Shimoda Takayuki

Japan Aerospace Exploration Agency | JAXA

The flow enthalpy of an arc-heated wind tunnel is an important parameter for reproducing planetary entry and performing heating tests. However, its distribution is insufficiently clarified, owing to complicated phenomena, such as arc discharge and supersonic expansion. In this paper, the authors assess the enthalpy of an arc-heated flow in a large-...

When a spacecraft orbiting the earth enters the earth's atmosphere, it is exposed to an aerodynamic heating environment. The outer surface of the spacecraft has been covered with a carbonized ablator made of a CFRP to prevent this heat input from entering this spacecraft. From the research conducted so far, it has been found that a CFRTP has a spec...

Spacecraft employs heat shield as protection from high heat during reentry into Earth atmosphere. However, current heat shields are labor intensive to manufacture and cost prohibitive. Additive manufacturing technology or 3D printing allows rapid manufacturing, reduced cost and design flexibility. Hence, a new thermal protection system (TPS) was pr...

The coking phenomenon within a lightweight carbon-phenolic ablator exposed to the heating environment of air is investigated. The existing one-dimensional charring ablation analysis code is modified so that the coking behavior of the ablator can be calculated as well as the thermal response behavior within a lightweight carbon-phenolic ablator. The...

Different plasma wind tunnels have been fabricated for developing reusable space probe transportation systems during the Earth atmospheres re-entry phase. Several probes faces a loss of communication due to the plasma sheath occurred, caused by high velocity, heat flux and wall temperature in front of the probe. The purpose of the experiment to stu...

Entering a planetary atmosphere is one of the most claim missions as the space probe faces a loss of communication, acknowledged as communication blackout, due to the plasma sheath occurred, caused by temperatures of several thousand degrees in front of the space probe. This paper presents a study about a new method of communication called end of r...

Entering a planetary atmosphere is one of the most claim missions as the space probe faces a loss of communication, acknowledged as communication blackout, due to the plasma sheath occurred, caused by temperatures of several thousand degrees in front of the space probe. This paper presents a study about a new method of communication called end of r...

When we develop a space probe, are needed to carry out its orbit analysis. Space industries and space agencies they have been using the System Tool Kit (STK) for these orbit analysis. Most of satellite projects were used this software. An allowable mass demand of a rocket to an ultra-small space probe is very severe, for this reason a throughput an...

For protecting the spacecraft against the severe heating during the atmospheric reentry, the ablative materials are commonly used as thermal shield. Recently, a new lightweight CFRP called the lightweight ablator series for transfer vehicle systems (LATS) was developed. Since LATS contains a resin that undergoes thermal decomposition by heating, cl...

This paper proposes a mission for observation of the upper atmosphere using an artificial meteor released by a mass driver installed on a microsatellite. The mass driver releases the sample, which comprises definite materials and deorbits to become an artificial meteor, where its emission provides valuable information concerning the upper atmospher...

"Hayabusa" is one of the Satellite which explore planets. To return samples of planets and protect them from great heating when re-entry to the atmosphere of Earth, the heat shield of the capsule is developed so far. However, the heat shield of the capsule is needed to reduce weight and to keep the heat resisting property from the viewpoint of cast...

Kyushu Institute of Technology has been developing the lightweight ablator series for transfer vehicle systems (LATS) as a thermal protection system at the time of reentry. This LATS is composed of a carbon fiber reinforced plastic (CFRP) and it has various densities. In this study, we have made two LATS materials which the specific densities are a...

In this paper, leak detection system of hydrogen fuel in a future reusable rocket is examined. Identification of a leaking engine line is a fundamental requirement considering specifications and characteristics of the rocket system. Design of the leak detection system satisfying the requirement is examined. Specification of the detection system is...

The outer wall of re-entry vehicles is covered with heat shield materials in order to protect them from severe aerodynamic heating. An ablator is a type of heat shield material effective for re-entry vehicles. In particularly an ablator made of Phenolic carbon fiber-reinforced plastics (CFRP) is known to possess superior resistance against severe a...

Gas turbine engines are utilized as jet engines of aircraft and industrial gas turbines. Then, heavy and expensive Ni-base super alloys are used for a material of the turbine blade due to very severe environment. Therefore, we are applying a CFRP for the material of the turbine blade instead of the alloy in order to reduce the weight and the expens...

Small satellites made by universities and small private companies are getting main streams in Japanese and global space developments. Some universities in Japan now have excellent potential and actually realized many fruitful outcome. Meanwhile reentry vehicles in Japan are not vigorous as before ceasing HOPE-X project. Researchers for heat resista...

When temperature suddenly changes an ablator material inside, a predicted in-depth temperature using the thermal conductivity that measured in the steady state, it does not accord it to measured value strictly. One of these reasons is because an input energy to a material is spent by the conductive heat transfer, the increase of the internal energy...

In case of the high-speed flight within the atmosphere, the orbital and suborbital spacecrafts suffer great aerodynamic heating. Using an efficient thermal protection system (TPS) is important for maintaining the structural integrity, but also for preserving the payload and onboard devices. The ablative materials are commonly used as thermal shield...

Japan Aerospace Exploration Agency has a plan to develop the HTV-R which is an extended version of the HTV. The HTV-R will be a spacecraft for developing a re-entry capsule similar to the Apollo spacecraft. We are expecting that the recovery on the sea surface is one of the promising methods to develop a Japanese capsule, therefore, we consider tha...

This paper shows the preliminary system study of manned spaceship. Low earth orbit mission and moon mission were assumed as reference missions, and based on these missions, system requirement analysis, subsystem study and spaceship concept study were done.

Following the two big projects, International Space Station and Space Shuttle, new projects are under consideration in many national agencies, especially in NASA, ESA, and JAXA. NASA has been developing ORION in Constellation program, but the new president, Obama changed the original planning. ESA is also considering a new project, and JAXA is disc...

The JEM elements are delivered to the ISS on three Shuttle flights and are assembled on orbit subsequently. The verification of JEM structural compatibility with the Space Shuttle was performed to certify its flight readiness. Structural compatibilities are required on weight and center of gravity, stiffness and structural damping, strength, and dy...

Bonding strengths of three types of adhesives were evaluated at different temperatures. The effects of temperature and adhesive thickness on the strength were clarified from the results. It concluded that EA9394 cured at room temperature is the overall best performing adhesive for CFRP applications at cryogenic temperatures. The initial failure mod...

A buckling analysis method based on Co-rotational formulated FEM for flexible multi body beam structures is proposed. This method makes it possible to analyze light weight deployable beam structures that may be subjected to buckling load. This paper especially focuses on a method of buckling mode identification and buckling mode injection while a s...

In this study, usefulness of lamb waves generated by chirp signals for NDI was examined. The target for the inspection is wall parts of composite propellant tanks. We first studied characteristics of lamb waves propagated around delamination zone by computer simulation. Then, the damage inspection using lamb waves generated by chirp signals was con...

This paper describes the results of an investigation into the current status of a satellite-rocket coupled load analysis technique and a vibration test technique used to validate analytical results in Europe and the USA. Their analytical techniques are at the same level as in Japan. They consider vibration testing to be important for validating ana...

Two liner-less CFRP concept tanks were prepared for internal pressurization tests at liquefied nitrogen (LN2) temperature. The tanks were designed in two patterns of eight-ply UD quasi-isotropic lay-up, in the shape as a cylinder of 600 mm in diameter and 1200 mm in length, covered with an aluminum flange at one end and with a CFRP hemisphere dome...

National Space Development Agency of Japan (NASDA) is conducting a feasibility study of applying CFRP to the cryogenic propellant tank of a reusable vehicle system. As a part of the feasibility study, we are now conducting tests of small filament winding (FW) tanks with 300mm diameter to study the possibility of the filament winding method for manu...

The purpose of our study is to understand the shear performance of layered CFRP laminates at wide temperature range changed from room temperature to cryogenic temperature. Analytical evaluations of the v-notched specimens (Iosipescu shear test) to determine the in plane and out-of-plane (interlaminar) shear properties (modulus and strength) of laye...

It is essential to utilize carbon fiber reinforced plastics (CFRP) for main structural materials of cryogenic propellant tanks in order to realize the drastic weight reduction needed for efficient reusable space transportation systems. Recently developed toughened CFRP materials, which are expected to show good cryogenic properties, are considered...

Numerical and experimental techniques are used to model the flow and pressure distribution around the forebody of the HYFLEX hypersonic flight vehicle. We compare numerical simulation results with modified Newtonian theory and flight data to determine the accuracy of the computational fluid dynamics (CFD) technique used. The numerical simulations c...

The rendezvous docking (RVD) and the space robot technologies are essential for future space activities such as supply, exchange and retrieve of equipment in space. Especially the capture berthing technology is a highly advanced and challenging one. Logistic support of the international space station and in-orbit satellite servicing are the driving...

The use of computational fluid dynamics simulations for calibrating a flush air data system is described, In particular, the flush air data system of the HYFLEX hypersonic vehicle is used as a case study. The HYFLEX air data system consists of nine pressure ports located flush with the vehicle nose surface, connected to onboard pressure transducers...

The angular motion of an orbital re-entry experiment (OREX) vehicle model was tested in a transonic wind tunnel using a single-degree-of-freedom test method to investigate the angular motion of the OREX vehicle. The purpose of the OREX is to test heat shield materials and to obtain measurements of an aerodynamically heated flowfield. Approximate st...

An overview of the Orbital Re-entry Experiment (OREX) vehicle development, including detail design, analyses on the overall system, guidance and control, propulsion, and data acquisition systems is presented. The outline of the experiment vehicle is shown. OREX flight is analyzed and the splash down point variance ellipse is shown. Vehicle body aer...

In order to study the cryogenic properties of CFRP tank, we conducted pressurization test of a small filament-wound (FW) tank at cryogenic temperatures. We first investigated the orienta-tion dependence of acoustic emission (AE) signals at both room temperature and LN 2 tempera-ture by using artificial source. Lamb-mode dispersive AE signals were m...