launch Vehicles  (Kakuda)  2019.03  -  2019.03  Japan Society for Aeronautical and Space Sciences

Development of a Deployable Small End Effector for Capturing Space Debris

Hiroshi Hirayama, Yuki Ohtani

(Kurume)  2018.10  -  2018.10  Japan Society for Aeronautical and Space Sciences

Development of a Space Structure Deployed by Electromagnets

Hiroshi Hirayama, Yuhei Nemoto

(Kurume)  2018.10  -  2018.10  Japan Society for Aeronautical and Space Sciences

Safety management and corporate collaboration in space education activities including Noshiro space event

Keisuke Maeda, Yutaka Wada, Akimasa Tsutsumi, Hiroshi Hirayama, Harunori Nagata, Hiroaki Akiyama

(Kurume)  2018.10  -  2018.10  Japan Society for Aeronautical and Space Sciences

Extension and Deformation Control Device of Morphable Beam

Shogo Saito, Hiroshi Hirayama

(Kurume)  2018.10  -  2018.10  Japan Society for Aeronautical and Space Sciences

A Study on Movement of a Multipoint Suspended Explorer in a Lunar Hole

Takehiro Suzuki, Hiroshi Hirayama

(Kurume)  2018.10  -  2018.10  Japan Society for Aeronautical and Space Sciences

Practical Space Education in Noshiro Space Event and Future Prospective

Akimasa Tsutsumi, Hiroshi Hirayama, Yutaka Wada, Keisuke Maeda, Hiroaki Akiyama

(Sendai)  2018.03  -  2018.03  Japan Society for Aeronautical and Space Sciences

Practical Space Education in Noshiro Space Event and Future Prospective

Akimasa Tsutsumi, Hiroshi Hirayama, Yutaka Wada, Keisuke Maeda, Hiroaki Akiyama

(Niigata)  2017.10  -  2017.10  Japan Society for Aeronautical and Space Sciences

Attitude Control Simulator for the Small Satellite and Its Validation by On-orbit Data of QSAT-EOS

Masayuki Katayama, Yuta Suzaki, Shigeru Aso, Hiroshi Hirayama

AIAA/USU Conference on Small Satellites  (Logan, Utah, USA)  2017.08  -  2017.08  AIAA/USU

The role of the microsatellites has become significant due to the progress of performance and miniaturization of the electronics devices. For the purpose of earth observation the constellation flight of the microsatellites has made it possible to obtain the continuous data of the designated location and it is expected that the data be utilized in wide variety of the filed such as science, agriculture, industries, and climate monitoring. As the microsatellites take the LEO, the time of observation on the designated location is limited. Therefore the agile and precise pointing performance is required so as the attitude control accuracies. This paper presents the development of the attitude control simulator for the microsatellite for the use of design of the attitude control subsystem. Quaternion feedback control is proved to be effective and stable. Then the on-orbit data of the QSAT-EOS (Kyushu Satellite for Earth Observation System Demonstration) is analyzed to confirm the effectiveness of the quaternion feedback control. QSAT-EOS was launched in 2014 and now is in the deorbit phase after two year operation. Results of the on-orbit data analysis have suggested some necessities of improvement of the simulator and control algorithm which are the future subject.

Space Engineering Education using Micro-satellite QSAT-EOS

Hiroshi Hirayama, Shigeru Aso, Kazuhiko Morishita, Kiyotaka Fujisaki, Tetsuo Yasaka, Shunsuke Onishi

(Hakodate)  2016.09  -  2016.09  Japan Society for Aeronautical and Space Sciences

Space Engineering Education using Micro-satellite QSAT-EOS

Hiroshi Hirayama, Tetsuo Yasaka, Hideaki Hinagawa, Akira Sakurai, Shigeru Aso, Kazuhiko Morishita

(Hakodate)  2016.09  -  2016.09  Japan Society for Aeronautical and Space Sciences