Japan - Suborbital Launches

[catdlr]

Overview of the launch of the S-520-34 sounding rocket

Scheduled for Aug 8, 2024
We will be live streaming a launch overview briefing for the S-520-34 sounding rocket, which is scheduled to be launched on Sunday, August 11, 2024 from 6:00 to 7:00.

Sounding rocket S-520-F34 Launch live streaming

Scheduled for Aug 10, 2024
The launch of the S-520-34 observation rocket, scheduled for Sunday, August 11, 2024 from 6:00 to 7:00, will be broadcast live from IHI Spaceport Uchinoura (Miyahara Rocket Observation Area).

[Steven Pietrobon]

https://global.jaxa.jp/press/2024/06/20240620-2_e.html

 The Japan Aerospace Exploration Agency (JAXA) is pleased to announce that the sounding rocket S-520-34 test will be conducted as follows.

record
Experiment period: August 11, 2024 (Sunday) ~ September 30, 2024 (Monday) (including preliminary period)
Scheduled test date: Sunday, August 11, 2024, 6:00~7:00 (Japan Standard Time)
Location: Uchinoura Space Observatory (Kagoshima Prefecture, Kagoshima Prefecture)
Launch vehicle: S-520-34
Outline of the experiment: [Liquid Propellant Rotational Detonation Engine System Flight Demonstration Experiment]
 Based on the success of the space demonstration of the detonation engine system (DES)* on the sounding rocket S-520-31, we have developed a swiveling detonation engine system (DES2) using liquid fuel (ethanol) and an oxidizer (liquefied nitrous oxide), and aim to actually operate it in space and evaluate its propulsion performance.
 Large amounts of data (digital images) acquired during the operation of DES2 are collected by the on-board inflatable data collection system (RATS2).

* Detonation engine system:
Rocket engine technology that safely and efficiently converts the shock wave (detonation wave) generated when a mixture of fuel and oxidizer reacts explosively into thrust

[Steven Pietrobon]

https://www.isas.jaxa.jp/home/kansoku/rocket/S-520-34/S-520-34.html

Outline of the experiment

The sounding rocket S-520-34 is intended to demonstrate advanced propulsion and control technologies for the development of next-generation space transportation systems, satellites, and probes. The two experimental instruments on board are a liquid-propellant-based detonation engine system (DES2) and a recovery module (RATS2) for collecting sounding rocket experiment data. The data and knowledge obtained through these experiments are expected to be an important step toward the practical application of innovative space technologies and make a significant contribution to future space development.


https://www.isas.jaxa.jp/home/kansoku/rocket/S-520-34/pi/DES2.html

Liquid Propulsion Detonation Engine System (DES2)

The detonation engine generates detonation and compression waves at extremely high frequencies (1~100kHz or more) to dramatically increase the reaction speed, thereby innovatively reducing the weight of the rocket engine and easily generating pressure thrust to improve performance. Detonation engines can be applied to a variety of space propulsion fields, such as kick motors, first- and two-stage engines, and engines for small satellites and spacecraft, and research is currently being conducted in Japan, Europe, the United States, and Asia with a view to practical application as a high-performance engine for space.

In this experiment, the sounding rocket S-520-34 will be equipped with a detonation engine system equipped with liquid propellant, and data on the combustion and propulsion performance of the swirling detonation engine (RDE) will be acquired in space. Ethanol is used as the fuel and liquefied nitrous oxide (N2O) is used as the oxidizer. These are pressurized with nitrogen and fed into RDE. The photograph shows a breadboard model (BBM) consisting of components equivalent to the flight model, and a ground combustion test of this BBM confirms that fuel and oxidizer are stably supplied to the engine.


https://www.isas.jaxa.jp/home/kansoku/rocket/S-520-34/pi/RATS2.html

Sounding Rocket Data Recovery Module （RATS2）

In recent years, there has been a growing demand for the recollection of experimental equipment in sounding rocket experiments in order to reuse large amounts of experimental data that cannot be obtained by telemetry communication and expensive experimental equipment. However, in Japan, due to the small size of the country, it is necessary to drop the experimental aircraft into the sea, so in addition to a slow descent system using a parachute, etc., a sea levitation function is required, and the technical difficulty is very high. Therefore, recovery experiments have not been carried out continuously until now.

 Against this background, in July 2021, the sounding rocket S-520-31 sounding rocket (RATS) was developed as a sounding rocket experiment data collection module using a deployable aeroshell. We have succeeded in recovering a large amount of data at sea. Unlike conventional systems such as Hayabusa and Hayabusa2, the atmospheric entry system using the deployable aeroshell adopted in RATS is attracting attention as a new option and has the potential to innovate atmospheric entry technology.

 In this RATS2, we aim to collect data from the main PI using the same system as the first unit. In addition, the RATS series will continue to be used regularly as an optional device for recovering sounding rockets.

◆ RATS2 system total mass: 13.6kg
◆ Mass of inrush part: 4.8kg
◆ RATS system size (when stored in aeroshell): Diameter 370 mm× Height 500 mm
◆ Plunge aircraft size at the time of entry (when aeroshell is deployed): Diameter 1.5 m× Height 360 mm

Aeroshell unfolded (diameter 1.2 m)

[catdlr]

[russianhalo117]

T-14 minutes and counting

[russianhalo117]

T-14 minutes and counting

Abort/Hold called during the automatic sequence. NET 24 hour scrub and recycle.

[Steven Pietrobon]

https://www.jaxa.jp/press/2025/07/20250708-1_j.html

Delay of the S-310-46 Observational Rocket Experiment

July 8, 2025 (Reiwa Year 7)

National Research and Development Agency: Japan Aerospace Exploration Agency (JAXA)

The Japan Aerospace Exploration Agency (JAXA) had planned to launch the S-310-46 observational rocket from the Uchinoura Space Centre on July 8, 2025 (Tuesday), aiming to clarify the formation process of sporadic E layers in the mid-latitude ionosphere. However, due to unfavourable launch conditions, the launch has been postponed.

A new launch date will be promptly announced as soon as it is decided.[Reference]

Experiment period: July 8, 2025 (Tuesday) - August 31, 2025 (Sunday) (including contingency period)

[Steven Pietrobon]

https://www.isas.jaxa.jp/home/kansoku/rocket/S-310-46/S-310-46.html

Observation Rocket S-310-46

Experiment Overview

Experiment Purpose

The purpose of this experiment is to clarify the formation process of the sporadic E (Es) layer that occurs during the day at mid-latitude ionosphere heights through direct observation of the neutral atmosphere, plasma atmosphere, wind, electric fields, and magnetic fields. Through this experiment, we aim to elucidate the coupling process between the neutral atmosphere and plasma atmosphere in the transition region from a neutral atmosphere-dominated Earth atmosphere to a plasma-dominated space. The apparatus developed here and the scientific results obtained are also intended to be applicable to elucidating phenomena in other regions around Earth, planets, and satellites where neutral particles and plasma coexist.

Experiment Method

In southern Japan, which is located in the East Asian region where the occurrence frequency of the Es layer is high, we will launch an S-310 type rocket around local solar time 12 to 14, when the probability of Es layer occurrence is highest, and carry out comprehensive direct measurements of the neutral atmosphere, plasma atmosphere, wind, and electric fields at altitudes of 90 to 130 km during the ascent and descent. This local time is when the Es layer develops and reaches around 105 km, a period when the interaction between the neutral atmosphere and plasma atmosphere becomes pronounced, allowing us to evaluate the contributions of electric fields and neutral atmospheric winds to Es layer formation. In addition to direct measurements with the rocket, ground observations will be conducted at multiple locations to measure the temporal development and spatial extent of the Es layer observed by the rocket.

Equipped Observation Instruments

Equipped Observation Instruments (abbreviations): Measurement Items
Ion Drift Velocity Measurement Device (IVA): Ion drift velocity, ion density
Electric Field Measurement Device (EFD): Electric field vector
Neutral Atmospheric Density and Wind Measurement Device (IOG): Neutral atmospheric density, neutral wind
Impedance Probe (NEI): Electron density
Neutral Atmospheric Mass Spectrometer (NMS): Neutral atmospheric composition
Magnetic Field Observation Device (MAG): Magnetic field vector
Langmuir Probe (FLP): Electron temperature and density

Image diagram of the sounding rocket experiment

[Steven Pietrobon]

The Japanese subsidiary of the Taiwanese rocket development company, jtSPACE Co., Ltd., will have NVS attempt to broadcast the launch of their suborbital rocket "VP01."

*Note that due to poor radio conditions, the broadcast may not be possible.
*There is a high possibility that the rocket will not be visible until it is launched.

Scheduled launch date: July 12, 2025
Scheduled launch time: Between 6:00-7:30, 10:50-12:00, or 16:00-17:00 (Japan Standard Time)
Launch site: Hokkaido Spaceport Launch Complex 1 – Launch Pad 12 (LC1-LP12)
Launch azimuth: Southeast
Launch purpose: To reach space at an altitude of over 100 km and verify the operation of all rocket systems

Morning Window 6:00-7:30
https://www.youtube.com/live/BgFqXDQv79M

Daytime Window 10:50-12:00
https://www.youtube.com/live/Nbv3lBcOI8s

Evening Window 16:00-17:00
https://www.youtube.com/live/1Av3DZ6jxDg

[AndrewM]

https://hokkaidospaceport.com/en/news/1901 [July 13]

jtSPACE Co., Ltd., a Japanese sister company of a Taiwanese rocket development company launched its suborbital rocket “VP01” from the Hokkaido Spaceport (HOSPO) at 11:40 on Saturday, July 12.

VP01 reached an altitude of 4 km, and the operation verification was completed for several rocket systems, including launch platform, stage separation, and re-ignition of the second stage.

The rocket’s first stage is currently being recovered. The second stage was terminated after separation, as it was determined that the mission could no longer proceed. It landed within the designated safety zone, on municipal land near the Toberi River, less than 1 km north of the launch site. jtSPACE will conduct a detailed investigation.

jtSPACE Co., Ltd., sister company of a Taiwanese entity tiSPACE (Taiwan Innovative Space Inc.), is a local Japanese entity that aims to develop a space transportation business in Japan. The purpose of this launch test was to reach VP01 to an altitude of about 100 km, verify each performance of the rocket, and support the development of an orbital launch vehicle capable of carrying a satellite.

This is the first launch of a rocket reaching outer space at an altitude of 100 km in HOSPO in four years, since the MOMO F6 of Interstellar Technologies Inc. (Taiki Town) in July 2021. The launch of jtSPACE was the first launch backed by a foreign capital in Japan.

[JulesVerneATV]

Interstellar landed a new ￥7 billion (~US$44 million) investment from Woven by Toyota

https://www.japanearthobserver.com/japan-earth-observer-2-the-curious-orbits-of-qzss/