Featured image credit: Kyodo
|October 12, 2022 – 00:50:43-00:55:11 UTC | 09:50:43-09:55:11 JST|
|RAISE-3 and others, Epsilon Flight #6|
|IHI Aerospace Co. Ltd (IA)|
|– Japan Aerospace Exploration Agency (JAXA)
– Q-Shu Institute of Space Pioneers Inc. (iQPS) (for QPS-SAR-3 and 4)
|Epsilon Launch Vehicle S|
|Uchinoura Space Center, Kimotsuki, Kagoshima Prefecture, Japan|
|~280 kg (~620 lbs)|
Where are the satellites going?
|Low Earth Orbit (LEO)|
Will they try to recover the first floor?
Where will the first stage land?
|It will crash into the South China Sea|
Will they try to recover the fairings?
Are these fairings new?
What weather is it ?
|To be determined|
It will be:
|– 1st orbital launch attempt for Japan in 2022
– 6th flight of an Epsilon rocket
– 2nd flight of the Epsilon PBS variant
– 135th orbital launch in 2022
where to watch
|If an official livestream is available, we’ll post the link here!|
What does all this mean?
The Japan Aerospace Exploration Agency launches RAISE-3 and 7 other payloads aboard an Epsilon rocket. A set of five CubeSats flies alongside the main payload.
The primary payload for this flight is an in-orbit demonstration mission. It is part of the Innovative Satellite Technologies Demonstration Program which has been ongoing since 2015. It is a 100 kg class satellite that hosts seven demonstration missions integrated with the main RAISE-3 satellite. You can find more information about this platform below.
|MAGNARO||10 x 10 x 34cm|
|MITSUBA||10 x 10 x 23cm|
|KOSEN-2||10 x 10 x 23cm|
RAISE-3 mission and others
RAISE-3 (RAPID SatellitE-3 Innovative Payload Demonstration)
|Assignment||Component name||Organization||Objectives (summary)|
|In-Orbit Demonstration of the Satellite IoT Platform in the 920 MHz Band Using Satellite MIMO Technology||LEOMI||Nippon Telegraph and Telephone Corporation (NTT)||In-orbit demonstration of multiple-input, multiple-output (MIMO) telecommunications technology|
|Software receiver using a flexible development method||SRX||NEC Space Technologies, Ltd.||In-orbit demonstration of a flexible, high-speed software receiver using a signal processing board with COTS parts|
|In-orbit evaluation of the commercial GPU and its model-based development||GEMINI||Mitsubishi Electric
|In-orbit evaluation of commercial GPUs enabling ultra-fast computing.|
|In-orbit demonstration of a micropropulsion system using a water thruster||KIR||PaleBlue Inc.||Demonstration in orbit of a micro-propulsion system using water as propellant.|
|In-orbit demonstration and performance evaluation of the PulsePlasma thruster for micro-satellites||TMU-PPT||Advanced
|In-orbit demonstration of the pulsed plasma thruster, enabling a small, low-power, low-cost propulsion system using solids
|In-orbit demonstration of
Deployable Membrane Deorbit
Mechanism for micro-satellite
|D-SAIL||Axelspace Corporation||In-orbit demonstration of a deployable membrane structure, aimed at increasing atmospheric drag and the rate of orbital decay.|
|In-orbit demonstration of a lightweight deployable membrane
Structure with energy generation and antenna function for society 5.0
|HELIOS||Sakase Adtech Co., Ltd.||In-orbit demonstration of a lightweight, deployable membrane structure with power generation and antenna function.|
The RAISE-3 platform is based on the previous RAISE-2 platform, with slightly modified specifications.
|Operational period||– 1 month for the commissioning phase
– 13 months for the nominal operating phase
|Orbit||– Sun-synchronous orbit (initial)
– Altitude: 560km (nominal)
– Tilt: 97.6 degrees (nominal)
– Local time descending node: 9:30 a.m.
|Launch||Expected in fiscal year 2022|
|Dimensions||Approx 1m x 0.75m x 1m
|Mass||Less than 110 kg|
|energy production||– More than 215W at BOL
– More than 180W at end of life
(Average electricity production during sunshine
|Communication||– S band for remote control: Uplink: 4kbps, Downlink: 64kbps
– X band for mission data and stored telemetry. Downlink: 16 Mbps
|Attitude control||– 3 stabilized axes
– Pointing towards the ground for the nominal attitude
|Resources available for mission payloads||– Mass: more than 23kg
– Power: 105Wh (BOL) and 62Wh (EOL) over one orbital period
– Data volume: 926.7 MB per day
– Payload mounting area: more than 2.5 m2
It is a 3U sized package that splits into two satellites after deployment. One is 2U and the other is 1U. They are connected by magnetism until they are separated. After separating, they will maintain a formation flight at a distance of 2-500 km from each other. Radio amateurs will be able to use these satellites as repeaters for long-range communications.
The satellites will be deployed in a sun-synchronous orbit at an altitude of 550 km. The combined mass of the two satellites is 4.4 kg. The name is abbreviated from “Magnetic separation nano-satellite with rotation for orbit control”. The satellites were designed and built at Nagoya University.
This satellite is described as “the observation of the in-orbit degradation of the COTS semiconductor to add value to the COTS database and the in-orbit demonstration of the general USB device”. It was built by the Kyushu Institute of Technology. The satellite has a mass of 1.7 kg.
This main satellite platform measures 11cm x 11cm x 23cm, with a YAGI-style directional antenna that extends after deployment. It is designed to study the deformation of the earth’s crust below the seabed. It uses dual reaction wheels to maintain attitude control. It takes observations using a combination of fish-eye camera lenses and magnetic sensors. It was developed by a partnership between the National Institute of Technology (KOSEN), Yonago College, Gunma College and other educational organizations.
This satellite is a technological demonstrator of 3D printed satellites. Its objective is to have zero fixing screws, zero mechanical parts to assemble and zero debris. This is achieved by 3D printing the entire chassis in one piece.
It will be used to conduct experiments regarding the deployment of membrane surfaces that could be used as solar panels for power generation or as a solar sail for propulsion. It was designed at Waseda University. The total mass of the satellite is 1.2 kg.
It is a cost-effective 1U size satellite with a multi-spectral camera and on-board data processing system. It is designed to demonstrate that this technology can be deployed and operated at this small scale and at low cost. The satellite has a mass of only 1.4 kg. It is built by the Future Science Institute.
QPS-SAR-3 and 4
The QPS-SAR satellites are a set of small Earth observation satellites built by the QPS Institute (Institute for Q-shu Pioneers of Space, Inc.). They feature high-resolution Synthetic Aperture Radar (SAR) in the X-band portion of the radio spectrum. When fully populated, the constellation is expected to have 36 functioning satellites.
This pair of satellites are improved in power generation and battery storage over their predecessors, QPS-SAR 1 and 2, but these were prototypes. QPS-SAR 3 and 4 each have a 3.6 m diameter antenna (after deployment) that has a mass as low as 10 kg. It is capable of resolving objects as small as 0.7m (~2ft).
Epsilon is essentially a three-stage vehicle using solid-state engines on all three stages, with an optional post-boost (PBS) stage that uses liquid monopropellant. This PBS, used on this flight, is based on the monopropellant reaction control system used on the H-II (A/B) rocket.
|Length||26 meters / 85 feet|
|Diameter||2.6m / 8.5ft|
|Total weight||96 t / 212,000 lb|
|Propellant (ton)||66.3||15.0||2.5||0.1||N / A|
|Thrust (kN)||2,271||372||98.8||0.4||N / A|
|Burning time (s)||116||140||90||1100||N / A|
|Hydrazine||N / A|
|Do)||284||300||301||215||N / A|
|twirl||thruster||N / A|
1 – Post-Boost Stage
2 – Payload fairing
3 – Hydroxyl terminated polybutadiene
4 – Thrust vector control
5 – Solid motor side jet
6 – Reaction control system
Flight profile and deployment schedule
|Walk||The description||Time (hms)||Time(s)||Altitude (km)||Speed (km/s)|
|1||To remove||00 00||0||0||0.4|
|2||Stop of the 1st stage||01 48||108||70||2.3|
|3||fairing jettison||02 31||151||115||2.1|
|4||1st stage of separation||02 41||161||123||2.1|
|5||2nd stage ignition||02 45||165||126||2.1|
|6||2nd stage burnout||04 54||294||202||4.8|
|seven||Separation 2nd floor||06 30||390||237||4.7|
|8||3rd stage ignition||06 34||394||237||4.7|
|9||3rd stage burnout||08 02||482||232||7.9|
|ten||3rd separation stage||09 54||594||235||7.9|
|11||PBS 1st start||16 33||993||277||7.8|
|12||PBS 1st stop||17 44||1,064||288||7.8|
|13||PBS 2nd start||41 24||2,484||554||7.5|
|14||PBS 2nd stop||50 46||3,046||572||7.6|
|15||RAISE-3 deployment||52 35||3,156||570||7.6|
|16||MITSUBA & WASEDA-SAT-ZERO Deployment||1 06 30||3,990||570||7.6|
|17||PBS 3rd start||1 08 11||4,091||572||7.6|
|18||PBS 3rd stop||1 08 26||4,106||572||7.6|
|19||QPS-SAR-3 Deployment||1 09 43||4,183||574||7.6|
|20||MAGNARO deployment||1 10 06||4,206||574||7.6|
|21||QPS-SAR-4 Deployment||1 11 19||4,279||575||7.6|
|22||KOSEN-2 & FSI-SAT deployment||1 11 42||4,302||576||7.6|