Solar Power Sail Research Articles

Joint Planetary and Astronomical Science with the Solar Power Sail Spacecraft

Joint Planetary and Astronomical Science with the Solar Power Sail Spacecraft

Development of Mission Devices and Sub-systems on Sail for World’s First Solar Power Sail IKAROS

Development of Mission Devices and Sub-systems on Sail for World’s First Solar Power Sail IKAROS

ソーラー電力セイル探査機によるトロヤ群小惑星探査および宇宙赤外線背景放射観測（特集「月惑星探査の来たる10年:第二段階のまとめ」）

ソーラー電力セイル探査機によるトロヤ群小惑星探査および宇宙赤外線背景放射観測（特集「月惑星探査の来たる10年:第二段階のまとめ」）

Future Small Body Exploration after the Investigation of Asteroid Itokawa by Remote Sensing and Returned Sample Analyses

AbstractThis paper outlines current achievements of the Hayabusa mission and future small body missions with an emphasis on scientific prospects by both remote sensing in the vicinity of target objects and retuned sample analyses of them. First, the Hayabusa spacecraft aimed as technology demonstration for the worldfs first deep space round trip and sample return from an asteroid and it was launched via the M-V rocket in May of 2003. Soon after the touchdown on Asteroid Itokawa, a sub-km, S-type NEO in November 2005, the spacecraft lost its attitude control due to the leak of RCS propellant; the communication link was lost for 46 days. While the ion engine thrusters reached their lifetime by November of 2009 owing to either of an ion source or neutralizers at each engine, a challenging combination of the neutralizer-A with the ion source-B was devised to resume the spacecraftfs propulsion. This enabled the spacecraft to have returned to the Australian desert on the Earth in June 2010. The sample return capsule (SRC) was successfully recovered and returned to Japan for initial inspection of the Itokawa samples. After the announcement of initial sample analysis results, international announcement of sample distributions has started in the spring of 2012. Following up the original Hayabusa mission, JAXA has approved the Hayabusa-2 project in 2011, an asteroid sample return mission to 1999 JU3, a sub-km, C-type NEO aiming for 2014-5 launch, 2018-9 remote sensing including artificial impactor excavation and 2020 Earth return of both surface and sub-surface samples of the asteroid. C-type asteroid is thought to be abundant in organic matters and hydrated compound, so it has important clues to solve the origin and evolution of the life. NASAfs OSIRIS-Rex and ESAfs Marco Polo-R missions are also carbonaceous asteroid sample return missions in 2010fs-2020fs. Cometary nucleus or/and D-type asteroid sample returns like Hayabusa-Mk-II concept are natural progression of this type of the endeavor. JAXAfs solar power sail mission aims for eventual rendezvous with Jovian Trojan asteroids, reservoir of D/P-type asteroids as either leftovers of Jupiter system formation or the second generation intruders from the Kuiper belt regions.

Achievement of IKAROS — Japanese deep space solar sail demonstration mission

This paper describes achievements of the IKAROS project, the world's first successful interplanetary solar power sail technology demonstration mission. It was developed by the Japan Aerospace Exploration Agency (JAXA) and was launched from Tanegashima Space Center on May 21, 2010. IKAROS successfully deployed a 20m-span sail on June 9, 2010. Since then IKAROS has performed interplanetary solar-sailing taking advantage of an Earth-Venus leg of the interplanetary trajectory. We declared the completion of the nominal mission phase in the end of December 2010 when IKAROS successfully passed by Venus with the assist of solar sailing. This paper describes the overview of the IKAROS spacecraft system, how the world's first interplanetary solar sailer has been operated and what were achieved by the end of the nominal mission phase.

IKAROS and Extended Solar Power Sail Missions for Outer Planetary Exploration

IKAROS and Extended Solar Power Sail Missions for Outer Planetary Exploration

DETECTION OF GAMMA-RAY POLARIZATION IN PROMPT EMISSION OF GRB 100826A

We report the polarization measurement in prompt $\gamma$-ray emission of GRB 100826A with the Gamma-Ray Burst Polarimeter (GAP) aboard the small solar power sail demonstrator IKAROS. We detected the firm change of polarization angle (PA) during the prompt emission with 99.9% ($3.5 \sigma$) confidence level, and the average polarization degree ($\Pi$) of $27 \pm 11$% with 99.4% ($2.9 \sigma$) confidence level. Here the quoted errors are given at 1 $\sigma$ confidence level for two parameters of interest. The systematic errors have been carefully included in this analysis, unlike any previous reports. Such a high $\Pi$ can be obtained in several emission models of gamma-ray bursts (GRBs), including synchrotron and photospheric models. However, it is difficult to explain the observed significant change of PA within the framework of axisymmetric jet as considered in many theoretical works. The non-axisymmetric (e.g., patchy) structures of the magnetic fields and/or brightness inside the relativistic jet are therefore required within the observable angular scale of $\sim \Gamma^{-1}$. Our observation strongly indicates that the polarization measurement is a powerful tool to constrain the GRB production mechanism, and more theoretical works are needed to discuss the data in more details.

Spinning solar sail orbit steering via spin rate control

The orbit of a solar sail can be controlled by changing the attitude of the spacecraft. In this study, we consider the spinning solar power sail IKAROS (Interplanetary Kite-craft Accelerated by Radiation Of the Sun), which is managed by Japan Aerospace Exploration Agency (JAXA). The IKAROS attitude, i.e., the direction of its spin-axis, is nominally controlled by the rhumb-line control method. By utilizing the solar radiation torque, however, we are able to change the direction of the spin-axis by only controlling its spin rate. With this spin rate control, we can also control indirectly the solar sail’s trajectory. The main objective of this study is to construct the orbit control strategy of the solar sail via the spin-rate control method. We evaluate this strategy in terms of its propellant consumption compared to the rhumb-line control method. Finally, we present the actual flight attitude data of IKAROS and the change of its trajectory.

A study of the guidance method for the Small Solar Power Sail Demonstrator, IKAROS

We present the guidance approach for the Small Solar Power Sail Demonstrator, IKAROS. This approach will be used for future solar sail missions. First, we show the range of orbital controllability, which is severely restricted by the attitude constraint from the power and communication. Second, we also present the adaptive guidance method, in which guidance parameters are updated based on the estimation of the spacecraft's parameters such as the area and reflectivity coefficient of the sail. Finally, we evaluate the guidance approach performance by comparing to flight data of IKAROS.

Study of emission mechanism of GRBs probed by the gamma-ray polarization with IKAROS-GAP

AbstractWe report a polarization measurement in prompt γ-ray emission of GRB 100826A with the Gamma-Ray Burst Polarimeter (GAP) aboard the small solar power sail demonstrator IKAROS. We detected a firm change of polarization angle (PA) during the prompt emission with 99.9% (3.5 σ) confidence level, and an average polarization degree (Π) of 27 ± 11% with 99.4% (2.9 σ) confidence level. Here the quoted errors are given at 1 σ confidence level for two parameters of interest. Non-axisymmetric (e.g., patchy) structures of the magnetic fields and/or brightness inside the relativistic jet are therefore required within the observable angular scale of ~ Γ−1. Our observation strongly indicates that the polarization measurement is a powerful tool to constrain the GRB production mechanism, and more theoretical works are needed to discuss the data in more details.

On-orbit verification of fuel-free attitude control system for spinning solar sail utilizing solar radiation pressure

This paper introduces a new attitude control system for a solar sail, which leverages solar radiation pressure. This novel system achieves completely fuel-free and oscillation-free attitude control of a flexible spinning solar sail. This system consists of thin-film-type devices that electrically control their optical parameters such as reflectivity to generate an imbalance in the solar radiation pressure applied to the edge of the sail. By using these devices, minute and continuous control torque can be applied to the sail to realize very stable and fuel-free attitude control of the large and flexible membrane. The control system was implemented as an optional attitude control system for small solar power sail demonstrator named IKAROS (Interplanetary Kite-craft Accelerated by Radiation Of the Sun). In-orbit attitude control experiments were conducted, and the performance of the controller was successfully verified in comparison with the ground-based analytical performance estimation.

A1 IKAROSによる世界初のソーラー電力セイル実証(IKAROS)

The Japan Aerospace Exploration Agency (JAXA) makes the world's first solar power sail craft IKAROS demonstration of photon propulsion and thin film solar power generation during its interplanetary cruise. The spacecraft deploys and spans a membrane of 20 meters in diameter using the spin centrifugal force. It also deploys thin film solar cells on the membrane, in order to evaluate its thermal control property and anti-radiation performance in the real operational field. The spacecraft weights approximately 310kg, launched together with the agency's Venus Climate Orbiter, AKATSUKI on May 21, 2010. This is a Front-Loading of new key technical issues of extended solar power sail mission toward Jupiter and Trojan asteroids via hybrid electric photon propulsion. This paper presents the summary of development and operation of IKAROS.

Empirical Model Reduction of Geometrical Constrained Gossamer Structures

The purpose of this research paper is to construct a low-order model of a geometrical constrained gossamer structure, especially for a solar sail. Currently, JAXA is working on a spin type solar power sail spacecraft. Computational analysis of the sail membrane's large mathematical model is difficult and time consuming. Therefore, this issue has a negative impact on design aspects. As a result, the model reduction technique is required. In other words, with a feasible, shortened, computational analysis period, a trade-off would be possible when designing and determining operation procedures. However, there is no model reduction methodology about solar sail dynamics. In this research paper, firstly, the full-order model of the spin type solar sail craft is modeled by the geometrically nonlinear FEM based on the energy momentum method (EMM). As a result, the numerical time integration is unconditionally stable. Secondly, the low-order model is constructed by the empirical model reduction method. And finally and complementarily to the former and latter sentence, the geometrical constraint is modeled by the penalty method based on the EMM. In this research paper, we will show that the low-order model can approximate the full-order model with sufficient accuracy.

J191063 ソーラー電力セイルで挑む惑星探査([J19106]構造・材料の高度化に向けた宇宙工学と材料力学の展開(6))

Japan Aerospace Exploration Agency (JAXA) successfully achieved the world's first solar power sail technology by IKAROS (Interplanetary Kite-craft Accelerated by Radiation Of the Sun) mission in 2010. It demonstrated a photon propulsion and thin film solar power generation during its interplanetary cruise. The 200m2-span sail was deployed and kept extended by centrifugal force of the spacecraft rotation. IKAROS also succeeded in accelerating and controlling the orbit by actively exploiting solar radiation pressure, and thus became the world's first actual solar sailer flying an interplanetary voyage. This paper presents the design of IKAROS solar sail system, operation results and introduces a perspective of this new technology to apply to the next generation mission toward Jupiter and Trojan asteroids.

S1901-1-3 小型ソーラーセイル実証機(IKAROS)のセイル展開ミッション(小型宇宙システム(1),社会変革を技術で廻す機械工学)

Japan Aerospace Exploration Agency (JAXA) developed a small demonstrator of solar power sail orbiter to demonstrate solar sail technology that utilizes photons from the sun for continuous acceleration and electrical power generation by thin flexible solar arrays. The small demonstrator "Interplanetary Kite-craft Accelerated by Radiation Of the Sun (IKAROS)" was launched on May 21st 2010, and succeeded in deploying solar power sail on Jun 9th. In this paper, we introduce the deployment mechanism for solar power sail of IKAROS, and report on flight data of sail deployment mission in orbit.

First Solar Power Sail Demonstration by IKAROS

The Japan Aerospace Exploration Agency (JAXA) will make the world's first solar power sail craft demonstration of photon propulsion and thin film solar power generation during its interplanetary cruise by IKAROS (Interplanetary Kite-craft Accelerated by Radiation Of the Sun). The spacecraft deploys and spans a membrane of 20 meters in diameter taking the advantage of the spin centrifugal force. The spacecraft weighs approximately 310kg, launched together with the agency's Venus Climate Orbiter, AKATSUKI in May 2010. This will be the first actual solar sail flying an interplanetary voyage.

Development of Deployment System for Small Size Solar Sail Mission

The Japan Aerospace Exploration Agency (JAXA) is studying the feasibility of using the solar power sail as a new propulsion engine for deep space exploration missions. In this paper, the sail shape and equipment layout for missions utilizing small-sized solar power sails are proposed. The two-stage deployment method of the sail is also proposed. The sail need to be deployed statically at the first stage, and two types of deployment mechanisms are introduced. On the other hand the second stage of the deployment can be performed dynamically, and the oscillating motion of the membrane is converged by tethers connecting the membrane to the main body. The deployment motions are analyzed by numerical simulations using multi-particle models in order to verify the deployment. They are compared with the results calculated by finite element method models. The numerical simulation results are discussed from the technological viewpoint of the sail deployment dynamics and mechanisms.

S1903-1-4 小型ソーラーセイル実証機(IKAROS)の膜面展開機構の評価・検証(宇宙構造・材料)

Japan Aerospace Exploration Agency (JAXA) develops a small demonstrator of solar power sail orbiter to demonstrate solar sail technology that utilizes photons from the sun for continuous acceleration and electrical power generation by thin flexible solar arrays. We proceed with "Interplanetary Kite-craft Accelerated by Radiation Of the Sun (IKAROS)" project, which planed to be launched in the summer of 2010. In this paper, we introduce the spread mechanism of solar power sail, and result of various tests or experiments of a proto-type model of IKAROS mission mechanism.